@inproceedings{oai:jaxa.repo.nii.ac.jp:00004373,
 author = {高橋, 孝 and 金田, 英和 and 岩永, 則城 and 堤, 誠司 and Takahashi, Takashi and Kaneda, Hidekazu and Iwanaga, Noriki and Tsutsumi, Seiji},
 book = {宇宙航空研究開発機構特別資料: 第43回流体力学講演会: 航空宇宙数値シミュレーション技術シンポジウム2011論文集, JAXA Special Publication: Proceedings of 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011},
 month = {Mar},
 note = {第43回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2011 (2011年7月7日-8日. 早稲田大学国際会議場) 東京, 43rd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2011 (July 7-8,  2011. Waseda University, International Conference Center), Tokyo Japan, This study considers the numerical prediction of sound transmission through a spacecraft payload fairing and the acoustic environment inside it. In general, a spacecraft is exposed to acoustic pressure loading on the fairing in a wide frequency range, thus numerical predictions and analyses of the acoustic environment inside the fairing are of crucial importance for reliable spacecraft developments. The authors have focused on the application of the wave based method (WBM), which is a deterministic approach and has been proposed for numerical predictions up to the mid-frequency range. In this study, a series of sound source, sound propagation and sound transmission prediction is applied to a rocket launch environment. Firstly, the sounds generated by a rocket engine are predicted by using computational fluid dynamcs. Secondly, the sound propagation to a payload fairing is computed by the Ffowcs Williams and Hawkings approach. Then, thirdly, the vibroacoustic analysis of the fairing structure and an interior fairing is performed by the hybrid finite element - wave based approach, which is proposed to solve vibroacoustic problems by combining the strengths of both involved methods, namely the high computational efficiency of the WBM and the high geometrical flexibility of the finite element method. Moreover, in order to predict the fill-effect, which is recognized as the difference in sound pressure level with and without payload, rigid payload models inside the fairing are also employed., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0065207001, レポート番号: JAXA-SP-11-015},
 pages = {1--6},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {ハイブリッド有限要素: 波動ベース法に基づいたフェアリング内音響振動予測},
 volume = {JAXA-SP-11-015},
 year = {2012}
}