Winter, B; Witting, M; Klein, M; Vaucher, D; Trompette, N; (1999) Systematic Investigations into the Numerical Response Prediction of a Solar Array Stack under Acoustic Excitation. In: Burke, WR, (ed.) Proceedings of the European Conference on Spacecraft Structures, Materials and Mechanical Testing. (pp. pp. 469-474). European Space Agency (ESA): Netherlands: Neuilly-sur-Seine, Noordwijk.

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Abstract

Satellites and payloads launched with large launch vehicles equipped with solid rocket boosters, e.g. ARIANE-5 and NSTS, will be subject to high noise levels during lift-off and atmospheric flight. Particularly sub-systems that have a large surface area and low mass can be very sensitive to acoustic excitation. Examples of such sub-systems are antenna reflectors and solar arrays. This paper presents the main results of a study that follows a systematic approach to investigate the numerical response prediction of a solar array stack, i.e. a solar array in stowed configuration, subject to acoustic excitation. The study has been carried out by Fokker Space (NL) and Metravib R.D.S. (F) under an ESA research and development contract. The hardware selected for the study has been the ARAFOM 5-panel wing. In the frame of the study, the wing has undergone a sequence of mechanical tests, namely a · modal survey test in air and in helium · shaker test with harmonic base excitation (sine test) · acoustic plane wave test · acoustic noise test Results of the modal survey and the sine test, particularly of the modal survey under helium providing a quasi-vacuum environment, have been used to correlate and update the initial mathematical finite element model of the wing. The target of this first step has been to establish a finite element model of the wing that represents as best as possible the dynamic characteristics of the the wing under vacuum conditions. The effects of the air on the dynamic response of the wing have then been modelled by a boundary element approach. This can accurately represent the fluid pressure and radiation impedance loads on the structure. A particular difficulty has been the modelling of the thin air gaps in between the individual panels of the wing. Responses of the wing to acoustic plane wave excitation have been computed and have been correlated with the responses measured from the acoustic plane wave testResponses have been evaluated in terms of structural accelerations and stresses, but also in terms of acoustic pressures in the inter panel gaps and the surrounding fluid. Eventually, the response of the wing to acoustic noise excitation has been numerically simulated using a superposition of plane acoustic waves, and the results have been correlated with the responses from the acoustic noise test.

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