@inproceedings{oai:jaxa.repo.nii.ac.jp:00005965,
 author = {高橋, 孝 and 村上, 桂一 and 青山, 剛史 and 相曽, 秀昭 and Takahashi, Takashi and Murakami, Keiichi and Aoyama, Takashi and Aiso, Hideaki},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2006論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2006},
 month = {Dec},
 note = {Spacecrafts are placed on top of launch vehicles, and are excited with mechanical (sinusoidal: 5-100 Hz and random: 20-2 kHz) vibrations via interfaces between spacecrafts and launch vehicles during launch. In addition to such mechanical vibrations, the spacecrafts are also exposed to acoustic pressure with wide frequency range (20-10 kHz). Lightweight and large area structures, such as solar arrays and antenna dishes, and components with relatively high natural frequencies are sensitive to acoustic loads. We have studied on a series of numerical simulation techniques for searching main acoustic sources at lift-off, and analyzing acoustic wave propagation, transmission through fairing and spacecraft acoustic vibrations. In this paper, we focus on spacecraft structural vibrations by acoustic loads using Finite Element Method (FEM), which is one of the most widely used deterministic prediction techniques other than statistical techniques such as Statistical Energy Analysis (SEA) to obtain detailed information. Then we investigate some fundamental random vibration analysis using some simple models to check FE modeling techniques and responses by structural analysis with random acoustic loads. Finally the simple primary structure with some stiffeners of a large spacecraft is modeled with FE, and is used to solve the eigen value problem, and transient and steady-state analysis with random acoustic loads., 資料番号: AA0063154021, レポート番号: JAXA-SP-06-010},
 pages = {113--118},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {音響によるロケットペイロードの構造振動に関する研究},
 volume = {JAXA-SP-06-010},
 year = {2006}
}