@inproceedings{oai:jaxa.repo.nii.ac.jp:00017449,
 author = {横山, 信宏 and 鈴木, 真二 and Yokoyama, Nobuhiro and Suzuki, Shinji},
 book = {宇宙輸送シンポジウム　平成13年度, Proceedings of Space Transportation Symposium FY2001},
 month = {Apr},
 note = {In the past studies on the ascent trajectory optimization of a space plane, mass point approximation is usually used to simplify the problem. However, the validity of those obtained trajectory must be verified under the more precise dynamics model. Especially; if the rigid body dynamics is considered, the attitude control system and vehicle's flight trajectory usually have a strong coupling. Therefore, this study considers the trajectory optimization of a SSTO with the rigid body dynamics. New proposed method, in which the guidance law and the attitude control system are optimized simultaneously, is compared with the conventional method, in which the guidance law and the attitude control system are optimized sequentially, and the advantages of the new method are demonstrated., 資料番号: AA0033392021},
 pages = {83--86},
 publisher = {宇宙科学研究所, The Institute of Space and Astronautical Science (ISAS)},
 title = {剛体ダイナミクスを考慮した宇宙往還機の上昇飛行経路最適化},
 year = {2002}
}