@inproceedings{oai:jaxa.repo.nii.ac.jp:00014458,
 author = {福田, 紘大 and 堤, 誠司 and 藤井, 孝蔵 and 宇井, 恭一 and Fukuda, Kota and Tsutsumi, Seiji and Fujii, Kozo and Ui, Kyoichi},
 book = {宇宙航行の力学シンポジウム, Symposium on Flight Mechanics and Astrodynamics},
 month = {Dec},
 note = {宇宙航行の力学シンポジウム(平成20年度)(2008年12月4～5日、宇宙航空研究開発機構宇宙科学研究本部), Symposium on Flight Mechanics and Astrodynamics 2008 (December 4-5, 2008. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)), Sagamihara, Kanagawa Japan, As part of the studies of the advanced solid rocket in JAXA,numerical simulations were carried out to investigate the effect of the flame deflector(FD) shape on the acoustic environment at lift-off. Firstly, verification of the simulation methodology is carried out by comparing the numerical results with measured data in a static firing test. From the results, it is confirmed that the numerical simulation is effective for acoustic prediction. The numerical simulation of acoustic environment of the advanced solid rocket at lift-off indicates that there are mainly two types of acoustic sources;1) impingement noise due to the interaction of the exhaust plume and FD, and 2) Mach wave generated by the flapping motion of the plume flowing over the FD. The impingement noise is a dominant noise source, because it propagates directly to the vehicle. Based on the knowledge obtained here, it is revealed that initial inclination of the FD should be steep for the reduction of the impingement noise. Moreover, the FD is desirable to have a curved shape both for reducing the size of the FD and for preventing another impingement noise that onginates in the rapid change of the FD shape., 資料番号: AA0064729035},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {CFD技術を用いた次期固体ロケット射点検討に向けた取り組み},
 volume = {平成20年度},
 year = {2009}
}