Post on 17-Jan-2016
description
Progress Presentation
ARDB Aircraft Systems Panel
October 22, 2002
RCI, Hyderabad
Centre for Aerospace Systems Design & Engineering
Indian Institute of Technology Bombay
Objectives, Mission
SDE EducationMulti-disciplinary Design Optimisation
System Level Studies
CASDE Shall Strive to Develop and Retain
Strong Links With Indian Aerospace Industry
And Shall
Engage in R&D Activities
With
Worldwide Visibility
October 12, 2001 to October 22, 2002
EVENTS • Oct 12, 2001 : ARDB ASP Meeting• Nov 22, 2001 : ARDB TC Meeting• Jan 2, 2002 : Prof. A Joshi is new Head• Feb 4, 2002 : VSSC hands over LVS• Apr 13, 2002 : 1-Day Workshop on MAV• Jun 4-6, 2002 : 3-Day Workshop on MDO• Jun 10, 2002 : 3rd JPC Meeting• Jun 27, 2002 : ARDB Meeting.
Visitors • Mr. Prahlada, Member, JPC• Dr. BN Suresh, Member, JPC
Visiting Faculty • Dr. Kota Harinarayana• Dr. PB Nair, Southampton• Dr. Sudhakara Rao, VSSC
http://www.casde.iitb.ac.in/History/
System Level Studies
http://www.casde.iitb.ac.in/History/PastEvents/mav-ws/mav-ws-summary.pdfhttp://www.casde.iitb.ac.in/History/PastEvents/mav-ws/mav-ws-conclusion.pdf
1-Day MAV Workshop (April 13, 2002)• OILS : Joint Conceptual Studies. CASDE & Prof. Gandhi (ME), IITB (June-July, 2002)• Propulsion systems test facility
y = 8.6958x2 + 14.881x - 6.0936
y = 8.0472x2 + 13.491x - 2.4657
-100.0
0.0
100.0
200.0
300.0
400.0
500.0
600.0
700.0
800.0
900.0
0.00 1.00 2.00 3.00 4.00 5.00 6.00 7.00 8.00 9.00 10.00
Voltage across motor (in V)
thru
st (
in m
N)
measured values
manufacturers data
Poly. (measured values)
Poly. (manufacturers data)Solar Powered Aircraft• CASDE & Tata BP Solar • Partial success
Applied MECHATRONICS Course
Course with a difference
2 theory and 3 lab hours per week.
Project on a miniature ground vehicle.
sensors, actuators, micro-controllers, etc
http://www.casde.iitb.ac.in/IMSL/
New Open M. Tech Programme
RAP - Trajectory Recording
Ram Air Parachute flight tests
GPS data for 45 mins
27.096 27.098 27.1 27.102 27.104 27.106 27.108 27.11 27.11277.9
77.92
77.94
0
2000
4000
6000
8000
10000
12000
3-Day Workshop (June 4-6, 2002)
• Progress Aero-elastic Capability Further
• Develop MDO-Framework Version-II
• Composite teams to solve problems
International Conference
“Modeling, Simulation, Optimization
For Design of Multi-disciplinary
Engineering Systems”
September 2003http://www.casde.iitb.ac.in/mso-dmes/
Ph. D Scholars • DRDL - Hypersonic Vehicles
• VSSC - Design under Uncertainty
• VSSC - Vehicle + Trajectory Optim
• VSSC - Re-usable Launch Vehicles
P&W shows interest
MDO Studies gather momentum
Software Architecture
Optimizer FSQP
I
N
T
E
R
F
A
C
E
History Block
Input Processor
Output Processor
Aerodynamics (VLM)
Structures MSC/
NASTRANNASTRAN
Interface
Analysis Block
AeroelasticityIterator
Simultaneous Aerodynamic and Structural Optimization of Aircraft Wing
NASTRAN Interface
Code
Wing Geometry Meshing
Parameters
Load Transformation
Input file for NASTRAN
Output file of NASTRAN
MSC/ NASTRAN
Loads Transferred on
FEM Nodes
FEM Nodal Co-ordinates
Aerodynamic Loads on Quarter Chord points of
VLM Panels
Max Stresses, Displacements, twist and
Wing Structural
Mass
Nodal displacements
Panel Angles of Attack
VLMWing Geometry,Mach Number
DisplacementTransformation
Analysis Block
(File parsing)
(Auto mesh & data-deck
Generation)
Figs. 1-4: Development of Wing model and loads
Figs. 5-6: Load Transformation Process
5 - Aerodynamic Loads and its Response
6 - Structurally equivalent Loads and its ResponseFEM Model
Entry Exit
y, z pmerger
x0 LmLm/2pentry
y1, z1 y2 ,z2
x
0 LL/3
Aentry
Aexit
2L/3
1
2
Mean Flow line variation
Area variation
3D duct (Y=0.1, Z=0.1, 1=0.1, 2=0.1)
Low Fidelity Analysis (LFA)• Wall angle < 6°• Diffusion angle < 3°• 6 * Eq. Radius < ROC• Pressure Recovery
Parameterization
• MFL shape is defined by two cubic splines. (y , z)
• Area variation from entry to exit is specified as cubic spline. (1 , 2)
Feasible space (LFA)
0
Response Surface Method• Define reduced design space through LFA• DOE in reduced design space• Perform high fidelity analysis at DOE
points (NS simulation for distortion and swirl)
• Replace high fidelity analysis with response surface
• Optimize using RS
3D-Duct Design using Variable Fidelity RSMhttp://www.casde.iitb.ac.in/MDO/3d-duct/
y z
Architectural Design• Intuitive GUI• object-oriented• handle large problems• multi-user support• standards based
Problem Formulation• complex branching• legacy/proprietary code• multiple optimizers
Problem Executtion• automate data movement• visualization• heterogeneous computing• distributed computing• batch processing
Information Access• database management• monitoring system status• fault tolerance
MDO Framework Requirements
DataServer
Sequence of Execution
Analysis 2 Analysis 3 Analysis 4
InitialData
Result
Analysis 1
1
23
45
6
Framework Version 1: Data server
Database
Configuration
ExecutionManager
Sequence Logic
MDOController
Status/LogHandler
DataServer
OPT1
Optimizer Manager
OPT2 OPT3
AM1
Agent
AM2 AM3
GUI
Framework Version 2: Architecture
Problems Attempted• Airborne Early Warning System• 3D Duct Design• Transport Aircraft Wing• MAV design
MDO Framework Development
CASDE – Proposal for Phase II
• 2 Years– MDO– SDE Education– Integrated Modelling & Simulation
• Funds – 53.475 + 44.275 = 97.75
• Draft Proposal pending with JPC/SPC
Interested in CASDE?
Visitors to http:// www.casde.iitb.ac.in/25 Visitors per day
htt p
: //w
ww
.ca s
de.i i
t b.a
c .in
/usa
ge/
Visit 100 schools
100th Year of First FlightTraveling CourseOn
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Aerospace to
Schools & Colleges.
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