CENTRE NATIONAL D'ETUDES SPAT1ALES

Premier colloque europeen sur la Technoiogie des LanceursFirst European conference on Launcher Technology

VIBRATIONS DES LANCEURS

LAUNCH VEHICLE VIBRATIONS

ACTESPROCEEDINGS

UNtVERGiTATGSIBLiGTHEKHANNOVER

14-16 decembre1999

Centre de Congres Pierre Baudis

Toulouse - FranceUB/TIB Hannover 89121 590 71.2.

Session d'ouverture / Opening session '. 21M. DESLOIRE, CNES, Evry, France

Conference generate / Keynote lecture

Control of the Ariane 5 vibrations: the development program challenges 31B. CHEMOUL, CNES, Evry, France

Delta III upper stage shock and vibroacoustic and development testing 53E.S. ROSENBAUM, Boeing Space and Defense Systems, Huntington Beach, USA

Overview of PROTON and ROCKOT dynamic environments 63A.K. NEDAIVODA, S.A. PETROKOVSKI, Salyut DB of Khrunichev, Moscou, Russie

Overview of GSLV dynamic environment 101R. V. PERUMAL, N. JAYACHANDRAN NAIR Vikram Sarabhai Space Centre, Trivandrum, India

VEGA small launcher dynamic environment modelling 113P. BAIOCCO, A. PREVE, FIAT AVIO, Roma, ItalyM. BONNET, VEGASPAZIO, Colleferro, Italy

Overview of ATLAS V Dynamic Environments 125G. SOWERS, Lockheed Martin Astronautics, Denver, USA

Session 1Environnement acoustique au decollage et methodes de reduction du bruitAcoustic environment during launch and lift-off, noise reduction methods

Aerodynamic and acoustic environment of a highly supersonic hot jet 135J. VARNIER, D. GELY, ONERA, Chatillon, FranceH. FOULON, CEAT, Poitiers, France

An experimental investigation of the acoustic field appearing during rocket ascent from a launching PAD 147D. MEL'NIKOV, V. KOMAROV, G. DUMNOV, Keldysh Research Center.Moscow, Russia

Direct computation of aerodynamic noise using large eddy simulation 157C. BOGEY, C. BAILLY, D. JUVE, Laboratoire de Mecanique des Fluides et d'Acoustique, Eculiy, France

Some unsteady sound phenomena during Ariane 5's lift-off 159J. VARNIER, C. BRESSON, ONERA, Chatillon, France

Technique for predicting the acoustical environment resulting from a launch vehicle enginejets interaction with a launch PAD 169V.C. DEMENTJEV, S.P. RYBAK, RKK "Energia", Korolev, Moscow region, RussiaV.V. KOUDRIAVTSEV, A.V. SAFRONOV, TSNIIMASSH, Korolev, Moscow region, RussiaB. TROCLET, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, France

Linear contribution of instability waves to supersonic jet noise 179C. BAILLY, Laboratoire de Mecanique des Fiuides et d'Acoustique, Eculiy, FranceM. POLLET, Aerospatiale Espace & Defense, Les Mureaux, France

Session 2Problemes vibroacoustiques : conception et optimisation de systemes d'attenuation passifs ouactifsVibro-acoustic problems: design and optimization of passive or active attenuation systems

Vibro-acoustic study of satellites excited by an external field . . . .»—. . ............... ............—.—191P. BLANC, Principia R.D., La Seyne sur Mer, FranceP. ROUX, CNES, Evry, France

Synthesis of vibroacoustic studies performed during Ariane 5 program. ...... . . .. ...... 201B. TROCLET, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, FranceB. CHEMOUL, P. ROUX, CNES, Evry, FranceD.GELY, G. ELIAS, ONERA, Chatillon, France

Frequency smoothing and structural path analysis for complex structures at medium frequencies 211A. GIRARD, 0 . FINKLER, Intespace, Toulouse, France

Session 3Environnement aerologique : fluctuations de vent, turbulence atmospherique et rafalesAerological environment: wind fluctuations, atmospheric turbulence and gusts

Some experimental and theoretical approaches of wind aloft for space activities 223B. JACQUEMIN, CNES, Kourou, French GuyanaT. VOIRON, CNES, Evry, France

Optimal filtering of wind and temperature balloon sounding........................... 233J.P. CHRETIEN, ONERA, Toulouse, France

Wind forecast for spatial centre of French Guyana 243C. SKANDRANI, C. MARAIS, S. JOURDAIN, Meteo-France, Toulouse, France

Session 4Comportement dynamique lateral des lanceurs :influence sur le controle de vol et la determination des efforts generauxLaunch vehicles' lateral dynamic behaviour: influence on flight control and the determination ofgeneral loads

A solution for structural coupling in a thrust vector control system (TVC) 255P. TRILLAT, D. MARTINEZ, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, France

Optimum conical shell for dynamic behaviour . 265A. GIRARD, M. PAWLOWSKI, Intespace, Toulouse, France

Launcher general loads specification and validation logic ....................... 273D. HAERENS, P. EYSSAUTIER, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, France

Consideration of vehicle flexibility during atmospheric flight and its influence on controllabilityand lateral loads in ISRO launch vehicles ......287K l . HANDOO, K. PRABHAKARAN,S. MURALIDHARAN, D.M. RAO, B. SASEENDRAN, Vikram Sarabhai Space Centre, Trivandrum, India

S e s s i o n 5 / 1Interactions fluide-structure: ballottementsFluid/structure interactions: sloshing

An advanced modelling of liquid sloshing in launchers . 303J.M. LE GOUEZ, C. DE JOUETTE, 0. LAGET, Principia R&D, La Seyne sur Mer, FranceN. PREIONI, CNES, Evry, France

S e s s i o n 5 / 2Interactions fluide-structure : aerodynamique instationnaire et aeroelasticiteFluid/structure interactions: unsteady aerodynamic and aeroelasticity

Analysis of steady and unsteady aerodynamic loads on the ARIANE 5 launch vehiclerear part during flight ascent 319B. TROCLET, F. JACQUOT, H. BOUCHARDON,M. DEPUYDT, F. RAMIANDRASOA, Aerospatiale Espace & Defense, Les Mureaux, France

Experimental and numerical aerodynamic simulations of an oscillating generic launcher 327J. OSWALD, F. DAVID, ONERA, Chatillon, FranceF. RUFFINO, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, France

Unsteady phenomena in flow over launch vehicles 337B.N. DANJKOV, ES. KORMENKO, V.V. KOUDRAVTSEV, TSNIIMASSH, Korolev, Mosoow region, Russia

S e s s i o n 5 / 3Interactions fluide-structure: hydroelasticiteFluid/structure interactions: hydroelasticity

Vibration analysis of elastic tanks partially filled with incompressible liquids in presence of a gravity field... 351S. SCHOTTE, ONERA, Chatillon, FranceR. OHAYON, CNAM, Paris, France

Dynamic pressures acting on the inner bulkhead of the ESC-LH2-tank 361S. DIEKER, Reimerdes + Dieker Ingenieure GbR, Bremen, GermanyR. BECK, MAN Technoiogie AG, Karlsfeld, GermanyR. GAJDACZ, DaimlerChrysler Aerospace AG, Bremen, Germany

The influence of compressibility on the dynamic behaviour of the ESC-tanks 371A. RITTWEGER, R. GAJDACZ, DaimlerChysler Aerospace, Bremen, GermanyS. DIEKER, Reimerdes - Dieker Ingenieure GbR, Bremen, Germany

S e s s i o n 6 / 1Previsions des chocs et methodes d'attenuationShock predictions and attenuation methods

Effects on real or simulated pyroshocks on electronic equipments 383H. GRZESKOWIAK, Matra BAe Dynamics France, Velizy-Villacoublay, France

Predictions of an electronic equipment response to a pyrotechnic shock excitation 397E. BODIN, B. BREVART, T. YOUSSEFI, Alcatel Space Industries Toulouse, France

Pyrotechnic shocks • SYLDA 5. Analysis of the 250 Hz mode occuring during short fairing cut-off 405M. DOMMANGET, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, France

Ariane 5 Shock attenuation device .......................................................................................................419P. BROTONS, E. CABRERA, F. CESPEDOSA,M. LANCHO, J.I. URIBARRI, Casa Space Division, Madrid, Spain

SYLDA 5 dynamic response identification for the HSS-separation shock 424B. KOTZIAS, W. HUBLER, DaimlerChrysler Aerospace, Bremen, Germany

S e s s i o n 6 / 2Previsions des chocs et methodes d'attenuationShock predictions and attenuation methods

SAC A, a recovery damping system to reduce shock at Ariane 5 front cone ejection 435F. JANON, S. GUINARD, Techlam, Cernay, France

Analysis of wave propagation in pyrotechnical shock tests 443G. BORELLO, InterAC, L'Union, France

Computational simulation of an expanding tube separation device 451M. QUIDOT, S. LECUME, D. DESAILLY, SNPE, Vert-le-Petit, FranceJ.P. DELON, Dassault Aviation, Velizy-Villacoublay, France

A computational approach to pyro-impact on 3D-structures with many frictional contacts 461H. LEMOUSSU, P. LADEVEZE, P.A. BOUCARD, LMT-Cachan, Cachan, France

Shock characterization by amplitude / duration spectrum ........471A. GIRARD, 0. FINKLER, Intespace, Toulouse, France

Pyroshock simulation using the Alcatel ETCA test facility 479E. FILIPPI, Alcatel ETCA, Charleroi, BelgiumH. ATTOUOMAN, C. CONTI, Faculte Polytechnique de Mons, Mons, Belgium

S e s s i o n 7 / 1Charges dynamiques et problemes de stabilite lies a la propulsion liquide : effet pogo ettransitoires de pousseeDynamic loads and stability problems due to liquid propulsion: pogo effect and thrust transients

Prediction of A5 low frequency dynamic environment: models - methods - results 493P. LAUMOND, N. BONNET, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, France

Analysis and modeling of vuicain engine shutdown transient chugging. 507G. ORDONNEAU, ONERA, Chatillon, FranceN. GIRARD, CNES, Evry, FranceN. DAVID, SNECMA, Vernon, France

Use of an elastic-acoustic element for pogo stability analysis of the Ariane 5 upper stage 517Y. MAURIOT, G. ORDONNEAU, N. PIET, ONERA, Chatillon, France

The prevention of the Pogo effect on the Ariane 5 launcher 527S. MULLER, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, FranceN. DAVID, SNECMA Division SEP, Vernon, France

S e s s i o n 7 / 2Charges dynamiques et problemes de stabifite Kes a la propulsion a poudte: oscillations depressionDynamic loads and stability problems due to solid propulsion: pressure oscillations

Ariane 5 - IMPS P230 thrust oscillations: theoretical analysis and tests results 539P. BAIOCCO, FIAT AVIO, Roma, ItalyF. SOULA, SEP, Saint Medard en Jalles, FranceB. PIN, Europropulsion, Suresnes, France

Recent advances in the prediction of SRM thrust oscillations 551P. LE BRETON, SNPE, Saint Medard en Jalles, FranceJ. F. GUERY, SNPE, Vert-le-Petit, FranceF. VUILLOT, ONERA, Chatillon, FranceM. PREVOST, ONERA, Toulouse, France

The Ariane 5 MPS aeroacoustics research at VKI: an overview 569J. ANTHOINE, 0. REPELLIN, J.M. BUCHLIN,D. OLIVARI, Von Karman Institute for Fluid Dynamics, Rhode-St-Genese, Belgium

The DIAS, a flexible system especially design for Ariane 5 EAP thrust oscillations filtering 579P. BARA, V. JACQUEMART, S.A.B.C.A., Bruxelies, BelgiumS. GUINARD, F. JANON, Techlam, Cernay, France

A damped vibration absorber for ARIANE 5 Plus 590P. MOUREY, CNES, Evry, FranceJ. EDER, Kayser-Threde GmbH, Munchen, Germany

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S e s s i o n 7 / 3Charges dynamiques induites par la propulsion: methodes de reductionDynamic loads induced by propulsion: reduction methods

Low frequency characterization of the Aestus engine 602P. SPAGNA, F. FASSL, DaimlerChrysler Aerospace, Munchen, GermanyY. MAURIOT, G. ORDONNEAU, ONERA, Chatillon, France

Dynamic analysis and optimization of the AR5 cryogenic upper stage ESC for tailoring of payioad response 620P. BORWARDT, W. BEUCHEL, R. BARTELS, DaimlerChrysler Aerospace AG, Bremen, Germany

Optimization of the new upper stage (cryogenic) of Ariane 5 on a dynamic point of view .--. 634P. MOUREY, CNES, Evry, FranceC. GRATIEN, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, FranceR. JAKEL, DaimlerChrysler Aerospace AG, Bremen, GermanyY. LEFEBVRE, GECI FRANCE, Evry, France

Session 8Qualification des lanceurs et charges utilesQualification of launch vehicles andpayloads

Shogun, a shock test device for satellites ........................................................... .. 648B. COLEAU, J.P. DELON, B. MARTIN, Dassault Aviation, Velizy-Villacoublay, France

Vibration and acoustic testing for Mars micromission spacecraft ..̂ ........................... . 660D.L. KERN, C.-P. KUO, T.D. SCHARTON, Jet Propulsion Laboratory, Pasadena, USA

Early prediction of shock environment for the SMART-1 satellite 670L. FANCHI, R. GRUNAGEL, J.L. PARQUET, M. KLEIN, ESA/ESTEC, Noordwijk, The Netherlands

Evaluation of SRS ratios for the definition of satellite equipment shock environment........... . ... ... 678J.L. PARQUET, S. KIRYENKO, M. KLEIN, ESA/ESTEC, Noordwijk, The Netherlands

Ariane 5 shock qualification logic for SPOT 5/HELIOS 2 satellites 688K. MERCIER, P. ROY, R. COLAS DES FRANCS, CNES, Toulouse, FranceJ.M. PIERINET, Matra Marconi Space, Toulouse, France

Session 9Techniques de mise au point et de validation des modeles dynamiquesTuning and validation techniques for dynamic models

New launcher design procedures for parameter uncertainty using fuzzy finite elements..... . 700D. VANDEPITTE, D. MOENS, K.U. Leuven, Leuven, Belgium

Updating Ariane 5 booster models using modal survey and real firing test data ... . .. . .......710J.P. LERICHE, 0 . QUEMERAS, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, FranceS. DILLINGER, A. GRILLENBECK, Industrieanlagen-Betriebsgesellschaft GmbH, Ottobrunn, GermanyP. MOUREY, CNES, Evry, France

Constitutive relation error estimators in dynamic model updating of dissipative structures 720A CHOUAKI, A. DERAEMAEKER, P. LADEVEZE, S. LE LOCH, LMT-Cachan, Cachan, France

Session 10Synthese des resultats de mesures en vol / Synthesis of in-flight results

Estimation of in-flight structural dynamics models of the ARIANE 5 launcher 732L. HERMANS, H. VAN DER AUWERAER, LMS International, Leuven, BelgiumD. HAERENS, Aerospatiale Matra Lanceurs Strategiques & Spatiaux, Les Mureaux, FranceA. BENVENISTE, M. GOURSAT, INRIA/IRISA, Rennes, FranceP. MOUREY, CNES, Evry, France

Solving the aeroelastic problem and computing internal loads for a three-dimensionnal launcher ............740F.X. GERBAUX, J. NATUREL, V. LARCHER, Bertin technologies, St Quentin en Yvelines, France

Lateral flight loads of the ARIANE 4 launch vehicle during INTELSAT 6 launches 748J.P. DULOUT, Arianespace, Evry, France

Modal tracking for a three-dimensionnal launcher using perturbation method,application to the ARIANE 5 Launcher ...................................................................................758J. NATUREL, F.X. GERBAUX, V. LARCHER, Bertin technologies, St Quentin en Yvelines, France

Session poster / Poster session

1 • Atmospheric measurements from ground to 100 km height 768J. DIOUGOANT, Delegation Generale pour I'Armement, Brest Naval, France

2 • Sea-landing modelling of ARD spacecraft and launcher elements 776Y. GOURINAT, F. BEN YAHIA, ENSICA, Toulouse, France

3 - Vibration tests on large aircrafts 784P. FARGETTE, ONERA, Chatillon, France

4 - Modeling and validation of a solid rocket motor dynamic model 792F. SOULA, SEP division de SNECMA, Saint Medard en Jalles, France

5 - Launch load monitoring on COSMOS LV via ORBCOMM and internet 802I. KALNINS, OHB-System GmbH, Bremen, Germany

6 - Improvement of Levy-Cahill/Williams matrix method applied for coupled load analysisof launch vehicle PROTON and spacecrafts 804Y. ILIENKO, K.P. KULAKOVA, N. ZOUEV, Salyut DB of Khrunichev, Moscow, Russia

Conclusion generale / General conclusion 826

Session de cloture / Closing session 834

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