J. Phys. IV France
Volume 04, Numéro C5, Mai 1994
3ème Congrés français d'acoustique
3rd French conference on acoustics
Page(s) C5-1013 - C5-1016
3ème Congrés français d'acoustique
3rd French conference on acoustics

J. Phys. IV France 04 (1994) C5-1013-C5-1016

DOI: 10.1051/jp4:19945223

Une méthode d'analyse des problèmes acoustiques externes et internes en aéronautique. Illustrations dans le cas du véhicule spatial Hermes


1  Dassault Aviation, Centre Spatial Dassault, 17 avenue Didier Daurat, BP. 23, 31701 Blagnac, France
2  Dassault Aviation, 78 Quai Marcel Dassault, 92214 Saint Cloud, France

To solve aeronautical and aerospace industrial vibro-acoustic problems (cabin noise, panel radiation, vibration environment, ...) Dassault Aviation has developed an attractive computation strategy. Actually, in the so-called 'Coupling Finite Element and Singularity method' (CFES), each field (structure dynamics, interior acoustics, exterior acoustics) is calculated independently from one another with the best suitable methods. As there is no reason to have coincidence between these optimized subsystems, elasto-acoustic couplings are performed via an original technique based upon the introduction of interfacing models both independent of structure and acoustic approximations. The effectiveness of this approach is fully illustrated through the studies undertaken for Hermes spacecraft project. Severe acoustic loadings were identified (engines noise at launch, take off transonic aeronoise, phases of maximum dynamic pressure during atmospheric reentry) which may have caused damage to the 'nose' of this glider. Thus, taking profit on our computational organisation, numerical simulations were done considering a mechanical model (of the nose) coupled with the inside acoustic cavity. This made possible numerous sensitivity analyses from the study of correlation length effect to the determination of equivalent loads for shaker tests on a scaled-down model.

© EDP Sciences 1994