World Congress: 8th

MathematEngineering, AeSão José dos Campos

CAIAA: American In

IEEE: Institute ofIFNA: Internation

IFIP: InternationalINPE: Brazil

FAPESP: Fundação de ACAPES: Coordenação de A

CSP: Cambridge S

PROGRAM & ABSTRACT

International Conference on ical Problems in rospace and Sciences

, Brazil, June 30- July 3, 2010

o-Sponsored by stitute of Aeronautics and Astronautics Electrical and Electronics Engineers al Federation of Nonlinear Analysts

Federation of Information Processing ian Institute for Space Research

mparo à Pesquisa do Estado de São Pauloperfeiçoamento de Pessoal de Nível Superiorcientific Publishers, Cambridge, UK

Wolfram Research

Welcome Message from the Conference General Chair As the general chair of the conference, I am happy to welcome you all to the 2010 World Congress - 8th International Conference on Mathematical Problems in Engineering, Aerospace and Sciences. With the natural beauty and rich cultural activities of São Paulo state and also the world-renowned areas of Brazil, the INPE location is an outstanding venue for the conference. The 7th International Conference was held in Genoa, Italy in 2008, and shattered the attendance records of all the previous conferences. This year, in São Jose dos Campos, despite the current world wide economic constraints, we have an even larger number of attendees/delegates and there were many more who wanted to attend but could not, due to lack of funding. We have an excellent program with several keynote addresses, general sessions, and special sessions on areas including: neural network dynamics, unmanned aerial vehicles, and advances in nonlinear differential equations, stability and Lyapunov theory, contributions of PhD Students, mathematical research in dynamical systems theory, methods of nonlinear analysis for partial differential equations, advances in fractional differential equations. Petri nets for complex systems, system identification, theory and application in aerospace, biology, engineering and science, nuclear power and research systems modeling, integral equations and their applications. There are also mini symposia on aeroelasticty, astrodynamics, spacecraft attitude dynamics and control, mathematical modeling and applications in electrical, aerospace and control engineering, multidisciplinary design and optimization in aerospace industry. I would like to thank the international advisory committee and the international organizing committee, the international awards committee, the local advisory and local organizing committee, the sponsors AIAA (American Institute of Aeronautics and Astronautics), IEEE (Institute of Electrical and Electronics Engineers), IFNA (International Federation of Nonlinear Analysts), IFIP (International Federation of Information Processing), INPE (Brazilian Institute for Space Research), FAPESP (Fundação de Amparo à Pesquisa do Estado de São Paulo, CAPES (Coordenação de Aperfeiçoamento de Pessoal de Nível Superior), Cambridge Scientific Publishers, UK and Wolfram Research for their assistance and support in the preparation of the conference. I also wish to express my special thanks to all who have helped me in planning the chairing of sessions to make this conference a very successful event. Finally, I would especially like to thank the local organizers Antonio Prado and Vivian Gomes, the conference coordinator Eva Kaslik, and the administrative chair Jose Ruiz for their tireless efforts to make this a successful conference. I hope that you all enjoy the conference, have an exciting scholarly cooperation, collaboration and interaction, and have a pleasant stay in Brazil Seenith Sivasundaram

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Conference Information

Registration Registration for the conference will be open at the following times, in the LIT building: Tuesday, June 29 2:00 PM – 5:00 PM Wednesday, June 30 8:00 AM – 6:00 PM Thursday, July 1 8:30 AM – 6:00 PM Friday, July 2 8:30 AM – 12.40 PM Saturday, July 3 9:00 AM – 12:00 PM Internet Wireless internet access is available in the LIT building, as well as a computer for general use. Lunch breaks The INPE restaurant offers a self service buffet, at the price of 14,00 BRL per kilo. There is also a cafeteria (near LIT), which offers coffee, drinks and snacks during all day. Reception – Wednesday, June 30, 6:00 PM - LIT There will be a welcome reception (cheese & wine party) in the LIT lobby at the end of the first conference day. Banquet – Friday, July 2, 8:00 PM Churrascaria Vila D'Aldeia - http://www.villadaldeia.com.br/ The banquet will take place in a very nice barbecue restaurant. There is a large buffet with salads, cheese and vegetables. The main attraction of the place is the delicious Brazilian barbecue served in an all-you-can-eat basis. They also serve grilled chicken and sea food. The following drinks are included: water, soft drinks, juices, beer and caipirinha (a delicious tradicional Brazilian drink, based on sugar, lemon and sugar cane alcoohol) and one dessert of your choice. The banquet is included in the registration fee. Additional tickets (for accompanying persons), can be purchased at the registration desk.

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Wolfram Research Tutorial: An Overview of Mathematica for Education

Presented by Igor Canales Antonio

Thursday, July 1, 1:10-2:10 PM - LIT

This seminar provides an overview of the Mathematica functionality that makes it easy for educators to integrate the software into higher education classrooms and research facilities. Whether you have used Mathematica for years or have no technical computing experience, you'll see many examples of Mathematica's use for education that can be implemented immediately. Resources and presentation materials are made available to participants. Igor Canales Antonio is a lead software developer in the Software Technology Group at Wolfram Research, Inc. Igor was born in Sao Paulo and joined Wolfram Research in 2003 after receiving his Bachelor of Science in Computer Science from the University of Illinois at Urbana-Champaign. He is responsible for development of many of Mathematica's external data handling capabilities, which allows individuals to import and export data to hundreds of file formats.

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Wednesday, June 30

MORNING PLENARY SESSION – LIT - Main Auditorium 9.00-9.40 Inauguration

9.40-10.30 Keynote Talk: A. V. BALAKRISHNAN

Title: Flutter Analysis in Viscous Flow Chair: Luiz Carlos Góes

10.30-11.00 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 1. Modern Aeroelasticity LIT - Main Auditorium Chair: Jiro Nakamichi 11.00-11.30 Transonic Aeroelasticity: Theoretical and Computational Challenges

Oddvar O. Bendiksen

11.30-12.00 Aeroelastic Analysis of a Typical Section Using of Shape Memory Wire Actuator Vinícius Piccirillo, Luiz Carlos Sandoval Goes, Jose Manoel Balthazar

12.00-12.30 Aeroelastic Behavior of a Wing with a Magnetorheological Hysteretic Model for the Damping Kleber Augusto Lisboa Castão, Luiz Carlos Sandoval Goes, José Manoel Balthazar

12.30-1.00 Flutter solution techniques and their applications Eulo Antonio Balvedi Jr., Roberto Gil Annes da Silva

MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control LIT - Small Auditorium Chair: Luiz Carlos DeSouza 11.00-11.30 Reduced order attitude dynamic model of a satellite with reaction wheels and

appendages Valdemir Carrara

11.30-12.00 IMU Calibration Procedure for a Redundant Tetrahedral Gyro configuration with Wavelet De-noising Élcio Jeronimo de Oliveira, Waldemar de Castro Leite Filho, Ijar Milagres da Fonseca

12.00-12.30 Differential Games of Stabilization Ximena Cubillos, Susana Dias, Luiz Gadelha, Anna Guerman, Georgi Smirnov

12.30-1.00 Performance Comparison of Attitude Determination Algorithms in a Microcontroller Platform Ricardo Oliveira Duarte, Luiz Siqueira Martins-Filho, Hélio Koiti Kuga

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SPECIAL SESSION 2. Unmanned Aerial Vehicles LIT – Room 1 Chair: Krzysztof Slavomir Sibilski 11.00-11.30 Nonlinear flight dynamics analysis of flapping wing micro-air vehicle model

Victor Mwenda Mwongera, Mark Lowenberg

11.30-12.00 UAS test platform for parameter identification of powered paraglider Andras Nagy, Jozsef Rohacs

12.00-12.30 Modeling and simulation of flapping wings nano-robots dynamics of flight Krzysztof Slavomir Sibilski

12.30-1.00 Structural modeling and optimization of a joined-wing configuration of a high-altitude long-endurance (HALE) aircraft at global and local levels Valentina Kaloyanova, Karman Ghia, Urmila Ghia

SPECIAL SESSION 10. System identification: Theory and Application in Aerospace, Biology, Engineering and Science IAI – Amphitheatre Chair: Sunil L. Kukreja 11.00-11.30 Robust nonlinear estimation in case of noises of unknown statistics

Endre Nagy

11.30-12.00 System Identification using Interval Analysis Erik-Jan van Kampen, Qi-Ping Chu, Bob Mulder

12.00-12.30 Flutter Prediction Analysis using Output Only Flight Test Jie Zeng, Sunil L. Kukreja

12.30-1.00 Global nonlinear system identification using multivariate splines Cornelis C. de Visser

GENERAL SESSION 1. IAI – Auditorium Chair: Kenzu Abdella

11.00-11.30 Flight or Fight - Battle of the Overheads Bins: Another Factor Contributing to the Air Rage Phenomenon Joyce A. Hunter

11.30-12.00 Temperature-dependent explicit stress-strain relations for stainless steel alloys Kenzu Abdella

12.00-12.30 Convergence study of the condition number for some preconditioners to the Stokes problem Omar Ali Aleyan

12.30-1.00 GA Optimization of Point Placement on a Hypersphere Janko Milutinovic, Dragoljub Pokrajac, Sam Kennerly

1.00-2.00 LUNCH BREAK

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AFTERNOON PLENARY SESSION – LIT - Main Auditorium 2.00-2.50 Keynote Talk: SANDRO DA SILVA FERNANDES

Title: Analytical Theory of Optimal Low-Thrust Limited-Power Trajectories Chair: Brian White

2.50-3.40 Keynote Talk: SUNIL L. KUKREJA Title: A Computational Biology Approach to Modelling and Identification of Human Physiology Chair: Antonio Prado

3.40-4.30 Keynote Talk: JOSE MANOEL BALTHAZAR Title: Recent Developments on Regular and Irregular Oscillations and Their Possible Controls in a “Macro”, “MEMS” and “NEMS” Nonlinear Engineering Science Chair: Firdaus E. Udwadia

4.30-5.00 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 1. Modern Aeroelasticity LIT – Main Auditorium Chair: Justin Jaworski 5.00-5.30 Aeroservoelastic Flight Control Design For Military Aircraft Weapon System

Wolfgang Luber

5.30-6.00 Critical and post-critical study of elastic aircraft wings subjected to non-conservative loads S. Ahmad Fazelzadeh, Abbas Mazidi

6.00-6.30 Aeroelastic Aircraft Landing Phase Simulation by Using Hybrid Modeling Approach S.Ahmad Fazelzadeh, Hanif Sadat Hoseini

6.30-7.00 Contributions on smart structures and materials for applications on aeroelasticity and power harvesting Flávio D. Marques, Carlos De Marqui Jr., Volnei Tita

MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control LIT – Small Auditorium Chair: Luiz Carlos DeSouza 5.00-5.30 Combined Attitude and Solar Tracking (CAST) System for Spacecraft

Mohd Faizal Allaudin, Renuganth Varatharajoo 5.30-6.00 Integer ambiguity resolution in attitude determination using GPS measurements

Leandro Baroni, Hélio Koiti Kuga 6.00-6.30 Modeling a Reaction Wheel

Valdemir Carrara 6.30-7.00 Attitude Synchronization for swarms of Pico-Satellites using Consensus Algorithms

Sid Ahmed Attia, Ariel Pratomo

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SPECIAL SESSION 2. Unmanned Aerial Vehicles LIT – Room 1 Chair: Andras Nagy 5.00-5.30 Determination of Intelligent Control system for a Nonlinear Model of an Autonomous

Scale-Model Helicopter by Emotional Learning Approach Abolfazl Mokhtari

5.30-6.00 Non linear filtering technique analysis for Navigation of an UAV Saman Mukhtar Siddiqui, Jiancheng Fang

6.00-6.30 Error Analysis of MEMS sensor data using Allan Variance technique Saman Mukhtar Siddiqui, Fang Jiangcheng

6.30-7.00 Discussion SPECIAL SESSION 10. System identification: Theory and Application in Aerospace, Biology, Engineering and Science IAI – Amphitheatre Chair: Sunil L. Kukreja 5.00-5.30 Frequency response analysis of an aircraft shell panel subject to geometrical

imperfections and material properties variations, using a stochastic finite element approach Francisco Scinocca, Airton Nabarrete

5.30-6.00 Use of subjective analysis in flight safety analysis Jozsef Rohacs, Vladimir Alexandrovich Kasaynov

6.00-6.30 CFD assisted analysis of Propeller theories Sathish Krishnan P.S.

6.30-7.00 Discussion SPECIAL SESSION 7. Methods of Nonlinear Analysis for Partial Differential Equations IAI – Auditorium Chair: Eduard-Wilhelm Kirr 5.00-5.30 Stability for fluid structure interaction models with non-linear dissipation at the

interface Roberto Triggiani

5.30-6.00 Bifurcations of Nonlinear Bound-States in Schroedinger type equations Eduard-Wilhelm Kirr

6.00-6.30 Elementary Numerical Differential and Integral Methods to Determine the Reaction Rates of Chemical Reactions Christopher Gunaseelan Jesudason

6.30-7.00 Discussion 7.00 PM RECEPTION - LIT

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POSTER SESSION – LIT GEN On the structural stability of systems of differential equations occurring in aerospace

engineering Stefan Balint

GEN Size, shape and stability evaluation for meniscus appearing in microfiber growth by pulling down method Agneta Maria Balint, Stefan Balint

GEN Model based planning of the capillary and thermal conditions for the growth of a silicon tube with a prior given inner and outer radius Loredana Tanasie, Stefan Balint

GEN Introduction to Theory of Physical-Geometry Space Ahmad Sabihi

GEN An Approach Towards the Proof of the Strong Goldbach's Conjecture for Sufficiently Large Even Integers Ahmad Sabihi

GEN Elementary proof of the Fermat's Last Theorem Artur Korgul, Rafał Andrzej Korgul

GEN Fuzzy differential equations Tofigh Allahviranloo

GEN Impact Behaviour of Sandwich Plates : Theoretical and experimental investigation Ertan Tengiz, Demet Balkan, Halit Suleyman Turkmen, Zahit Mecitoglu

GEN On Thermal Instabilities Occuring in Fires Vasily Novozhilov

SS6 Homogenization Results for a Wave Equation with Interior and Boundary Damping Claudia Timofte

SS6 Optimal Transfer Trajectories from Lagrangian Collinear Points Mihai Popescu

SS6 Computational Methods for Panel Flutter Analysis Florin Frunzulica, Marius Stoia-Djeska, Alexandru Dumitrache

SS6 Unsteady free-wake vortex particle model for prediction of the aerodynamic loads of HAWT rotor blades Florin Frunzulica, Alexandru Dumitrache, Horia Dumitrescu, Vladimir Cardos

SS6 Generalized Riccati equations in Banach spaces Viorica Mariela Ungureanu

SS6 Three-dimensional effects on rotor blade sections in stall Vladimir Cardos, Horia Dumitrescu

SS6 A numerical algorithm to study the propagation of elastic plastic waves in bars Olga Martin

SS6 Stability Study of Constrained Systems Ion Stroe

SS6 Studies for type-II and type-III intermittencies Ezequiel del Rio, Sergio Elaskar, Jose Manuel Doloso

SS1 Neural Network based Model Predictive Controller for Simplified Heave Model of an Unmanned Helicopter Mahendra Kumar Samal, Sreenatha Anavatti, Matthew Garratt

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Thursday, July 1

MORNING PLENARY SESSION – LIT - Main Auditorium 8.30-9.20 Keynote: OTHON C. WINTER

Title: On the Dynamics of Triple Asteroid Systems Chair: Harry H. Hilton

9.20-10.10 Keynote Talk: BRIAN WHITE Title: Path Planning and Decision Making for Co-operative Multiple UAVs Chair: Elbert Macau

10.10-10.40 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 2. Astrodynamics LIT – Main Auditorium Chair: Antonio Prado 10.40-11.10 The close approach between a planet and a cloud of particles

Vivian M. Gomes, Antonio F.B.A. Prado

11.10-11.40 Closed Loop Control System Applied to Transfer Maneuvers Using Continuous Thrust Evandro Marconi Rocco, Eliel Wellington Marcelino, Antonio F,B.A. Prado

11.40-12.10 Optimal Low-Thrust Limited-Power Transfers in a Non-central Gravity Field – Transfers Between Arbitrary Orbits Carlos Silveira, Sandro da Silva Fernandes

12.10-12.40 Maneuvers control of a spacecraft through aerodynamics changes under the effects of the upper atmosphere Willer Gomes, Evandro Marconi Rocco, Valdemir Carrara

MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control LIT – Small Auditorium Chair: Valdemir Carrara 10.40-11.10 Fly-by guidance approach for rendezvous and capture of non-cooperating targets

Gilberto Arantes Jr., Ananth Komanduri, Daniel Bindel, Luiz de Siqueira Martins-Filho

11.10-11.40 Attitude Control of Spacecraft Using Three Axis Magnetorquer Only Ahmad Faraag, Ahmad Raffie, Ahmad Bahgat

11.40-12.10 Preparation of Uniformly Distributed Onboard Guide Star Catalog Masood Ur Rehman

12.10-12.40 Fine maneuver control for spacecraft simulator by reaction wheels using sliding mode speed controller Mohammad Hossein Beheshti

12.40-13.10 On the modeling of a flexible spacecraft attitude motion considering fuel sloshing Vahid Rezvani

13

SPECIAL SESSION 11. Nuclear Power and Research Systems Modeling LIT – Room 1 Chair: Claubia Pereira 10.40-11.10 Mathematical modelling of a system for brachytherapy

Wagner Leite Araujo, Tarcisio Passos Ribeiro Campos

11.10-11.40 Comparative study of the neutron production by spallation and fusion reactions for subcritical hybrid systems applications Graiciany P Barros, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa, Patrícia A. L. Reis

11.40-12.10 Comparation between WIMSD-5B and MCNPX 2.6.0 codes simulating a PWR fuel element Clarysson A. Mello da Silva, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa

12.10-12.40 Evaluation of spallation source for neutrons production by Monte Carlo methods Maurico Gilberti, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa, Clarysson A. Mello da Silva

SPECIAL SESSION 9. Petri nets for complex systems IAI – Amphitheatre Chair: Joslaine Cristina Jeske de Freitas 10.40-11.10 Simulation of Industrial Metabolism using Predicate Transition Petri Nets combined

with Differential Equations Liliane Nascimento Vale, Stéphane Julia, Núbia Rosa Silva, Márcio Souza Dias

11.10-11.40 Distributed modelling and simulation of complex systems using Petri net Fabrício Junqueira, Cristiano da Silva Costa, Diolino José dos Santos Filho, Paulo Eigi Miyagi

11.40-12.10 Control Algorithms Partition Method for Distributed Control Systems Diolino Jose dos Santos Filho, Andre Cesar Martins Cavalheiro

12.10-12.40 A Hybrid Method to Generate Control Algorithms for Complex Systems Francisco Yastami Nakamoto, Diolino José dos Santos Filho, Fabrício Junqueira, Paulo Eigi Miyagi

GENERAL SESSION 2. IAI – Auditorium Chair: Vanessa Avelino Xavier de Camargo 10.40-11.10 Evolutionary Programming with Adaptative Stable Distributions

Leopoldo Bulgarelli Carvalho

11.10-11.40 Semi active suspension control techniques using only one measurement sensor Fábio Luis Marques dos Santos, Luiz Carlos Sandoval Goes, Alberto Luiz Serpa

11.40-12.10 Designing Phase-Locked Loops for Frequency Modulation Atomic Force Microscope Atila Madureira Bueno, José Manoel Balthazar, José Roberto Castilho Piqueira

12.10-12.40 Improvement in Relational Databases Query Using Fuzzy Logic Vanessa Avelino Xavier de Camargo, Wemerson Leonardo Ramos, Esdras Teixeira Costa, Marcos Wagner Souza Ribeiro

12.40-2.20 LUNCH BREAK

14

1.10-2.10 Wolfram Research Tutorial: An Overview of Mathematica for Education Igor Canales Antonio

AFTERNOON PLENARY SESSION – LIT - Main Auditorium 2.20-3.10 Keynote Talk: SILVIA MARIA GIULIATTI WINTER

Title: New Horizons Mission and the Pluto-Charon System Chair: Roberto Triggiani

3.10-4.00 Keynote Talk: IRENA LASIECKA Title: Well-posedness and long time behavior of finite energy solutions corresponding to 3-d flows interacting with dynamic elasticity Chair: Toshiya Nakamura

4.00-4.30 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 2. Astrodynamics LIT – Main Auditorium Chair: Vivian M. Gomes 4.30-5.00 Innovative Dynamical Analysis of the Algorithmic Weak Stability Boundary

Maisa de Oliveira Terra, Priscilla Andressa de Sousa Silva

5.00-5.30 Escape Basins and Chaotic Saddles in the Planar Circular Restricted Three-Body Problem for the Earth-Moon System Sheila Crisley de Assis,, Maisa de Oliveira Terra

5.30-6.00 Gravitational Capture under the Restricted Three-Body Problem Alexandre Lacerda Machuy Francisco, Antonio F.B.A. Prado, Teresinha de Jesus Stuchi

6.00-6.30 Using extended Kalman filter and least squares method for spacecraft attitude estimation. Roberta Veloso Garcia, Helio Koiti Kuga, M.C. Zanardi

6.30-7.00 A comparison of gravity-assisted maneuvers in different planets to optimize interplanetary missions Flaviane Venditti, Evandro Marconi Rocco, Antonio F.B.A. Prado, Alexander A. Sukhanov

15

SPECIAL SESSION 12. Integral Equations and their Applications LIT – Small Auditorium Chair: Luis Castro 4.30-5.00 Stability of Fredholm integral equations in the framework of generalized metric

spaces Luis Castro

5.00-5.30 Constructions of the approximate solutions of singular integral equations by using the Tikhonov regularization and the theory of reproducing kernels Saburou Saitoh

5.30-6.00 Integral equations of Wiener-Hopf type characterized by piecewise almost periodic elements in Lebesgue spaces with weights Anabela Silva

6.00-6.30 Splitting property for singular integral operators with a weighted shift Edixon Rojas

6.30-7.00 Fredholm-Stieltjes integral equations with (O-M)integral in time scales and applications Luciano Barbanti, Berenice Camargo Damasceno, Jose Manoel Balthazar

SPECIAL SESSION 11. Nuclear Power and Research Systems Modeling LIT – Room 1 Chair: Antonella Lombardi Costa 4.30-5.00 Initial Development of a Coupling Methodology between Thermal-Hydraulic and

Neutron Kinetic Codes for Simulation of the IPR-R1 TRIGA Reactor Claubia Pereira, Patrícia A. Lima Reis, Antonella Lombardi Costa, Maria Auxiliadora Fortini Veloso, Clarysson A Mello da Silva

5.00-5.30 Design of a deuteron accelerator for a portable neutron generator Wagner Leite Araujo, Tarcisio Passos Ribeiro Campos

5.30-6.00 GB - a linking code between MCNP and ORIGEN2.1 - DEN/UFMG version Renan Cunha, Claubia Pereira, Daniel Campolina, André Cavatoni, Maria Auxiliadora Fortini Veloso

6.00-6.30 Application of Nuclear Codes WIMSD-5B and MCNPX 2.6.0 to a Qualitative Evaluation of MHR (MODULAR HELIUM REACTOR) Clarysson A. Mello da Silva, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa

6.30-7.00 A preliminary neutronic evaluation and depletion study of HTR using WIMSD5 and MCNPX2.6.0 codes Fabiano Cardoso Silva, Claubia Pereira, Clarysson A. Mello da Silva, Maria Auxiliadora Fortini Veloso, Antonella Lombardi Costa

16

SPECIAL SESSION 9. Petri nets for complex systems IAI – Amphitheatre Chair: Diolino Jose dos Santos Filho 4.30-5.00 A model to represent human behavior in workflow management systems.

Joslaine Cristina Jeske de Freitas, Stephane Julia, Robert Valette 5.00-5.30 Safety Instrumented Systems Design Based on Bayesian network and Petri net

Reinaldo Squillante Junior, Diolino Jose dos Santos Filho, Jose Isidro Garcia Melo, Fabricio Junqueira, Paulo Eigi Miyagi

5.30-6.00 Intelligent Building – Modeling and Reconfiguration using Petri Net and Holons Julio Arakaki, Diolino Jose dos Santos Filho, Fabricio Junqueira, Paulo Eigi Miyagi

6.00-6.30 Scheduling Heuristic based on Time Windows for Service-oriented Architecture Marcosiris Amorim de Oliveira Pessoa, Diolino Jose dos Santos Filho, Jose Isidro Garcia Melo, Fabricio Junqueira, Paulo Eigi Miyagi

6.30-7.00 Collaborative Control Model for Multifunctional Machine Tools Environment Osvaldo Luis Asato, Diolino Jose dos Santos Filho, Fabricio Junqueira, Paulo Eigi Miyagi

SPECIAL SESSION 3. Advances in Nonlinear Differential Equations IAI – Auditorium Chair: Anjan Biswas 4.30-5.00 Optical solitons with higher order dispersion

Anjan Biswas 5.00-5.30 Wavelet transforms and its connection to established theories and Image processing

Bharat Namdeo Bhosale 5.30-6.00 Solutions of Kadomtsev-Petviashvili equation with power law nonlinearity in 3+1

dimensions Chaudry Masood Khalique

6.00-6.30 The Combined Effect of the Linear and Nonlinear Couplings on the Phase and Velocity Shifts of Interacting Solitons in Coupled Nonlinear Schrodinger Equations Michail D Todorov

6.30-7.00 Generalized Radon transform and Microlocal analysis Guoping Zhang, Fengshan Liu

17

POSTER SESSION – LIT M4 A Comparision of PO Approximations with FDA Method to Obtain RCS of Simple

Shapes Ahmad Sabihi, Mohammad Ali Vaziry Z.

M4 Smart beam deflection behavior due to two or more SMA wires attachment Hamid Salehi, Saeed Zeiaei Rad, Mohammad Reza Zakerzadeh, Mohammad Ali Vaziry Zanjani

M4 On the Laser Cross Section of Various Targets Ahmad Sabihi, Mohammad Ali Vaziry Z.

M4 On the Electromagnetic Waves and Propagation in Relativity-Quantum Space Ahmad Sabihi

M4 Solving the Sitnikov Equation by Means of the Fourier Expansion Mojtaba Dehghan Manshadi, Mohammad Farahani, Mohammad Ali Vaziry

M4 On the Modification of Node Swapping Method in graph partitioning Omid Talebi, Ahmad Sabihi, Pejman Khadivi

M4 A Non-Model Based Damage Detection Technique Using Dynamically Measured Flexibility Matrix Mehdi Salehi, Saeed Ziaei-Rad, Mostafa Ghayour, Mohammad Ali Vaziri-Zanjani

M4 Design and Simulation of Intelligent Aircraft Longitudinal Autopilots Using Particle Swarm Optimization Algorithms Mostafa Lotfi Forushani, Bahram Karimi, Ghazanfar Shahgholian, Alireza Karami Horestani

M4 Robust SDC Parameterization for a Class of Extended Linearization Systems Sam Nazari, Bahram Shafai

M4 Pseudo-stochastic-chaotic systems in Engineering Applications Hilda Angela Larrondo, Luciana De Micco

M4 Finite volume simulation of supersonic flows Sergio Elaskar, José Tamagno

M4 Finite volume solution of compressible magnetohydrodynamics equations Sergio Elaskar, Livio Maglione, Mariano Martinez

SS8 Fractional differential equations with piecewise constant argument deviations William Edmond Dimbour

SS8 Pseudo almost periodic and pseudo almost automorphic functions and their applications to fractional differential equations Ti-Jun Xiao

SS8 New results on fractional differential and integrodifferential equations in Banach spaces Jin Liang

SS8 Optimal control of a class of fractional diffusion equation Gisele Mophou

SS8 Existence and uniqueness of mild solution for fractional integro-differential equations Gaston Mandata N’Guérékata, Fang Li

SS4 Ultimate boundedness of solutions of non-homogeneous vector differential equation of the third-order Mathew Omonigho Omeike

SS4 New stability and boundedness results of solutions of nonlinear differential equations of second and third order with variable delay Cemil Tunc

18

Friday, July 2

MORNING PLENARY SESSION – LIT - Main Auditorium 8.30-9.20 Keynote Talk: TOSHIYA NAKAMURA

Title: JAXA's Aeronautical Research Project for Civil Transport - Endeavours to Enhance Safety and Environmental Friendliness Chair: S.N. Balakrishnan

9.20-10.10 Keynote Talk: FIRDAUS E. UDWADIA Title: Advances in the Modeling and Control of Complex Multibody Systems Chair: Naira Hovakimyan

10.10-10.40 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 2. Astrodynamics LIT – Main Auditorium Chair: Evandro Marconi Rocco 10.40-11.10 The FEFF Methodology for Proximity Maneuvering Spacecraft Formations

Laura Garcia-Taberner, Josep J. Masdemont

11.10-11.40 Precise predicted extended ephemeris solution for GPS Rajendra P. Prasad, Hélio Koiti Kuga, Nagaraj Dixit

11.40-12.10 Internal loading distribution in a statically loaded ball Mário César Ricci

12.10-12.40 Evaluation of the Fuel Consumption in Orbital Maneuvers with Time and Position Constraints Thais Carneiro Oliveira, Evandro Marconi Rocco, Antonio F.B.A. Prado

SPECIAL SESSION 6. Mathematical Research In Dynamical Systems Theory LIT – Small Auditorium Chair: Maisa de Oliveira Terra 10.40-11.10 Risk-Sensitive Second Grade Optimal Filtering Design

Maria Aracelia Alcorta-Garcia, Hector Flores Cantu, Sonia Guadalupe Anguiano-Rostro

11.10-11.40 Biparametric investigation of the general standard map: multistability and crises Priscilla Andressa de Sousa Silva, Maisa de Oliveira Terra

11.40-12.10 Non-linear Inverse Dynamics Control of the Smart Column with Support Excitation S. Ahmad Fazelzadeh, E. Azadi, M. Azadi

12.10-12.40 Risk-Sensitive Third Grade Optimal Filtering Design Maria Aracelia Alcorta-Garcia, Hector Raymundo Flores-Cantu, Mauricio Torres Torres

19

SPECIAL SESSION 1. Neural Network Dynamics LIT – Room 1 Chair: Seenith Sivasundaram 10.40-11.10 Bifurcation Networks: An Approach to Cortical Modeling and Higher Level Brain

Function Nabil H. Farhat

11.10-11.40 Bumps in a two population neural field model John Wyller

11.40-12.10 Controlling the chaotic dynamics of neural networks Francisco Welington Lima, Tarik Hadzibeganovic

12.10-12.40 Almost Periodic Solutions of Impulsive Hopfield Neural Networks with Periodic Delays Haydar Akca, Valery Covachev, Zlatinka Covacheva

MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering IAI – Amphitheatre Chair: , Leonardo D. Chiwiacowsky 10.40-11.10 An Hierarchical Approach for the Structural Damage Identification

Leonardo B. L. Santos, Leonardo D. Chiwiacowsky, Haroldo F. Campos Velho

11.10-11.40 On the Active Vibration Control and Stability of the Tubular Structures by Piezoelectric Patch-Like Actuators Sergey N. Shevtsov, Michail B. Flek, Vladimir A. Acopyan, Vladimir N. Axenov

11.40-12.10 Passive Thermal Control with Pulsating Heat Pipe Liomar de Oliveira Cachuté, Roger Ribeiro Riehl

12.10-12.40 On an Optimal Linear Control Design Applied to a Non-Ideal and Ideal Structure controlled through MR Damper Angelo Marcelo Tusset, Fábio Roberto Chavarette, Jorge L. P. Felix, José Manoel Balthazar

MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry IAI – Auditorium Chair: Amer Farhan Rafique 10.40-11.10 Implementation, Validation and Testing of an Inverse Design Tool for Redesigning

NACA 65-410 Wing Profile Árpád Veress, András Nagy, József Rohács

11.10-11.40 Sensitivity analysis of an aircraft shell panel with geometry imperfections Airton Nabarrete, Francisco Scinocca

11.40-12.10 Trajectory Optimization of Air Launched Satellite Launch Vehicle using Genetic Algorithm Amer Farhan Rafique

12.10-12.40 Design and Optimization of Slotted Tube Grain Configuration using Simulated Annealing Ali Kamran, Liang Guozhu

12.40-2.20 LUNCH BREAK

20

AFTERNOON PLENARY SESSION – LIT - Main Auditorium 2.20-3.10 Keynote Talk: STANISLAV VASSILYEV

Title: Analysis of dynamics of hybrid systems with nonlinear vector fields by homomorphic mappings Chair: Firdaus E. Udwadia

3.10-4.00 Keynote Talk: ELBERT MACAU Title: Controlling Chaotic Transient and the Improvement of System Flexibility Chair: Irena Lasiecka

4.00-4.30 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 2. Astrodynamics LIT – Main Auditorium Chair: Helio Koiti Kuga 4.30-5.00 Analysis of disturbing effects in the dynamical model of orbit determination using

GPS Paula C.P.M. Pardal, Rodolpho Vilhena de Moraes, Helio Koiti Kuga

5.00-5.30 Artificial Satellites: Orbital Perturbations Rodolpho Vilhena de Moraes

5.30-6.00 Optimization of Low-Thrust Spiral Transfers between Two Given Orbits Alexander A. Sukhanov

SPECIAL SESSION 4. Stability and Lyapunov Theory SPECIAL SESSION 8. Advances in Fractional Differential Equations LIT – Small Auditorium Chair: Olufemi Adeyinka Adesina 4.30-5.00 Some remarks on the exponential stability and periodicity of solutions for certain

delayed differential equations of fourth order Olufemi Adeyinka Adesina

5.00-5.30 Pseudo-almost automorphic solutions to a class of semilinear fractional equations Marcos Rabelo

5.30-6.00 Numerical analysis for singularly perturbed delay differential equations Fevzi Erdogan

21

SPECIAL SESSION 1. Neural Network Dynamics LIT – Room 1 Chair: Haydar Akca 4.30-5.00 Multistability in impulsive Hopfield neural networks with time-dependent and

distributed delays Eva Kaslik, Seenith Sivasundaram

5.00-5.30 Artificial neural networks applied to low cost INS/GPS integrated navigation systems Edmundo Alberto Marques Filho, Atair Rios Neto, Helio Koiti Kuga

5.30-6.00 Stability and Bifurcation Analysis Of Three Neuron Delayed Network Model Of Hopfield Type Narayan Chandra Majee, Amiya Bhusan Roy

MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering IAI – Amphitheatre Chair: Ilse Camacho Cervantes 4.30-5.00 Spacecraft Trajectory Optimization Using State Parameterization and Interval

Analysis Elwin de Weerdt, Q.P. Chu, J.A. Mulder

5.00-5.30 Hybrid Tracking Control of Fixed Wing Aerial Vehicles Ilse Camacho Cervantes, Fany Mendez Vergara

5.30-6.00 A Micro-Tuning-Fork Gyroscope Coupling with an Electrodynamic Engine Ana Rosa Klinke, J.M. Balthazar, Luiz Palacios Felix, F.R. Chavarete

MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry IAI – Auditorium Chair: Amer Farhan Rafique 4.30-5.00 Optimization of an Aeronautical Composite Structure through a Parallel Multilevel

Approach Leonardo Dagnino Chiwiacowsky, Paolo Gasbarri, Haroldo Fraga de Campos Velho, Arthur Tórgo Gómez

5.00-5.30 New heuristic approach for the multiobjective nonidentical circle packing problem José Carlos Becceneri

5.30-6.00 Information Entropy as a Tool for Innovation Projects Fuzzy Front End Decision Luis Wwaack Bambace

8.00 PM BANQUET – Churrascaria Vila D'Aldeia

http://www.villadaldeia.com.br/

22

POSTER SESSION – LIT M5 Optimal PID Controller Tuning in Missile Design Based on PSO Algorithm

Alireza Karami Horestani, Mostafa Lotfi Forushani, Mohamad Hoseinyar

M5 Comparison Study of Geometrically and Numerically Regression of the Star Grain Design for SRM Soe Hlaing Tun, Xiang Hong Jun

M5 Experimental Study of Laminar Horseshoe Vortex Using PIV Zaw Zaw Oo, Muhammad Yamin, Hua Zhang

M5 Efficient Shock Capturing Scheme for Transonic Aerodynamics Hasan Junaid Hasham

M5 Review of Reduced Order Models for CFDCSD Interaction Problems Hasan Junaid Hasham

M5 Study on Random Initial Point Trajectory Planning for Missile Borne Unmanned Air Vehicle Wang Wei, Wang Hua, He LinShu

M5 Integrated Multidisciplinary Design and Multi-Objective Optimization Approach for Space Launch Vehicle Naeem Zafar, He LinShu

M5 Constraint Handling Approach using Multi-Objective Evolutionary Optimization Naeem Zafar, He LinShu

M5 Parametric Design Approach for Aero-performance of Hypersonic Reentry Body Muhammad Amjad Sohail, Yan Chao, Zahid Maqbool

M5 Inviscid and Viscous Computation on Aerodynamic Characteristics of a Conventional Projectile with and without Fins Configuration by using Flux Difference Scheme Muhammad Amjad Sohail, Yan Chao, Zahid Maqbool, M. Yamin Younis, Muhammad Afzal, Mukkarum Hussain

M5 Application of Sensitivity Region Based Robust Design Approach in MDO of Flight Vehicle Ma Ying, He LinShu

M5 Effectiveness optimization for a surface-to-air missile system based on MDO Jiang Huan, Chen Wanchun

M5 Optimization of Free-Flying Time between Two Joined Stages for Solid-Fuel Ballistic Missile Htoo Hlaing Win, Linshu He

SS10 Steady State Problems in Financial Option Pricing Dejun Xie

SS10 A Fuzzy Neural Network for Emitter Identification Mohamad Hoseinyar, Mostafa Lotfi Forushani

SS10 FPGA Implementation of LMS-Based System Identification Core Omid Sharifi Tehrani, Ebrahim Hosseini, Mohsen Ashourian

SS10 Damping identification in a non-linear aeroelastic structure Gareth A. Vio

SS5 Numerical Analysis of Aerodynamic Performance of a Aircraft Wing With Simulated Glaze Ice Accretion Aung Ko Wynn, Cao Yi Hua, Ma Cao

SS5 Physical Programming based Multidisciplinary Optimization for 2D Turbine Airfoil Zhang Nannan

23

Saturday, July 3

MORNING PLENARY SESSION – LIT - Main Auditorium 8.30-9.20 Keynote Talk: Robert M.M. Matheijj

Title: Flow in networks Chair: S. Sivasundaram

9.20-10.10 Keynote Talk: NAIRA HOVAKIMYAN Title: The Theory of Fast and Robust Adaptation Chair: Antonio Prado

10.10-11.00 Keynote Talk: S.N. BALAKRISHNAN Title: Approximate Dynamic Programming Based Control for Aircraft and Space Vehicles in the Presence of Uncertainties Chair: Brian White

MINISYMPOSIUM 1. Modern Aeroelasticity LIT – Small Auditorium Chair: Oddvar Bendiksen 9.00-9.30 Limit Cycle Oscillations of Very Flexible High-Aspect-Ratio Wings

Justin W. Jaworski, Earl H. Dowell

9.30-10.00 Dynamic Instability of Viscoelastic Plate in Supersonic Flow Botir Usmonov

10.00-10.30 Reconstruction of Aerodynamic Loads Based on Inverse Analysis Toshiya Nakamura, Hirotaka Igawa

10.30-11.00 Bending without normal stress case on an isotropic micropolar beam Juan Alejandro Vazquez Feijoo

11.00-11.30 COFFEE BREAK PARALLEL SESSIONS MINISYMPOSIUM 1. Modern Aeroelasticity LIT – Main Auditorium Chair: Wolfgang Luber 11.30-12.00 Application of Correction Methods for Aeroelastic Stability Analysis of Wing

Structures in Transonic Flow Roberto Gil Annes da Silva Ricardo Franco Amaral

12.00-12.30 The influence of starting transients, aerodynamic definition and boundary conditions on elastic and viscoelastic panel and wing flutter Craig G. Merrett, Harry H. Hilton

12.30-1.00 Research on Aileron Buzz Controling by Changing Boundary Layer Thickness Masato Tamayama

24

1.00-1.30 Dynamic responses and eigenanalysis of non-classical vibrating beams Julio R. Claeyssen , Teresa Tsukazan, Rosemaira D. Copetti, Antonio L. Bidel

1.30-2.00 A bifurcation based approach to the analysis and control of flexible aircraft Mohamed Nadjib Baghdadi

SPECIAL SESSION 5. Contributions of PhD students (and post-doctoral researchers) LIT – Small Auditorium Chair: Anne Caroline Bronzi

11.30-12.00 Axi-symmetric, Darcy-Brinkman-Forchheimer flow through an annulus Pradeep Ganapathi Siddheshwar, Ashoka Basavaraje Gowda Sangarashettahally

12.00-12.30 Heat transfer in a Darcy-Forcheimmer-Brinkman flow through a curved channel Mahesha Narayana, Vishwanath Kadaba Puttanna, Pradeep Ganapathi Siddheshwar

12.30-1.00 Weak solutions of the incompressible ideal flow equations Anne Caroline Bronzi

1.00-1.30 Superposition of a pulsating and oscillating flow of a complex structural liquid Edtson Emilio Herrera-Valencia

1.30-2.00 Differential Transform Method of Solution for Non-Linear Boundary Value Problem: An Illustration Madhavanpillai Sumathykuttyamma Jagadeesh Kumar, Suresh G Singh, Pradeep Ganapathi Siddheshwar

2.00-2.30 A Lane-Emden-Fowler type problem Dragos-Patru Covei

GENERAL SESSION 3. LIT – Room 1 Chair: Luis Waack Bambace 11.30-12.00 Diversity QPSK-CDMA schemes for LEO mobile communication

Luis Waack Bambace

12.00-12.30 A new real inversion formula for the Sumudu Transform Fethi Bin Muhammad Belgacem

12.30-1.00 Dynamic simulation of light space structures by finite element modeling and order reduction in state space Leandro Gonzalez, Eduardo N Zapico

1.00-1.30 Nonlinear Analysis of Cables and Guyed Towers Shahin Nayyeri Amiri

1.30-2.00 6-DOF data and aerodynamic models for real-time flight simulation Pedro S. Giraudo, Javier E. Luiso, Eduardo N. Zapico, Horacio A. Abbate

25

MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering IAI – Amphitheatre Chair: ,Ismail Hameduddin 11.30-12.00 On the Nonlinear Dynamics and Control of Modal Interactions Resulting from the

Longitudinal and Lateral Flight of an Aircraft Rodrigo Bassinello Ramazotti

12.00-12.30 Aircraft Generalized Dynamic Inversion Control Abdulrahman Hasan Bajodah, Ismail Hameduddin

12.30-1.00 Position and Vibration Control of a Nonlinear Slewing Flexible Structure Considering Fluid-Structure Interaction André Fenili, Cayo Prado Fernandes Francisco

1.00-1.30 Semi-Lagrangian Reachability Analysis for Aircraft Safe Flight Envelope Determination Eddy van Oort

MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry IAI – Auditorium Chair: Amer Farhan Rafique 11.30-12.00 Design and Optimization of Star Grain Configuration using Simulated Annealing

Ali Kamran, Khurram Nisar, Amer Farhan Rafique, Qasim Zeeshan

12.00-12.30 Development of a new algorithm for optimization of closed-loop liquid rocket engines Davood Ramesh

12.30-1.00 Robust Design Optimization of Booster Phase Energy Management of Dual Thrust Propulsion System Muhammad Aamir Raza

1.00-1.30 Nonlinear Stability and Optimization Techniques Arthur Cave

END OF CONFERENCE

26

ABSTRACTS

TABLE OF CONTENTS

KEYNOTE TALKS 2

GENERAL SESSION 7

SPECIAL SESSION 1. Neural Network Dynamics 14

SPECIAL SESSION 2. Unmanned Aerial Vehicles 16

SPECIAL SESSION 3. Advances in Nonlinear Differential Equations 19

SPECIAL SESSION 4. Stability and Lyapunov Theory 21

SPECIAL SESSION 5. Contributions of PhD Students (and Post-Doctoral Researchers) 23

SPECIAL SESSION 6. Mathematical Research in Dynamical Systems Theory 25

SPECIAL SESSION 7. Methods of Nonlinear Analysis for Partial Differential Equations 29

SPECIAL SESSION 8. Advances in Fractional Differential Equations 30

SPECIAL SESSION 9. Petri Nets for Complex Systems 31

SPECIAL SESSION 10. System Identification: Theory and Application in Aerospace, Biology,Engineering and Science

34

SPECIAL SESSION 11. Nuclear Power and Research Systems Modeling 38

SPECIAL SESSION 12. Integral Equations and Their Applications 41

MINISYMPOSIUM 1. Aeroelasticty 43

MINISYMPOSIUM 2. Astrodynamics 49

MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control 55

MINISYMPOSIUM 4. Mathematical Applications in Electrical, Aerospace and Control Engineering 60

MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry 67

Author Index 74

27

KEYNOTE TALKS

A.V. BALAKRISHNAN, UCLA, United States

Title: Flutter Analysis in Viscous Flow

The problem of Flutter - an inherent destructive instability of aircraft in subsonic flow which mandatesthe maximum speed at any altitude by the Federal Aviation Administration to be within 15% of theFlutter Boundary-continues to be of interest even as we consider unmanned aircraft. Much is understoodabout Flutter phenomena in nonviscous airflow but the extension to viscous flow is still open - and theonly known technique involves the Prandtl Boundary Layer theory, still not proven mathematically.

S.N. BALAKRISHNAN, Missouri University of Science and Technology, USA

Title: Approximate Dynamic Programming Based Control for Aircraft and Space Vehiclesin the Presence of Uncertainties

Approximate dynamic programming formulation implemented with an Adaptive Critic (AC) based neuralnetwork (NN) structure has evolved as a powerful alternative technique that eliminates the need forexcessive computations and storage requirements needed for solving the Hamilton-Jacobi-Bellman (HJB)equations. A typical AC structure consists of two interacting NNs. In this paper, a novel architecture,called the Single Network Adaptive Critic (SNAC) is used to solve control-constrained optimal controlproblems. Only one network is used that captures the mapping between states and the cost function.This approach is applicable to a wide class of nonlinear systems where the optimal control (stationary)equation can be explicitly expressed in terms of the state and costate variables. A non-quadratic costfunction is used that incorporates the control constraints. Necessary equations for optimal control arederived and an algorithm to solve the constrained-control problem with SNAC is developed. Convergenceof the network training is discussed. Benchmark nonlinear systems are used to illustrate the working of theproposed technique. Extensions to optimal control-constrained problems in the presence of uncertaintiesare also considered. Two aerospace tracking applications – an aircraft and a space vehicle with modeland parametric uncertainties will be shown.

Jose Manoel BALTHAZAR, UNESP, Brazil

Title: Recent Developments on Regular and Irregular Oscillations and Their PossibleControls in a Macro, MEMS and NEMS Nonlinear Engineering Science

The study of the vibrating systems when the external excitation it is influenced by the response of thesystem, has been considered a major challenge in theoretical and practical engineering research. Whenmotors are attached to structures that need excitation power levels similar to the power capacity ofthose motors, interesting non-linear phenomena may happen, such as: Modal saturation-energy transferbetween modes and Sommeferld effect. On one hand, it is also well know that those Micro-electro-mechanical systems (MEMS) are one of the new and modern challenges in the engineering sciences field,owing to its interdisciplinary nature of research and extremely small feature size, which are now producedcheaply and in very small packages, in the micro domain. The research is going on, by using macro modelas a possible outlook in this area. We mention the study of the characteristics of the parameters needto be studied in more detail to guarantee the reliability of the (MEMS). On the other hand, the atomicforce microscope (AFM) system has become a useful instrument to measure the intermolecular forces,with atomic-resolution, since its discovery in 1986. The nonlinear dynamic (AFM), consists itself of avibrating micro cantilever, with a nanoscale tip, which interacts with a sample surface via short- andlong-range intermolecular forces. Amplitude-modulation (AFM) involves amplitude oscillations between1 and 100 nm. It is known that, micro cantilevers possess several distinct eigenmodes and the tip-sample interaction forces are Highly nonlinear. The adopted cantilever-sample mode interaction wasmathematically modeled as a number of single spring-mass (mass: being the tip of the cantilever). Thecantilever interacts with the sample via a tip, which is mounted on the cantilever.

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Sandro DA SILVA FERNANDES , Instituto Tecnologico de Aeronautica - ITA, Brazil

Title: Analytical Theory of Optimal Of Low-Thrust Limited-Power Trajectories

In this work, an analytical theory of optimal low-thrust limited-power trajectories is presented. Thistheory is based on properties of generalized canonical systems, Lie-Hori canonical perturbation methodand Hamilton-Jacobi canonical transformation theory. The optimization problem associated to thegeneral space transfer problem is formulated as a Mayer problem of optimal control theory with Cartesianelements - position and velocity vectors - as state variables. After applying the Pontryagin MaximumPrinciple and determining the maximum Hamiltonian, classical orbital elements are introduced througha canonical transformation derived from the properties of generalized canonical systems. Short periodicterms are then eliminated from the maximum Hamiltonian function through an infinitesimal canonicaltransformation built by applying Lie-Hori canonical perturbation method. The new Hamiltonian function,resulting from the infinitesimal canonical transformation, describes the extremal trajectories associatedwith the long duration maneuvers for simple transfers (no rendez-vous). This new Hamiltonian functioncan be simplified for four special classes of maneuvers: transfers between elliptical coplanar orbits,transfers between elliptical non-coplanar coaxial orbits, transfers between elliptical non-coplanar co-parameters orbits and transfers between orbits with very small eccentricities, and, closed-form analyticalsolutions can be obtained through Hamilton-Jacobi theory. Using Lie-Hori algorithm, first orderapproximated analytical solutions, which include short periodic terms, are obtained for these particularproblems.

Silvia GIULIATTI WINTER, Orbital Dynamics & Planetology Group - UNESP, Brazil

Title: New Horizons Mission and the Pluto-Charon system

Two new companions to the Pluto-Charon binary system, Nix and Hydra, have been detected in 2005by Weaver et al., 2006 beyond Charon’s orbit. Although they are small when compared to Charon, theirgravitational perturbations can decrease the stability of the external region of this binary system. In thiswork we present the results of a sample of numerical simulation concerning particles in P and S-type orbitsunder the gravitational perturbations of the four massive bodies: Pluto-Charon-Nix-Hydra. For thoseparticles in S-type orbits around Pluto and Charon we found several stable regions whose the families ofthe periodic orbits have been identified through an analysis of the Poincare surface of sections. Differentvalues of the eccentricity and inclination of the particles have been investigated. The size of the stableregions reachs its minimum for those particles with initial inclination equals to 110, and its maximumfor an inclination equals to 180. Through a sample of numerical simulations we have also determinedthe size and locaton of a sample of hypothetical satellites which could lie in the external region of thePluto-Charon binary system.

Naira HOVAKIMYAN , University of Illinois at Urbana-Champaign, USA

Title: The Theory of Fast and Robust Adaptation

The history of adaptive control systems dates back to early 50-s, when the aeronautical community wasstruggling to advance aircraft speeds to higher Mach numbers. In November of 1967, X-15 launched onwhat was planned to be a routine research flight to evaluate a boost guidance system, but it went into aspin and eventually broke up at 65,000 feet, killing the pilot Michael Adams. It was later found that theonboard adaptive control system was to be blamed for this incident. Exactly thirty years later, fueled byadvances in the theory of nonlinear control, Air Force successfully flight tested the unmanned unstabletailless X-36 aircraft with an onboard adaptive flight control system. This was a landmark achievementthat dispelled some of the misgivings that had arisen from the X-15 crash in 1967. Since then, numerousflight tests of Joint Direct Attack Munitions (JDAM) weapon retrofitted with adaptive element have metwith great success and have proven the benefits of the adaptation in the presence of component failuresand aerodynamic uncertainties. However, the major challenge related to stability/robustness assessmentof adaptive systems is still being resolved based on testing the closed-loop system for all possible variationsof uncertainties in Monte Carlo simulations, the cost of which increases with the growing complexity ofthe systems. This talk will give an overview of the limitations inherent to the conventional adaptivecontrollers and will introduce a new paradigm for design of adaptive control systems that leads to fastand robust adaptation with provable control specifications and guaranteed stability/robustness margins.Various applications will be discussed during the presentation to demonstrate the tools and the concepts.

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Sunil L. KUKREJA, NASA Dryden Flight Research Center, Edwards, California, USA

Title: A Computational Biology Approach to Modelling and Identification of HumanPhysiology

We demonstrate the practical application of methods developed for identification of linear, nonlinear andhybrid (multimode) systems to human physiology. Although these tools were developed with biologicalapplications in mind, they are generalizable to a large set of problems that span many disciplines. After anintroduction to the system identification problem and model class considered in our work, we demonstratethe usefulness of a computational biology approach to the study of human biology. Two specific topicsare highlighted, the modeling and identification of the human (i) neuromuscular and (ii) vestibular ocularreflex system. These topics are of importance to NASA’s Digital Astronaut Project for long term humanspace exploration.

Results demonstrate that a computational biology approach to predicting the effects of spaceflight onthe human body may allow for characterization of disease, early detection and quantification of oculardisease and balance disorder and better design of robotic motor control systems.

Irena LASIECKA, University of Virginia, USA

Title: Well-posedness and long time behavior of finite energy solutions corresponding to 3-Dflows interacting with dynamic elasticity

We shall discuss finte energy solutions corresponding to 3-D flows (gas or fluid) interacting on an interfacewith dynamic nonlinear elasticity. Specific examples include : fluid structure interactions (Navier Stokesequation coupled with wave equation), structural acoustic interaction (wave equation coupled withnonlinear dynamic plate or shell equation), flow-gas interaction (linearised Euler equation interactingwith a nonlinear dynamic plate). The interaction in these models takes place on a manifold of lowerdimension.

Of particular interest to this talk are evolutions with ”supercritical” (with respect to Sobolev’s embed-dings) nonlinearities. These include supercritical semilinear wave equations, von Karman evolutions,Kirchhoff Bousinesq equations and other non-linear plate equations. This class of models, while mo-tivated by a multitude of physical applications, does not seem to have well established mathematicalmethodology for dealing with the issues such as existence, uniqueness and stability (including long timebehavior) of solutions posed in physically significant finite energy space. The issue at hand is a well rec-ognized dychotomy between global existence and uniqueness. Existence for weak (finite energy) solutionsis known, while uniqueness holds for strong solutions that are defined only locally.

In this talk we shall single out several classes of models for which rather general techniques have beenrecently developed. (see Ref. [1-4] and references therein). These techniques lead -ultimately- to theresolution of the dychotomy and also provide a treatment for the study of long time behavior (globalattractors) for the resulting dynamics. The results presented will supply positive answers to several openquestions raised in the context of ”supercritical” dynamic elesticity.

The methods discussed are based on tools such as : harmonic analysis, compensated compactness andlogarithmic control of Sobolev’s embeddings.

References:

[1] J. Ball, Global attractors for semilinear wave equations, Discr. Cont. Dyn. Sys. 10 (2004), 31-52.

[2] G. Sell and Y. You. Dyanamics of Evolutionary Equations. Springer Verlag, 2002.

[3] I. Chueshov and I. Lasiecka, Long-time behavior of second order evolution equations with nonlineardamping, Memoirs of AMS, vol.195, no. 912, AMS, Providence, RI, 2008.

[4] I. Chueshov and I. Lasiecka. Von Karman Evolutions-Wellposedness and Long Time Dynamics,Springer Verlag, to appear 2009.

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Elbert MACAU , National Institute for Space Research - INPE, Brazil

Title: Controlling Chaotic Transient and the Improvement of System Flexibility

In this work, we address the problem of how to exploit the dynamics behind a chaotic transient behavior toimprove system performance and adaptability to many operational conditions requests. The phenomenonof chaotic transient is explained as due to the presence of a chaotic saddle in the phase space. Differentsystems operation points can be associated to the set of unstable periodic orbits that exists embedded inthe chaotic saddle. A classical control procedure associated with a control of chaos strategy is proposedas a methodology to quickly guide system trajectories among different operation points and to keep thesystem on a particular operation point. The methodology is applied on an electronic circuit system.

Robert M.M. MATTHEIJ , Technische Universiteit Eindhoven, The Netherlands

Title: Flow in networks

Turbines (jet engines or gasturbines) have rotors at the hot end that need to be cooled. This coolingis done by blowing cool air through the blade (internal cooling) or through holes in the surface (toprovide for film cooling). A variety of methods is used to drill these holes (electrochemistry or laserdrilling), Simulation of the flow eventually provides for a complex problem that is tackled by a domaindecomposition technique.

Toshiya NAKAMURA, Japan Aerospace Exploration Agency, Japan

Title: JAXA’s Aeronautical Research Project for Civil Transport - Endeavours to EnhanceSafety and Environmental Friendliness -

The Aviation Program Group of Japan Aerospace Exploration Agency (APG/JAXA) is moving forwardin its research and development on advanced / fundamental aeronautical technologies in considerationof social demand such as advancement of aircraft safety and environmental compatibility for diversifyneeds and increase of air transport in the future. One of the goals of JAXAs aviation program is todevelop the cutting-edge technologies which can be applied to the development of competitive aircraftin the world market. To achieve this, JAXA launched a research project in 2003 which covers widevariety of aeronautical science and technology: computational fluid dynamics (CFD), advanced opticalmeasuring methods in wind tunnel test, aero-acoustic analysis (computational aero-acoustics, CAA) andidentification of noise sources, computational tool to analyze transonic flutter behavior, analysis and testfor crashworthiness, composite materials and structures, and control systems. This presentation describesJAXAs efforts conducted in the project in some details.

Firdaus E. UDWADIA, University of Southern California, Los Angeles, USA

Title: Advances in the Modeling and Control of Complex Multibody Systems

A new general integrated method for the modeling and control of complex multibody systems is presented.The method utilizes recent results in analytical dynamics adapted to general complex multibody systems.The term complex is employed to denote those multibody systems whose equations of motion are highlynonlinear, non-autonomous, and possibly yield motions at multiple time and distance scales. Theapproach considered herein opens up new routes for modeling general multibody systems by explicitlydeveloping closed form expressions in terms of any desirable number of generalized coordinates that mayappropriately describe the configuration of the multibody system. Furthermore, the approach is simple inimplementation because it poses no restrictions on the total number and nature of modeling constraintsrequired to construct the equations of motion of the multibody system. Conceptually, the method relieson a simple three-step procedure. It utilizes a new set of equations of motion developed, which describesthe explicit equations of motion for constrained mechanical systems with singular mass matrices. Thesimplicity of the method is highlighted by illustrating its use in the modeling and control of a multibodyspacecraft system for which we provide numerical results of the system’s response.

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Stanislav N. VASSILYEV , Institute of Control Sciences, Russian Academy of Sciences

Title: Analysis of Dynamics of Hybrid Systems with Nonlinear Vector Fields by Homomor-phic Mappings

Hybrid systems with switching nonlinear vector fields of ordinary differential equations (ODE) areconsidered. The analysis of the dynamical properties of stability and attractivity in those models arereduced to a problem of analysis of analogous dynamics in impulsive differential equations. A reductionmethod with trajectory homomorphism from the initial model to auxiliary one is used. Some examplesare considered.

Brian WHITE , Cranfield University, Defence Academy of the United Kingdom

Title: Path Planning and Decision Making for Co-operative Multiple UAVs

The use of multiple UAVs for mapping and surveillance is becoming practical in the near future. Assuch, autonomous behaviour that is robust and predictable is necessary for such use. This presentationwill describe the role of decision making and path planning in producing an autonomous system that cansurvey areas that have some rural areas and some urban areas, together with some structured waterways.This implies that paths need to follow route structures that are related to road networks, waterways orother natural features that require specific paths, such as valleys, forest clearings.

In order to produce an autonomous system that has specific guaranteed behaviours, the link between thedecision making code and the path planning needs to be defined in such a way as to be expressible inboth domains. In terms of path planning, routines to search route networks will involve examining graphconcepts such as the Chinese Postman Problem to produce a path that will traverse each road within thenetwork, the Travelling Salesman Problem to produce paths that will overfly all raod junctions within thenetwork, together with techniques to survey open areas with multiple UAVs. Decision making techniquesusing Temporal Logic to define the system behaviours will be presented.

The resulting decision making and path planning techniques are illustrated by use of case studies thatcover tracking contaminant clouds, monitoring highway traffic to surveying rural areas using UAVs andUGVs will be presented.

Othon C. WINTER, Orbital Dynamics & Planetology Group - UNESP, Brazil

Title: On the Dynamics of Triple Asteroid Systems

In 2005 was discovered the first triple asteroid system, named Sylvia with satellites Romulus and Remus.This system is located in the middle of the main asteroid belt. At the present moment are known almostten triple asteroid systems. They were found not only in the main asteroid belt, but also among theNEAs and among the TNOs. Their dynamics and stability are quite complex. There are cases whereappear intriguing resonances, close encounters with planets and the non-spherical gravitational potentialof the central body can play an important role on the stability of the system. In this presentation we willgive a general view of this class of systems and will discuss the stability and evolution of the particularcases of 87 Sylvia and the 2001SN263.

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GENERAL SESSION

Temperature-dependent explicit stress-strain relations for stainless steel alloys

Kenzu Abdella , Qatar University, Qatar

This paper presents a new stress-strain relation for stainless steel alloys that provides the stress as anexplicit function of strain and temperature. The relation is an approximation of the closed form inversionof an existing two-stage stress-strain relation based on a modified Ramberg-Osgood equation with anappropriate modification to account for temperature dependence. This new expression for the stress asan explicit function of the total strain, and temperature is obtained by making a modified power lawassumption on the fractional deviation of the actual stress-strain curve from an idealized linear elasticbehaviour.

The validity of the temperature-dependent expression is tested over a wide range of material parametersand a wide range of temperatures. The tests show that the new expression is both qualitativelyand quantitatively consistent with the fully iterated numerical solution of the full-range temperature-dependent stress-strain relation at moderate and high temperatures.

Convergence study of the condition number for some preconditioners to the Stokes problem

Omar Ali Aleyan , University of Almergeb, Faculty of Arts and Science Zliten, Libya

We deal with the properties of the approximation of the Stokes equation which leads to the linearsystem Ax = b. We investigate the preconditioners of Block Diagonal, Upper Block Triangular, LowerBlock Triangular and the Incomplete LU factorization preconditioner; Wathen and Silvester, Elman andSilvester, Grad-Div stabilization and Artificial Compressibility type. We also study the Simple, Simplicand Simpler preconditioners. We show the dependence of the condition number on the mesh size bothon tables and graphs.

Fuzzy differential equations

Tofigh Allahviranloo, Azad University, Tehran, Iran

In this presentation I am going to discuss about several methods of finding, numerically and analytically,solutions of first order Fuzzy Differential Equations(FDEs) and higher order FDEs. First of all, theexistence and uniqueness of the solution are discussed. Then, difference methods such as Runge-Kutta,Predictor-Corrector and the differential transformation method are presented. Analytical methods suchas the fuzzy Laplace transformation, Eigen value and vector and Expansion methods are also introduced.Finally, all of the above mentioned methods are followed by consideration of related theorems in detailand some numerical examples are solved.

Nonlinear Analysis of Cables and Guyed Towers

Shahin Nayyeri Amiri , Kansas State University, USA

The research reported herein is on the nonlinear analysis of cables and guyed towers. Cables are analyzedwithout making a prior assumption as regards the type of loading on them and their final geometry.Nonlinear constitutive relations are also considered. After discussing the previously proposed analysistechniques, a Newton-Rasphson solution procedure is proposed for solving the cable equilibrium equations.The mast of the tower is assumed to be a beam-column having a spring mounted base and supported bypreloaded nonlinear springs. These springs represent the effect of guy cables. A procedure is describedand a computer program is developed for the nonlinear analysis of guyed towers under arbitrary loads.The program is applied to the analysis of some sample guy cables and guyed tower models to check theaccuracy of the analysis procedure and of the program.

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Size, shape and stability evaluation for meniscus appearing in microfiber growth by pullingdown method

Agneta Maria Balint, Stefan BalintWest University of Timisoara, Romania

The process parameter considered in this paper is the pressure p, which incorporates the gas pressurein front of the free surface of the meniscus, the hydrostatic pressure of the melt column situated behindthe meniscus, the hydrodynamic pressure associated to the thermoconvection in the meniscus and theMarangoni pressure associated to the Marangoni convection. The meniscus’s shape and size are analyzedin function of the above parameter p. More precisely, for a meniscus having a given shape and size, therange of the values where p should be, is found. Furthermore, it is shown that if p is in a prescribedrange, then a meniscus, having a given shape and the size (crystal radius) in a given range, is obtained.Finally, the (static) stability of the menisci is analyzed. For NdYAG microfiber numerical illustrationsare given.

On the structural stability of systems of differential equations occurring in aerospaceengineering

Stefan Balint, West University of Timisoara, Romania

Frequently, the evolution of real phenomena is described by systems of ordinary differential equations.These systems express physical laws, geometrical connections, and they are often obtained by neglectingsome influences and quantities which are assumed negligible with respect to others. The simplified systemdescribes correctly the real phenomenon if and only if it is topologically equivalent to the system in whichthe small influences and quantities are also included. This means that there exists a homeomorphism ofthe parameter space and a parameter dependent homeomorphism of the phase-space, which sends theorbits of the simplified system onto the orbits of the non simplified system. A system defined in a regionD is structurally stable in a sub-region of D if any system sufficiently close in D is topologically equivalentin the sub-region to the initial system. This talk presents systems used in aerospace engineering whichare structurally stable, systems for which structural stability has never been proved, and systems whichare not structurally stable, opening the problem of legitimacy of the use of the last two types of systems.

Diversity QPSK-CDMA schemes for LEO mobile communication

Luis Wwaack Bambace , National Institute for Space Research -INPE, Brazil

CDMA radio to station links are asynchronous and thus user signals are not absolutely orthogonal thoughinterference is low. Separation from a cell to another requires a long code that with a period different ofthe symbol. Due to residual interference issues if all user operates at full power the number of possible useris reduced, so good capacity is assured by fast control of individual user transmission levels, independentlyof what error correcting code is used. In satellite systems the transmission delay avoids a fast control,and its necessary to use another scheme to enhance traffic capacity. Except for Globalstar, that remainclose to IS95 standard, all the other systems made option to long pseudo random codes and Gold codesto separate users. Here is described a diversity scheme that use the fact that slipping the long code andkeeping matched the Gold codes of copies of messages of a radio, they are nearly orthogonal one to eachother, and its annoying effect in other user per unit of energy is unchanged. This channeling expansionallows diversity to be used, reducing the average power per user and enhancing capacity.

A new real inversion formula for the Sumudu Transform

Fethi Bin Muhammad Belgacem , Arab Open University, Kuwait

So far the inversion formula for the Sumudu transform has been complex related established through theresidue theorem. In this paper, we present a new real inversion formula for the Sumudu transform.

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Designing Phase-Locked Loops for Frequency Modulation Atomic Force Microscope

Atila Madureira Bueno, Universidade Estadual Paulista, BrazilJose Manoel Balthazar , Universidade Estadual Paulista, BrazilJose Roberto Castilho Piqueira , Universidade de Sao Paulo, Brazil

The Atomic Force Microscope introduced the surface investigation with true atomic resolution. In thenoncontact mode of operation both amplitude and frequency modulation methods can be implemented byusing Phase-Locked Loops (PLLs). The Frequency Modulation - Atomic Force Microscope (FM-AFM)control system consists of two control loops, i. e, the amplitude and distance control loops. The amplitudeloop controls the cantilever’s oscillation amplitude, and the distance loop controls the mean distancebetween tip and sample. The PLL performance is vital to FM-AFM control system since it generates thefeedback signals to both the amplitude and distance control loops. Nevertheless, little attention is drawnto PLL design and performance in atomic force microscopy literature. Perhaps because designing stablehigher order PLLs, in contrast to second-order, demand some effort. A virtual FM-AFM is implementedand the calculations of FM-AFM images are presented. The results are compared considering the variousPLL designs, attempting to determine the best characteristics of PLL response to the FM-AFM system.

Improvement in Relational Databases Query Using Fuzzy Logic

Vanessa Avelino Xavier de Camargo, Wemerson Leonardo Ramos , Esdras Teixeira Costa,Marcos Wagner Souza RibeiroFederal University of Goias, Brazil

Fuzzy Logic and Fuzzy Set Theory have been widely exploited on account of their feature to translateuncertain, ambiguous and vague information - typical of human beings thoughts - to numerical data.The scope of fuzzy applications is actually large and it may be increasing. One of its applications is inRelational Databases, promoting an improvement in information retrieval. In this context, this paperpresents a convenient and simple way to treat linguistic variables in database queries with the aim to makedata retrieval closer to imprecise human reasoning. A trigger, using Structured Query Language (SQL)and MySQL Database Management System, has been created to make fuzzy membership degrees basedon trapezoidal fuzzy numbers. With the purpose to illustrate and test the advantages of this approach,a case study based on age variables - child, young, middle-age, elderly - has been done, assuming aninsurance company interested in setting values according to the age of customers. As conclusion, aparallel between fuzzy and traditional (crisp) queries results has been shown, beyond future works.

Evolutionary Programming with Adaptative Stable Distributions

Leopoldo Bulgarelli Carvalho, Pedro P.B. de OliveiraMackenzie University, Brazil

Recent applications in evolutionary programming have suggested the use of further stable probabilitydistributions, such as Cauchy and Levy, in the random process associated with the mutations, as analternative to the traditional, also stable, Normal distribution. This work considers a new self-adaptativeclass of algorithms in respect to the determination of the more adequate stable distribution parametersfor optimization problems. Evaluations that rely upon standard analytical benchmarking functions andcomparative performance tests between them were carried out in respect to the baseline defined by astandard algorithm using Normal distribution. Additional comparative studies were made in respect tovarious self-adaptive approaches, also proposed herein, and an adaptive method drawn from the literature.The results suggest numerical and statistical superiority of the more general stable distribution basedapproach, when compared with the baseline. However, they show no improvement over the adaptivemethod available in the literature, possibly due, at least partially, to implementation decisions that hadto be made in the present implementation, that were not made explicit therein.

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Semi active suspension control techniques using only one measurement sensor

Fabio Luis Marques dos Santos, Luiz Carlos Sandoval Goes, Alberto Luiz SerpaInstituto Tecnologico de Aeronautica, Brazil

In this paper two control strategies are addressed - the Linear Quadratic Regulator (LQR) and theInternal Model Control (IMC). These techniques were tested in a system where saturation is present, thesemi-active suspension problem. They are then evaluated by some performance indexes that characterizethe problem as optimization problems, and solved by the use of some specific tools of the MATLABsoftware. The main goal is to obtain optimal performance, in order to minimize the sprung mass (chassis)acceleration and to ensure road-holding characteristics, while minimizing the number of feedback sensorsused. To make-up for the minimum sensor usage, state observers are designed. A comparison is thenmade, by means of numerical simulation, using a quarter-car model and real road profiles as well.

6-DOF data and aerodynamic models for real-time flight simulation

Pedro S. Giraudo, National University of Cordoba, ArgentinaJavier E. Luiso, Instituto de Investigaciones Cientıficas y Tecnicas para la Defensa, ArgentinaEduardo N. Zapico, National University of Cordoba, ArgentinaHoracio A. Abbate , Instituto de Investigaciones Cientıficas y Tecnicas para la Defensa, Argentina

The purpose of this paper is to present the data model developed for a 6DOF real-time flight simulator.The simulation engine in which this data model is embedded is also briefly presented. As usual, theaircraft aerodynamic is defined through aerodynamic coefficients, which are dimensionalised to calculatethe acting forces and moments on the aircraft. In order to take into account a complete aerodynamicparameter set, which results necessary for an accurate simulation, great information volume is required;in this paper the matrix organization used for the treatment of these data is presented, which provedto be fast and accurate, moreover allowing to use simple search and interpolation algorithms. Finally,simulation results obtained for a 6-DoF model of a military trainer aircraft are presented.

Dynamic simulation of light space structures by finite element modeling and order reductionin state space

Leandro Gonzalez, Eduardo N. ZapicoNational University of Cordoba, Argentina

The state space formulation of the equations of motion allows to achieve simple dynamic models fromcomplex structures, in order to integrate them to a dynamic simulation program which will be acting likean efficient platform for high shock load structures design, suitable on space mission development.

In the beginning of a new structural design project will be required to acquire sensitivity and knowleadgeon the dynamic problem to study, when no definitive design has been established yet, and the componentdynamic properties of the structure are not certainly known either. Its usual to propose simplified systemmodels for several constructive solutions, while latter project stages involves generally structural changeswhich compel to re-examine the entire dynamic behaviour; then is desirable in this design stage to have thesmallest dynamic model that still provides a precise representation of system dynamics and allows a quickproposal evaluation, with the aim to reduce the solicitations over critical satellital components.¡/p¿¡p¿Inthis paper a certain satellital configuration is proposed for a preliminar dynamic analysis by the finiteelement method, with the aim of generate a flexible enough model to admit latter adjusts on the basisof behaviour appreciations and test results. Then, a reduction method for high order lineal dynamicsystems is applied by means of balanced gramians, with the intention to obtain a state space reducedorder model.

Flight or Fight - Battle of the Overheads Bins: Another Factor Contributing to the AirRage Phenomenon

Joyce A. Hunter , Saint Xavier University, Graham School of Management, Chicago, USA

Baggage fees have been implemented within many of the airline carriers for both domestic and foreigntravel. With the recent mandate for baggage fees by airlines, passengers are struggling to gain accessto the overhead compartments. As more flyers use carry-on bags, there is less room in the bins. Sixpassengers are competing for overhead bin space designed to fit four wheelie bags. This condition leaves

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some fliers out of luck at a time when more of them are opting to lug their bags, rather than check them,to avoid airline fees.

Boarding lines move at a snail’s pace when the last luggage bins are filled and passengers are forced todeplane and return to the jet bridge to check their bags.

The baggage situation has frustrated travelers and, for many of them, has added even more stress totheir travel experience. This stress is a physiological and psychological experience of disruption to theirhomeostatic balance.

It has been documented that since the start of last year, the number of bags checked at the boardinggate has risen nearly 50 percent, while the volume of bags checked at the ticket counters has dropped 18percent.

Air travel has changed over the past year and a half. Both the fees and space constraints can contribute toa breakdown in social conventions as passengers increasingly feel that they are left to fend for themselves.As planes fill and tensions rise, carriers are exploring ways to ease congestion in their aisles.

This paper will focus on strategies to deal with the battle for limited overhead bin space and exploresolutions to alleviate the related passenger congestion in the aisle on board the aircraft.

Elementary proof of the Fermat’s Last Theorem

Artur Korgul, Rafal Andrzej KorgulPatent Office of the Republic of Poland

Fermat’s Last Theorem (FLT) was until the mid-1990’s the most famous unsolved problem in mathe-matics. In about 1637 Pierre de Fermat stated that: For all n > 2 there do not exist x, y, z such thatxn + yn = zn, where x, y, z are positive integers. He claimed that he had a simple proof of this theo-rem, but no record of it has ever been found. Ever since that time, countless professional and amateurmathematicians have tried to find a valid proof. Even outstanding mathematicians (e.g. Euler, Legen-dre, Dirichlet and others) could only prove that this equation worked for individual numbers n. In 1994professor Andrew Wiles of Princeton University announced that he had discovered a proof while workingon a more general problem in geometry [1]. Wile’s proof is based on modern mathematical tools, whichwere not known for Fermat. Apparently the Fermat’s proof should be not beyond seventeenth centurymathematics. Is it possible that FLT has a simple solution, it was an open question to date. This paperpresents an elementary proof of Fermat’s Last Theorem.

Reference: [1] Singh, Simon. Fermat’s Enigma. New York: Anchor Books, 1998.

GA Optimization of Point Placement on a Hypersphere

Janko Milutinovic, Delaware State University, USADragoljub Pokrajac, Delaware State University, USASam Kennerly , Drexel University, USA

Placement of points on a hypersphere according to a pre-specified optimization criterion is an importantproblem with potential applications ranging from spherical coding theory to computational geometry todefense. Unfortunately, optimal point configurations are known only for a limited number of cases inlower dimensional spaces. Genetic algorithms have been applied to optimal point placement on a 2Dsphere. Here, we investigate applications of genetic algorithms to higher dimensional optimization. Weutilize minimal energy or maximized minimal inter-point distance optimization criteria, and propose andcompare several genetic algorithms crossover and mutation operators.

On Thermal Instabilities Occuring in Fires

Vasily Novozhilov , University of Ulster, UK

The presentation identifies a unified mathematical approach to description of a number of thermalinstabilities typically observed in fire behaviour.

Consideration is mostly focused on compartment fires. The two key instabilities that are most importantin fire behaviour are ignition and flashover.

Proposed mathematical framework for consideration of these instabilities relies on the concept of conjugate

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thermal explosion, proposed and developed recently by the author. This concept generalises the classicalthermal explosion theory, and has been found very useful in interpreting fire instabilities, as well as someother combustion phenomena.

In the present talk, relevant mathematical models are developed, and their dynamics is investigated.Generally, the proposed formulation leads to non-linear integro-differential equations. As a specificexample, dynamical model of fire flashover is investigated in more detail. For such a model, we studyqualitatively the set of corresponding integro-differential equations, and derive critical conditions forflashover. Finally, other potential application of conjugate thermal explosion theory are briefly discussed.

Introduction to Theory of Physical-Geometry Space

Ahmad Sabihi , Sharif University of Technology, Tehran, Iran

In this paper, the Author wishes to present a novel Mathematical-Physics Theory in an n-dimensionalspace which is called Physical-Geometry Space Theory. This theory deals with global space geometry ofthe universe. As well-known, Einstein gave General Theory of Relativity in 1915. The theory representeda general view of the universe so that could connect mechanical sciences with non-Euclidian space inpure mathematics. The theory does not consider space’s geometrical characteristics in each time createdby physical conditions. On the other word, the parameters of geometry and physics are consideredto be isolated from one another. Here, the Author improves the theory by considering geometricalcharacteristics and parameters in combination with physical variations made by both observer coordinatesystem oscillation and circumstances. Also, the universe extension and curvature of space and time aretaken into account. Therefore, the Author proves that variation of geometrical parameters of space canaffect mechanical and physical events. String, superstring theory, and M-theory can demonstrate thespecial cases of this theory in quantum mechanics and general relativity or quantum relativity mechanics(quantum field theory).

An Approach Towards the Proof of the Strong Goldbach’s Conjecture for Sufficiently LargeEven Integers

Ahmad Sabihi , Sharif University of Technology, Tehran, Iran

The author approaches to a new proof of the strong Goldbach’s conjecture for sufficiently large evenintegers by applying to the Dirichlet’s series. Using Perron formula and the Residue Theorem in complexvariable integration, one could show that any large even integer is demonstrated as a sum of two primes.A novel function is defined on the natural numbers set. This function is a typical sieve function. Thenbased on this function, several new functions are represented and using Prime Number Theorem, theConjecture is proved for large even integers.

Model based planning of the capillary and thermal conditions for the growth of a silicontube with a prior given inner and outer radius

Loredana Tanasie, Stefan BalintWest University of Timisoara, Romania

This paper an algorithm is presented for the choice of the capillary and thermal conditions which assurea stable growth of a silicon tube with a prior given inner and outer radius. The algorithm is based anmathematical model in which the tube growth is described by a system of the three nonlinear ordinarydifferential equations.

Impact Behaviour of Sandwich Plates : Theoretical and experimental investigation

Ertan Tengiz, Demet Balkan, Halit Suleyman Turkmen, Zahit MecitogluTurkey

The sandwich materials are widely used in aerospace structures. This is because they have high stiffnessto weight and strength to weight ratios, good vibration damping characteristics, and impact resistance.In this study, the sandwich plates subjected to the impact loading are investigated theoretically andexperimentally. For this purpose, two types of sandwich plates are produced. The first one hascarbon/epoxy facings and aramid honeycomb core and the second one has glass/epoxy facings and a

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stepwise graded viscoelastic core. The plates are produced using a heated vacuum table and hand lay-uptechnique. The plate is tested against an impact. The plate is also modeled using the finite elementmethod and impact analysis is achieved. In the finite element method, the plate is modeled using thelayered shell elements. The mechanical properties of the sandwich plate are obtained experimentally.For this purpose, three point bending test and dynamic mechanical analyzing (DMA) test are used. Theproperties determined experimentally are used in the impact analysis. The results are compared and anagreement is found between the experimental and numerical results.

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SPECIAL SESSION 1. Neural Network Dynamics

Organizers: Eva Kaslik (Romania), Seenith Sivasundaram (USA)

This special session will focus on the area of neural networks mathematical theory, analysis, simulationsand applications in engineering, aerospace and all areas of sciences. Intended audience includes researchersfor neural applications as well as those with mathematical interests.

Almost Periodic Solutions of Impulsive Hopfield Neural Networks with Periodic Delays

Haydar Akca , United Arab Emirates University, Al Ain, UAEValery Covachev , College of Science, Sultan Qaboos University, Muscat, Sultanate of Oman andInstitute of Mathematics, Bulgarian Academy of Sciences, Sofia, BulgariaZlatinka Covacheva , Higher College of Technology, Muscat, Sultanate of Oman and Higher College ofTelecommunications and Post, Sofia, Bulgaria

An impulsive Hopfield neural network with delay which differs from a constant by a small amplitudeperiodic perturbation is considered. If the corresponding system with constant delay has an isolatedω-periodic solution and the period of the delay is rationally independent with ω, then under suitableassumptions it is proved that in a sufficiently small neighbourhood of this orbit the perturbed system hasa unique almost periodic solution.

Bifurcation Networks: An Approach to Cortical Modeling and Higher Level Brain Function

Nabil H. Farhat , University of Pennsylvania, USA

Evidence is presented in support of the hypothesis that the basic functional unit in the cortex, theseat of higher-level brain function, maybe mathematically modeled by a bifurcation processing elementconsisting of a parametrically driven noninvertible map on the unit interval such as the logistic map.Such simplifying abstraction is shown to capture functional attributes of thalamo-cortical units as seenin numerical simulations to be presented for a network of parametrically coupled maps. Under extrinsicdynamic input, the network exhibits input-specific attractors in the form of isolated clustering of activityanalogous to Hebbian assemblies and the ”hot-spots” of activity revealed in functional fMRI in the brainof a subject engaging in a cognitive task. These networks can play an important role in explainingself-organization, bifurcation and chaos in higher-level brain function and lead to their abstraction intoartificial systems for use in specific applications that are beyond the abilities of present day neuralnetworks and connectionist models.

Artificial neural networks applied to low cost INS/GPS integrated navigation systems

Edmundo Alberto Marques Filho, Atair Rios Neto , Helio Koiti KugaNational Institute for Space Research - INPE, Brazil

This paper addresses the use of artificial neural network (ANN) into Global Positioning System (GPS)aided low cost inertial navigation systems based on micro-electromechanical sensors (MEMS). TheGPS technology dominates, nowadays, the positioning and navigation (POS/NAV) general market, andalternative POS/NAV systems are only needed because GPS does not work in all environments, or cannot provide reliable solutions, under certain circumstances, during some time interval. There are differentsolutions to fulfill information during GPS blockage and integrated inertial sensors systems with GPSare frequently used with stochastic parameter estimation techniques. However, low cost inertial sensorshave the disadvantage of accumulating continuous errors in great extension, leading to poor systemperformance. In this context a multi-layer feed-forward ANN is applied, to provide better NAV/POSsolutions, during the lack of information in GPS outages portion of time. This work presents: an approachto model the input-output ANN signals based on a set of constrained land vehicle navigation equations;an adaptive ANN training Kalman filtering methodology and preliminary numerical simulation resultsbased on urban vehicular positioning application data, acquired from low cost Crossbow CD400-200inertial measurement unit and an Astech Z12 GPS receiver.

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Multistability in impulsive Hopfield neural networks with time-dependent and distributeddelays

Eva Kaslik , West University of Timisoara, RomaniaSeenith Sivasundaram , USA

In this paper, we investigate the multistability properties of impulsive hybrid Hopfield-type neuralnetworks with time-dependent and distributed delays, by using Lyapunov functionals, stability theoryand control by impulses. Examples and simulation results are given to illustrate the effectiveness of theresults.

Controlling the chaotic dynamics of neural networks

Francisco Welington Lima , Universidade Federal do Piauı, BrazilTarik Hadzibeganovic, Austria

Roughly the past decade of research on chaos control in neural networks will be reviewed and discussed,with a focus on the most actively developing directions and applications. A particular attention willbe given to a method using local control, i.e. pinnings acting only on a small subset of neuronal units.Pertinent simulation results employing this method will be compared against other competing approaches.As it will be demonstrated, there are many practical advantages in knowing how to take a system witha large number of degrees of freedom from a chaotic to a fixed or periodic behavior.

Stability and Bifurcation Analysis Of Three Neuron Delayed Network Model Of HopfieldType

Narayan Chandra Majee, Amiya Busan RoyJadavpur University, India

In this paper we have studied the dynamics of three neuron network model of Hopfield type with timedelay in signal transmission. Results regarding delay independent stability, estimation of critical delayto preserve stability for the linearised system is obtained. Considering time delay as the bifurcationparameter Hopf type bifurcation is discussed of the said model. Computer simulation results are alsopresented depicting different dynamics like stable equilibrium, stable limit cycle and twin limit cycle ofthe model.

Neural Network based Model Predictive Controller for Simplified Heave Model of anUnmanned Helicopter

Mahendra Kumar Samal , Sreenatha Anavatti, Matthew GarrattUniveristy of New South Wales at Australian Defence Force Academy, Australia

Neural Network based model predictive controller (NN-MPC) scheme for designing autonomous flightcontrol of a rotary-wing unmanned aerial vehicle is presented in this paper. The applicability of the NN-MPC scheme is evaluated on a simplified heave model of the helicopter in simulation. Neural Network(NN) based system identification (NNID) technique is used to model the nonlinear dynamics of theunmanned helicopter. The NN model is then used in the MPC algorithm to estimate the future controlmoves. To show the efficacy of the NN-MPC scheme, controller results are provided. Results indicate thatNN-MPC scheme is capable of handling external disturbances and parameter variations of the system.

Bumps in a two population neural field model

John Wyller, Norwegian University of Life Sciences, Norway

Neural field models have a long tradition in mathematical neuroscience. In the present talk a survey of atwo-population neural field model describing excitatory and inhibitory neurons interacting via nonlocalspatial connections will be given. Results from investigations of such models on the existence and stabilityof stationary localized activity pulses (”bumps”) and generation of stationary spatial and spatiotemporaloscillations through a Turing-type of instabilities will be described.

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SPECIAL SESSION 2. Unmanned Aerial Vehicles

Organizer: Gilney Damm (IBISC Lab. - Evry - Val d’Essonne University, France)

This special session is dedicated to Unmanned Aerial Vehicle’s (UAV) control, models and applications.UAVs may be of different kinds, and may range from helicopters less than 1 meter wide used for indoorsinspection, to unmanned airplanes of several meters.

Structural modeling and optimization of a joined-wing configuration of a high-altitude long-endurance (HALE) aircraft at global and local levels

Valentina Kaloyanova, Karman Ghia, Urmila GhiaUniversity of Cincinnati, USA

A high-altitude long-endurance mission requires a light vehicle flying at low speed at altitudes of60, 000 − 80, 000 ft, with a continuous loiter time of up to several days. To provide high lift and lowdrag at these high altitudes, where the air density is low, the wing area should be increased, i.e., high-aspect-ratio wings are necessary. To reduce the structural deformation, and increase the total lift in along-spanned wing, a sensorcraft model with a joined-wing configuration, proposed by AFRL, is employed.A detailed finite-element model of the joined-wing is built and nonlinear static analysis performed for theaerodynamic load corresponding to flow at altitude 60, 000 ft, M = 0.6 and α = 12 . Design optimizationis carried out at global and local levels. At local level detailed models of wing panels are constructed.Bi-level optimization resulted in a wing structure with mass of 1001.33 kg and wing tip deflection of 3.93m or 10.5% of the wing length.

Determination of Intelligent Control system for a Nonlinear Model of an AutonomousScale-Model Helicopter by Emotional Learning Approach

Abolfazl Mokhtari , K.N. Toosi University of Technology, Iran

There is a growing interest in the modeling and control of model helicopters using nonlinear dynamicmodels and nonlinear control. Application of a new intelligent control approach called Brain EmotionalLearning Based Intelligent Controller (BELBIC) to design autopilot for an autonomous helicopter isaddressed in this paper. This controller is applied to a nonlinear model of a helicopter. This methodologyhas been previously proved to present robust characteristics against disturbances and uncertaintiesexisting in the system. The controller design goal is that the helicopter tracks a special maneuver toreach the commanded height and heading. The performance of the controllers is also evaluated forrobustness against perturbations with inserting a high frequency disturbance. Simulation results show adesirable performance in both tracking and improved control signal by using BELBIC controller.

Nonlinear flight dynamics analysis of flapping wing micro-air vehicle model

Victor Mwenda Mwongera, Mark LowenbergDepartment of Aerospace Engineering, University of Bristol, UK

The limitations placed on the size of flapping wing micro-air vehicles (MAVs) means that they operate in aregion of highly unsteady aerodynamics, dominated by 3D effects. Thus, a comprehensive flight dynamicsmodel would be nonlinear, with associated problems in evaluating stability and control. Nonlineardynamical systems theory - specifically bifurcation methods - is therefore seen to be useful for analysingthe flight dynamics system of equations.

An aerodynamic model has been created to capture the flow regime, using a modified blade element theory.The model is initially limited to rigid body modes, with only the effects of inertial accelerations of theflapping wing being coupled to the modified quasi-steady aerodynamic analysis. The system is periodicallyforced and an appropriate form of numerical bifurcation analysis is then applied to this system. From this,tools for looking at the oscillatory steady states can be developed, especially in response to perturbationsin wing beat parameter changes; the flap, lag and feather frequencies and amplitudes. The stabilityanalysis and steady state variation will then be used to define preliminary simplified vehicle controlsystem boundaries, and also create a base of knowledge for introducing other effects such as structuraldynamics, wind gusts/perturbations and ultimately time-dependent aerodynamics.

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UAS test platform for parameter identification of powered paraglider

Andras Nagy, Jozsef RohacsBudapest University of Technology and Economics, Hungary

The design of remotely controlled and unmanned aerial system (UAS) is an important direction in modernaircraft development. Some researches are aimed at UASs which use paraglider canopy as their wing.This group of UASs can be successfully used in applications where stable, low speed flying and mobilityare required.

In this paper, we introduce a UAS test platform being developed by us, which can be used to testdifferent paraglider canopy. We focus on paragliders used for leisure purposes which have take-off weightup to 150 kg. The most important thing when a new type of UAS is born is the automatic control,which has a very critical function: it has to keep the vehicle in stable fly. To realize this functionthe motion equations and the parameters of the mathematical model must be known. With the helpof our test platform this parameters can be identified and measured along with other flight dynamicsparameters. The mathematical model applied in this paper and suggested in another paper is focused onthe longitudinal motion of powered paragliders. The applied mechanical model of the vehicle representsa single rigid body with three degrees of freedom that consists of a canopy (wing) and the UASs body(gondola). The wing and the gondola are connected by lines, which are modelled by rigid rods. Apropeller producing a thrust is mounted on the gondola. This simple model is the first approximation ofthe powered paraglider, but it seems it is enough when we concentrate on its longitudinal motion. Firstinvestigations show that the difference remains under 4 − 5% between the results of the non-linear andlinear model.

Modeling and simulation of flapping wings nano-robots dynamics of flight

Krzysztof Slavomir Sibilski , Air Force Institute of Technology, Poland

Flapping wings micro aerial vehicles (MAV) flight stability and control presents some difficult challenges.The low moments of inertia of MAVs make them vulnerable to rapid angular accelerations, a problemfurther complicated by the fact that aerodynamic damping of angular rates decreases with a reductionin wingspan. Another potential source of instability for MAVs is the relative magnitudes of wind gusts,which are much higher at the MAV scale than for larger aircraft. Other problem occurs with influenceof flapping wings on MAVs body motion. The birds and flying insects, the biological counterpart ofmechanical MAVs, can offer some important insights into how one may best be able to overcome theseproblems. Biological systems, while forceful evidence of the importance of vision in flight, do not, however,in and of themselves warrant a computer-vision based approach to MAV autonomy. Fundamentally, flightstability and control requires measurement of the MAVs angular orientation. While for larger aircraftthis is typically estimated through the integration of the aircrafts angular rates or accelerations, a vision-based system can directly measure the MAVs orientation with respect to the ground. The two degrees offreedom critical for stability the bank angle and the pitch angle can be derived from a line correspondingto the horizon as seen from a forward facing camera on the aircraft. Therefore, we have developed avision-based horizon-detection algorithm that lies at the core of our flight stability system.

Non linear filtering technique analysis for Navigation of an UAV

Saman Mukhtar Siddiqui, Jiancheng FangBeijing University of Aeronautics and Astronautics, China

Integrated Navigation using Low cost MEMS Inertial Sensors and GPS along with some other secondarysensor is a wide area of research these days. Complementary characteristics of GPS and INS in giving longterm and short term accuracy respectively make them an ideal combination for these type of systems. Thismultisensor approach has proved beneficial economically but requires intelligent filtering algorithims. Thenon linear dynamics of system prevents the use of conventional Kalman filter. Usually Extended Kalmanfiltering is a replacement in non linear environment but has certain limitations. This paper explores othertechniques such as unscented Kalman Filter and Partical Filter to address the same problem on the sameset of data of a UAV. The results are compared and demerits and merits of all approaches is deduced.The GPS is integrated in loosely coupled mode like all commercially available low cost systems. Othersensors include three accelerometers three gyros magnetometer, pressure sensor and air speed sensor. Asimple north pointing navigation scheme is used with WGS84 earth model. The results are verified both

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on simulations and actual tests.

Error Analysis of MEMS sensor data using Allan Variance technique

Saman Mukhtar Siddiqui , Jiancheng FangBeijing University of Aeronautics and Astronautics, China

For low cost commercial Navigation systems usually MEMS type inertial sensors are used along withGPS and other secondary sensors. These MEMS are low cost, light weight, easily manufacturable buthighly erroneous as compared to their tactical grade counterparts. Error modelling of these sensors isdone using techniques like PSD or Allan Variance technique. Allan Variance was originally developed fordetermining clock bias stability, a lot of work has been done on it with reference to calibration of inertialsensors and their sensitivity towards thermal change. This paper describes a study of calibration anderror modelling of MEMS type sensors used in a UAV using Allan Variance technique.

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SPECIAL SESSION 3. Advances in Nonlinear Differential Equations

Organizers: Anjan Biswas (USA), Fengshan Liu (USA), Chaudry Masood Khalique (South Africa)

This session will include all talks that are related to nonlinear differential equations that are both ordinaryand partial. It will also include Stochastic Differential Equations. The focus will be on the solutiontechniques that include asymptotic analysis, Lie symmetry and Lie transform approach, Inverse ScatteringTransform, Hirota Calculus, sub-ODE method, G’/G method, Adomian decomposition method, He’svariational principle and many more. The solutions will include nonlinear waves like the solitary waves,shock waves, compactons, cnoidal waves and others. The solutions obtained by using the multiple-scaleperturbation analysis are also encouraged.

Optical solitons with higher order dispersion

Anjan Biswas, Delaware State University, Dover, Delaware, USA

This talk is on optical solitons, in presence of higher order dispersion terms. The governing equation,namely the nonlinear Schrodinger’s equation, will be integrated by the aid of He’s semi-inverse variationalprinciple. Both Kerr law and power law are taken into consideration.

Wavelet transforms and its connection to established theories and Image Processing

Bharat Namdeo Bhosale , University Of Mumbai, India

Wavelet theory is the mathematics associated with building a model for a signal, system or process with aset of special signals. The past two decades have witnessed the development of wavelet analysis, a new toolwhich emerged from mathematics and was quickly adopted by diverse fields of science and engineering.In the brief period since its emergence in 1987-88, it has reached a certain level of maturity as well aswell defined mathematical discipline; having broad range of applications including signal processing, dataand image compression, solution of partial differential equations, modeling multiscale phenomena, andstatistics. The connections with research in other fields have emerged and become clarified in recent years.In this paper, a strong relationship of FrFT with the Wavelet transform is established in n-dimensionalset up. By exploiting this relationship, WT is extended to the spaces of Tempered Distributions. It isproved that the WT and its inverse, is a continuous isomorphism from S(Rn) onto S(Rn). GeneralizedWT is then defined using duality argument; and it is shown to be a continuous isomorphism from S(Rn)onto S(Rn). The theory so developed will have virtues of both FrFT and WT. This framework is usedto explore its connections with established theories that include Fourier transform, Wigner distribution,Ambiguity function, Radon-Wigner transform and its applicability in Signal/Image processing.

Solutions of Kadomtsev-Petviashvili equation with power law nonlinearity in 3+1 dimen-sions

Chaudry Masood Khalique , North-West University, Mmabatho, South Africa

In this talk we present some solutions of the Kadomtsev-Petviasvili equation with power law nonlinearityin 3+1 dimensions. The Lie symmetry approach as well as extended tanh-function and G′/G methods areused to carry out the analysis. Subsequently, the soliton solution is obtained for this equation with powerlaw nonlinearity. Both topological as well as non-topological solitons are obtained for this equation.

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The Combined Effect of the Linear and Nonlinear Couplings on the Phase and VelocityShifts of Interacting Solitons in Coupled Nonlinear Schrodinger Equations

Michail D. Todorov, Technical University of Sofia, Bulgaria

For a system of nonlinear Schroedinger equations (SCNLSE) coupled both through linear and nonlinearterms, we investigate numerically the taking-over interaction dynamics of elliptically polarized solitons.In the case of general elliptic polarization, analytical solution for the shapes of a steadily propagatingsolitons are not available, and we develop a numerical algorithm finding the initial shape. We use assuperposition of generally elliptical polarized solitons as the initial condition for investigating the solitondynamics. In order to extract the pure effect of the linear coupling, we consider the case without cross-modulation: the Manakov system to which a linear coupling term with real coefficient is added, whenthe individual solitons are actually breathers whose breathing frequency is defined by the linear couplingparameter. The interactions properties of the breathers differ from the the stationary shapes, mostly inthe fact that changes of the initial phase angle of the components of the vector soliton do not affect thevalues of polarization after the interaction. The masses of the individual quasi-particles (QPs) oscillate,but the sum of the masses for the two QPs is constant. Respectively, the total energy oscillates during oneperiod of the breathing, but the average over the period is conserved. When the linear coupling is purelyimaginary then we observe gain or self-dispersion of solitons. Involving, however, into the interaction anontrivial cross-modulation combined with different initial phase angles causes velocity shifts of interactedsolitons. The results of this work outline the role of the initial phase, initial polarization and the interplaybetween the linear and nonlinear couplings on the interaction dynamics of soliton systems in SCNLSE. Allthe numerical experiments are implemented by using of fully conservative difference scheme in complexarithmetic.

Generalized Radon transform and Microlocal analysis

Guoping Zhang, Fengshan LiuDelaware State University, Dover, Delaware, USA

One of the major inventions in last century is the CT-scanner (computerized Tomography). Cormackand Hounsfield got the Nobel-prize in Medicine 1979 for their work with computed axial tomography.The CT-scanner can be used for reconstruction of X-ray absorption in the interior of structures, such aspatients or machine parts with possible internal fractures. The crucial idea for the image reconstructionis that Radon transform can provide a natural link between the image function of the object and themeasurement of the machine such as CT-scanner and MRI. In this talk we will give a brief introductionto Radon transform, the generalized Radon transform and their relations with microlocal analysis theory.We will also provide some of their applications to image processing.

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SPECIAL SESSION 4. Stability and Lyapunov Theory

Organizer: Cemil Tunc (Yuzuncu Yil University, Van, Turkey)

This session will be devoted to the Stability and Lyapunov Theory in Ordinary Differential Equations,Integral and Integro-Differential Equations, Functional Differential Equations (differential equations withconstant delay, variable delay, neutral differential equations with constant delay, variable delay andtheir applications in control theory, mathematical modeling, shell theory, fluid dynamics, informatics,oscillation theory etc.).

Some remarks on the exponential stability and periodicity of solutions for certain delayeddifferential equations of fourth order

Olufemi Adeyinka Adesina , Obafemi Awolowo University, Ile-Ife, Nigeria

The frequency domain method is used to prove the existence of a bounded solution which is exponentiallystable, periodic or almost periodic (according as the forcing term is periodic or almost periodic). Resultsin the literature on corresponding situations where there are no delays are generalized.

Numerical analysis for singularly perturbed delay differential equations

Fevzi Erdogan , Yuzuncu Yil University, Van, Turkey

We study numerical analysis of a difference scheme applied to singularly perturbed initial value problemfor a linear second-order delay differential equations. An exponentially fitted difference scheme isconstructed in an equidistant mesh, which gives first order uniform convergence in the discrete maximumnorm. The difference scheme is shown to be uniformly convergent to the continuous solution with respectto the perturbation parameter. Numerical results are presented.

References:

[1] R. Bellman, K.L. Cooke, Differential-Difference Equations, Academy Press, New York, 1963.

[2] R.D. Driver, Ordinary and Delay Differential Equations, Belin-Heidelberg, New York,Springer, 1977.

[3] E.R. Doolan, J.J.H. Miller, W.H.A. Schilders, Uniform Numerical Methods for Problems with Initialand Boundary Layers, Boole, Press, Dublin, 1980.

[4] P.A. Farrell, A.F. Hegarty, J.J.H. Miller, E. O’Riordan, G.I. Shishkin, Robust ComputationalTechniques for Boundary Layers; Chapman-Hall/CRC, New York, 2000.

[5] H.G. Roos, M. Stynes, L. Tobiska, Numerical Methods for Singularly Perturbed Differential Equations,Convection-Difusion and Flow Problems, Springer Verlag, Berlin, 1996.

[6] G.M. Amiraliyev, Y.D. Mamedov, Difference schemes on the uniform mesh for singularly perturbedpseudo-parabolic equations, Tr. J. of Math.,19(1995) 207-222.

[7] G.M. Amiraliyev, F. Erdogan, Uniform numerical method for singularly perturbed delay differentialequations, J.Comput. Math. Appl. 53(2007)1251-1259.

[8] H. Tian, The exponential asymptotic stability of singularly perturbed delay differential equations witha bounded lag, J. Math. Anal. Appl. 270(2002)143-149.

[9] C.G. Lange, R.M. Miura, Singular perturbation analysis of boundary-value problems for differential-difference equations. v. small shifts with layer behavior, SIAM J. Appl. Math.54 (1994) 249-272.

[10] M.K. Kadalbajoo, K.K. Sharma, Numerical analysis of singularly perturbed delay differentialequations with layer behavior, Appl. Math. Comput. 157 (2004) 11-28.

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Ultimate boundedness of solutions of non-homogeneous vector differential equation of thethird-order

Mathew Omonigho Omeike , University of Agriculture, Abeokuta, Ogun State, Nigeria

We present here the ultimate boundedness of solutions of some nonlinear non-homogeneous vectordifferential equation of the third order, by means of the Lyapunov second method. We provide, insimple form, sufficient conditions which ensure ultimate boundedness of solutions of equations of theform

...

X +φ(X)X + G(X) + H(X) = P (t,X, X, X).

Results obtained generalize, improve and include the results obtained by previous authors.

New stability and boundedness results of solutions of nonlinear differential equations ofsecond and third order with variable delay

Cemil Tunc, Yuzuncu Yil University, Van, Turkey

In this paper, we investigate stability and boundedness of solutions to nonlinear certain differentialequations of second and third order with variable delays. We find some sufficient conditions for solutionsof these equations to be asymptotically stable and bounded by means of Lyapunov functional approach.Specific examples are given to show the effectiveness of our results.

References:

[1] Afuwape, A. U.; Omeike, M. O. On the stability and boundedness of solutions of a kind of third orderdelay differential equations. Appl. Math. Comput. 200 (2008), no. 1, 444-451

[2] Tunc, C., Some stability and boundedness results to nonlinear differential equations of Lienard typewith finite delay. J. Comput. Anal. Appl. 11(4), (2009), 711-727.

[3] Tunc, C., On the stability and boundedness of solutions to third order nonlinear differential equationswith retarded argument. Nonlinear Dynam. 57 (2009), no. 1-2, 97-106.

[4] Tunc, C., Some stability and boundedness conditions for non-autonomous differential equations withdeviating arguments. Electron. J. Qual. Theory Differ. Equ. 1 (2010), 1-12.

[5] Tunc, C., Some new stability and boundedness results of solutions of Lienard type equations withdeviating argument, Nonlinear Analysis: Hybrid Systems, 4 (1), (2010), 85-91.

[6] Tunc, C.; Tunc, E., On the asymptotic behavior of solutions of certain second-order differentialequations. J. Franklin Inst., Engineering and Applied Mathematics 344 (5), (2007), 391-398.

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SPECIAL SESSION 5. Contributions of PhD Students (and Post-Doctoral Researchers)

Organizers: Anne Caroline Bronzi (Brazil), Dragos-Patru Covei (Romania)

Many developments in the fields of Engineering, Aerospace and Sciences frequently occur as a resultof the interaction between scientists and applied mathematicians. The high complexity of practicalapplications requires the joint work of specialists from different fields. The aim of this session is to givean opportunity to Ph.D. students and young post-doctoral researchers to present their own contributionsrelated to mathematical problems from different fields, as well as to interact with other Ph.D. students.

Weak solutions of the incompressible ideal flow equations

Anne Caroline Bronzi , UNICAMP, Brazil

The notion of weak solution allows for rather irregular, perhaps even turbulent, flows to be studied assolutions of the incompressible ideal flow equations. However, it is also clear that the notion of weaksolution has severe shortcomings, allowing clearly nonphysical examples of weak solutions. We surveythe analytical theory of weak solutions, specially some of the examples of weak solutions that highlightthe shortcomings of the notion of weak solution and the possible avenues for producing a physicallymeaningful, complete theory.

A Lane-Emden-Fowler type problem

Dragos-Patru Covei , University Constantin Brancusi of Tg.-Jiu, Romania

The problem of existence, non-existence, uniqueness, asymptotic behaviour, determination or numericapproximation of solutions for the Lane-Emden-Fowler type problems plays an important role in thescientific community, especially from the point of view of the fact that a significant number of processesfrom applied sciences are modelled by them, and general development provides us with new perspectivesand research ways. This article improves the results achieved so far for some problems studied by theauthor during his PhD training as well as by other researchers from the scientific community.

Superposition of a pulsating and oscillating flow of a complex structural liquid

Edtson Emilio Herrera-Valencia, McGill University, Canada

The rectilinear Poiseuille flow of a complex liquid flowing in a vibration pipe coupled with a pulsating-timepressure gradient is analyzed. The pipe wall performs ultrasonic vibrations (longitudinal and transversal).Pulsating flow can be adequately represented by a time Fourier series. In order to find an analyticalexpression for the flow enhancement a quasi-static perturbation solution in terms of a small parameter issuggested. The stress tensor is separated in two contributions, the first due to the solvent and the secondto the polymer. The solvent is characterized by a Newtonian liquid and the complex liquid with theBautista-Manero-Puig model (BMP) constitutive equation, consisting in the Upper Convected Maxwellequation coupled to a kinetic equation to account for the breakdown and reformation of the fluid structure.Several particular cases are analyzed and the results are consistent with other simple models that havebeen analyzed in the literature. The viscoelastic, kinetic and structural mechanisms were characterized bythe association of non-dimensional numbers to each mechanism. Finally, flow enhancement is predictedusing experimental data reported elsewhere for a worm-like micellar solutions of CETAT.

Differential Transform Method of Solution for Non-Linear Boundary Value Problem: AnIllustration

Madhavanpillai Sumathykuttyamma Jagadeesh Kumar , Vellore Institute of Technology, IndiaSuresh G. Singh , University of Kerala, IndiaPradeep Ganapathi Siddheshwar , Bangalore University, India

Darcy Forchheimer Brinkman flows through porous media in different geometries are known to be quiteformidable due to the governing equation being quasi-linear. A boundary value problem arising in sucha flow through a rectangular porous box is considered in this paper for arriving at its solution by thedifferential transform method with assistance from the secant method. Comparison of the results of our

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study is made with those obtained by using the finite difference method with quasi-linearization. Goodagreement is found between the two results.

Physical Programming based Multidisciplinary Optimization for 2D Turbine Airfoil

Zhang Nannan , Northeastern University, China

This paper concerns on the computation and development of 2D turbine airfoil. In order to obtain a tur-bine blade shape with better performance, a physical programming based multidisciplinary optimizationstrategy is employed. The aim of multidisciplinary optimization here is to minimize the total pressureloss as well as to maintain a good structural stress. So there must be a compromise between aerodynamicperformance and structural performance. That part of work is done by physical programming method inthis paper, which can get more reasonable results than traditional ones. And the optimization processstudied a range of design factors including the airfoil geometry parameters, the deviation angle, and atwo-dimensional k-e turbulence model.

Heat transfer in a Darcy-Forcheimmer-Brinkman flow through a curved channel

Mahesha Narayana , M.S. Ramaiah Institute of Technology, Bangalore, IndiaVishwanath Kadaba Puttanna , Jawaharlal Nehru Centre for Advanced Scientific Research, IndiaPradeep Ganapathi Siddheshwar , Bangalore University, Bangalore, India

The paper presents the analysis of forced convective heat transfer in a flow through a curved channelfilled with porous matrix using a most general model of Darcy-Forcheimmer-Brinkman. A homotopy-based method is employed in order to arrive at the solution for the governing nonlinear equation with anassured convergence. Darcy and Brinkman model is recovered as a limiting case of the study. The Nusseltnumber is calculated for different values of the parameters involved, namely, curvature parameter, Darcynumber, Brinkman number and Forcheimmer number.

Axi-symmetric, Darcy-Brinkman-Forchheimer flow through an annulus

Pradeep Ganapathi Siddheshwar, Ashoka Basavaraje Gowda Sangarashettahally, BangaloreUniversity, India

The nonlinear boundary value problem arising in the two-dimensional fully-developed Darcy-Brinkman-Forchheimer flow through an annulus is solved numerically using a combination of finite-difference andhomotopy continuation methods. The RKF45 procedure is used to solve the initial value problem arisingin the homotopy method. Results of the study are compared with those obtained by the shooting method.The effect of increasing Darcy number is to flatten the velocity profile. The influence of the Brinkmanand Forchheimer numbers on the velocity is not as significant as that of the Darcy number.

Numerical Analysis of Aerodynamic Performance of a Aircraft Wing With Simulated GlazeIce Accretion

Aung Ko Wynn, Cao Yi Hua, Ma CaoSchool of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics, China

This paper deals with the computational studies carried out on the aircraft rectangular wing with andwithout leading edge glaze ice accretion at subsonic Mach number conditions. The rectangular wingwas extruded from a business jet GLC 305 airfoil sections with a 6 minute glaze ice 072895-05 accretiondenoted as a two dimensional glaze ice shape. The aerodynamic performance degradation of lift, dragand pitching moment coefficients and pressure coefficients were evaluated. The computation were carriedout at Mach number 0.3 with the Reynolds number 6.4x106 conditions to obtain the flow field around theaircraft rectangular wing with and without 6 minute glaze ice accretions. The pressure distribution overthe aircraft wing with ice accretion on the angle of attack (4 and 6) degrees has also been investigated.This computational study is based on the Fluent-UNS code using the one equation Spalart-Allmaras(S-A)turbulence model and second order upwind differencing. The results show that the 3D-CFD computationcan accurately predict the lift, drag and pitching moment coefficients for the aircraft rectangular wingwith 6 minute glaze ice accretion.

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SPECIAL SESSION 6. Mathematical Research in Dynamical Systems Theory

Organizer: Mihai Popescu (Institute of Applied Mathematics, Bucharest, Romania)

This special session is devoted to the study of a large class of dynamical systems corresponding to physicalphenomena. Some of the presented problems represent mathematical researches within aerospace sciencesand include studies related to stability, controllability and optimization of the analyzed phenomena. Allconsidered problems are contributions in nonlinear dynamical system theory and applications.

Risk-Sensitive Second Grade Optimal Filtering Design

Maria Aracelia Alcorta-Garcia, Hector Flores Cantu, Sonia Guadalupe Anguiano-RostroAutonomous University of Nuevo Leon, Mexico

The risk-sensitive filter design problem for polynomial systems of second grade drift terms and intensityparameters multiplying diffusion terms in the state and observations equations with respect to theexponential mean-square criterion is considered for stochastic Gaussian systems. The closed form optimalfiltering algorithm is obtained using quadratic value functions as solutions to the corresponding Focker-Plank-Kolmogorov equation. The performance of the obtained risk-sensitive filter for stochastic seconddegree polynomial systems is verified in a numerical example against the optimal polynomial for secondgrade filter through comparing the exponential mean-square criteria values. The simulation resultsreveal strong advantages in favor of the designed risk-sensitive algorithm for all values of the intensityparameters.

Risk-Sensitive Third Grade Optimal Filtering Design

Maria Aracelia Alcorta-Garcia, Hector Raymundo Flores-Cantu, Mauricio Torres TorresAutonomous University of Nuevo Leon, Mexico

The risk-sensitive filter design problem with respect to the exponential mean-square criterion is consideredfor stochastic Gaussian systems with polynomial of third grade drift terms and intensity parametersmultiplying diffusion terms in the state and observations equations. The closed-form optimal filteringalgorithm is obtained using quadratic value functions as solutions to the corresponding Focker-Plank-Kolmogorov equation. The performance of the obtained risk-sensitive filter for stochastic third degreepolynomial systems is verified in an numerical example against the optimal polynomial for third gradefilter through comparing the exponential mean-square criteria values. The simulation results reveal strongadvantages in favor of the designed risk-sensitive algorithm for large values of the intensity parameters.

Three-dimensional effects on rotor blade sections in stall

Vladimir Cardos, Horia DumitrescuInstitute of Statistics and Applied Mathematics, Bucharest, Romania

Most aerodynamic design tools for wind energy converters are based on the blade element-momentumtheory. Due to the nature of this theory, the design tools need 2D steady sectional lift and drag curvesas an input. In practice, flow over a wind turbine rotor blade is neither two-dimensional nor steady, andis affected by rotation. Pioneering experiments have identified a consequence: at inboard rotor bladesections stall is delayed. This so-called Himmelskamp effect gives a longer lift than predicted, and, as aresult, a higher power and loading than expected. Consequently, an aerodynamic analysis tool is neededto predict sectional lift and drag under rotating conditions. In this paper, development and validation ofsuch a tool is described, with the wind turbine application in mind.

Non-linear Inverse Dynamics Control of the Smart Column with Support Excitation

S. Ahmad Fazelzadeh, E. Azadi, M. AzadiShiraz University, Iran

In this paper, the non-linear vibrations of a smart column carrying the tip mass under support excitationwhen a pair of piezoelectric layers is attached are controlled. The column is subjected to a support motion,with one end fixed and the other end has an effect on a concentrated mass. The governing equations, which

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are based on classical beam theory, include the large deformation nonlinearity. Moreover, the analysis isbased on the generalized function theory and Lagrange-Rayleigh-Ritz technique. The inverse dynamicscontrol is used to suppress the vibrations of the column under lateral excitation. The mathematicalmodeling of the column with control algorithm is derived and in purpose to study the effects of theamount of tip mass, size and location of the piezoelectric layers and the type of the support excitationon the column vibrations, the system is simulated. The performance of the nonlinear control system isexamined. Also, the numerical results are shown that the vibration of the column is suppressed for eachcondition.

Unsteady free-wake vortex particle model for prediction of the aerodynamic loads of HAWTrotor blades

Florin Frunzulica , Politehnica University of Bucharest, Faculty of Aerospace Engineering, RomaniaAlexandru Dumitrache , Institute of Statistics and Applied Mathematics, Bucharest, RomaniaHoria Dumitrescu , Institute of Statistics and Applied Mathematics, Bucharest, RomaniaVladimir Cardos, Institute of Statistics and Applied Mathematics, Bucharest, Romania

In the design of horizontal axis wind turbines (HAWT) one problem is to determine the aeroelasticbehaviour of the rotor blades for the various wind inflow conditions. A step in this process is topredict with accuracy the aerodynamic loads on the blades. The Vortex Lattice Method (VLM)provides a transparent investigation concerning the role of various physical parameters which influencethe aerodynamic problem. A major problem encountered in the numerical simulation of the three-dimensional incompressible inviscid flows is the expensive computation effort to specify the wake locationand its influence. In this paper we present a method for the calculation of the non-uniform induceddownwash of a HAWT rotor using the vortex ring model for the lifting surface coupled with an unsteadyfree-wake vortex particle model. Comparative studies between results obtained with different models ofwake for a generic HAWT are presented.

Computational Methods for Panel Flutter Analysis

Florin Frunzulica , Politehnica University of Bucharest, Faculty of Aerospace Engineering, RomaniaMarius Stoia-Djeska, Politehnica University of Bucharest, Faculty of Aerospace Engineering, RomaniaAlexandru Dumitrache , Institute of Statistics and Applied Mathematics, Bucharest, Romania

The panel flutter phenomenon is a self-excited oscillation of a thin shell exposed to high speed flow. Froman engineering point of view, the panel flutter analysis is performed using frequency and/or time domaincomputational techniques. This paper is concerned with the evaluation of three different approaches forthe numerical analysis of the panel flutter phenomenon. The structural model is based on the finiteelement discretization and is assumed to be linear, while the aerodynamic model can be linear or non-linear.

A large number of numerical results are presented for supersonic flows over a rectangular metallic shell.The predictions provided by the three methods are used for the analysis of the influence of the simplifiedpiston theory, coupling algorithms and time steps in the panel flutter analysis.

A numerical algorithm to study the propagation of elastic plastic waves in bars

Olga Martin , Romania

The action of loads suddenly applied to a body is not propagated instantaneously but is transmittedfrom one particle to another in a wave-like manner. In this paper, we study the impact loading ofsemi-infinite prismatic bars using a numerical algorithm based on the finite element method (FEM)and finite-differences method (FDM). A detailed analysis of the calculus errors is made and a theoremconcerning the approximations is proved. The numerical example confirms the efficiency of the proposedmethod.

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Optimal Transfer Trajectories from Lagrangian Collinear Points

Mihai Popescu , Institute of Applied Mathematics, Bucharest, Romania

The present paper illustrates the study of transferring the space vehicle from the collinear libration pointsof the Earth-Moon system to the maximum distance assuming that the evolution time is given. After theanalysis of the admissible states, the optimal control which represents the absolute extremum in a classof relative extremum is determined.

Studies for type-II and type-III intermittencies

Ezequiel del Rio, Universidad Politecnica de Madrid, SpainSergio Elaskar , CONICET - Universidad Nacional de Cordoba, ArgentinaJose Manuel Donoso, Universidad Politecnica de Madrid, Spain

We have proposed a new method to evaluate the reinjection probability function for type-II and type-IIIintermittencies [1]. The new reinjection probability density (RPD) has been observed in the broad classof maps as we have checked by numerical simulations and analytical studies. For type-II intermittency,we have presented a new one-parameter family of functions describing the reinjection probability. It hasbeen proved that the usual uniform reinjection is a particular case of our RPD. We have also found a newexpression for the RPD in type-III intermittency by extending the analysis used for type-II intermittency.For the type-III case, a new two-parameters family of RPD has been found from which one can be derivethe lower bound of reinjection (LBR). Using the news RPD we have also derived the densities of thelaminar phase lengths and the new characteristic relations.

[1] Ezequiel del Rio and Sergio Elaskar - New Characteristic Relations in Type-II Intermittency.International Journal of Bifurcation and Chaos. Vol. 20 April (2010)

Biparametric investigation of the general standard map: multistability and crises

Priscilla Andressa de Sousa Silva, Maisa de Oliveira TerraInstituto Tecnologico de Aeronautica, Brazil

We investigate global bifurcations in the phase space of a biparametric two-dimensional map, the standardmap, derived from a model for the periodically kicked mechanical rotor. This mathematical modelpresents a wide assortment of dynamical phenomena, being an adequate paradigm for studying severalfundamental features such as multistability, crises, and chaotic transients. Starting with the conservativecase of the map, we illustrate the mechanisms of creation, merging and destruction of typical chaoticattractors, as dissipation builds up. Through the characterization of an interior, a merging and a boundarycrisis, we study the crucial role played by important invariant structures, such as unstable periodic orbitsand their invariant manifolds, in the mechanisms by which the phase space is globally transformed. Also,special attention is payed to the effects of the dissipative and the forcing parameters in the feature ofmultistability.

Stability Study of Constrained Systems

Ion Stroe , Politehnica University of Bucharest, Romania

A new method for systems’ stability analysis is presented. This method is called weight functions methodand it replaces the problem of finding a Liapunov function with a problem of finding a number of functions(weight functions) equal to the number of first order differential equations describing the system. It isknown that there are no general methods for finding Liapunov functions. The weight functions method issimpler than the classical method since one function at a time has to be found. This methods conditionsof solution stability and holonomic systems with dependent variables are analyzed. Also, applicationssuch as the Lurie-Postnikov problem, stability of the rotational motion of a rigid body, the rigid bodycommand stabilization are presented.

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Homogenization Results for a Wave Equation with Interior and Boundary Damping

Claudia Timofte , Faculty of Physics, University of Bucharest, Romania

The asymptotic behavior of the solution of a singularly perturbed wave equation with dynamic boundaryconditions in a periodically perforated medium is analyzed.

We consider, at the microscale, an ε-periodic structure obtained by removing from a bounded connectedopen set Ω in Rn a number of closed subsets of characteristic size ε. As a result, we obtain an open set Ωε,which will be referred to as being the perforated domain. In this domain, we consider a wave equation,with interior sources and damping and with dynamic boundary conditions imposed on the boundaries ofthe perforations.

Assuming suitable initial conditions, we prove that this boundary value problem is a well-posed one. Thistype of boundary-value problems can be encountered in the modelling of various phenomena arising, forinstance, in electricity, magnetism, in the theory of elasticity, in vibrations theory or in hydrodynamics.

We are interested in describing the asymptotic behavior, as the small parameter ε which characterizesthe size of the perforations tends to zero, of the solution of such a problem. Using an homogenizationprocedure, we prove that the effective behavior of this solution is governed by a new parabolic equation,defined on the nonperforated domain Ω.

Generalized Riccati equations in Banach spaces

Viorica Mariela Ungureanu , Romania

In this paper we consider the existence problem of some global solutions for a general class ofdiscrete-time backward nonlinear equations defined on ordered Banach spaces. The discussed class ofnonlinear equations includes as special cases many of the discrete-time Riccati equations arising both indeterministic and stochastic optimal control problems. Based on a linear matrix inequalities (LMI)approach we give necessary and sufficient conditions for the existence of the maximal solution, thestabilizing solution and respectively the minimal positive semi-definite solution of the considered discrete-time backward nonlinear equations. This paper extends the results in [V. Dragan, T. Morozan, A class ofdiscrete time generalized Riccati equations, Journal of Difference Equations and Applications, 1563-5120,11 December 2009] and [V. M. Ungureanu, Optimal control for linear discrete-time systems with Markovperturbations in Hilbert spaces, IMA J. Math. Control Inform. 26 (2009), no. 1, 105-127].

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SPECIAL SESSION 7. Methods of Nonlinear Analysis for Partial Differential Equations

Organizers: Eduard-Wilhelm Kirr (USA), Radu Precup (Romania)

This special session will focus on methods of nonlinear functional analysis: fixed point theorems, criticalpoint theory, upper and lower solutions method, iterative techniques etc. for partial differential equationsand systems arising from the mathematical modeling in engineering, aerospace and all areas of science.Intended audience includes researchers in nonlinear analysis, partial differential equations and appliedmathematics.

Elementary Numerical Differential and Integral Methods to Determine the Reaction Ratesof Chemical Reactions

Christopher Gunaseelan Jesudason , Chemistry Department, University of Malaya, Malaysia

Quantitative chemical reaction rate determination are derived mainly by linear plots of reagent concen-tration terms or its logarithm (depending on the order) against time with initial concentration specified,which is experimentally challenging. By definition, the rate constant is an invariant quantity and thekinetic equations follow this assumption. Different schemes have been used to circumvent specifyinginitial concentrations. Here, the differential method focuses on the gradient which provides a sensitivemeasure of the rate constant that does not require specification of initial concentrations and the resultsare compared with those derived from standard methodologies from an actual chemical reaction andone simulated ideally. It is shown that the method is feasible. We verify experimentally our previoustheoretical conclusion based on simulation data [J. Math. Chem. 43 (2008) 976-1023] that the so calledrate constant is never constant even for elementary reactions and that all the rate laws and experimentaldeterminations to date are actually averaged quantities over the reaction pathway. The integral approachis also developed and proved feasible. It is concluded that elementary nonlinear methods in conjunctionwith experiments could play a crucial role in extracting information of various kinetic parameters.

Bifurcations of Nonlinear Bound-States in Schroedinger type equations

Eduard-Wilhelm Kirr , University of Illinois at Urbana-Champaign, USA

I will discuss recent results on existence, bifurcations and stability of periodic in time, localized in spacesolutions (bound-states) of nonlinear Schroedinger equation. They form curves in certain Sobolev spacesparametrized by their period. It turns out that, under generic assumptions, the curves bifurcate leadingto changes in both the spatial shape of the bound-states (symmetry-breaking) and in their dynamicalstability. I will identify and classify the bifurcations and their effect on the dynamical stability of thesolutions. This is joint work with D. Pelinovski, P. Kevrekidis and V. Natarajan.

Stability for fluid structure interaction models with non-linear dissipation at the interface

Roberto Triggiani , University of Virginia, Mathematics Department, USA

We consider an established fluid structure interaction: a structure (the hyperbolic dynamic system ofelasticity) is immersed in a fluid (the minearized navier-Stokes equation) with coupling at the interfacebetween the two media. The original system is at best sytrongly stable mod a one-dimensional factorspace, under favorable geometrical conditions of the structure (the sphere is excluded). We then introducea dissipative term at the boundary interface: the linear system is uniformly stable under no geometricalconditions and so is the non-linear boundary case. We follow via the linear theory into the Lasiecka-Tataru’s approach in the non linear case. Joint work with G. Avalos and I. Lasiecka.

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SPECIAL SESSION 8. Advances in Fractional Differential Equations

Organizers: Gisele M. Mophou (Guadeloupe, France), Gaston M. NGuerekata (USA)

This session is devoted to the qualitative theory of fractional differential equations and its applicationsto science and engineering. Main focus includes existence theorems, controllability as well as long termbehavior of solutions of such equations and related numerical problems.

Fractional differential equations with piecewise constant argument deviations

William Edmond Dimbour , Guadaloupe, France

Fractional differential equations of advanced type with piecewise constant argument deviations arestudied. The fractional time derivative is considered in Caputo sense. Existence, uniqueness, stability ofsolutions of these equations are proved.

New results on fractional differential and integrodifferential equations in Banach spaces

Jin Liang , China

We are concerned with the existence and uniqueness of solutions to fractional differential and integrodif-ferential equations in Banach spaces. New existence and uniqueness theorems are obtained by fixed pointtheorems and monotone iterative techniques. Some examples are given to illustrate our abstract results.

Optimal control of a class of fractional diffusion equation

Gisele Mophou , Universite des Antilles et de la Guyane, Guadaloupe, France

In this paper we apply the classical control theory to a fractional diffusion equation in a bounded domain.The fractional time derivative is considered in Riemann-Liouville sense. We first study the existence andthe uniqueness of the solution of the fractional diffusion equation in a Hilbert space. Then interpretingthe Euler-Lagrange first order optimality condition with an adjoint problem defined by means of Weylfractional integral type, we obtain an optimality system for the optimal control.

Existence and uniqueness of mild solution for fractional integro-differential equations

Gaston Mandata NGuerekata , Morgan State University, Baltimore, USAFang Li , Yunnan Normal University, China

In this paper, we study the existence and uniqueness of mild solution to a class of some nonlinear fractionalintegro-differential equations in a Banach space. We present an application to the abstract results.

Pseudo-almost automorphic solutions to a class of semilinear fractional equations

Marcos Rabelo, Universidade Federal de Pernambuco, Brazil

We study pseudo-almost automorphic (mild) solutions of the semilinear fractional equation

∂αt u = Au + ∂α−1

t f(·, u), 1 < α < 2 ,

considered in a Banach space X, where A is a linear operator of sectorial type ω < 0.

Pseudo almost periodic and pseudo almost automorphic functions and their applications toabstract fractional differential equations

Ti-Jun Xiao, China

Examples are given to show that the decomposition of weighted pseudo almost periodic function isnot unique for certain ρ ∈ U∞. Some basic properties of weighted pseudo almost periodic functions andpseudo almost automorphic functions are presented. Moreover, an new existence and uniqueness theoremof pseudo almost automorphic solutions to abstract fractional differential equations is obtained.

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SPECIAL SESSION 9. Petri Nets for Complex Systems

Organizer: Joslaine Jeske de Freitas (Universidade Federal de Goias, Campus Jataı, Brazil)

Petri nets have graphical representation and are easy to learn. Their use makes it possible to describethe static and dynamic aspects of the system with the necessary mathematical formalism. This session isdevoted to present the use of formal models based on Petri nets for modeling, simulation and validationof complex systems.

Intelligent Building - Modeling and Reconfiguration using Petri Net and Holons

Julio Arakaki , Pontificia Universidade Catolica de Sao Paulo, BrazilDiolino Jose dos Santos Filho, Fabricio Junqueira, Paulo Eigi MiyagiUniversity of Sao Paulo, Brazil

The evolution of technology has increased the complexity of intelligent buildings environments. Thispaper proposes a procedure for the modeling of control systems in intelligent buildings (IB). The proposedprocedure adopts the concept of Discrete Event System (DES), Holon, and Petri net and its extensionsto describe the structure and the operation of control systems in IB. The procedure focuses on the FTCS(Fault-Tolerant Control Systems) requirements, with special attention on the system reconfiguration.The approach adopted in the modeling process is based on Petri net. The holons can be physical(chiller, sprinkler, PLC, etc.) or logical components (service, order, etc.). The interactions betweenholons are described using Petri net. The mechanism adopted to implement control architecture enablesit to be hierarchical or heterarchical, and react to faults in a more agile way. This work involves theedition, simulation and validation of Petri net models. From the valid models it is possible to derive thespecification of programs that should be executed in PCs (programmable controllers) and supervisorysystems.

Collaborative Control Model for Multifunctional Machine Tools Environment

Osvaldo Luis Asato, Diolino Jose dos Santos Filho, Fabricio Junqueira, Paulo Eigi MiyagiUniversity of Sao Paulo, Brazil

In general, Manufacturing Systems (MS) are composed by a set of resources and can execute a set ofprocesses. According to these processes the control system of the MS realizes the allocation of thetransformation resources (e.g., machines) to execute the activities. In order to assure the global efficiencyof production systems with multiple processes strongly connected that share a set of resources, it isessential to apply the concept of lean manufacturing to avoid machine idles. However, when the MSis composed by several multifunctional machine tools, there is a new level of control that needs to behandled: the functionality of the machines. The purpose of this paper is to present a control systemof MS compatible with this behavior. The contributions can be synthesized as the improvement ofthe control system with a new architecture based on Petri net models that is capable to deal with apartition between the resource allocation and the functionality allocation, i.e. the functionality of themultifunctional machines can be controlled dynamically.

A model to represent human behavior in workflow management systems

Joslaine Cristina Jeske de Freitas, Universidade Federal de Goias, Campus Jataı, BrazilStephane Julia , Universidade Federal de Uberlandia, BrazilRobert Valette , Laboratoire dAnalyse et dArchitecture des Systemes, Toulouse, France

Currently, the need to represent the information needs is essential. One of the great difficulties thatexist is to represent human behavior when it comes to Workflow. The purpose of Workflow ManagementSystems is to execute Workflow Processes. Workflow Processes represent the sequence of activities thathave to be executed within an organization to treat specific cases and to reach a well-defined goal. Of allnotations used for modeling Workflow Processes, Petri Nets are the most appropriate. Moreover, Petrinets can be used for specifying the real time characteristics of Workflow Management Systems (in thetime Petri net case) and resource allocation mechanisms. The aim of this paper is to present a model ofhuman resource allocation based on Petri nets to workflow management systems.

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Distributed modelling and simulation of complex systems using Petri net

Fabrıcio Junqueira, Cristiano da Silva Costa,Diolino Jose dos Santos Filho, Paulo Eigi MiyagiDepartamento de Eng. Mecatronica e de Sistemas Mecanicos da EPUSP, Brazil

The man-made systems are becoming more complex. This is due to changes in productive systems, suchas the adoption of different technologies (heterogeneous components and subsystems), and even for moreinteraction between companies. Consequently, the productive systems are becoming more susceptibleto errors of projects. For this, models and simulation techniques can be used to minimize the chancesof error. In particular, modelling and simulation distributed stand out. It deals with the execution ofsimulation in physically dispersed computers connected through a network. It allows different teams towork simultaneously on the system being modelled and the use of multiple computers can reduce thesimulation time. In this context, this paper presents a method for distributed modelling using Petri net.To illustrate the method, this is applied to model systems of a conventional submarine.

A Hybrid Method to Generate Control Algorithms for Complex Systems

Francisco Yastami Nakamoto, Diolino Jose dos Santos Filho,Fabrıcio Junqueira, Paulo Eigi MiyagiDepartamento de Eng. Mecatronica e de Sistemas Mecanicos da EPUSP, Brazil

Access to intelligent technology of sensors and actuators, monitoring, control and communication inindustrial environments contributed to a significant increase of the demand for complex automation andcontrol. Concomitantly, the presence of more efficient and effective computational resources promotesnew technologies and new methodologies for systems control project . The basis of the convergence offactors for a common point of view is the integration, flexibility and reuse of the elements that make upthe system, i.e. hardware and software. This will only be possible if there are availability and access tostandards and procedures. In this context, the IEC 61499 standard has provided subsidies that guide theproject to develop control of production systems with emphasis on modularization, i.e. the botton-upapproach. However, the first challenge in the modeling process of such systems is the understanding,definition and sequencing of activities of the global processes that the system should control. Thus,the aim of this paper is to present a hybrid method based on global and local state representation togenerating the control algorithm, represented by a derivative of the Petri net through the use of graphicaltools for modeling.

Scheduling Heuristic based on Time Windows for Service-oriented Architecture

Marcosiris Amorim de Oliveira Pessoa , University of Sao Paulo, BrazilDiolino Jose dos Santos Filho, University of Sao Paulo, BrazilJose Isidro Garcia Melo, Universidad del Valle Cali, ColombiaFabricio Junqueira , University of Sao Paulo, BrazilPaulo Eigi Miyagi , University of Sao Paulo, Brazil

Nowadays the global economic markets have an intense world-wide competition. The modern manufac-turing enterprises are dispersed in a world-wide area. In this context, the enterprises are more geographicdispersed and the productive activities could need the global distributed productive systems. Hence,there are some new requirements for production scheduling in this distributed productive systems. Thedistributed productive systems could be developed in Service-Oriented Architecture (SOA). The SOAhas become a technologic unifying architecture for the integration of distributed software systems witchdisparate software components using Internet Protocols. The web service composition is highly importantfor the development in service-oriented architecture. In this way, the Business Process Execution Lan-guage for Web Services (BPEL) is becoming the industrial standard for modeling the web-service. Thispaper proposes a scheduling heuristic based in Time Windows to attend the new requirements of the dis-tributed systems and a procedure for modeling and analysis the results of the scheduling heuristic in thisnew distributed context. For modeling the distributed productive systems was characterized as a discreteevent dynamic system. The procedure uses techniques derived from Petri net to mapping the BPEL pro-cess definition and to perform the modeling.

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Control Algorithms Partition Method for Distributed Control Systems

Diolino Jose dos Santos Filho, Andre Cesar Martins CavalheiroUniversity of Sao Paulo, Brazil

The evolution of control devices and the Software Engineering techniques increase the flexibility, autonomyand reliability of control systems. As result, new programmable controllers need to be considered, takinginto account aspects such as capacity and processing speed as well as communication functions accordingto IEC 61499. In this context, the challenge is to specify a distributed control system for ManufacturingSystems composed by a set of autonomous resources (logical and physical dispersed) that are able toexecute great number of different processes, simultaneously. In this way, the control strategy cannotbe concentrated in a single device, i.e., it must be distributed in different controllers. Currently, thesoftware engineering has been contributing with new approaches to systematize the control algorithmsdevelopment. In this work a method to specify an efficient distributed control architecture is proposed:Petri net is applied to structure the internal organization of programmable controller programs andfunction blocks; the control algorithms is partitioned using techniques derived from operational researchto arrive at optimal or near-optimal solutions according to the specification of the controllers architecturethat can be used. This proposal is supported by IEC 61131-3 and IEC 61499 standards.

Safety Instrumented Systems Design Based on Bayesian network and Petri net

Reinaldo Squillante Junior , University of Sao Paulo, BrazilDiolino Jose dos Santos Filho, University of Sao Paulo, BrazilJose Isidro Garcia Melo, Universidad del Valle Cali, ColombiaFabricio Junqueira , University of Sao Paulo, BrazilPaulo Eigi Miyagi , University of Sao Paulo, Brazil

Actually, Safety Instrumented Systems (SIS) are designed to prevent and / or mitigate accidents, avoidingundesirable high potential risk scenarios and saving costs and protecting health of people, environmentand equipments. It demands formal methods to assure the safety specifications. In this sense, this paperintroduces a methodology for modeling diagnostic and treatment of critical faults using Bayesian networks(BN) and Petri nets (PN) respectively. This approach considers some critical faults got from hazard andoperability (HAZOP) study in the equipment or system under control and define each safety instrumentedfunction (SIF) as well determine the safety instrumented level (SIL) by each SIF. The present approachuses Bayesian networks (BN) for diagnoses and decision-making proposes, and the Petri nets (PN) forthe synthesis, modeling and control proposes implemented by Safety PLC to prevent and / or mitigateaccidents. A case study considering diagnostic and treatment of critical faults is presented.

Simulation of Industrial Metabolism using Predicate Transition Petri Nets combined withDifferential Equations

Liliane Nascimento Vale , Universidade Federal de Goias, BrazilStephane Julia , Universidade Federal de Uberlandia, BrazilNubia Rosa Silva , Universidade Federal de Uberlandia, BrazilMarcio Souza Dias, Universidade Federal de Goias, Brazil

The goal of our work is to propose an approach based on modeling for the study of industrial metabolism,improving the metabolic flows of industrial processes and the appropriate use of materials. The industrialmetabolism is characterized as a result of physical and chemical transformations to convert raw materialsinto manufactured products. We begin by using an ordinary Petri net model to show the main activitiesand different routes that make up an industrial metabolism. After this, we present a hybrid model usingpredicate transition Petri nets. These nets are combined with systems of differential equations for theallocation of resources such as industrial equipment, and quantity of materials to be used. A predicatetransition Petri net with differential equations allows combining continuous and discrete aspects in asingle model. Continuous part represents a set of differential equations which indicates, the quantity ofresources (raw materials) to be used, maximizing production. Discrete part is indicated by the predicatetransition Petri net where industrial activity for the production of a certain product is represented.Finally, it is presented a case study including hybrid modeling and simulations in the Java programminglanguage for the analysis and validation of industrial metabolism modeling.

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SPECIAL SESSION 10. System Identification: Theory and Application in Aerospace,Biology, Engineering and Science

Organizer: Sunil Kukreja (NASA Dryden Flight Research Center, USA)

This special session is devoted to the theory, development of novel algorithms and applications to awide range of unique problems in aerospace, biology, engineering and science. The papers presentedin this session will introduce innovative techniques for unsolved problems in system identification andapplications to ongoing research problems in industry, government laboratories and universities.

Global nonlinear system identification using multivariate splines

Cornelis de Visser , Delft University of Technology, The Netherlands

The ability to identify accurate global models of complex nonlinear systems is highly desired in many fieldsof science and engineering. We present a powerful new method for global nonlinear model identificationbased on a recent type of multivariate spline, the multivariate simplex spline. Multivariate simplexsplines are defined on non-rectangular domains and can be used to accurately fit scattered nonlineardatasets in any number of dimensions. The simplex splines consist of piecewise defined, ordinarymultivariate polynomials with a predefined continuity between neighboring polynomial pieces. A newlinear regression model for the simplex splines was developed. This regression scheme allows for the useof standard parameter estimators, like generalized least squares and maximum likelihood estimators, forthe estimation of the polynomial coefficients of the splines. The new identification method was used toestimate a global 5-dimensional aerodynamic model for the aerodynamic force and moment coefficientsof the F-16 fighter aircraft based on a NASA wind tunnel dataset. The multivariate simplex spline basedaerodynamic model was validated and integrated in a non-linear F-16 simulator.

A Fuzzy Neural Network for Emitter Identification

Mohamad Hoseinyar, Mostafa Lotfi Forushani , Iran

In this article, a new effort is done to decrease the emitter identification (EID) procedure based on amultilayer vector neural network (VNN) and Fuzzy Logic via a supervised learning algorithm along withmore comprehensive input parameters of the received signal in a real-time manner. As a matter of fact,we define a new Pulse Descriptor Word (PDW) used for modern RWRs (Radar Warning Receivers) andprovide the signal recognition pattern using simultaneously processing parameters encompassing CareerFrequency (CF), Pulse Repetition Frequency (PRF), Pulse-Width (PW), Pulse Amplitude (PA), Angleof Arrival (AOA), Transmitter Power (TP) and Antenna Scan Rate (ASC). The input parameters areranked via applicable values so as to prioritize the learning algorithm of the VNN; consequently, theprocessing time would decrease to a certain extent compared to the same approaches and more reliableresults in coping with the problem of multi-threats ambiguity are gained.

Robust nonlinear estimation in case of noises of unknown statistics

Endre Nagy , Japan

The paper presents two different methods for nonlinear robust estimation. The frame of the estimationin both cases is nonlinear regression; however, they differ in the form of applied prediction: in one ofthe cases prediction is performed through optimum estimation of past noises, in the other case throughthe concept multi intersample linearization. To avoid consequences of model errors and not expectedlarge noises, robust estimator design is desirable. The paper first deals with the problem of design ofnon - robust estimators in case of noises of unknown statistics, then it shows how to make them robust.When prediction is made through optimum noise estimation, a particular problem is the great number ofvariables to determine. As a rule a long horizon is desirable, but the number of variables increases linearlywith extension of the horizon. However, when the dynamic optimization method optimized stochastictrajectory / output sequence tracking is used, only the noise and state components at the bottomof horizon and the parameter values for parameter estimation have to be considered as independentvariables; the others may be computed from optimization. The estimated noise components will be theones, which best fit the process, i.e. the ones at the values of which a suitable performance index has

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its minimum. In case of applying the principle multi intersample linearization, nonlinear evolution ofstates between sampling instants is followed in linear increments, computed with linear equations. Thenonlinear parameter estimator gives the value of estimated states, too, together with the parameterestimates. Several methods are presented in the paper for robustification.

Use of subjective analysis in flight safety analysis

Jozsef Rohacs, Budapest University of Technology and Economics, HungaryVladimir Alexandrovich Kasaynov , Kiev Aviation University, Ukraine

The central deterministic element of the aircraft conventional control systems is a subject that is anoperator - pilot. Such systems are called as active endogenous systems. The pilots make decision oncontrol depending on their situation awareness, knowledge, practice and skills. The pilots must makedecisions in situations characterized by a lack of information, human robust behaviors and their individualpossibilities. So, the decisions origin from analysis of pilot-subjects or subjective analysis.

Safety of aircraft control can be characterized with use of subjective analysis together the aircraft motionmodels. The general model of solving the control problems includes the passive (information, energy -like aircraft control system in its physical form) and active (physical, intellectual, psychophysiology, etc.behaviors of subjects) resources. The decision making is the right choosing the required results givingthe best (effectively, safety, etc.) solutions.

The proposed lecture investigates the flight safety with using the subjective analysis. There are used thestatistical hypotheses and a special chaotic attractor, namely a modified Loraenz attractor.

This lecture gives some results of the national and EU projects, as SafeFly and PPLANE and describenew models for investigation of the less-skilled pilots aspects.

CFD assisted analysis of Propeller theories

P.S. Sathish Krishnan , India

In this study, various propeller theories such as momentum theory, blade element theory (BET) andthe combined blade element-momentum theories (BEMT) are compared for finding the performanceparameters of an aircraft propeller operating at subsonic regime. The lift and drag coefficients ofpropeller airfoil sections are computed and validated against a standard airfoil. An analysis to check theindependency of the airfoil grid density and different turbulence models available in the CFD softwareare also done. Panel method is used to find the drag coefficient, whereas, Reynolds-averaged Navier-Stokes (RANS) equations are used to find the lift coefficient of the airfoil, due to better accuracies. Theresults of the propeller sections are finally integrated to get the performance of the entire propeller, afterconsidering the tip loss factor. The computed results are then compared with the experimental results. Aspecial condition of propeller undergoing yawed inflow condition has also been analyzed through propellertheories.

Frequency response analysis of an aircraft shell panel subject to geometrical imperfectionsand material properties variations, using a stochastic finite element approach

Francisco Scinocca, Airton NabarreteITA - Instituto Tecnologico de Aeronautica, Brazil

Frequency response analysis of an aircraft shell panel subject to geometrical imperfections and materialproperties using a probabilistic approach was evaluated. A stochastic finite element model was developedand implemented applying the Monte Carlo method to perform several spectral distributions andobtaining non-deterministic results. This work extends previous results obtained with the bucklinginstability analysis for an aircraft plate panel. In this research, the investigation considers the variationsfor shell panel geometry and material properties. In order to observe the major contributors, a sensitivityanalysis was performed. The modal results and the frequency response function variations are presented.

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FPGA Implementation of LMS-Based System Identification Core

Omid Sharifi Tehrani, Ebrahim Hosseini, Mohsen AshourianIslamic Azad University of Majlesi, Isfahan, Iran

A synthesizable FPGA-based system identification core is proposed. Adaptive filters are widely usedin different applications such as adaptive noise cancelation, prediction, equalization, inverse modelingand system identification. FIR adaptive filters are mostly used because of their low computation costsand their linear phase. Least mean squared algorithm (LMS) is used to train FIR adaptive filterweights. Advances in semiconductor technology especially in digital signal processors (DSP) and fieldprogrammable gate arrays (FPGA) with hundreds of mega hertz in speed, will allow digital designersto embed essential digital signal processing units in small chips. But designing a synthesizable core onan FPGA is not always as simple as DSP chips due to complexity and limitations of FPGAs. In thispaper we design a LMS-based FIR adaptive filter for system identification based on VHDL97 hardwaredescription language (HDL) and Xilinx SPARTAN3E (XC3S500E) which utilizes low resources and is highperformance and FPGA-brand independent so can be implemented on different FPGA brands (Xilinx,ALTERA, ACTEL). Simulations are done in MODELSIM and MATLAB and implementation is donewith Xilinx ISE. Finally, results are compared with otherpapers for better judgment.

System Identification using Interval Analysis

Erik-Jan van Kampen, Qi-Ping Chu, Bob MulderDelft University of Technology, The Netherlands

Interval analysis deals with interval numbers, which are an extension of the regular numbers. Intervalnumbers have their own set of arithmetic rules and operations, which are derived from the intervalinclusion theorem. Interval analysis was initially introduced in the 1960s for investigation of errorpropagation in dynamical systems. Later, it was shown that interval analysis is an excellent tool forsolving global nonlinear optimization problems.

In this paper the application of interval analysis for system identification in aerospace applications ispresented. System identification methods often rely on minimization of possibly nonlinear cost functionsand interval analysis can guarantee to find the global minimum of a cost function, thereby guaranteeingthe optimal identification of the system parameters.

Two aerospace related applications of interval identification are presented in this paper: firstly theidentification of the parameters in a multimodal human pilot perception model (visual and vestibular),and secondly the identification of all trim points for a generic nonlinear aircraft model.

For both applications the interval identification method produces better estimates of the parameters thanthe conventional gradient-based methods, which can get stuck in a local optimum.

It can be concluded that interval analysis is a promising tool for system identification.

Damping identification in a non-linear aeroelastic structure

Gareth A. Vio, UK

The study of nonlinearity in aircraft is increasingly becoming a necessity. The main driver behind theresearch is the fact that nonlinear aeroelastic systems display dynamic behaviour that cannot be modelledor predicted using linear methods. One area that has not received much attention is the field dampingidentification. Damping is present in every vibrating structure: a portion of the energy input by externalforces is always dissipated by damping mechanisms.

The common and simplest approach to identify damping in large degree-of-freedom systems is linearviscous damping. However, this approach is usually chosen for its mathematical convenience and canrepresent a valid approximation especially when damping is considered to be small.

In this paper an energy-based method is proposed to identify damping parameters from time historiesof responses to sets of single-frequency harmonic excitation. The method is intended to be practicallyapplicable to real structures and is able to identify the spatial location and value of damping. It willbe shown that if the system is undergoing Limit Cycle Oscillations, no external force is required forthe identification process. There is no need to know or to evaluate the mass and stiffness matrices.Spatial incompleteness can be successfully overcome by modal expansion of the measurements and modal

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incompleteness does not affect the method in the range of interest. The spatial expansion may be avoidedif the locations of the main damping energy sinks are known.

Steady State Problems in Financial Option Pricing

Dejun Xie , Jinan University, China

This paper considers a financial contract where the borrower makes a continuous payment to the lender ateach moment when the contract is in effect. We study the optimal financial decision from the borrower’spoint of view when he has the choice of early settlement of debt and when alternative market investmentis available. Assume market interest follows the CIR model, an infinite horizon problem is formulatedwith an unknown optimal early settlement interest rate to be determined together with the contractvalues at all interest rate levels. The well posedness of the problem is established. The analytical solutionto the problem is obtained using variational method. Finally, a finite element scheme is designed forfinding numerical solutions.

Flutter Prediction Analysis using Output Only Flight Test

Jie Zeng , Zona Technology Inc., USASunil L. Kukreja , NASA Dryden Flight Research Center, USA

In this paper, a flutter boundary prediction technique for an aeroeasltic/ aeroservoelastic structure isintroduced. This approach utilizes time series flight flutter test data to compute an accurate estimate ofthe flutter speed. The flutter boundary prediction tool discussed in this paper can be categorized intothree steps. (i) A signal preprocessing technique is introduced to compute the auto power spectrum whenonly responses from sensors can be measured due to a strong turbulence perturbation during flight fluttertest. (ii) A frequency domain system identification methodology combined with a stabilization diagramis implemented to extract elastic modes of the flexible structure. Accuracy of modes estimated in thesecond step directly affects the robustness of flutter prediction. (iii) A well known flutter prediction tool,the so-called Zimmerman-Weissenburger flutter margin, is used to perform flutter prediction. Applicationof the proposed flutter boundary prediction method to the Aeroelastic Test Wing (ATW) demonstratesthat it is an efficient tool for flutter boundary prediction of aeroelastic/aseroservoelastic structures.

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SPECIAL SESSION 11. Nuclear Power and Research Systems Modeling

Organizers: Antonella Lombardi Costa, Claubia Pereira (Universidade Federal de Minas Gerais, Brazil)

This special session will focus on simulation methodologies applied to Nuclear Engineering. The maintopics include neutronic, thermohydraulics and safety analysis.

Mathematical modelling of a system for brachytherapy

Wagner Leite Araujo, Tarcisio Passos Ribeiro CamposUniversidade Federal de Minas Gerais, Brazil

The present article describes the prototype design of a system that helps permanent brachytherapy anda software that constitute its methodology of operation. Bractron is a system that consists of a chamberand a multi degree-of-freedom mechanical arm whose extremity holds a device designed to aid radioactiveseeds implant on soft tissues. A laser device is placed under the plate that holds the template and isfree to perform 2D rotation. The templates are made with a fine set of holes in which needles can beintroduced. These holes draw a topologic spatial distribution on the region of the implant. Variousgeometrical patterns are defined for the purpose of setting up linear segments separated each othermaintaining a fixed distance after implantation. The software developed assigns an orientation to theplate and the mechanical arm fixes it on the space, after adjust and calibration is done by means of alaser pointer. Moreover, the software determines the needles length. The algorithm for this proposeswill be depicted. This mechanism allows the user to reproduce the implant protocol on the patient.An accurate adjustment of the seeds in the tumor region is expected with the use of this system forperforming brachytherapy procedures.

Design of a deuteron accelerator for a portable neutron generator

Wagner Leite Araujo, Tarcisio Passos Ribeiro CamposUniversidade Federal de Minas Gerais, Brazil

Neutron generators based on particle accelerators offer various advantages over the others two availablesources of neutrons, nuclear reactors and sealed sources of radioisotopes. As example the devices mobilityand the fact that radiation can be turned off are suitable features of those generators. The basic projectof a small size neutron generator includes the design of a modern and compact accelerator, a gas-controlreservoir, a plasma and ion source to generate and gather the ions in a beam shape, respectively; and atarget constituted of material loaded of deuterium hydrides on metal. This article explores basic conceptsof the portable neutron generators. It describes an analytical modeling to the electrodes positioning in theion extraction system in order to evaluate the maximum deuteron current. The result of the mathematicaldevelopment provided some parameters to the computer simulation of the deuteron transport in the ionextraction system and inside the particle accelerator device. Results from the analytical model and thesimulations are presented. As conclusion, on the final set up, the deuteron beam showed a low emissivity.Hence, experimental essays to validate the computational simulation shall be developed in the near future.

Comparative study of the neutron production by spallation and fusion reactions forsubcritical hybrid systems applications

Graiciany P. Barros, Claubia Pereira, Maria Auxiliadora Fortini Veloso , AntonellaLombardi Costa, Patrıcia A. L. ReisUniversidade Federal de Minas Gerais, Brazil

Subcritical hybrid nuclear systems consist in a sub-critical reactor core and an external neutron sourcefor the maintenance of the fission chain. Such an external source may be either spallation or fusionreactions, which are used, respectively, in accelerators driven systems (ADS) or fusion-fission systems. Inthis work the MCNPX 2.6.0 code is used to evaluate the neutron production taking into account severaltypes of targets commonly utilized in ADS. The concept of ADS combines a particle accelerator with asub-critical reactor core. The particles of accelerator are driven on a target for the neutron productionby spallation reactions. This paper provides the results regarding the neutron production by spallationreactions induced by protons with energy of 1 GeV in various targets materials. The MCNPX 2.6.0

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code is further used in the present study for the modeling of fusion reactions that occur in sub-criticalfusion-fission systems. The simulation results regarding the neutron production by spallation and fusionreactions as well, allows us to compare these two types of neutron sources for sub-critical systems. Theresults also enable us to verify differences between the energy spectrums of the neutrons emitted by eachtype of source.

GB - a linking code between MCNP and ORIGEN2.1 - DEN/UFMG version

Renan Cunha, Claubia Pereira, Daniel Campolina, Andre Cavatoni, Maria AuxiliadoraFortini VelosoUniversidade Federal de Minas Gerais, Brazil

The GB code is a linking code between Origen2.1 (Oak Ridge National Laboratory) and MCNP (LosAlamos National Laboratory). ORIGEN 2.1 is a deterministic code to solve Bateman equations that candetermine isotopic composition balance considering a given input power. The MCNP is a general-purpose,continuous-energy, generalized-geometry, time-dependent, coupled neutron/photon/electron Monte Carlotransport code. A first version of GB code described the behavior during the burn up only to 25 isotopes.In this version, the goal is to increase this isotope amount. The results were compared with the onesobtained with the MCNPX 2.6.0 code and were very similar.

Comparation between WIMSD-5B and MCNPX 2.6.0 codes simulating a PWR fuel element

Clarysson A. Mello da Silva, Claubia Pereira, Maria Auxiliadora Fortini Veloso, AntonellaLombardi CostaUniversidade Federal de Minas Gerais, Brazil

In this work, the codes WIMSD-5B and MCNPX 2.6.0 were used to study a cycle of a PWR reactor(ANGRA II). The same geometry was configured in both codes and two fuels type were studied: (1) UO2(2) (U-Pu-MAs)O2. It was evaluated the multiplication factor and the fuel composition at zero powerand during the burnup at full power. The main goal is evaluate the results obtained using a deterministiccode (WIMSD-5B) and a stochastic code (MCNPX 2.6.0).

Application of Nuclear Codes WIMSD-5B and MCNPX 2.6.0 to a Qualitative Evaluationof MHR (Modular Helium Reactor)

Clarysson A. Mello da Silva, Claubia Pereira, Maria Auxiliadora Fortini Veloso, AntonellaLombardi CostaUniversidade Federal de Minas Gerais, Brazil

Deterministic and stochastic nuclear codes have been used to simulate several reactor types around theworld. The deterministic code spent short time in the simulations but have the disadvantageous of thesimplification in the geometry. In the statistical codes, the geometry can be configured very detailed butit spent very time in the simulations. In this work, the deterministic code WIMSD-5B and the stochasticcode MCNPX 2.6.0 were used to simulate a representative core of a Modular Helium Reactor (MHR).Two geometries (cell and cluster) were evaluated in both codes to a qualitative study. In this way, theeffective multiplication factor (keff) during steady state and burnup were evaluated.

Evaluation of spallation source for neutrons production by Monte Carlo methods

Maurico Gilberti, Claubia Pereira, Maria Auxiliadora Fortini Veloso, Antonella LombardiCosta, Clarysson A. Mello da SilvaUniversidade Federal de Minas Gerais, Brazil

In the interaction of high energy protons with heavy materials and extended targets such as lead andtungsten, a high neutron fluxes is produced by bombarding target of the so-called spallation process.These neutrons can be used to drive a sub-critical nuclear assembly for energy generation and/or forthe transmutation of the long-lived nuclear waste isotopes. These nuclear assemblies are referred to asaccelerator driven systems (ADS).

Knowledge of the neutron yield in the spallation process and an understanding of the behavior of theseneutrons in the desired sub-critical nuclear assembly are the most important and determining factors in

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the design and operation of these systems.

This work uses the Los Alamos High Energy Transport Code (LAHET) into Monte Carlo code MCNPX2.6, which allows to simulate the interaction of wide variety of particles for calculations and simulationthe spallation reaction. Evaluating the cost of electric production of neutrons in the targets, flux e heatabsorbed, resulting of incidence of a high energy beam protons with heavy massive materials, in energyrange 200 Mev a 10 Gev. From this analysis it was possible to characterize and optimize the spallationreaction with a view to production neutrons for a sub-critical reactor.

Initial Development of a Coupling Methodology between Thermal-Hydraulic and NeutronKinetic Codes for Simulation of the IPR-R1 TRIGA Reactor

Claubia Pereira, Patrıcia A. Lima Reis, Antonella Lombardi Costa, Maria AuxiliadoraFortini Veloso, Clarysson A. Mello da SilvaUniversidade Federal de Minas Gerais, Brazil

The TRIGA IPR-R1 research reactor is located in the Nuclear Technology Development Center (CDTN),Brazil. It is a 250 kW, light water moderated and cooled, graphite-reflected, open pool type researchreactor. The development and the assessment of a RELAP5 model for the IPR-R1 TRIGA have beenvalidated for steady state and transient situations. Giving continuity to this study this paper presentsan initial idea of model for the IPR-R1 including the coupling between the RELAP5/MOD3.3 thermalhydraulic (TH) system code and the PARCS-2.4 3D neutron kinetic (NK) code. This technique consistsin incorporating three-dimensional (3D) neutron modeling of the reactor core into system codes mainly tosimulate transients that involve asymmetric core spatial power distributions and strong feedback effectsbetween neutronics and reactor thermal-hydraulics.

To perform such model it is necessary to supply adequate cross sections to the PARCS code. Therefore,the idea is to employ the two-dimensional (2D) transport calculations with the TRITON/NEWT modulefrom the SCALE6 package to produce the averaged cross-section libraries as a function of fuel temperatureand coolant temperature and density for PARCS calculations. The general scheme of the calculation ispresented in this work.

A preliminary neutronic evaluation and depletion study of HTR using WIMSD5 andMCNPX2.6.0 codes

Fabiano Cardoso Silva, Claubia Pereira, Clarysson A. Mello da Silva, Maria AuxiliadoraFortini Veloso, Antonella Lombardi CostaUniversidade Federal de Minas Gerais, Brazil

In this study, it will be analyzed two HTR concepts, VHTR and LS-VHTR, using reprocessed fuel comingfrom typical PWRs. Neutronic parameters obtained using the WIMSD5, and MCNPX2.6.0 codes areevaluated and compared. The results show good agreements in BOL but presents differences during theburnup.

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SPECIAL SESSION 12. Integral Equations and Their Applications

Organizers: Luis Castro, Stefan Samko (Portugal)

This section is devoted to integral equations and their applications to the areas of the general scope ofthe conference. Special emphasis is put in the analysis of properties of Fredholm, Volterra and singularintegral equations including equations generated by Wiener-Hopf, Toeplitz, Hankel and fractional orderintegral operators and their various applications. Talks presenting the use of integral equations in theareas of aerodynamics, fluid mechanics and wave diffraction are especially welcomed.

Fredholm-Stieltjes integral equations with (O-M)integral in time scales and applications

Luciano Barbanti , UNESP, BrazilBerenice Camargo Damasceno, MAT-FEIS-UNESP-Ilha Solteira, BrazilJose Manoel Balthazar , DEMAC-IGCE-UNESP-Rio Claro, Brazil

Time scale calculus is a unification of the theory of difference equations and the differential equations,unifying integral and differential calculus with the calculus of finite differences, offering a formalismfor studying hybrid discrete-continuous dynamical systems. Established in 1988 by S. Hilger, it hasapplications in any field that requires simultaneous modeling of discrete and continuous data. In thecontext of the time scale calculus we have the integral concerning the Riemann-Stieltjes (R-S) type,done by D.Mozyrska, E.Pawluszewicz and D.F.M.Torres in 2009. An essentially proper extension of the(R-S) one, named odd-meshed integral (O-M) was defined in 2010 by L.Barbanti, B.C.Damasceno andJ.M.Balthazar in general Banach spaces. Here we introduce the Fredholm-Stieltjes integral equations inthe context of the regulated functions (that is, having discontinuities only of the first kind) with operatorsof semi-variation that compose a dual structure when using the bilinear association (O-M). Later, resultsregarding periodicity and stability will be presented by using difference kind equations associated withthe Fredholm-Stieltjes general ones. We conclude this work with an application of the results in thespectral concentration problem as considered by D. Slepian, in signal processing.

Stability of Fredholm integral equations in the framework of generalized metric spaces

Luis Castro, Universidade de Aveiro, Aveiro, Portugal

Considerable attention has been recently given to the study of the Hyers-Ulam-Rassias stability offunctional equations. The concept of stability for a functional equation arises when we replace thefunctional equation by an inequality which acts as a perturbation of the equation. Thus, the stabilityquestion of functional equations is how do the solutions of the inequality differ from those of the givenfunctional equation. In the present talk, we will consider such question for certain Fredholm integralequations by using fixed point arguments in the framework of generalized metric spaces. In particular,conditions to ensure the Hyers-Ulam-Rassias stability of such equations will be obtained.

Splitting property for singular integral operators with a weighted shift

Edixon Rojas, Universidade de Aveiro, Aveiro, Portugal

We use operator relations and a polynomial collocation method to obtain information about the k-splitting property and kernel dimension of singular integral operators with a weighted Carleman shift,and having piecewise continuous functions as coefficients. Due to the increasing importance of this kind ofoperators in numerical applications, the order of convergence of the singular values of the correspondingapproximation method will be described in detail.

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Constructions of the approximate solutions of singular integral equations by using theTikhonov regularization and the theory of reproducing kernels

Saburou Saitoh, Universidade de Aveiro, Aveiro, Portugal

In this Conference, we first would like to introduce some fundamental theory for linear transforms in theframework of Hilbert spaces and its general applications with very concrete typical examples. Secondly,we introduce the construction of the approximate solutions of the equations by using the Tikhonovregularization and the theory of reproducing kernels. Thirdly, we will propose a new method that thesingular integral equations may be transformed to regular and discrete integral equations. The contentswill be given by the following key words: Reproducing kernel, Pythagorean theorem, inversion of the linearsystems, numerical analysis, inverse problem, inverse heat conduction, observation data, discretization,noise, error estimate, generalized inverse, Tikhonov regularization, singular integral equations with shift.

Integral equations of Wiener-Hopf type characterized by piecewise almost periodic elementsin Lebesgue spaces with weights

Anabela Silva, Universidade de Aveiro, Aveiro, Portugal

The talk will be devoted to the study of operators which characterize equations of Wiener-Hopf typehaving so-called Fourier symbols in the algebra of piecewise almost periodic elements. A main part ofthe talk will be addressed to identify conditions which ensure the Fredholm property of those operatorsin weighted Lebesgue spaces. In addition, the Fredholm index will be discussed as well. The equationsunder study are known to be useful in the modelling of various applied problems.

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MINISYMPOSIUM 1. Aeroelasticty

Organizers: Jiro Nakamichi (Japan), A.V. Balakrishnan (USA), Luiz Carlos Goes (Brazil)

Advanced aeroelasticity research progresses are demonstrated in this session, theoretically by CFD andexperimentally by up-to-date measurement techniques. Nonlinear phenomena due to coupling betweenstructures and aerodynamic forces are focused on in aeronautics. Other fields are also welcome, forexample, mechanical engineering, civil engineering and so on.

A bifurcation based approach to the analysis and control of flexible aircraft

Mohamed Nadjib Baghdadi , UK

Modern aircraft designs are continuously driven towards a light weight configuration due to performanceand mission requirements. Consequently, these aircraft are characterised with high structural displace-ments resulting in a reduction of the frequency margin between rigid-body and flexible modes. Strongdynamic coupling may occur in the presence of nonlinearities and in such cases, classical analysis methodsare unable to accurately identify the resulting nonlinear behaviour. In this paper, we demonstrate theeffect of dynamic coupling between rigid-body, flexible and controller modes on the stability and controlof flexible aircraft using a novel analysis approach based on the use of bifurcation analysis linked toclassical methods. The robustness of different control law design is also demonstrated.

Flutter solution techniques and their applications

Eulo Antonio Balvedi Jr., Roberto Gil Annes da SilvaInstituto Tecnologico de Aeronautica, Brazil

The main purpose of the flutter solution techniques is to evaluate the aeroelastic system stability by meansof eigenvalue analysis. We present a comparison among the principal methods available in literatureapplied to a typical section airfoil. Modern aeroelastic fields, like nonlinear analysis and active controldesign, require the system representation in time domain. Normally, the aerodynamic forces are availableonly in frequency domain with implicit dependency on the reduced frequency. Thus, a series of rationalfunctions are used to approximate airloads and the flutter solution techniques are carried out to evaluatethe accuracy. Moreover, a generalization of the Roger rational function approximation is presented.Theoretically, the transcendental characteristic of the flutter equations could lead to an unlimited numberof roots, in contrast to the algebraic equations. The existence and the physical meaning of these additionalroots are also discussed.

Transonic Aeroelasticity: Theoretical and Computational Challenges

Oddvar O. Bendiksen , University of California, Los Angeles, USA

Despite research extending over more than 50 years, we still do not have a good understanding of transonicflutter or other aeroelastic phenomena occurring near Mach 1. Transonic flutter prediction remains amongthe most challenging problems in aeroelasticity, both from a theoretical and a computational standpoint.It is also of considerable practical importance, as large subsonic transport aircraft cruise at transonic Machnumbers, and supersonic fighter aircraft must be capable of sustained operation near Mach 1, where theflutter margin often is at a minimum. In this lecture, we review unsteady transonic flow theory andcombine classical results from the nonlinear asymptotic theory with new results based on computationalfluid dynamics. Because transonic flows are inherently nonlinear even in the limit of small disturbances,a flutter analysis based on the classical Hopf bifurcation theory may not be able to predict all typesof transonic flutter, because no uniformly valid linearization may be possible. Examples of nonclassicalflutter behaviors observed in our time-marching simulations include delayed flutter and period-triplingflutter. The usefulness of transonic similarity principles in understanding flutter, divergence, and controlreversal phenomena are illustrated through practical examples.

Among the computational challenges, the fluid-structure coupling problem remains of central importance,and accurate and reliable flutter solutions cannot be obtained unless certain dynamic consistencyconditions are met. Advances in computational methods have made it feasible to study problemswith structural as well as fluid nonlinearities, and in some cases both must be considered in order to

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obtain the correct stability behavior. Recent results for a swept transport wing show that interactionsbetween aerodynamic and structural nonlinearities may lead to multiple limit cycles and counterintuitiveflutter behaviors. For example, decreasing the dynamic pressure at a fixed Mach number may becomedestabilizing, and flutter then occurs at altitude rather than at sea level.

Aeroelastic Behavior of a Wing with a Magnetorheological Hysteretic Model for theDamping

Kleber Augusto Lisboa Castao, Technological Institute of Aeronautics, BrazilLuiz Carlos Sandoval Goes, Technological Institute of Aeronautics, BrazilJose Manoel Balthazar , Sao Paulo State University - Campus Rio Claro

This paper shows the application of a hysteretic model for the Magnetorheological Damper (MRD) placedin the plunge degree-of-freedom of aeroelastic model of a wing. This hysteretic MRD model was developedby the researchers of the French Aerospace Lab. (ONERA) and describe, with a very good precision,the hysteretic behavior of the MRD. The aeroelastic model used in this paper do not have structuralnonlinearities, the only nonlinearities showed in the model, are in the unsteady flow equations and are thesame proposed by Theodorsen and Wagner in yours unsteady aerodynamics theory; and the nonlinearityintroduced by the hysteretic model used. The main objective of this paper is show the mathematicalmodeling of the problem and the equations that describes the aeroelastic response of our problem; andthe gain obtained with the introduction of this hysteretic model in the equations with respect to othermodels that do not show this behavior, through pictures that represents the time response and Phasediagrams. These pictures are obtained using flow velocities before and after the flutter velocity. Finally,an open-loop control was made to show the effect of the MRD in the aeroelastic behavior.

Dynamic responses and eigenanalysis of non-classical vibrating beams

Julio R. Claeyssen , Federal University of Rio Grande do Sul, Porto Alegre, BrazilTeresa Tsukazan , Federal University of Rio Grande do Sul, Porto Alegre, BrazilRosemaira D. Copetti , Federal University of Santa Maria, BrazilAntonio L. Bidel , Federal University of Santa Maria, Brazil

Elastic beams models with no-classical and non-linearities are of importance in aeroelasticity, control,atomic force microscope and carbon nanotubes. The eigenanalysis of such beams is formulated hereby using a basis generated by the initial value Green response of the corresponding modal equation.The system function and the impulse response are given in closed form. The non-linear models areapproximated by using the Galerkin method. We discuss forced responses of a damped cantilever Euler-Bernoulli beam with an attached damper at the free end and a Timoshenko beam subject to an axialforce and to an elastic append. The matrix frequency response of the beam and the distributed impulseresponse are approximate by using spectral matrices and time matrix functions. The dynamic responseis obtained through dual integral equations that involve time convolutions with the non-linear forcingand nonhomogeneous boundary conditions.

Application of Correction Methods for Aeroelastic Stability Analysis of Wing Structuresin Transonic Flow

Roberto Gil Annes da Silva, Ricardo Franco AmaralIAE/DCTA, Brazil

In spite of the recent development in computational aeroelasticity and CFD tools for unsteady flows,most of the aeroelastic stability analyses of wing structures in the transonic regime that are performedin engineering environment still rely on the application of correction methods to the aerodynamicloadings provided by linear aerodynamic theory based codes. However, there is lack of literature onthe capabilities and limitations of each method, just as on their adequacy to each wing design orphysical phenomenon involved. This paper presents a study on three different correction methods (NLRmethod - use of local Mach number; SKEM - Successive Kernel Expansion Method; Dau-Garner method),applied to three different wing structures (PAPA supercritical wing; AGARD 445.6 weakened wing; YXXairplane wing). Correlation between theoretical predictions and experiment indicates that distinct wingdesigns, dominated by dissimilar physical phenomena, require the use of different methods for accurateincorporation of the dominant nonlinear features to classical aeroelastic analysis tools.

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Aeroelastic Aircraft Landing Phase Simulation by Using Hybrid Modeling Approach

S. Ahmad Fazelzadeh, Hanif Sadat HoseiniShiraz University, Iran

In this paper flight simulation of aeroelastic aircraft in landing phase is presented. Hybrid state equationsof motion in terms of quasi-coordinates provide the framework for nonlinear simulation. The wings ofthe aircraft are assumed to be flexible and modeled as cantilever beams undergoing elastic bending andtorsion about their elastic axis. Unsteady aeroelastic forces are computed using strip theory and finitestate induced flow theory. An asymmetric landing condition in which the elastic aircraft encounters crosswind all the way to touchdown is considered. In order to design the landing controller, nonlinearly coupledequations of motion are linearized about trim condition and separated to two sets of decoupled equationsin which the elastic variables affect lateral-directional equations. An optimal-integral-feedforward controlscheme is exploited to realize the auto-landing while suppressing wind effects on flight path as well aselastic variables. The performance of the control system is examined through nonlinear simulation.

Critical and post-critical study of elastic aircraft wings subjected to non-conservative loads

S. Ahmad Fazelzadeh , Shiraz University, IranAbbas Mazidi , Yazd University, Iran

As a result of recent technological advances, the importance of stability investigations of elastic systemshas increased considerably. The development of modern mechanical and aeronautical engineering hasconsiderably widened the class of the load types requiring investigation. Non-conservative forces areassociated with theoretically interesting and, from the practical point of view, very important problemsin engineering. Of particular interest is the stability behavior of systems subject to non-conservativeexternal forces in connection with alternative manifestations instability like divergence (static instability)or flutter (dynamic instability). Mathematically such an analysis leads to non-self-adjoint boundary valueproblems.

In this study, the aeroelastic modeling and critical and post-critical behavior analysis of the wingshosting arbitrarily placed masses and subjected to arbitrarily placed follower forces and also, subjectedto general maneuvering conditions is considered. Furthermore, discussions about the combined effectsof the maneuver induced forces, external masses, and follower forces in conjunction with airflow on thecritical boundary and the post critical regions is presented.

Bending without normal stress case on an isotropic micropolar beam

Juan Alejandro Vazquez Feijoo, CIIDIR - Oax Instituto Politecnico Nacional, Mexico

Microcontinua contains the best elasticity theories for description of the behavior of certain materialsused for damping purposes such as the liquid crystal polymers that possesses large damping coefficientsat all operation frequencies. This is a theoretical work aimed to been able to understand better this kindof materials under the engineering point of view.

Based on the isotropic micropolar constitutive equations, the problem of a beam bearing an uneven forcefield is solved in the elastic range. It results in a case of a beam bending without the presence of normalstresses. The beam is simple clamped, a polynomial displacement field is assumed.

The force field is introduced into the constitutive equations as a microcouple per unit of volume. Theflexion is produced then by a shear stress produced because of the antisymmetric shear strain thatcharacteristic of the micropolar media.

Limit Cycle Oscillations of Very Flexible High-Aspect-Ratio Wings

Justin W. Jaworski , Air Force Research Laboratory, Wright-Patterson AFB, OHEarl H. Dowell , Duke University, USA

A nonlinear aeroelastic analysis is performed for a flexible high-aspect ratio wing representative of highaltitude long endurance (HALE) aircraft. Such aircraft are susceptible to aeroelastic response to gusts anddynamic instabilities such as flutter, which can lead to large-amplitude limit cycle oscillations. Structuralmotions are modeled by Hodges-Dowell beam theory, which includes leading-order nonlinear elasticcoupling. Aerodynamic forces are represented by the ONERA dynamic stall model with its coefficients

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calibrated to computational fluid dynamics (CFD) data as an alternative to wind tunnel test data. Timemarching computations of the coupled nonlinear beam and ONERA system highlight a number of featuresrelevant to the aeroelastic response of HALE aircraft, including the sensitivity of the flutter boundaryand limit cycle oscillations to aerodynamic CFD or test data, and the roles of structural nonlinearity andnonlinear aerodynamic stall in the dynamic stability of high-aspect-ratio wings.

Aeroservoelastic Flight Control Design For Military Aircraft Weapon System

Wolfgang Luber , Germany

The aim of the aeroservoelastic flight control system design for a military aircraft weapon system is mainlyto optimize for a given control law forward path and feedback structure the control law parameters likegains, phase advance filters and notch filters which cover all conditions in a full flight envelope forall envisaged aircraft configurations as external missiles, stores, bombs for all possible symmetric andasymmetric combinations. The control law gains and phase advanced filters which are derived during theoptimization process are considered to be Mach number and altitude dependent whereas the structurefilters i. e. notch filters may be constant or variables for all flight conditions and groups of the hugenumber of external store configurations.

The design strategy of the Flight Control System development and the procedure is described whichincludes the modelling of the coupled system of the flight dynamics, the structural dynamics ofrepresentative selected external stores, the actuators and sensors as well as the effects of the digitaladvanced flight control system.

Different external store examples are demonstrated which document the design procedure.

The design of FCS notch filters is based upon a model of the aircraft describing the coupled flight dynamic,flight control dynamics and in addition on the structural dynamic behaviour measured by on ground-and in flight structural coupling tests of a representative number of external store configurations. Thepaper outlines design procedures, design and clearance requirements, correlation tests and model updatefor on ground and in flight.

Contributions on smart structures and materials for applications on aeroelasticity and powerharvesting

Flavio D. Marques, Carlos De Marqui Jr., Volnei TitaSchool of Engineering of Sao Carlos, Brazil

The study of Active Fiber Composites (AFC) in aerospace applications has increased due to the potentialof manufacturing structures that satisfy high performance requirements needed in this area. Intelligentstructures can be designed as sensors and actuators for applications such as structure health monitoring,aeroelasticity and power harvesting. A model of AFC composed of lead zirconate titanate (PZT) andpolymeric matrix is studied. Numerical simulations using finite element method are presented, consideringthe AFC with different fiber arrangements. Piezoelectric composites can be classified into 14 types,depending on the nature of fiber distribution in the matrix, and divided in 3 groups: unimodal-periodic,bimodal-periodic or aperiodic, concerning the periodicity of fiber distribution and size of fiber cross-sectional area. Simulations of relevant cases of the first group are presented. The AFC is modeled ina micro-mechanical view through Representative Volume Element, appropriately chosen for each fiberarrangement with suitable boundary conditions applied to make the unit cell provide the entire behaviorof the piezoelectric composite. The material properties of each component of the composite are known,which permits to estimate the effective properties of the AFC by applying different loading cases to theunit cell. After that, the effective properties of PZT are used in aeroelasticity and power harvestingproblems.

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The influence of starting transients, aerodynamic definition and boundary conditions onelastic and viscoelastic panel and wing flutter

Craig G. Merrett, Harry H. HiltonUniversity of Illinois at Urbana-Champaign, USA

In past and present elastic and viscoelastic analyses, the starting transient contributions of the deforma-tions remain unresolved. Their important influence is due to the inherent memory and energy dissipationassociated viscoelastic material behavior. While mathematically acceptable, physically simple harmonicmotion (SHM), or any other function, cannot suddenly appear in their pristine states at the proverbialt = 0, nor can flight velocities instantaneously reach a finite value. The SHM is achieved in the deflectionsolution w(x, t) ∼ exp (d + ı ω) when the flutter velocities and frequencies reach eigenvalues at d = 0.

The SHM deflections must be preceded by a build-up during a preferably short time interval where d < 0and V < Vf . Thus the buildup and possible short time resultant transient responses are chosen to becontained in the elastic portion of the relaxation modulus curve and no additional memory effects willbe imposed on the SHM portion, provided any transient responses die out before relaxation begins.

Analytical studies are undertaken to ascertain the effects on elastic and viscoelastic flutter of (1) startingtransients due to changes in flight velocity, (2) boundary conditions and (3) unsteady aerodynamicforce definitions. Panel flutter is considered and varied boundary condition effects are also studied.In addition to the various unsteady aerodynamic theories, the effects due to the presence of spatialdeflection derivatives on pressure distributions are also examined. Necessary and sufficient conditions forthe onset of flutter in the form of simple harmonic motion are also formulated and evaluated.

Simulation results indicate that the inclusion of starting transients, deflection derivatives and distinctboundary conditions in the flutter analyses each produce significant increases and decreases in fluttervelocities and frequencies.

Reconstruction of Aerodynamic Loads Based on Inverse Analysis

Toshiya Nakamura, Hirotaka IgawaJapan Aerospace Exploration Agency, Japan

The data of operational load is quite useful in managing the structural integrity of an aerospace system.Identifying the aerodynamic load from finite number of measured strain data is not easy because theload distributes continuously on the structure surface which means the degree of freedom is infinity. Aflexible interpolation method for continuous load distribution is proposed in the present study and thefull-field continuous load is reconstructed from finite number of strain data using the conventional finiteelement method and pseudo-inverse matrix. The effects of measurement error are discussed where twomethods of rank reduction and Tikhonov-Phillips regularization are employed to improve the accuracyof the inverse analysis. It will be shown that both two methods are effective but the determination ofthe proper rank and the regularization parameter are not easy.

Aeroelastic Analysis of a Typical Section Using of Shape Memory Wire Actuator

Vinıcius Piccirillo, BrazilLuiz Carlos Sandoval Goes, ITA, BrazilJose Manoel Balthazar , UNESP, Brazil

Shape memory alloys (SMAs) provide a compact and effective actuation for a variety of mechanicalsystems. In this paper, a numerical simulation study of a three degree of- freedom airfoil, subjected totwo-dimensional incompressible inviscid flow using a SMA is presented. SMA wire actuators are used tocontrol the flap movement of a wing section. Through the thermo-mechanical constitutive equation ofthe SMA proposed by Brison, we simulate numerically the behavior of a double SMA wire actuator. TwoSMA actuators are used: one to move the flap up and the other to move the flap down. Through thenumerical results conducted in the present study, the behavior and characteristics of an SMA actuatorwith two SMA wires are shown the effectiveness of the SMA actuator. In conclusion, this paper showsthe feasibility of using SMA wire actuators for flap movement, with success.

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Research on Aileron Buzz Controling by Changing Boundary Layer Thickness

Masato Tamayama , Japan Aerospace Exploration Agency, Japan

Transonic unsteady aerodynamics on aileron buzz phenomenon has been studied in JAXA and somekinds of knowledge were acquired. If a shock wave oscillates on an aileron around its middle chord-wiselocation, the aileron acquires energy from surrounding flow and the possibility of aileron buzz occurrencewill increase. As another knowledge, an existence of boundary layer on an airfoil surface influences theextent of shock wave oscillation: From the unsteady CFD simulations with forced aileron oscillation,a shock wave in an inviscid flow oscillates at more backward location than the one in a viscid flow.Inspired from these results, one idea was raised that to control boundary layer thickness around theairfoil might suppress aileron buzz occurrence. This idea has been tried by conducting CFD simulationsanalyzing Navier-Stokes equations. As the method to control the boundary layer thickness, air blowingand breathing from the airfoil surface are selected. The airfoil model is a two dimensional wing ofNACA0003 airfoil cross-section with a 25% chord length aileron attached. In the conference, the resultsof these simulations will be presented.

Dynamic Instability of Viscoelastic Plate in Supersonic Flow

Botir Usmonov, Uzbekistan

The present work is investigating the aero-elastic instability of a viscoelastic plates under compressiveforces. The Bubnov-Galerkin method used to solve the governing equations. The quasi-steady aerody-namic loadings are determined using linear piston theory. The nonlinear integro-differential equation ofthe plate is transformed into a set of nonlinear algebraic equations through a Galerkin approach. Theresulting system of the equations is analytically solved. The influence of elastic and viscoelastic proper-ties and the compressive load characteristics of the plate material on the value of critical parameters arediscussed.

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MINISYMPOSIUM 2. Astrodynamics

Organizers: Vivian Gomes, Antonio Prado (INPE, Brazil)

This special session covers topics related to the orbital motion of artificial satellites, including spacecraftsthat are orbiting the Earth, as well as the ones that go outside the vicinity of the Earth. The main topicsinclude orbital maneuvers but also orbit determination and propagation, effects of perturbative forces,atittude determination and propagation, chaos and planetary motion.

Escape Basins and Chaotic Saddles in the Planar Circular Restricted Three-Body Problemfor the Earth-Moon System

Sheila Crisley de Assis, Maisa de Oliveira TerraITA, Brazil

The goal of the present paper is to investigate the escape basins and the associated fractal invariantsets in the context of the planar circular restricted three-body problem (PCRTBP) for the earth-moonsystem. These exit basins and respective boundaries are intimately related with transport processesbetween the realms defined around each primary body, which can be important both in the contextof space mission designs and in the dynamical investigation of natural systems. Given a value of thePCRTBP integral of motion, one of the five possible Hill regions (accessible regions) and respectivetransport channels are established. Considering an initial condition set around one of the two primaries,exits are defined according with the opened necks around the collinear equilibria. Escape basins areobtained for two cases: considering the primaries as punctual mass and treating them as finite bodieswith the inclusion of their mean radii. These escape basins can reveal the existence of regular and fractalbasin boundaries, associated with chaotic saddle and its invariant manifolds. The qualitative dynamicalinvestigation through Poincare sections is performed in order to elucidate the obtained results.

Artificial Satellites: Orbital Perturbations

Rodolpho Vilhena de Moraes, UNESP/FEG, Brazil

A brief comment about some scientific applications of artificial satellites is presented showing the necessityof precise orbital determination for the success of the mission.

The main orbital perturbations: geopotential, atmospheric drag, tides, solar radiation pressure (directand reflected), electric drag, third body perturbation, are described. Resonance’s effects are discussed.The equations describing the motion of artificial satellites are given considering conservative and non-conservative perturbations. Some original analytical solutions for the equations of motion are presented.Applications are done for real and hypothetical satellites. Orders of magnitudes for the perturbationsare exhibited. Simulations show that resonance can produce important long period terms in the timevariation of the orbital elements. For intervals shorter than one fourth of the period of the resonant termthis could be regarded as a secular variation.

Gravitational Capture under the Restricted Three-Body Problem

Alexandre Lacerda Machuy Francisco, National Institute for Space Research - INPE, BrazilAntonio F.B.A. Prado, National Institute for Space Research - INPE, BrazilTeresinha de Jesus Stuchi , Universidade Federal do Rio de Janeiro, Brazil

The objective of the present paper is to study the ballistic gravitational capture in a dynamical modelthat has the presence of three bodies. A temporary gravitational capture happens when a spacecraft (orany particle with negligible mass) changes from a hyperbolic orbit around of a heavenly body to an ellipticorbit without the use of any propulsive force in the system. The force responsible for this change in theorbit of the spacecraft is of the gravitational nature. In was made a numerical study of the gravitationalcapture. The mathematical model used to analyze this phenomenon is the restricted problem of threebodies. We used Neptune and Triton as the two primary bodies. This phenomenon is explained in termsof the integration of the perturbing forces with respect to time. Numerical simulations are performedto show the trajectories of the spacecraft. There are also graphs that have the purpose to obtain the

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minimum consumption of fuel.

Using extended Kalman filter and least squares method for spacecraft attitude estimation

Roberta Veloso Garcia, National Institute for Space Research - INPE, BrazilHelio Koiti Kuga, National Institute for Space Research - INPE, BrazilM.C. Zanardi , Faculdade de Engenharia de Guaratingueta - FEG / UNESP, Brazil

The purpose of this paper is to compare the attitude estimation results between the least squares methodand the extended Kalman filter of an artificial satellite using real data of on-board attitude sensors.

The attitude of satellite represents how the satellite is oriented in the space. The accuracy in theattitude determination impacts directly on the performance of the attitude control system and affectsthe interpretation of information obtained from the experimental payloads of the satellite.

There are many methods to determine the attitude of a satellite. The choice of the method depends on thetype of application, of the mission, and on the requirements to be satisfied, such as the real time processingand the precision. However, independent of the method chosen, a minimum set of measurements suppliedby sensors on board the satellite are needed.

Among estimations methods applied for nonlinear problems, two of them are traditionally picked out forattitude estimation: the least squares method and the extended Kalman filter. The first is an alternativefor the estimation criterion of minimum variance, and yields instantaneous attitude determination, byprocessing the attitude sensors data (horizon and Sun sensors). However, the extended Kalman filtercarries out the processing of such sensors measurements in real time, and its formulation accounts forthe dynamic noise of the states, yielding a kinematic attitude determination, using additionally the gyromeasurements. It is observed that the averages of the values of the attitude estimated by the least squaresmethod are very close to the results for the extended Kalman filter. In this way it can be concluded thatthe algorithm of the extended Kalman filter converges to the least squares solution when fed with realdata supplied by the attitude sensors.

The FEFF Methodology for Proximity Maneuvering Spacecraft Formations

Laura Garcia-Taberner , Universitat de Girona, SpainJosep J. Masdemont , Universitat Politecnica de Catalunya, Barcelona, Spain

To have a robust and efficient optimal control technique avoiding possible collision risks is a mainrequirement in the maneuvers involving proximity of spacecrafts. In this work we develop a methodologyto compute optimal reconfigurations for a formation of satellites in a given fixed time interval using asystematic approach.

The FEFF methodology (Finite Elements for Formation Flight) models the trajectories of the satellitesusing finite elements in time. The problem is essentially set up as an optimal control problem, wherethe objective function is directly related to the delta-v expenditure of the satellites in their controlledtrajectories. Geometry of controls depending on the orientation of the thrusters and weighted trajectoriescan also be considered, when for instance, fuel resources or other particular satellite conditions, are inbetter or worse state than in others.

Once formulated, the problem is solved via a variational numerical method where collision avoidanceand other types of constraints are introduced in a natural way. During the procedure mutual distancesbetween spacecraft are checked and possible collisions are avoided.

In this presentation we apply and study the costs, in terms of delta-v, of the FEFF methodology forreconfiguration of formations in the vicinity of libration points.

The close approach between a planet and a cloud of particles

Vivian M. Gomes, Antonio F.B.A. PradoNational Institute for Space Research - INPE, Brazil

The idea of the present paper is to study the swing-by maneuver between one of the planets of the SolarSystem and a cloud of particles. This is what happens when a fragmented comet crosses the orbit ofa planet like Jupiter, Saturn, etc. We used the dynamical system that is formed by two main bodies(the Sun and one of the planets of the Solar System) and we assumed that they are in circular orbits

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around their center of mass and a cloud of particles is moving under the gravitational attraction of thesetwo primaries. The motion is assumed to be planar for all the particles and the dynamics given by the”patched-conic” approximation is used, which means that a series of two-body problems are used togenerate analytical equations that describe the problem. The main objective is to understand the changeof the orbit of this cloud of particles after the close approach with the planet. It is assumed that all theparticles that belong to the cloud have semi-major axis a ± da and eccentricity e ± de before the closeapproach with the planet. It is desired to known those values after the close approach. In particular, wewill study the effects of the periapsis distance in this maneuver.

Maneuvers control of a spacecraft through aerodynamics changes under the effects of theupper atmosphere

Willer Gomes, Evandro Marconi Rocco, Valdemir CarraraNational Institute for Space Research - INPE, Brazil

In several missions it is necessary to perform orbital maneuvers. Aeroassisted maneuvers using atmo-spheric forces can be used to change the trajectory and velocity of a spacecraft. Several studies in this areahave indicated that a significant fuel reduction can be achieved using aeroassisted maneuvers rather thanfully propulsive maneuvers. Therefore, this allows an increase in the payload capacity of the vehicle. Aspacecraft equipped with controllable aerodynamic plates have the ability to change their projected areaand hence the aerodynamic forces suffered. In this context, the studies about the feasibility and efficiencyof the spacecraft control system are very important. Therefore, this paper presents a simulation modelwhich considers a closed-loop control system used to control the angle of attack of the aerodynamicplates during aeroassisted maneuver in the upper atmosphere. The proposed technique was validatedthrough numerical simulations. The results showed the difference between the proposed maneuver and apropulsive one.

Evaluation of the Fuel Consumption in Orbital Maneuvers with Time and Position Con-straints

Thais Carneiro Oliveira, Evandro Marconi Rocco, Antonio F.B.A. PradoNational Institute for Space Research - INPE, Brazil

The main goal of this work is to evaluate the total fuel consumption in a spacecraft transfer orbitprocedure, using two-impulsive orbital maneuvers between elliptical orbits, with a time limit to performthe transfer, considering specifics positions on the initial and final orbits to start and finish the transfer.This is known as Lambert’s problem. The problem consists of calculating the transfer orbit that connectsa point on the initial orbit to another point on the final orbit in a certain amount of time. To find thesolution, an algorithm using a numerical method can be used. Therefore, the contribution of this workis the solution of the problem using universal variables in a algorithm which uses two computed searchstages (rough and fine search). This approach allows achieving accurate results with a low CPU effort.This algorithm was implemented to provide a maneuver simulator capable to assist in the spacecraftmission analysis, seeking for the best combination of time and fuel consumption.

Analysis of disturbing effects in the dynamical model of orbit determination using GPSPaula C.P.M. Pardal (1), Rodolpho Vilhena de Moraes (1,2), Helio Koiti Kuga (1)(1) National Institute for Space Research - INPE, Brazil(2) UNESP - Univ. Estadual Paulista, Brazil

The problem of orbit determination consists essentially of estimating parameters values that completelyspecify the body trajectory in the space, processing a set of information (measurements) from this body.Such observations can be collected through a tracking network on Earth or through sensors.

The Global Positioning System (GPS) is a powerful and low cost means allowing the computation of orbitsfor artificial Earth satellites. The T/P satellite is an example of using this system for space positioning.

The orbit determination of artificial satellites is a nonlinear problem in which the disturbing forces are noteasily modeled, like geopotential and direct solar radiation pressure. Through an onboard GPS receiverit is possible to obtain measurements (pseudo-ranges) that can be used to estimate the state of the orbit.

The main target here is to determine the orbit of an artificial satellite, using signals of the GPS

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constellation and least squares algorithms as a method of estimation, with the aim of improvingthe performance of the orbits estimation process and, at the same time, minimizing the procedurecomputational cost. Perturbations up to high degree and order for the geopotential coefficients, directsolar radiation pressure, and sun-moon gravitational attraction were taken into account. It was alsoconsidered the position of the GPS antenna on the satellite body that, lately, consists of the influenceof the satellite attitude motion in the orbit determination process. Pseudo-range measurements werecorrected from ionospheric effects, although the accuracy on orbit determination is not expressive. Anapplication has been done, using real data from the Topex/Poseidon satellite, whose ephemeris are freelyavailable at Internet. The best accuracy obtained in position is shown for short period (2 hours) and forlong period (24 hours) orbit determination. In both cases, the perturbations mentioned before were takeninto consideration and the analysis occurred without selective availability on the signals measurements.

Precise predicted extended ephemeris solution for GPS

Rajendra P. Prasad , Space Mechanics and Control Division - DMC, INPE, BrazilHelio Koiti Kuga , Space Mechanics and Control Division - DMC, INPE, BrazilNagaraj Dixit , Texas Instruments Inc. - Bangalore, India

After 3 decades of increasingly widespread use, Satellite navigation-based services have changed signifi-cantly. Global navigation satellite systems like GPS, GLONASS or the future systems like Galileo requireprecise orbit and clock estimates in order to provide high positioning performance. New technology en-ablers such as assisted GPS (A-GPS) the use of massively parallel correlation and the application ofadvanced positioning techniques have significantly enhanced the time-to-first-fix (TTFF) and sensitivityof todays receivers. A-GPS significantly improves GPS performance by taking advantage of an exist-ing communications link to the device, whether wireless or via cradle, to download ”assistance data”,essentially a copy of what the GPS satellites are actually transmitting. This helps bypass the bulk ofthe initial GPS signal acquisition delays, thereby yielding faster TTFF, lower battery drain and highersensitivity. The time taken to decode the ephemeris from the satellite signal forms a significant part ofthe TTFF. This time ranges from about 18-30 seconds at high signal levels ( 140dBm), to several minutesat low signal levels ( 148dBm). During very low signal levels scenario, decoding the ephemeris from thesatellite signal may not be possible at all times. Providing the receiver with ephemeris from other meansis thus important, as it bypasses the need for decoding the ephemeris from the satellite signal. This will(a) significantly decrease the TTFF, and (b) allow the receiver to give position fixes even with the satel-lites at very low signal levels. Traditional approaches to provide the receiver with ephemeris assistancehave involved downloading the satellite ephemeris. However, this approach requires that the receiverhas real time connectivity via either a mobile phone network or the internet. Extended Ephemeris is akey component of Assisted GPS (A-GPS) which enables GPS platforms to operate where direct satellitedata is unavailable. The innovative implementation is developed in-house to allow for transmission overa multitude of communication media to deliver maximum availability and unparalleled accuracy. In thisapproach the receiver has algorithm capable of predicting extended ephemeris for a period of time (typ-ically 3 to 6 days), with an availability of broadcast ephemeris which aids to predict precise ephemerisfor the above duration. In this context precise Satellite orbit prediction molding was carried out and thesoftware is designed on the server based approach initially. Ultimately the software shall be ported onto a chip. The initial results are very encouraging and the prediction accuracy in 6 days was betterthan 60m, which meets the requirements. These server based solutions further lower TTFF to the 6-15srange. The paper describes the need aspect, the orbit prediction modeling and description of chip basedarchitecture along with typical case studies.

Internal loading distribution in a statically loaded ball

Mario Cesar Ricci , National Institute for Space Research - INPE, Brazil

A new, rapidly convergent, numerical procedure for internal loading distribution computation in staticallyloaded, single-row, angular-contact ball bearings, subjected to a known combined radial, thrust, andmoment load, is used to find the load distribution differences between a loaded unfitted bearing atroom temperature, and the same loaded bearing with interference fits which might experience radialtemperature gradients between inner and outer rings. For each step of the procedure it is required theiterative solution of Z + 3 simultaneous nonlinear equations - where Z is the number of the balls - toyield exact solution for axial, radial, and angular deflections, and contact angles. Numerical results are

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shown for a 218 angular-contact ball bearing.

Closed Loop Control System Applied to Transfer Maneuvers Using Continuous Thrust

Evandro Marconi Rocco, Eliel Wellington Marcelino, Antonio F,B.A. PradoNational Institute for Space Research - INPE, Brazil

This work considers the problem of controlling the trajectory during orbital transfer maneuvers, usinga propulsive system capable of applying continuous thrust for a long period of time. Some non-idealityof the thrusters and their effects on the control system during the transfer orbit were analyzed. Itwas considered a control system in closed loop and low-thrust propulsion with high specific impulse.Through some simulations, it was possible to analyzed the deviation in the trajectory and evaluate thecontrol system. Two cases were considered: velocity increment applied tangentially to the trajectory,with and without errors in the propulsion system. Therefore, a gradual increase of the semi-major axiswas obtained. To validate the simulator, the results were compared with the literature. The resultsshowed that the use of continuous thrust might present advantages for some space missions. It was alsoconfirmed the requirement of a closed loop control system for these missions.

Optimization of Low-Thrust Spiral Transfers between Two Given Orbits

Alexander A. Sukhanov , Space Research Institute (IKI) of the Russian Academy of Sciences, Russia

Power-limited low-thrust transfers between two given orbits in a strong gravity field are considered. Ina general case such transfers are spiral, i.e. they include many revolutions around the attracting center,what makes the transfer optimization a difficult task. A simple and effective method for opimization ofthese multi-revolution transfers is suggested. This method is based on the linearization of the motionnear reference Keplerian orbits and use of the Pontryagins maximum principle for the linearized problem.The suggested method allows calculation of three types of transfers, such as follows:

• transfers from a given state vector to a given orbit with optimal entry position into the final orbit;

• transfers from a given orbit to a given state vector and obtaining an optimal start position fromthe initial orbit;

• transfers between two given orbits and obtaining optimal initial and final positions of the transfertrajectory. All of the three transfer types are considered.

However, linear approach does not make it possible obtaining a global optimum. A second-orderapproximation is also considered and the respective solution of the problem is given.

The suggested method demonstrates good convergence in the cases of a big number of revolutions anda big difference between the initial and final orbits in size, inclination and orbit types. The method isalso applicable if there is a constraint on thrust direction and for the case of partly given final orbit; forexample, when only energy or semi-major axis and eccentricity of the final orbit are specified.

Numerical examples showing the high effectiveness and the wide applicability of the suggested methodare given. Linear and second-order solutions are compared.

Optimal Low-Thrust Limited-Power Transfers in a Non-central Gravity Field - TransfersBetween Arbitrary Orbits

Carlos Silveira , EMBRAER, BrazilSandro da Silva Fernandes, ITA, Brazil

This paper presents a study of optimal low-thrust limited-power trajectories in a non-central gravityfield which includes the oblateness of the Earth (i.e., includes the second zonal harmonic J2 in thegravitational potential). Initially, the space trajectories optimization problem is expressed in Mayerform, with Cartesian elements - position and velocity vectors - as state variables. The concepts ofOptimum Control Theory, namely, the Pontryagin Maximum Principle, a re then applied to this problem,providing a maximum Hamiltonian. The resulting formulation is afterwards modified by introducing aset of suitable orbital elements through a canonical transformation. A version of the Hori method - aperturbation technique based on Lie series - specific to semigeneralized canonical systems is then applied to

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this new formulation, resulting in an averaged maximum Hamiltonian, which characterizes long durationtransfers. A numerical solution for this problem is obtained for some transfers between arbitrary ellipticalorbits, employing an algorithm based on the second variation method (neighboring extremals) to solvethe two-point boundary value problem associated with the averaged Hamiltonian. The results obtainedare compared to those provided by the same method for the undisturbed problem (central gravity field),in order to analyze the influence of J2 in the transfers considered.

Innovative Dynamical Analysis of the Algorithmic Weak Stability Boundary

Maisa de Oliveira Terra, Priscilla Andressa de Sousa SilvaITA, Brazil

In this contribution, we rebuilt and analyze the Weak Stability Boundary (WSB) algorithmic definitionwith the inclusion of the moon and earth collisional sets and the explicit construction and subclassificationof the associated unstable set generated by this definition. The WSB concept associated to lunar ballisticcapture in the final portion of the earth-moon transfer orbit was introduced by E. Belbruno (1987and beyond) in the context of alternative techniques proposed to design low energy transfer orbits,by exploiting the intrinsic nonlinear dynamics of three and four body problems in a more natural way.With the aim of clarifying the applicability of the WSB in realistic mission design, a refined investigationof the several possible stable-unstable transitions is performed by considering elucidative criteria basedon three-body problem dynamical elements.

A comparison of gravity-assisted maneuvers in different planets to optimize interplanetarymissions

Flaviane Venditti, National Institute for Space Research - INPE, BrazilEvandro Marconi Rocco, National Institute for Space Research - INPE, BrazilAntonio F.B.A. Prado, National Institute for Space Research - INPE, BrazilAlexander A. Sukhanov , Space Research Institute (IKI) of the Russian Academy of Sciences, Russia

This work presents a comparison of different possibilities of gravity-assisted maneuvers on Mars, Jupiterand Saturn. The problem involving interplanetary trajectories can be formulated as a multi-objectiveproblem due to the nature of the mission. The optimization problem is solved using a methodologybased on the Non Inferiority Criterion (Pareto, 1909) and the Smallest Loss Criterion (Rocco et al.2003), where all objectives are considered simultaneously, without reducing the problem to the case ofoptimizing a single objective. The three objectives to be optimized are: fuel consumption, in otherwords, the DV; the duration of the mission; and the waiting time on Earth for launch, The trajectory isdivided into three parts, where the first and the last one are inside the sphere of influence of a planet,and the intermediate part is a heliocentric phase. This methodology is called Patched Conics. Severalsimulations were obtained using the Transfer Trajectory Design Programs (Sukhanov, 2004), analyzingthe best way to reach Pluto using gravity-assisted maneuvers. For this purpose a few planets were testedwith different combinations of dates for the maneuvers, launch and arriving windows. Then a conclusionof which planet is best suited for the chosen dates was obtained.

References:

Pareto, V. Manuale di economia politica com una introduzione alla scienza sociele. Milao: Societa‘Editrice Libraria, 1909.

Rocco, E. M. Manutencao orbital de constelaco es simetricas de satelites utilizando manobras impulsivasotimas com vınculo de tempo. Sao Jose dos Campos. 178 p. Tese (Doutorado em Engenharia e TecnologiaEspaciais / Mecanica Espacial e Controle) - Instituto Nacional de Pesquisas Espaciais, 2002.

Sukhanov, A, ”Users Guide for Transfer Trajectory Design Programs”. Manual tecnico, IKI, Moscou,Rssia, 27pp, 2004.

Venditti, F.; Rocco, E.M.; Prado, A.F.B.A.; Sukhanov, A., ”Gravity-Assisted Maneuvers Applied in theMultiobjective Optimization of Interplanetary Trajectories”. IAC 2009- 60th International AstronauticalCongress. Daejeon, Republic of Korea, October 12-16, 2010.

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MINISYMPOSIUM 3. Spacecraft Attitude Dynamics and Control

Organizer: Luiz Carlos DeSouza (INPE, Brazil)

Space mission success depends on adequate dynamics investigation and control system performance.Besides, future advanced space missions will involve control system design technique with novel archi-tectures, technologies, and algorithms to solve the Spacecraft Attitude Dynamics and Control Systemproblems. This session is open to papers with topics ranging from dynamics theoretical formulations toinnovative control systems design that will advance the state of the art, reduce the cost of applications,and speed the convergence to hardware, numerical, or design trade solutions.

Combined Attitude and Solar Tracking (CAST) System for Spacecraft

Mohd Faizal Allaudin, Renuganth VaratharajooUniversity Putra Malaysia

The spacecraft solar panel Sun tracking mechanism is utilized as an attitude control system. This isdone by manipulating the tracking control of both the solar panels along the spacecraft pitch axis togenerate torque in order to counter-act the external disturbance along this axis. The two solar panels arerotated at different speeds in order to generate the required torque. Matlab Simulink was used to evaluatethe system where the inputs are Sun tracking function and attitude reference while the outputs are thesolar panel rotation angle due to Sun tracking and spacecrafts pitch attitude. The governing equationstogether with the onboard attitude and solar tracking architecture are established. The architecture is thenumerically tested. The simulation results are discussed especially from the attitude control standpoint.The integrated system complies very well with the reference mission requirement.

Fly-by guidance approach for rendezvous and capture of non-cooperating targets

Gilberto Arantes Jr., University of Bremen, GermanyAnanth Komanduri , University of Bremen, GermanyDaniel Bindel , University of Bremen, GermanyLuiz de Siqueira Martins-Filho, Universidade Federal do ABC, Brazil

Non-cooperative satellites include a vast category of spacecrafts which have lost their control oroperational capabilities due to erroneous orbit injection or/and component failure. Space debris andNear-Earth Objects (NEO) belong to those class of non-cooperating targets as well. Space missions likeOrbital Express launched in 2007 open up a new era in space - on-orbit servicing - which is definedby repair, retrieval, maintenance, and rescue of satellites on orbit. The development of technologiesfor autonomous rendezvous and docking plays an important role for the mitigation of space debrisproblem. A fundamental challenge of on-orbit servicing is the safe approaching of the spacecraft to anunstable/uncontrollable target. In this case the target satellite is not able to cooperate with the servicesatellite during the rendezvous and capture phases. This work focuses on the guidance functions that canhandle a satellite possibly rotating and lacking the ability to maintain its docking port or grasping fixturealigned with the on-orbit servicing requirements. The viability and suitability of the fly-by approach aretested through numerical simulations and preliminary sensibility analysis. The results show that thefly-by method can be an interesting guidance alternative for rendezvous and capture of non-cooperatingtargets.

Attitude Synchronization for swarms of Pico-Satellites using Consensus Algorithms

Sid Ahmed Attia , Ariel PratomoTU-Berlin, Germany

In this paper, we consider the problem of attitude synchronization for a swarm of pico-satellites. Theapproach proposed consists of two distinct stages. The first stage consists in using a feedback linearizationtechnique that allows transformation of the satellite equations of motion to a set of decoupled doubleintegrator dynamics. The second stage consists then in applying consensus algorithms for the linearizeddynamics. An exchange of information between the different pico-satellites to synchronize the attitudesis carried out at this level. The obtained law is thus formulated for the transformed system. Inverse

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transform is then applied to extract the real control inputs to the pico-satellites. Simulation results forthe BeeSat platform are included for both cases of ideal communication links and for links with packetloss and compared to state of the art approaches.

Integer ambiguity resolution in attitude determination using GPS measurements

Leandro Baroni , Helio Koiti KugaNational Institute for Space Research - INPE, Brazil

If three or more GPS antennas are mounted properly on a platform and difference of GPS signalsmeasurements are collected simultaneously, the baselines vectors between antennas can be determined andthe platform orientation defined by these vectors can be calculated. Thus, the prerequisite for attitudedetermination technique based on GPS is to calculate baselines between antennas. For accurate attitudesolutions can be obtained, carrier phase double differences are used as main type of measurements,including all independent combinations of antenna positions. Baselines between antennas must bedetermined in millimeter level of accuracy. The use of carrier phase measurements leads to the problem todetermine precisely the ambiguous integer number of cycles in the initial carrier phase (integer ambiguity).To increase confidence and accelerate the process by limiting the search space, three types of restrictionscan be established from the knowledge of antenna system fixed geometry. In this work was implementedand tested algorithms for ambiguity resolution allowing accurate real-time attitude determination usingmeasurements given by GPS receivers in the uncoupled form, which is, estimating baselines independentlyfrom each other, and in coupled form, which the platform orientation (Euler angles) is obtained throughprocessing all baselines. The results showed that LSAST method performance is similar to LAMBDA asthe number of epochs which are necessary to resolve ambiguities, but with processing time significantlyhigher. The final result accuracy was similar for both methods, better than 0.1 to 0.2, when consideredbaselines decoupled form.

Fine maneuver control for spacecraft simulator by reaction wheels using sliding mode speedcontroller

Mohammad Hossein Beheshti, Iran

This work addresses the attitude control of a triaxial spacecraft simulator by applying variable structurecontrol theory to design a set of proper speed controllers for reaction wheels in presence of unknowndisturbances and parametric uncertainties. The controller goal is to change the rotational speed ofreaction wheels to adjust the spacecraft simulator in desired course. The mathematical models of satellitesimulator consisting of a rigid base body and three reaction wheels as actuator are developed. Variablestructure control theory is then applied to synthesize a set of linear controllers that deals with bothnonlinearities in the equations and disturbance sources. Based upon sliding mode control theory, thisspeed controller is independent from static friction model of reaction wheels, so that the difficulty ofgetting an accurate model is avoided. The simulated model response to wheel speed shows that thesliding mode speed controller is effective and the attitude error could be reduced in comparison to PIDspeed controller.

Modeling a Reaction Wheel

Valdemir Carrara, National Institute for Space Research - INPE, Brazil

It is well known that reaction wheels, that have special role in satellite attitude control, present a non-linear behavior in low angular velocities, due to static and Coulomb friction torques. In general thesenon-linearities are neglected by the control system, as the control law can easily treat then as an ordinaryerror. Therefore attitude errors tend to increase during the zero crossing of the wheels angular velocity.Solutions have been implemented in onboard computers, like robust control, or the use of distinct gainsin low angular velocities to minimize the error, or to keep the wheel operating in only one sense, to avoidzero crossing. This paper aims to model the non-linear, zero crossing behavior of a reaction wheel, andto use this mathematical model to derive the control action, i.e. the electrical current imparted to thewheel motor. To do so, a 0.65 Nm wheel was tested in a lab environment to collect the necessary data toobtain the parameters of the model. The new control model was then tested in an air-bearing table andthe results were compared to the normal PID controller. Results showed that the new model significantlyaffected both the error and control performance.

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Reduced order attitude dynamic model of a satellite with reaction wheels and appendages

Valdemir Carrara, National Institute for Space Research - INPE, Brazil

Satellite attitude simulation is largely employed during planning, design, integration, test and operation ofa space mission. Qualification tests of the attitude control subsystem require substantial modeling effortin order to assure simulator fidelity. Nevertheless, equations of motion based in rigid body assumptionare still used due to its simplicity and reliability. Body flexibilities are considered only when explicitlyrequired. Although dynamic models that include reaction wheels and eventually nutation dampers arecommonly employed in simulators, they lack the effects of appendages, like the rotation of solar panels,articulated robotic arms, booms, and mass movement in the satellite motion. When such effects areconsidered in the dynamic model, they increase the order and the complexity of the differential equations,due to the change in the satellite center of mass position caused by appendage motion. In order to avoidmodel complexity the angular momentum can be written with respect to a fixed point instead of the centerof mass, which in turns make necessary to invert a 3(A+W) + 6 matrix to evaluate the angular velocitiesof a satellite with A appendages and W reaction wheels. Also, the torque in each appendage joint shouldbe known, which requires motor, bearing and joint control modeling. This work presents a new approachto solve both the increasing of model order and unknown torque. Taking the angular moment relative tothe center of mass the resulting differential equations can be written directly in angular velocity variables,which reduces the order to 3(A+W) + 3. Assuming also that the appendages acceleration are known(which is more realistic than the joint torque), then order of the dynamic model is reduced to mere 3W+ 3. The resulting reduced order but complex model is presented in this work.

Differential Games of Stabilization

Ximena Cubillos, BrazilSusana Dias, PortugalLuiz Gadelha , BrazilAnna Guerman , PortugalGeorgi Smirnov , University of Minho, Brazil

Pontryagin’s theory of linear differential games [1] is a natural tool to solve local stabilization problemsunder conditions of uncertainty. In this work we develop stabilization methods based on the differentialgames approach. Differential games of stabilization [2] have some special characteristic features distin-guishing them from other differential games. We discuss theoretical and computational aspects of thisclass of differential games. The main area of applications considered in this work is attitude stabilizationof spacecrafts with unknown mass properties, mobile and flexible elements [3].

Bibliography:

[1] L. Pontrygin, Linear Differential Games of Pursuit, Mathematics of the USSR-Sbornik, 40, 1981, pp.285-303.

[2] G. Smirnov, Introduction to the Theory of Differential Inclusions, Graduate Studies in Mathematics,vol. 41, American Mathematical Society, 2002.

[3] K. Yamada and S. Yoshikawa, Adaptive Attitude Control for an Artificial Satellite with Mobile Bodies,Journal of Guidance, Control and Dynamics, vol. 19, No. 4, 1996, pp. 948-953.

Performance Comparison of Attitude Determination Algorithms in a MicrocontrollerPlatform

Ricardo Oliveira Duarte , Universidade Federal de Minas Gerais, BrazilLuiz Siqueira Martins-Filho, Universidade Federal do ABC, BrazilHelio Koiti Kuga, Instituto Nacional de Pesquisas Espaciais, Brazil

This paper presents a study concerning the practical implementation and the performance analysis ofattitude determination procedure for artificial satellites implemented in a microcontroller environment.Three different algorithms were selected and implemented in a microcontroller platform. The threealgorithms were compared according to numerical precision, CPU cycles, program and data memoryrequired. The algorithms considered to calculate the attitude were the TRIAD, the Q-Method and theQUEST. Each of them requires at least two measurement vectors, in our system, given by the Earthmagnetic field and the sun directions to calculate the attitude. The attitude representation in the project

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was parameterized using the quaternions. The main goal of this project is the development of an embeddedsystem for application in Brazilian satellites. This project is supported by the UNIESPAO Program ofthe Brazilian Space Agency - AEB and has a purpose to obtain a processing system able to properlycalculate the attitude using an architecture based on low-cost COTS components provided with fault-tolerance techniques. The whole embedded system is composed by a three axis solid state magnetometer,a photo-position sensor as a solar sensor and a PIC microcontroller.

Attitude Control of Spacecraft Using Three Axis Magnetorquer Only

Ahmad Faraag , Egyptian Space Program, EgyptAhmad Raffie , Egyptian Space Program, EgyptAhmad Bahgat , Faculty of Engineering, Cairo University, Egypt

The problem of satellite detumbling after separation from launcher and attitude acquisition of a smallsatellite using magnetic actuators only is considered, a comparison between commonly used attitudecontrol algorithms is presented. Simulation results are also given to show a qualitative comparisonbetween the used algorithms.

IMU Calibration Procedure for a Redundant Tetrahedral Gyro configuration with WaveletDe-noising

Elcio Jeronimo de Oliveira , IAE/DCTA, BrazilWaldemar de Castro Leite Filho, IAE/DCTA, BrazilIjar Milagres da Fonseca , INPE, Brazil

The aim of this paper is to present a calibration procedure applied to an inertial measurement unit (IMU)composed by a triad of accelerometers and four gyros (FOG) in a tetrad configuration. The proceduretakes into account a technique based on Least-square methods and wavelet de-noising to perform thebest estimate of the sensor axis misalignments. The wavelet analysis takes place in order to removehigh and undesirable frequency components via multiresolution signal decomposition analysis appliedto accelerometer and gyro signals. Equations for the least-square methods and wavelets analysis arepresented, and the procedure is verified experimentally.

Preparation of Uniformly Distributed Onboard Guide Star Catalog

Masood Ur Rehman

Attitude determination accuracy of an autonomous star sensor for continues operation, depends uponmany factors. The essential component of the star sensor is the onboard guide star catalog (GSC), whichserves as the accurate inertial reference. The optimal selection of stars for GSC from the master starcatalog (MSC) mainly depends upon the spectral response, visual sensitivity limits and Field of View(FOV) of the star sensor. The optimal GSC selection under memory and computational constraintsrequires having a constant number of stars in any random boresight direction (BS). Therefore starsselected for GSC must be uniformly distributed on the whole celestial sphere, whereas, natural distributionof stars is highly non-uniform. Many methods which produced nearly uniformly distributed GSC havebeen proposed in literature. In this paper a new approach is proposed to construct uniformly distributedGSC which emphasizes brightest stars to enhance the life time performance of star tracker for deepspace missions. The comparison of statistical results demonstrates that results of the proposed schemeare promising. The propose scheme extends the life time performance of the star tracker by selectingbrightest stars throughout entire celestial sphere. In addition, the selected stars are geometrically wellseparated which is beneficial for attitude determination accuracy of the star tracker.

On the modeling of a flexible spacecraft attitude motion considering fuel sloshing

Vahid Rezvani

A complete three dimensional attitude motion of a flexible spacecraft considering the effect of sloshing innot fuel-filled tank has been investigated in this study. The problem of modeling such complex spacecraftconfiguration has found crucial applications in complicated space missions, such as interplanetary missionswhere huge amount of fuel and large flexible pads must be carried out. The spacecraft consists of a centralrigid box with two flexible pads, and a spherical tank located at the center of the rigid box. To present

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sloshing effects in the zero gravity condition without thrust consideration, an equivalent mechanical massspring model has been developed. In this way, the spacecraft is modeled as a flexible multi body systemand based on the Lagrangian equation, the mathematical model of system is derived. Afterwards, thesimulation results of a typical model are computed and compared to those of a non-flexible spacecraftwith fuel sloshing and rigid model consideration. The main novelties of this work are to develop a threedimensional equivalent mechanical model for fuel sloshing and to present the effects of both pad vibrationand fuel sloshing on the angular responses.

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MINISYMPOSIUM 4.Mathematical Applications in Electrical, Aerospace and Control Engineering

Organizer: Ahmad Sabihi (Sharif University of Technology, Tehran, Iran)

The aim of this session is to disseminate recent developments of mathematical applications in electricaland aerospace engineering, control, mechanics, electromagnetic fields, and radar cross section engineering.The session also surveys new contributions in applied mathematics and engineering sciences.

Aircraft Generalized Dynamic Inversion Control

Abdulrahman Hasan Bajodah, Ismail HameduddinKing Abdulaziz University, Saudi Arabia

The new and evolving paradigm of generalized dynamic inversion (GDI) is applied to aircraft maneuveringcontrol design, through the development of a new multiple constraint formulation. The flexibility of GDIin utilizing nullspace of the controls coefficient matrix is exploited to eliminate the problems of excessivecontrol effort and limited performance that are associated with classical dynamic inversion. Scalardeviation functions of the aircraft state error variables are differentiated along the aircraft mathematicalmodel solution trajectories, and linear time varying stable dynamics in these deviation functions aremanipulated to obtain linear algebraic constraint equations in the control vector. The constraint equationsare inverted using the Greville formula, resulting in the control law. The particular part of the controllaw drives the states to their desired values, and the auxiliary part acts to stabilize the vehicles innerdynamics by means of the null-control vector. The null-control vector is constructed via a novel class ofpositive semidefinite Lyapunov functions and nullprojected Lyapunov equations. The closed loop controlsystem is assessed by performing a fully coordinated simultaneous heading-velocity change maneuver.The new type of GDI control laws shows to require low control effort, in addition to providing excellenttransient response and reasonable steady-state tracking accuracy.

Passive Thermal Control with Pulsating Heat Pipe

Liomar de Oliveira Cachute, Roger Ribeiro RiehlNational Institute for Space Research INPE / Space Mechanics and Control Division DMC, Brazil

Passive thermal control on aircrafts and spacecrafts is a major issue on modern equipments once thethermal loads on avionics and other electronics installed on these vehicles have increased dramaticallyover the last decade. The need for heat dissipation is such an issue that a slight increase on the operationtemperature of certain electronics might present a severe damage on its performance, yielding to theequipment shutdown. Constant temperature control for a given heat load that might be varying along timeis a complicated thermal problem to be solved, especially on applications where conventional pumpingsystems cannot be used. In this specific case, the use of passive thermal control devices that operate bymeans of capillary forces (such as regular heat pipes and loop heat pipes) and by means of slug/pluggeneration (such as pulsating heat pipes) are widely used with reliable operation. Heat pipes and loopheat pipes have been used for spacecrafts thermal control since the 70s but the application of pulsatingheat pipes is still require investigations towards the definition of design and operational parameters. Theobjective of this work is presenting a brief investigation on a pulsating heat pipe operating with differentworking fluids and orientations, where its performance is analyzed and discussed. The results indicatethat the pulsating heat pipe is able to operate at any orientation with reliable control of the heat sourcetemperature.

Hybrid Tracking Control of Fixed Wing Aerial Vehicles

Ilse Camacho Cervantes, Fany Mendez VergaraInstitute for Scientific and Technological Research of San Luis Potosi (IPICYT), Mexico

In this paper, we introduce a coordinated guidance-tracking hybrid controller in order to control velocity,position and attitude of various fixed wing aircrafts. The proposed controller is able to adapt its operationdepending on the trajectory, altitude, and external perturbations. The adaptive mechanism is activatedvia the satisfaction of a set of prescribed restrictions which are both security and performance based.

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The nature of the controller is hybrid because the system dynamics is modeled continuously with theinteraction of an adaptive discrete control action which defines the next active behavior of aircraft.Features of the control are so that security and performance restrictions may be state or trajectorydependent. Additional restrictions can be easily included as long as the entire state space has assigned asingle closed-loop dynamics in a finite number of state partitions. Here, conditions of stability are studiedas well as their dependence with control gains, control bounds, and switching restrictions. Numericalsimulations in a Cessna 182 are used for illustrating the proposed control method. Experimental work isdeveloped to illustrate some of the control features in a scaled aircraft.

Finite volume solution of compressible magnetohydrodynamics equations

Sergio Elaskar, Livio Maglione, Mariano MartinezArgentina

Flow studies related to an electrically conducting gas that moves in a magnetic field have beendeveloped. The objectives of theses studies are to solve 1D and 2D, time-dependent, viscous andresistive magnetogasdynamics, or compressible magnetohydrodynamics, flows and 3D time-dependent,ideal magnetogasdynamics flows. Its numerical approach is based on a finite volume technique and tocompute the numerical fluxes across cells interfaces, an approximate Riemann solver coupled with theTotal Variation Diminishing (TVD) scheme proposed by Harten and Yee is utilized. Besides implementingthe eigensystem technique and the eigenvectors normalization for the magnetogasdynamics equations, anew sonic fix for the Harten-Yee scheme is applied. The computational code has been tested with thesimulations of the magnetogasdynamics Riemann problem and of the Hartmann flow. At the present,this code is being applied to simulate the internal plasma dynamics of solar post-flare loops and of thedark inflow in post-flare-supra-arcade.

Finite volume simulation of supersonic flows

Sergio Elaskar, Jose TamagnoArgentina

A TVD scheme has been implemented on a non structured 3D finite volume formulation for solving theEuler equations. To simultaneously, achieve adequate accuracy in smooth flows, high resolution at flowdiscontinuities and to avoid spurious oscillations, different flux limiter functions are applied in a wave-to-wave basis. This technique implements compressive limiter functions in waves from the family twoto four and diffusive limiter functions in waves one and five, thus, the robustness of the TVD scheme ispreserved and a reduction of the numerical viscosity can be achieved. This sort of adaptive scheme hassatisfactorily been applied to the slip interface between two parallel flows and to supersonic flows overan airfoil and a blunted bi-conic body. The code has also been used to compute the flow around re-entrybodies.

Finite rate chemical effects can be introduced accounting for source terms in the Euler equations. Suchsource terms representing the chemical kinetics and vibration relaxation are often large, making thealgorithm too stiff to be advanced explicitly. To avoid this stiffness an implicit treatment of the sourcesterms is implemented. To describe the hydrogen-oxigen-nitrogen mechanism 13 chemical species and 33one step chemical reactions are employed.

Position and Vibration Control of a Nonlinear Slewing Flexible Structure Considering Fluid-Structure Interaction

Andre Fenili , Cayo Prado Fernandes FranciscoUniversidade Federal do ABC, Brazil

Position and vibration control of a nonlinear flexible beam-like structure in slewing motion is investigatedhere. A DC motor is used as actuator and the movement of the motor axis provides the slewing motion.The flexible structure is mathematically modeled considering linear curvature and clamped-free boundaryconditions. A cubic nonlinearity resulting from the coupling between the angular displacement of themotor axis and the flexible vibration of the beam is considered. One also includes in the mathematicalmodel a drag force acting along the beam length. This force is modeled through the Rayleigh dissipationfunction. For position of the slewing axis and elimination of vibration in the beam the nonlinear controlmethod named State Dependent Riccati Equation (SDRE) is applied to the DC motor axis. Sufficiently

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large angular displacements and velocities are considered in order to the system to undergo nonlinearbehavior. For small and for large initial angles (here considered as position errors) the system responseconverges satisfactorily to the desired final states.

Design and Simulation of Intelligent Aircraft Longitudinal Autopilots Using Particle SwarmOptimization Algorithms

Mostafa Lotfi Forushani, IranBahram Karimi, Amir Kabir Univesity and Technology, IranGhazanfar Shahgholian, Islamic Azad University Najafabad, IranAlireza Karami Horestani, Iran

Proportional-Integral-Derivative (PID) controller is still widely used in control and aerospace engineering.All the aircrafts benefit from a PID controller in Autopilot Control System for Longitudinal and Lateral-Directional axes. The PID controllers are associated with their PID gains which can either be tunedmanually or optimized by the methods like Particle Swarm Optimization (PSO) to get better controland enhancement in the performance. Particle Swarm Optimization is a powerful stochastic evolutionaryalgorithm that is used to obtain the global optimum solution in search space. This algorithm introducesmutation operator with adaptive mutation probability into the PSO algorithm as well as it replaces thoseparticles which fly out the solution space with new generated random particles during the searchingprocess. Here, PSO algorithm is successfully applied to Altitude Hold (AH) in longitudinal axis autopilotcontrol of an aircraft. Our system is simulated by MATLAB programming based on Particle SwarmOptimization algorithm. Furthermore, the advantage of PSO algorithm in controlling parameters andperforming the system is compared with traditional PID tuning method as Ziegler Nichols tuning rule.The results show good agreement and promising.

A Micro-Tuning-Fork Gyroscope Coupling with an Electrodynamic Engine

Ana Rosa Klinke, J.M. Balthazar, Luiz Palacios Felix, F.R. Chavarete, UNESP: Univ.Estadual Paulista, Rio Claro - SP, Brazil

Nowadays, the technology of micro-electro-mechanical systems (MEMS) has many applications onEngineering Sciences. This technology allows that the movement to be expressed by a function of micro-scale ranging devices. However, the design of such mechanical systems can be quite challenging due tononlinear effects which may strongly affect the dynamics behavior. The MEMS problem studied here iscomposed of an inverted pendulum fixed in a suspension space of mass movements having two degrees offreedom. The physical model under study is implemented by coupling between the electrodynamic engineand the system of inverted pendulum. This implementation concludes a model of a micro-tuning-forkgyroscope coupling with an electrodynamic engine. The numerical simulations are then carried out andone can obtain the vibration modes of the MEMS model. This model is excited by a sinusoidal voltagewhich applied to an electro-dynamic engine. The study also shows an interdependence of the invertedpendulum and the engine dynamics so that the pendulum motion influences on the vertical excitationsupplied by the engine.

Pseudo-stochastic-chaotic systems in Engineering Applications

Hilda Angela Larrondo, Luciana De MiccoFacultad de Ingenieria - Universidad Nacional de Mar del Plata, Argentina

The statistical properties of chaotic systems made them capable play the role of stochastic sourcesin many applications. In this paper we review a number of engineering applications: chaotic spreadspectrum communication systems, chaotic electromagnetic compatibility improvement, chaotic noise,chaotic sampling, etc. In many of these applications chaotic systems must work as pseudo randomnumber generators. Several processing techniques used to improve the stochastic behavior of chaoticsystems behave are evaluated by means of information theory quantifiers. The effect of discretizationover randomness is also considered.

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Solving the Sitnikov Equation by Means of the Fourier Expansion

Mojtaba Dehghan Manshadi, Mohammad Farahani, Mohammad Ali VaziryIran

In this paper, the problem of a zero mass body oscillating perpendicular to a plane in which two heavybodies of equal mass orbit each other on Keplerian ellipses is considered. The zero mass body intersectswith the primaries plane at the systems barycenter. This problem is universally known as the SitnikovProblem. The authors solve the Sitnikov problem using the Fourier Expansion. Furthermore, the createdanalytic solution is compared to results obtained from numerical integration of the exact equation ofmotion. Conclusions of comparison show a good agreement. The results also show that increasing inamount of eccentricity and the derivation of amplitude in the initial condition status, the decision timeof solving the problem decreases but increasing the number of the sentences of the Fourier expansion, itgrows up.

Robust SDC Parameterization for a Class of Extended Linearization Systems

Sam Nazari, Bahram ShafaiNortheastern University, USA

We consider nonlinear regulation of systems with parametric uncertainty. Under mild conditions,these systems can be brought into a pseudo-linear form known as extended linearization. Under thisformulation, conventional linear control synthesis methods can be applied. One popular techniquethat mimics the LQR method of optimal linear control is referred to as the State Dependent RiccatiEquation (SDRE) approach. SDRE control relies on a nonunique factorization of the system dynamicsknown as the State Dependent Coefficent (SDC) parameterization. Under system uncertainty, each SDCparameterization will produce its own radius of stability in a region of interest in the state space. In thispaper a method to compute the radius of stability in a special class of systems is used to obtain the SDCparameterization which results in the maximum radius of stability for the original nonlinear system inthe region of interest. Finally, the approach is demonstrated on a testbed Segway Robot.

On the Nonlinear Dynamics and Control of Modal Interactions Resulting from the Longi-tudinal and Lateral Flight of an Aircraft

Rodrigo Bassinello Ramazotti, UNESP-Bauru, Brazil

In this study, we analyze the nonlinear dynamic behavior of an aircraft in flight longitudinal and lateralshifts and interactions with one another. The aim of this study is to improve performance of the aircraft,cargo release, artifact weapons, releasing supplies in cases which a high degree of flexibility and survivalreliability are needed.

We conduct the analysis of the bifurcational behavior of the aircraft F-8 ”Crusader”. Before developingthe research, a project namely Linear Optimal Control is proposed to stabilize the oscillations of angleof attack considering the critical regions of nonlinear behavior of the aircraft.

The variation of longitudinal and lateral speeds of the aircraft aiming the numerical simulations in avirtual wind tunnel are also included.

On the Electromagnetic Waves and Propagation in Relativity-Quantum Space

Ahmad Sabihi, Sharif University of Technology, Tehran, Iran

Relativity-quantum space refers to a type of space representing characteristics of the Einstein’s relativityand quantum theory of particles. Einstein gave a theory, namely special theory of relativity in 1905. Inthis theory, he claimed that the velocity of light is a measurable quantity which holds a constant value in allinertial frames of references. Also, he presented the theory of photoelectric effect having said light showsparticle-like property. Light also shows wave-like property. The author wishes to do an investigationshowing electromagnetic waves can also have both wave and particle-like properties. Here, a surveyof the theories such as: Quantum Mechanics, Wave-Particle Duality, Homogeneous and InhomogeneousElectromagnetic Wave Equations, Maxwell’s Equation in Curved Space-time, Quantum Electrodynamics,Quantum Chromodynamics, and Gravitational Waves will be accomplished by the Author.

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Comparision of PO Approximations with FDA Method to Obtain RCS of Simple Shapes

Ahmad Sabihi, Sharif University of Technology, Tehran, IranMohammad Ali Vaziry Z., Amir Kabir University of Technology, Iran

Here, the Authors compare the Radar Cross Section (RCS) of some simple shapes such as: Cylinder,Sphere, Rod, Rectangle, and Right-Triangle by Physical Optics (PO) approximations with computedRCS values of same shapes by Fast Decomposing Algorithm (FDA) method.

On the Laser Cross Section of Various Targets

Ahmad Sabihi, Sharif University of Technology, Tehran, IranMohammad Ali Vaziry Z., Amir Kabir University of Technology, Iran

This Paper surveys Laser Cross Section (LCS) prediction methods of various objects as sphere, flat plate,corner reflector, and complex targets as an aircraft. Here, it is found expressions for total LCS of a flatcircular disk of optional radius.

A Non-Model Based Damage Detection Technique Using Dynamically Measured FlexibilityMatrix

Mehdi Salehi, Saeed Ziaei-Rad, Mostafa Ghayour, Mohammad Ali Vaziri-ZanjaniIran

Although many damage detection methods have been developed to detect damage in a structure usingmeasured modal parameters, most of them have to make use of modal data of the structure for the intactstate as baseline or a correlated finite element model. For beamlike structures, curvature techniques asmode shape and flexibility curvatures have been applied for localizing damage. An approximate flexibilitymatrix can be derived using a lot of number of vibration modes whose columns are referred as flexibilityshapes. In this paper, a damage localization method is developed based on changes in flexibility shapesas well as its curvature. Differential Quadrature Method (DQM) is implemented in order to obtain thecurvatures of flexibility shapes. As shown before by other authors, this method is sufficient for modelingdamage. To reduce error values due to experimental data differentiation, a moving curve fit method aswell as DQM is implemented on flexibility shapes. The proposed method is validated by numerical andexperimental case studies.

Smart beam deflection behavior due to two or more SMA wires attachment

Hamid Salehi, Saeed Ziaei-Rad, Mohammad Reza Zakerzadeh, Mohammad Ali VaziryZanjaniIran

This paper is concerned with the deflection behavior of an Euler-Bernoulli beam when two Shape MemoryAlloy (SMA) wires are attached to it. In real application of SMA as an actuator for shape control purposes,the number of actuators is not limited to one. In order to solve the problem, first, the large deflectionformulation of a beam under two applied forces is derived. Then, the thermomechanical behavior ofwires with the load deflection behavior of the beam is coupled and governing equations are extracted.Finally, the measurement is carried on the SMA wires to obtain the parameters associated to the utilizedthermomechanical model for the SMA wires. Several case studies are then accomplished and the resultsare discussed in details.

An Hierarchical Approach for the Structural Damage Identification

Leonardo B. L. Santos, National Institute of Space Research - INPE, BrazilLeonardo D. Chiwiacowsky, Universidade do Vale do Rio dos Sinos (UNISINOS), BrazilHaroldo F. Campos Velho, National Institute of Space Research - INPE, Brazil

The use of global techniques for damage identification is based on the fact that the presence of a fault willcause changes in the structural properties of the system, which in turn lead to a change in its dynamicresponse. The changes in the structural properties could be assessed by measures in the time, frequencyor modal domains. To solve this inverse problem - Structural Health Monitoring - is possible to use,for example, methods from the Calculus of Variations, with the Conjugate Gradient Method (CGM -

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Alifanov approach) in the form of adjoint equation.

The central objective of this research is to significantly increase the speed of the method developedby Chiwiacowsky et al, 2005 which has been used for the damage identification. The new strategy forattacking the problem is based on the application of an hierarchical search to evaluating the different areaswhere damage may be present, starting with a coarse discretization and promoting gradual refinementonly in the areas where the possibility of damage was not discarded.

Preliminary results has shown that, in case of random (non-correlated) distribution of damage, thehierarchical approach can be until twenty-three times faster than the traditional search.

On the Active Vibration Control and Stability of the Tubular Structures by PiezoelectricPatch-Like Actuators

Sergey N. Shevtsov , South Center of Russian Academy, RussiaMichail B. Flek, Rostvertol, RussiaVladimir A. Acopyan, Institute of Mechanics & Applied Mathematics, RussiaVladimir N. Axenov, Don State Technical University, Russia

We present some theoretical and real-world approaches to design and implement smart vibration controlof aircraft tubular structures which are controlled by feedback with power PZT patches. Experimentaltests show that active vibration control and stability of a control loop may be lost at some parameters ofvibration and feedback. To determine the causes of instability, a flexible tubular structure with surface-bonded PZT patch actuated is modeled by PD controller using Euler-Bernulli beam theory. Emphasis inthis study is given to the effect of actuator size and location based on the observability, controllability,and stability of the control system.

Using finite element transient analysis of a beam structure of bonded PZT patches controlled by feedback,linear function of local strain and strain velocity of strain gauge placement is developed. Such action workmode can be stable both at relatively small feedback and narrow frequency band. Also, due to nonlinearnature of a coupled electro-mechanical distributed control, the suppressed vibration mode shape can betransformed to vibration of other forms.

We approach to a new method for all actively controlled PZT patches driven at a narrow frequency band,filtering preferentially on the first eigenfrequencies. Moreover, installed shunted passive PZT patches willdamp high vibration frequencies, while simultaneously the stability of the control loop increases. Finally,we present some experimental results obtained by a scaled (1/7) helicopter rotor.

On the Modification of Node Swapping Method in graph partitioning

Omid Talebi, Ahmad Sabihi, Pejman KhadiviIran

In this paper, the authors propose a new algorithm for the Node Swapping Method in graph partitioning.Here, the proposed algorithm modifies that method so that any number of graph or network’s nodes canbe partitioned into any optional number of subsets (preferably into a divisible respect). The applicationof given method on the some random graphs is also validated by well-known Complete Search Method.The final conclusions show a good improvement in time processing and error values with respect to theother old methods.

On an Optimal Linear Control Design Applied to a Non-Ideal and Ideal Structure controlledthrough MR Damper

Angelo Marcelo Tusset , UFTPR, BrazilFabio Roberto Chavarette , UNESP - Ilha Solteira, BrazilJorge L.P. Felix, UNIJUI, BrazilJose Manoel Balthazar, UNESP - Rio Claro, Brazil

This paper presents the control strategies of non-linear dynamics of a particular structure coupled (oruncoupled) to an essentially nonlinear oscillator using a magnetorheological (MR) damper. We makeuse of an optimal linear control design for reducing the amplitudes and energy consumption of the MRdamper oscillations derived from both ideal and non-ideal mathematical models. The authors approachto a model in order to control the mechanical and electrical parts of the systems by the MR damper using

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the two different methods. Firstly, we formulate and resolve the control problem in order to design thelinear feedback dumping force controller. Then, the control dumping force functional values are convertedto electrical control signals by a proposed mathematical model. The numerical simulations accomplishedshow that the presented method is so effective in controlling the non-linear dynamics of a particularstructure. Also, using the proposed MR damper, one is able to determine electric current values appliedto the control system.

Semi-Lagrangian Reachability Analysis for Aircraft Safe Flight Envelope Determination

Eddy van Oort , Delft University of Technology, The Netherlands

To prevent aircraft loss-of-control incidents, knowledge of the safe maneuvering envelope is of extremeimportance. The safe maneuvering envelope can be determined by means of reachability analysis froma known safe set, for example the set of all trim states. Implicit surfaces provide a convenient wayto describe sets because of their ability to inherently handle merging and pinching of sets. Level setmethods add dynamics to implicit surfaces, and the evolution can be tracked by the viscosity solution ofa Hamilton-Jacobi partial differential equation.

Unfortunately, uniform grid based solvers for level set methods suffers greatly from the curse ofdimensionality. Additionally, for Eulerian methods the time step is limited by the Courant-Friedrich-Lewycondition. This combination makes application to aircraft dynamics too computationally demanding. Inthis paper an alternative method is used based on a Semi-Lagrangian solution method on adaptive kd-treegrids. This method allows a larger timestep, and adapts the grid as required during the evolution of theimplicit surface.

The method is applied to several examples in two- and three dimensions. The results are compared withan Eulerian solution method. Based on the results conclusions are drawn and future research directionsare formulated.

Spacecraft Trajectory Optimization Using State Parameterization and Interval Analysis

Elwin de Weerdt, Q.P. Chu , J.A. MulderDelft University of Technology, Faculty of Aerospace Engineering, The Netherlands

Trajectory optimization of spacecraft has been an active research field for many years. Many solvers arebased on local optimizers (gradient based, heuristic methods) therefore lacking the guarantee of findingthe global optimum within finite time. A novel optimization algorithm is introduced based on intervalanalysis which does provide this guarantee. Moreover, all optimal solutions in the solution set will befound. State parameterization is used to transfer the infinite dimensional trajectory optimization probleminto a finite dimensional, static optimization problem. By using state parameterization instead of thecommonly used control parameterization one can prevent explicit integration of the dynamics. Insteadthe dynamics are used to derive the control trajectories based on the state trajectories via the equationsof motion. Preventing explicit integration reduces the computational load significantly. The proposedsolver (optimization and parameterization) is validated using three examples: the orbit transfer problem(Hohmann transfer), rendezvous and docking problem (using Hill-Clohessy-Wiltshire equations), andformation flying with large inter-satellite distances. The results demonstrate that the proposed solvercan indeed produce guaranteed optimal trajectories for linear and non-linear complex problems.

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MINISYMPOSIUM 5. Multidisciplinary Design and Optimization in Aerospace Industry

Organizers: Ali Kamran, He LinShu, Amer Rafique (BUAA, China)

Multidisciplinary Design Optimization (MDO) is an emerging field in aerospace engineering that attemptsto introduce a structured methodology to locate the best possible design in a multidisciplinary environ-ment, through the application of optimization algorithms. MDO can be considered to be a disciplinein and of itself with an intention of acting as an agent to bind the other disciplines together. Papersare sought that address topics in development or application of MDO methodology, MultidisciplinaryAnalysis, and optimization methods. MDO applications of interest address aerospace and mechanicalsystems for use in Aerospace Industry that may incorporate any number of enabling technologies. Papersare also sought on Space Propulsion System design and Optimization. This includes design, optimizationand application of solid rocket motor and liquid engine systems and subsystems.

Information Entropy as a Tool for Innovation Projects Fuzzy Front End Decision

Luis Wwaack Bambace, National Institute for Space Research - INPE, Brazil

Project decisions The Suh Entropy axiom links the success probability to information entropy andalso too usable and total variable field. With trial success probability, binomial distribution, detailedwork breakdown structure and time-motion study is possible to compare design alternatives in terms ofdeveloping effort regardless of the level of organization of the project team. The total number of designvariables in specification, processes, trade off, regulation and so on less the number of fundamentalvariables in the item and less available equations gives the number of totally unknown degrees of freedomthe main part of entropy in designs that are new to the developers. This together with residual lackof information due to failures in documentation, for instance obtained with Mils and Jelinski-Morandamodels give and extra entropy part. This tool together with parallel development, and Real Optionsinformation value, and detailed probability calculations of development trees allows new concept withintrinsic advantages and few complementary solutions and possible ad-ons to it to be compared withtraditional solutions with a large number of ad-ons in terms of project reliability, easing Fuzzy Front EndDecisions.

New heuristic approach for the multiobjective nonidentical circle packing problem

Jose Carlos Becceneri, National Institute for Space Research - INPE, Brazil

In this paper we present a heuristic for the multiobjective nonidentical circle packing problem (MNCPP),where none of the pairs of circles overlap (a bi-dimensional space are considered). We considered twoimportant objectives for allocation of instruments or pieces of equipment in a spacecraft or satellite: tominimize the radius of the circle containing all of the objects and the imbalance (attempts to minimizethe non-equilibrium of mass of all objects around the central point).

In this new heuristic, the circles are sorting the mass and the radius of each circle, trying to get a viablesolution that minimizes the imbalance. Next, an evolutionary algorithm is used to improve the bestsolutions met previously. The results are compared with test cases already known in the literature andfuture works are suggested.

Nonlinear Stability and Optimization Techniques

Arthur Cave, USA

As is well known, the engineering and applied sciences, the physical and mathematical sciences, andother areas are all somewhat interrelated and dependent to some extent upon stability and optimizationtechniques. Selected nonlinear stability and optimization techniques are briefly reviewed in terms of theircontrasts and inherent relationships with one another. Then examples, different than those developedin ICNPAA-2000, ICNPAA-2002, ICNPAA-2004, ICNPAA-2006 and ICNPAA-2008 are developed toillustrate the techniques. The application areas considered are combinations of the following: 1)Mechanics and Circuits, 2) Estimation and Control, 3) Signal Processing and Communications, 4)Computational Methods.

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Optimization of an Aeronautical Composite Structure through a Parallel Multilevel Ap-proach

Leonardo Dagnino Chiwiacowsky, Universidade do Vale do Rio dos Sinos - UNISINOS, BrazilPaolo Gasbarri, Universita di Roma La Sapienza, ItalyHaroldo Fraga de Campos Velho, Instituto Nacional de Pesquisas Espaciais, BrazilArthur Torgo Gomez, Universidade do Vale do Rio dos Sinos - UNISINOS, Brazil

Optimal design of complex engineering systems, such as aircraft composite structures, can often beaccomplished only by decomposition techniques. In general, it is characterized by a multidisciplinarytask, usually involving multiple objectives, with many design variables and several constraints associatedto each one of the disciplines taken into account. One of these techniques is represented by the multilevelapproach, where the complex problem of multidisciplinary optimization is solved based on the idea divideand conquer. The original problem is split into several smaller subproblems, making the new configurationinherently suited for parallel and distributed computing. In this paper, the optimal design of a compositewing-box is addressed by using a parallel two-level scheme, where a stochastic method is used to solveeach problem level. At the second level, since the changes in the components of one of the subproblemshave no influence on the solution of the others, they can be solved simultaneously. In addition, also thestochastic method used in the solution of each problem level is applied in a parallel form. Simulationresults have shown that, beyond the reduction of the computation time, the parallel version has providedbetter results if compared with those provided by the serial version.

Efficient Shock Capturing Scheme for Transonic Aerodynamics

Hasan Junaid Hasham, China

The aim of the paper is to validate the Implicit Finite Difference Method (FDM) based NND scheme tosolve Navier-Stokes Equation (NSE). The NND scheme is a sort of TVD scheme with limiter functions.In this case the spatial discretization is 2nd order accurate and the temporal accuracy is also 2nd orderaccurate. To accelerate the convergence of the coupled system, pseudo-time stepping technique was used.Algebraic turbulence model is used to account for the viscous flow effects. The discretization of residual,namely the spatial derivatives, is very critical to the accurate simulation of transonic flow. The viscousterms are centrally differenced as usual. However, the convection terms are differentiated with NNDscheme. The flux vector splitting is done based on the eigenvalues. For positive eigenvalues, backwarddifferencing is used and for negative eigenvalues, forward differencing is used. The steady state solution ofthis unsteady NSE is performed using Implicit LUSGS. To accelerate convergence pseudo time steppinghas also been used. The test case chosen for validation is that of NACA0012 airfoil which is solved onC-type grid with grid density of (x, η) 258 x 43. The results compare well with the published data.

Review of Reduced Order Models for CFDCSD Interaction Problems

Hasan Junaid Hasham, China

Typically a design team would be required to evaluate thousands of parameters so as to finalize the mostoptimal design. Similarly for stability analysis the evaluation of various flow conditions are required toobtain the complete result. In transonic flight regime these analyses generally require the use of verylarge high fidelity models which incur large computational cost. To overcome this Reduced Order Models(ROMs) are used. A ROM is any low-order model (small number of DOFs) that retains the characteristicsand dynamics of the original system. Another advantage of the ROMs is that they provide any insightto the physics of the problem itself.

Many ROM techniques have been used however they are basically classified into two categories. First isfinding the global modes of the system and projecting the full system on to the reduced space formed bythese modes. The other category is where the system is given input(s) and the outputs are measured.Transfer functions are evaluated to relate the inputs to the outputs. Within these two categories thereare many variants in this paper only the ROM techniques that are used in CFDCSD interaction problemsof Computational Aeroelasticity are reviewed.

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Optimal PID Controller Tuning in Missile Design Based on PSO Algorithm

Alireza Karami Horestani, Mostafa Lotfi Forushani, Mohamad HoseinyarIran

In the present paper, a new approach is performed to optimize the tuning of PID controller in missilecontrol system. In fact, the behavior of an aerospace vehicle, such as a missile can be described with a setof non-linear differential equations by assuming six degrees of freedom (three ones for linear motions andthe rest for angular motions) around x, y and z axes. Regarding this complexity, designing an effectivecontroller in missiles has been one of the most challenging subjects in optimal control context. On theother hand, the recent optimization methods in parameters tuning of the PID controllers have convertedit into one of the most useful methods in missile designing. Here, the PSO algorithm which is one of themost powerful tools in the field of global optimization used for a various range of problems is successfullyapplied for longitudinal axis control of a missile using MATLAB simulation for optimal tuning of PIDcontroller. At the end, the results of simulations are visualized in figures. Accordingly, the overall systemperformance has been considerably enhanced due to this new methodology.

Effectiveness optimization for a surface-to-air missile system based on MDO

Jiang Huan, Chen WanchunBeijing University of Aeronautics and Astronautics (BUAA), China

A multi-tier trajectory optimization framework for a surface-to-missile system is proposed based onthe Multi-Tier Optimization Process (MTOP) theory for the system effectiveness optimization. Theentire multi-tier trajectory optimization framework is divided into pre-launch phase, the midcoursetrajectory optimization, the terminal homing phase and the warhead damaging process. A tier canbe seen as a subsystem, the multi-tier trajectory optimization problem is essential a multidisciplinarydesign optimization (MDO) problem. A solution of the multi-tier trajectory optimization frameworkis presented based on the MDO theory and methods through discipline analysis and system analysis.The Global Sensitivity Equation (GSE) method and All-in-One method are used to solve the systemeffectiveness optimization problem, and the results obtained by these methods are given and analyzed.

Design and Optimization of Slotted Tube Grain Configuration using Simulated Annealing

Ali Kamran, Liang GuozhuBeijing University of Aeronautics and Astronautics (BUAA), China

Simulated Annealing is applied in optimization of Slotted Tube grain configuration. We propose CADbased geometry calculation function, to increase calculation accuracy, integrated with a simple ballisticmodel to calculate performance. CAD representation encapsulate all of the geometric entities pertinent tothe grain design in a parametric way, allowing manipulation of grain entity (web), performing regressionand automating geometrical data calculations. Average thrust is the impetus driver on performance, soconsidered as objective of grain design process. It is demonstrated with a constrained optimization forSlotted Tube grain using simplified internal ballistics model that maximizes average thrust for minimaldeviations from neutrality.

Design and Optimization of Star Grain Configuration using Simulated Annealing

Ali Kamran, Khurram Nisar, Amer Farhan Rafique, Qasim ZeeshanBeijing University of Aeronautics and Astronautics (BUAA), China

Grain Design is most imperative in completing the design of any Solid Rocket Motor (SRM). Recentlyauthors have considered the grain design and optimization using evolutionary optimization techniques butstill the potential of using meta-heuristic search algorithms like Simulated Annealing (SA) for the designand optimization of SRM grains has not yet been gauged. This paper presents a design methodologyfor efficient design of complex Solid Rocket Motor (SRM) Grains involving computationally intensiveanalysis with number of design variables. A technique has been proposed to design and analyze theStar grain geometry and thereafter extract optimal solution of the SRM grain using Simulated Annealing(SA). Maximum Thrust has been computed as the objective function with constraints of burning timeand propellant mass while remaining within fixed length and diameter of grain. The performance ofproposed methodology is investigated in this paper for the designing, analysis, performance prediction

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and optimization of 2 D grain design using Star configuration for Solid Rocket Motors that can be usedfor various missile systems and space launch vehicles. The results show that all desired functions havebeen achieved and an optimal design has been attained qualifying all ballistic parameters.

Sensitivity analysis of an aircraft shell panel with geometry imperfections

Airton Nabarrete , Francisco ScinoccaInstituto Tecnologico de Aeronautica - ITA

Frequency response analysis of an aircraft shell panel subject to geometry imperfections using a probabilis-tic approach was evaluated. A stochastic finite element model was developed and implemented applyingthe Monte Carlo Method to perform several spectral distributions and obtaining non-deterministic re-sults. This work extends the previous results obtained with the buckling instability analysis for an aircraftplate panel. In this research, the investigation considers the variations for the shell panel geometry andmaterial properties. In order to observe the major contributors, a sensitivity analysis was performed.The modal results and the frequency response function variations are presented.

Experimental Study of Laminar Horseshoe Vortex Using PIV

Zaw Zaw Oo, Muhammad Yamin, Hua ZhangChina

The study provides topological analysis of juncture flows generated by the cylindrical body mounted on aflat plate using PIV (Particle image velocimetry) technique. Various vortex structures are predictedfor ReD (Diameter Reynolds number) ranging from 500 to 2500. The vortex structures and theirvariation with the change of ReD is discussed in detail. Experiments were conducted to investigatethe effect of various Reynolds number and the variation of the height of the cylinder aspect ratio (H/T)on hydrodynamics performance of three-dimensional flat plate and circular cylinder. Both steady andperiodic laminar horseshoe vortex flows generated upstream of a cylinder/flat plate juncture is presented.As the flow approaches the cylinder, the adverse pressure gradient produces three-dimensional boundary-layer separation, resulting in the formation of laminar horseshoe vortices. The standard or classical typeof laminar horseshoe vortex topology is identified.

Trajectory Optimization of Air Launched Satellite Launch Vehicle using Genetic Algorithm

Amer Farhan Rafique, Beijing University of Aeronautics and Astronautics (BUAA), China

Powered flight phase dictates the performance of any launch vehicle. Good ascent guidance can help inreducing cost, reducing load indicators, and consequently increase its performance. The powered flight ofAir Launched Satellite Launch Vehicle is divided in several phases. After a short horizontal launch phase,the vehicle undergoes a launch maneuver by introducing a carefully selected Angle of Attack profile. FlightProgram is optimized under the constraints of the maximum allowed AOA, lateral and axial overloads.The main focus of this study is the endo-atmospheric phase of the ascent trajectory. To analyze theascent fight-path, a three degree-of-freedom 3DOF trajectory model is modeled in SIMULINK. GeneticAlgorithm is used to optimize the Flight Program, as it is better suited in view of the efficiency of globalsearch performance. In this paper the proposed design optimization approach is applied to design thetrajectory of Air Launched Satellite Launch Vehicle and the performance index is the altitude achieved.The method described in this paper provides the designer with a simple yet powerful approach to theascent trajectory optimization.

Development of a new algorithm for optimization of closed-loop liquid rocket engines

Davood Ramesh, Iran

The reduction of Liquid Rocket Propulsion System (LRPS) conceptual design costs in conjunction withan increase in engines performance caused to develop a noticeable engineering software to simulateand optimize LRPS with staged combustion cycle and oxidizer rich pre-burner. An enabling staticmathematical modeling core feature of this tool has the ability to rapidly produce closed solutions forengine power balance and engine independent parameters (combustion chamber pressure, combustionchamber mixture ratio, expansion ratio of turbine nozzle and etc.) with respect to maximize performance(specific impulse as objective function) of LPRS and managed to select optimum regime.

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Finally, it must be finalized selection of optimum regime or optimum parameters. The developedalgorithm has applied for RD-253 engine, and results have compared with the modified RD-253. Accordingto the developed algorithm, a software is written in the modern engineering, object-oriented Compaqvisual Fortran 6.6 programming language. Execution times are approximately 5 to 10 seconds.

Robust Design Optimization of Booster Phase Energy Management of Dual Thrust Propul-sion System

Muhammad Aamir Raza, Northwestern Polytechnical University Xian, China

The regularization of energy management program of dual thrust solid rocket motor is considered. In-depth analysis of energy constituting parameters in booster phase of dual thrust solid rocket motorsshows that there is uneven rise and fall in chamber pressure. Among other factors, this pressure behavioris found to be associated with the design variables constituting the grain geometry in booster phase.The uncertainty and variation in grain geometry causes loss in booster energy in terms of maximumaverage thrust and total impulse. A robust design frame work is proposed based on hybrid optimizationof Genetic Algorithm followed by Simulated Annealing. To increase the optimization efficiency, designof experiment employing uniform Latin Hypercube Sampling is used. The sensitivity analysis is doneusing Hadamard matrices approach. The optimal design solution is perturbed with different variationlevels to reach robust design optimization using random Monte Carlo simulation. The suggested schemeshows excellent results to ameliorate the design space to reach the right set of design parameters whichis insensitive to booster phase performance.

Parametric Design Approach for Aero-performance of Hypersonic Reentry Body

Muhammad Amjad Sohail, Yan Chao, Zahid MaqboolBeijing University of Aeronautics and Astronautics, China

This research effort presents the parametric studies of different shapes of reentry vehicle with different radiiand cone half angles. Higher order low dissipative scheme verifies the simulated results with experimentaldata. All simulations are at high Mach number and shock parameters determined using shock capturingtechnique. The patterns of shock waves and aerodynamics performance are studied for varying radiusand cone angle. We performed simulations for 12 geometries, with varying tip and base radius, at Mach5.9 and angle of attack -4, -2, 0, 2, 4, 6, 8, 10, 12 deg. Based on results, we intend to compute theaerodynamics coefficients and best lift to drag ratio geometry.

Inviscid and Viscous Computation on Aerodynamic Characteristics of a ConventionalProjectile with and without Fins Configuration by using Flux Difference Scheme

Muhammad Amjad Sohail, Yan Chao, Zahid Maqbool M. Yamin Younis, Muhammad Afzal,Mukkarum HussainBeijing University of Aeronautics and Astronautics, China

The performances of Inviscid model, viscous turbulence K-ω SST turbulence model and high order lowdissipative Flux difference scheme of Roe are evaluated against experimental flow fields at differentgeometries and angle of attacks at supersonic Mach numbers. Inviscid and viscous effects on cylindricalbody with and without fins are described and discussed in detail. The numerical predictions include lift,drag and pitching moment coefficients at different angle of attacks and Mach number. Most significantly,this research provides a sensitivity study on the accuracy of the solutions with respect to the effects offree stream turbulence, grid resolution, grid spacing near the wall, initial conditions, numerical methodsand free stream Mach number effects on compressible flows. Comparison of two geometries, cone cylinderand cone cylinder with fins is provided in order to study the effects on the aerodynamics characteristicsby the addition of the lifting surfaces and the same is compared with the available experimental data.For the present study supersonic flow is simulated at Mach number 4 and the angle of attack is varied.First calculation are done on inviscid modeling and using Flux difference scheme of Roe which is firstorder accurate but limiters are used to get higher order accuracy and suppress the oscillations in highpressure gradient flows and in discontinuity regions. First order scheme produces oscillations and unstablesolutions in discontinuities and shocks. Then results obtained from these inviscid calculations are underpredicted so viscous turbulent modeling of K-ω SST model of Menter is used to capture the viscousand turbulence effect of flows. It was observed that inclusion of viscous effect increase the accuracy of

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the solutions and results have very good agreement with the experimental results. Roe TVD schemeand limiters are successfully implemented for supersonic flows and hyperbolic equations. Three differenttypes of limiters are used here to get second order accuracy and to stable the solutions near shock and indiscontinuous regions. Cone-cylinder body (with and without fins) is used for the above methodology tosimulate the flows for inviscid and viscous flows and results for both these two cases are obtained at mach4 and at different angle of attacks. The results have very good agreement with experimental results.

Comparison Study of Geometrically and Numerically Regression of the Star Grain Designfor SRM

Soe Hlaing Tun, Xiang Hong JunBeijing University of Aeronautics and Astronautics (BUAA), China

When the neutral burning characteristic with respect to time is needed in a mission, star grain geometryof solid propellant is used. Most of the grain regression is done by the geometric evolution analysisduring its combustion. In this study, we present the comparison of the regression of two dimensionalstar grain geometry of a solid rocket motor by geometrical and numerical approach. In the geometricevolution technique, it is required to predefine the evolution zones to estimate the internal ballistics ofthe rocket motor before the grain regression occurs. But using the numerical method, no predefinedzones are needed while it gives close result to that of the previous one. Both methods are based on theprinciple that burning will occur in the normal direction of the solid propellant surface.

Implementation, Validation and Testing of an Inverse Design Tool for Redesigning NACA65-410 Wing Profile

Arpad Veress , Andras Nagy , Jozsef RohacsBME, Department of Aircraft and Ships, Hungary

Two dimensional Euler equations based compressible flow solver has been implemented, validated andextended for inverse design applications. The inverse design method, as usual, consists of three main steps;direct, inverse and wall modification algorithm. The emphasis has been placed on the developments ofan accurate, robust and fast method with the capability of providing solutions for a wide range of targetpressure distributions as it is going to be a part of the optimization tool in the next steps. In caseof the inverse design problems, the existence of the geometry belongs to an arbitrary target pressuredistribution is not straightforward. There are several problems, e.g. the cross over of the pressure andsuction side, which are often a part of the solution. Numerical investigations have been completed tofind the basic mechanism of the unwanted phenomena and a practical solution has been proposed toovercome the problem. NACA 65-410 profile has been used for the validation over the wing and cascadeflows. The inverse design method with the proposed improvements is tested by imposing several arbitrarytarget pressure distributions around the wing profile. The lift coefficients of the original and redesignedgeometry are compared with each other.

Study on Random Initial Point Trajectory Planning for Missile Borne Unmanned AirVehicle

Wang Wei, Wang Hua, He LinShuBeijing University of Aeronautics and Astronautics (BUAA), China

As the location and velocity direction of the initial point for missile borne unmanned air vehicles projectedfrom missile is random, the hierarchical trajectory planning idea is proposed: global trajectory planningoff-line first and then partial trajectory planning on-line. A partial trajectory planning method ispresented, in which a geometric analysis method is adopted in the horizontal plane and cubic splinemethod is adopted in the vertical plane to plan the beginning part of the trajectory on -line. It cansatisfy the dynamic constraints for the initial and cut-in point, and it is simple and quickly, so as to meetreal-time request. The simulation results show that the proposed method is efficient and has a certainengineering value.

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Optimization of Free-Flying Time between Two Joined Stages for Solid-Fuel BallisticMissile

Htoo Hlaing Win, LinShu HeBeijing University of Aeronautics and Astronautics (BUAA), China

Optimization of free-flying times between two consecutive stages to enhance the overall range of three-stage solid ballistic missile conceptual design is presented herein. Free-flying time is of great importancein enhancing final range of missile. For a given optimized mass of vehicle, the range is maximizedby considering different free-flying times between first stage burn-out and second stage ignition as wellas between second stage burn-out and third stage ignition. Mathematical modeling is performed inSIMULINK. Genetic Algorithm is used as optimizer to get the optimum settings of free-flying times formaximum range.

Application of Sensitivity Region Based Robust Design Approach in MDO of Flight Vehicle

Ma Ying, He LinShuBeijing University of Aeronautics and Astronautics (BUAA), China

A novel robust design method was applied to multi-disciplinary design optimization of a flight vehicle.Math model of the robustness method based on concept of worst case sensitivity region (WCSR) wasintroduced. The proposed system was divided into five sub-disciplines according to design mission, namelystructure, weight, aerodynamics, propulsion and trajectory. Analysis models were established in differentprofessional tools. MDO model was built by integrating sub-disciplines into one framework. The dataflowin the framework was described. Traditional optimization method and WCSR based robustness methodwere both conducted. The robustness scheme was found without any presumed probability distributionof design variables, and compared to the traditional optimum scheme. The objective variation of robustscheme was limited in acceptable range while the system feasibility was maintained. The novel robustnessmethod is suitable for typical robust optimization problem of flight vehicle design, in which the probabilitydistribution and gradient information are not available.

Integrated Multidisciplinary Design and Multi-Objective Optimization Approach for SpaceLaunch Vehicle

Naeem Zafar, He LinShuSchool of Astronautics, BeiHang University, China

This paper proposes an approach for the integrated design and optimization of space launch vehicle,wherein the structure/weight, aerodynamics, propulsion and the trajectory system design are performedsimultaneously. The integrated design problem is posed as an optimization problem in which all thediscipline parameters constitute the design variables, which are used to optimize the multi-objectivefunction, thereby resulting in an optimal overall design. The approach is demonstrated by application tothe integrated design of a four stage solid launch vehicle. This work addresses three objectives for thedesign process: the minimization of total liftoff weight, total constraint violation and the minimizationof differences between the actual and desired orbital parameters. The mission is to deliver predefinedpayload to the low earth (circular) orbit. An existing, real world system has been used to validate themultistage launch vehicle system model.

Constraint Handling Approach using Multi-Objective Evolutionary Optimization

Naeem Zafar, He LinShuSchool of Astronautics, BeiHang University, China

This paper presents a new constraint handling scheme based on non-dominated sorting and crowdingdistance sorting theme. The proposed method treats the constraints as objective functions and handlesthem using the concept of NSGA-II. The approach does not require the use of a penalty function and itdoes not need niching to maintain diversity in the population. We validated the algorithm using severaltest functions taken from the specialized literature and compared the results with respect to algorithmsrepresentative of the state-of-the-art in the area. Results indicate that proposed scheme is a highlycompetitive alternative to solve constraint optimization problem.

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Index

ABBATE, Horacio A., 36ABDELLA, Kenzu, 33ACOPYAN, Vladimir A., 91ADESINA, Olufemi Adeyinka, 47AFZAL, Muhammad, 97AKCA, Haydar, 40ALCORTA-GARCIA, Maria Aracelia, 51ALEYAN, Omar Ali, 33ALLAHVIRANLOO, Tofigh, 33ALLAUDIN, Mohd Faizal, 81AMARAL, Ricardo Franco, 70AMIRI, Shahin Nayyeri, 33ANAVATTI, Sreenatha, 41ANGUIANO-ROSTRO, Sonia Guadalupe, 51ARAKAKI, Julio, 57ARANTES Jr., Gilberto, 81ARAUJO, Wagner Leite, 64ASATO, Osvaldo Luis, 57ASHOURIAN, Mohsen, 62ATTIA, Sid Ahmed, 81AXENOV, Vladimir N., 91AZADI, E., 51AZADI, M., 51

BAGHDADI, Mohamed Nadjib, 69BAHGAT, Ahmad, 84BAJODAH, Abdulrahman Hasan, 86BALAKRISHNAN, A.V., 28BALAKRISHNAN, S.N., 28BALINT, Agneta Maria, 34BALINT, Stefan, 34, 38BALKAN, Demet, 38BALTHAZAR, Jose Manoel, 28, 35, 67, 70, 73, 88, 91BALVEDI Jr., Eulo Antonio, 69BAMBACE, Luis Wwaack, 34, 93BARBANTI, Luciano, 67BARONI, Leandro, 82BARROS, Graiciany P., 64BECCENERI, Jose Carlos, 93BEHESHTI, Mohammad Hossein, 82BELGACEM, Fethi Bin Muhammad, 34BENDIKSEN, Oddvar O., 69BHOSALE, Bharat Namdeo, 45BIDEL, Antonio L., 70BINDEL, Daniel, 81BISWAS, Anjan, 45BRONZI, Anne Caroline, 49BUENO, Atila Madureira, 35

CACHUTE, Liomar de Oliveira, 86CAMARGO, Vanessa Avelino Xavier de, 35CAMPOLINA, Daniel, 65CAMPOS, Tarcisio Passos Ribeiro, 64CANTU, Hector Flores, 51CAO, Ma, 50CARDOS, Vladimir, 51, 52CARRARA, Valdemir, 77, 82, 83CARVALHO, Leopoldo Bulgarelli, 35CASTAO, Kleber Augusto Lisboa, 70CASTRO, Luis, 67

CAVALHEIRO, Andre Cesar Martins, 59CAVATONI, Andre, 65CAVE, Arthur, 93CERVANTES, Ilse Camacho, 86CHAO, Yan, 97CHAVARETE, F.R., 88CHAVARETTE, Fabio Roberto, 91CHIWIACOWSKY, Leonardo D., 90, 94CHU, Qi-Ping, 62, 92CLAEYSSEN, Julio R., 70COPETTI, Rosemaira D., 70COSTA, Antonella Lombardi, 64–66COSTA, Cristiano da Silva, 58COSTA, Esdras Teixeira, 35COVACHEV, Valery, 40COVACHEVA, Zlatinka, 40COVEI, Dragos-Patru, 49CUBILLOS, Ximena, 83CUNHA, Renan, 65

DA FONSECA, Ijar Milagres, 84DA SILVA, Clarysson A. Mello, 65, 66DA SILVA, Roberto Gil Annes, 69, 70DAMASCENO, Berenice Camargo, 67DE ASSIS, Sheila Crisley, 75DE MARQUI Jr., Carlos, 72DE MICCO, Luciana, 88DE MORAES, Rodolpho Vilhena, 75, 77DE OLIVEIRA, Elcio Jeronimo, 84DE OLIVEIRA, Pedro P.B., 35DE VISSER, Cornelis, 60DE WEERDT, Elwin, 92DEL RIO, Ezequiel, 53DIAS, Marcio Souza, 59DIAS, Susana, 83DIMBOUR, William Edmond, 56DIXIT, Nagaraj, 78DONOSO, Jose Manuel, 53DOS SANTOS, Fabio Luis Marques, 36DOWELL, Earl H., 71DUARTE, Ricardo Oliveira, 83DUMITRACHE, Alexandru, 52DUMITRESCU, Horia, 51, 52

ELASKAR, Sergio, 53, 87ERDOGAN, Fevzi, 47

FANG, Jiancheng, 43, 44FARAAG, Ahmad, 84FARAHANI, Mohammad, 89FARHAT, Nabil H., 40FAZELZADEH, S. Ahmad, 51, 71FEIJOO, Juan Alejandro Vazquez, 71FELIX, Jorge L.P., 91FELIX, Luiz Palacios, 88FENILI, Andre, 87FERNANDES, Sandro Da Silva, 29, 79FILHO, Diolino Jose dos Santos, 57–59FILHO, Edmundo Alberto Marques, 40FILHO, Waldemar de Castro Leite, 84FLEK, Michail B., 91

100

FORUSHANI, Mostafa Lotfi, 60, 88, 95FRANCISCO, Alexandre Lacerda Machuy, 75FRANCISCO, Cayo Prado Fernandes, 87FRUNZULICA, Florin, 52

GADELHA, Luiz, 83GARCIA, Roberta Veloso, 76GARCIA-TABERNER, Laura, 76GARRATT, Matthew, 41GASBARRI, Paolo, 94GHAYOUR, Mostafa, 90GHIA, Karman, 42GHIA, Urmila, 42GILBERTI, Mauricio, 65GIRAUDO, Pedro S., 36GIULIATTI WINTER, Silvia, 29GOES, Luiz Carlos Sandoval, 36, 70, 73GOMES, Vivian M., 76GOMES, Willer, 77GOMEZ, Arthur Torgo, 94GONZALEZ, Leandro, 36GUERMAN, Anna, 83GUOZHU, Liang, 95

HADZIBEGANOVIC, Tarik, 41HAMEDUDDIN, Ismail, 86HASHAM, Hasan Junaid, 94HERRERA-VALENCIA, Edtson Emilio, 49HILTON, Harry H., 73HORESTANI, Alireza Karami, 88, 95HOSEINI, Hanif Sadat, 71HOSEINYAR, Mohamad, 60, 95HOSSEINI, Ebrahim, 62HOVAKIMYAN, Naira, 29HUA, Cao Yi, 50HUA, Wang, 98HUAN, Jiang, 95HUNTER, Joyce A., 36HUSSAIN, Mukkarum, 97

IGAWA, Hirotaka, 73

JAGADEESH KUMAR, M.S., 49JAWORSKI, Justin W., 71JESKE DE FREITAS, Joslaine Cristina, 57JESUDASON, Christopher Gunaseelan, 55JULIA, Stephane, 59JULIA, Stephane, 57JUN, Xiang Hong, 98JUNQUEIRA, Fabricio, 57–59

KALOYANOVA, Valentina, 42KAMRAN, Ali, 95KARIMI, Bahran, 88KASAYNOV, Vladimir Alexandrovich, 61KASLIK, Eva, 41KENNERLY, Sam, 37KHALIQUE, Chaudry Masood, 45KIRR, Eduard-Wilhelm, 55KLINKE, Ana Rosa, 88KOMANDURI, Ananth, 81KORGUL, Artur, 37KORGUL, Rafal Andrzej, 37KUGA, Helio Koiti, 40, 76–78, 82, 83

KUKREJA, Sunil L., 30, 63

LARRONDO, Hilda Angela, 88LASIECKA, Irena, 30LIANG, Jin, 56LIMA, Francisco Welington, 41LINSHU, He, 98, 99LIU, Fengshan, 46LOWENBERG, Mark, 42LUBER, Wolfgang, 72LUISO, Javier E., 36

MACAU, Elbert, 31MAGLIONE, Livio, 87MAJEE, Narayan Chandra, 41MANSHADI, Mojtaba Dehghan, 89MAQBOOL, Zahid, 97MARCELINO, Eliel Wellington, 79MARQUES, Flavio D., 72MARTIN, Olga, 52MARTINEZ, Mariano, 87MARTINS-FILHO, Luiz de Siqueira, 81, 83MASDEMONT, Josep J., 76MATTHEIJ, Robert M.M., 31MECITOGLU, Zahit, 38MELO, Jose Isidro Garcia, 58, 59MERRETT, Craig G., 73MILUTINOVIC, Janko, 37MIYAGI, Paulo Eigi, 57–59MOKHTARI, Abolfazl, 42MOPHOU, Gisele, 56MULDER, Bob, 62MULDER, J.A., 92MWONGERA, Victor Mwenda, 42

N’GUEREKATA, Gaston Mandata, 56NABARRETE, Airton, 61, 96NAGY, Andras, 43, 98NAGY, Endre, 60NAKAMOTO, Francisco Yastami, 58NAKAMURA, Toshiya, 31, 73NANNAN, Zhang, 50NARAYANA, Mahesha, 50NAZARI, Sam, 89NAZIDI, Abbas, 71NETO, Atair Rios, 40NISAR, Khurram, 95NOVOZHILOV, Vasily, 37

OLIVEIRA, Thais Carneiro, 77OMEIKE, Mathew Omonigho, 48OO, Zaw Zaw, 96

PARDAL, Paula C.P.M., 77PEREIRA, Claubia, 64–66PESSOA, Marcosiris Amorim de Oliveira, 58PICCIRILLO, Vinıcius, 73PIQUEIRA, Jose Roberto Castilho, 35POKRAJAC, Dragoljub, 37POPESCU, Mihai, 53PRADO, Antonio F.B.A., 75–77, 79, 80PRASAD, Rajendra P., 78PRATOMO, Ariel, 81PUTTANNA, Vishwanath Kadaba, 50

101

RABELO, Marcos, 56RAFFIE, Ahmad, 84RAFIQUE, Amer Farhan, 95, 96RAMAZOTTI, Rodrigo Bassinello, 89RAMESH, Davood, 96RAMOS, Wemerson Leonardo, 35RAZA, Muhammad Aamir, 97REHMAN, Masood Ur, 84REIS, Patrıcia A.L., 64REZVANI, Vahid, 84RIBEIRO, Marcos Wagner Souza, 35RICCI, Mario Cesar, 78RIEHL, Roger Ribeiro , 86ROCCO, Evandro Marconi, 77, 79, 80ROHACS, Jozsef, 43, 61, 98ROJAS, Edixon, 67ROY, Amiya Busan, 41

SABIHI, Ahmad, 38, 89–91SAITOH, Saburou, 68SALEHI, Hamid, 90SALEHI, Mehdi, 90SAMAL, Mahendra Kumar, 41SANGARASHETTAHALLY, Ashoka B.G., 50SANTOS, Leonardo B. L., 90SATHISH KRISHNAN, P.S., 61SCINOCCA, Francisco, 61, 96SERPA, Alberto Luiz, 36SHAFAI, Bahram, 89SHAHGHOLIAN, Ghazanfar, 88SHEVTSOV, Sergey N., 91SIBILSKI, Krzysztof Slavomir, 43SIDDHESHWAR, Pradeep Ganapathi, 49, 50SIDDIQUI, Saman Mukhtar, 43, 44SILVA, Anabela, 68SILVA, Fabiano Cardoso, 66SILVA, Nubia Rosa, 59SILVA, Priscilla Andressa de Sousa, 53, 80SILVEIRA, Carlos, 79SINGH, Suresh G., 49SIVASUNDARAM, Seenith, 41SMIRNOV, Georgi, 83SOHAIL, Muhammad Amjad, 97SQUILLANTE Junior, Reinaldo, 59STROE, Ion, 53STUCHI, Teresinha de Jesus, 75SUKHANOV, Alexander A., 79, 80

TALEBI, Omid, 91TAMAGNO, Jose, 87TAMAYAMA, Masato, 74TANASIE, Loredana, 38TEHRANI, Omid Sharifi, 62TENGIZ, Ertan, 38TERRA, Maisa de Oliveira, 53, 75, 80TIMOFTE, Claudia, 54TITA, Volnei, 72TODOROV, Michail D., 46TORRES, Mauricio Torres, 51TRIGGIANI, Roberto, 55TSUKAZAN, Teresa, 70TUN, Soe Hlaing, 98TUNC, Cemil, 48

TURKMEN, Halit Suleyman, 38TUSSET, Angelo Marcelo, 91

UDWADIA, Firdaus E., 31UNGUREANU, Viorica Mariela, 54USMONOV, Botir, 74

VALE, Liliane Nascimento, 59VALETTE, Robert, 57VAN KAMPEN, Erik-Jan, 62VAN OORT, Eddy, 92VARATHARAJOO, Renuganth, 81VASSILYEV, Stanislav N., 32VAZIRY, Mohammad Ali, 89, 90VELHO, Haroldo Fraga de Campos, 90, 94VELOSO, Maria Auxiliadora Fortini, 64–66VENDITTI, Flaviane, 80VERESS, Arpad, 98VERGARA, Fany Mendez, 86VIO, Gareth A., 62

WANCHUN, Chen, 95WEI, Wang, 98WHITE, Brian, 32WIN, Htoo Hlaing, 99WINTER, Othon C., 32WYLLER, John, 41WYNN, Aung Ko, 50

XIAO, Ti-Jun, 56XIE, Dejun, 63

YAMIN, Muhammad, 96YING, Ma, 99YOUNIS, M. Yamin, 97

ZAFAR, Naeem, 99ZAKERZADEH, Mohammad Reza, 90ZANARDI, M.C., 76ZAPICO, Eduardo N., 36ZEESHAN, Qasim, 95ZENG, Jie, 63ZHANG, Guoping, 46ZHANG, Hua, 96ZIAEI-RAD, Saeed, 90

102

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