音響フィルエフェクト負荷時の宇宙機振動応答に関する簡易計算法(機械力学,計測,自動制御)

概要

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Spacecraft inside a fairing experiences severe high-level random acoustic loads during its launch. To confirm that the spacecraft structures and equipment withstand the launch environment, ground acoustic test is performed in the process of design. Spacecraft is exposed to a diffuse sound field in a large reverberant room during ground acoustic test. On the other hand, spacecraft, especially that has a narrow clearance between spacecraft exterior panel and fairing wall, is exposed to the standing wave sound field, which is called 'Fill Effect', instde a fairing during launch. Fill effect has been identified for these few decades, but there have been few reports to discuss the vibration response of a spacecraft induced by the fill effect. In this paper, the simplified approach is proposed to compare the vibration response of a spacecraft induced by standing wave sound field with the one by diffuse sound field. This approach can be dedicated to the desigh of a spacecraft which may be exposed to severe fill effect. One analysis example of a plate structure under these two sound fields is shown.
2010-11-25