@inproceedings{oai:jaxa.repo.nii.ac.jp:00004924,
 author = {石井, 達哉 and 生沼, 秀司 and 賀澤, 順一 and 福田, 紘大 and 堤, 誠司 and 宇井, 恭一 and 峯杉, 賢治 and 藤井, 孝蔵 and Ishii, Tatsuya and Oinuma, Hideshi and Kazawa, Junichi and Fukuda, Kota and Tsutsumi, Seiji and Ui, Kyoichi and Minesugi, Kenji and Fujii, Kozo},
 book = {宇宙航空研究開発機構特別資料: 第41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2009論文集, JAXA Special Publication: Proceedings fo 41st Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2009},
 month = {Feb},
 note = {平成21年6月18-19日. 宇宙航空研究開発機構調布航空宇宙センター, 18 June-19 June, 2009, Japan Aerospace Exploration Agency, High-speed and high-temperature gas flow of the rocket motor radiates enormous level of sound while launching, leading to crucial damage on the payload. Alleviation of such acoustic damage is a key to a reliable and competitive rocket system. JAXA, planning an advanced solid rocket system, started design of the launch-pad with less acoustic impact. Semi-empirical model such as NASA-SP-8072 and numerical model by computational aero-acoustics (CAA) have been introduced to establish better design guideline. However, more experimental data in static firing tests should be obtained for validation and improvement of both models. Meanwhile, we had an opportunity of testing three solid rocket motors; NAL735, M24 and KM-V1 since December in 2007. This paper outlines acoustic measurement carried out in the ground firing tests of these motors., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064672026, レポート番号: JAXA-SP-09-011},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {地上燃焼試験における固体ロケットモータの音響計測},
 volume = {JAXA-SP-09-011},
 year = {2010}
}