@inproceedings{oai:jaxa.repo.nii.ac.jp:00003650,
 author = {高橋, 知之 and 益田, 克己 and 下澤, 雄太 and 藤野, 貴康 and Takahashi, Tomoyuki and Masuda, Katsumi and Shimosawa, Yuta and Fujino, Takayasu},
 book = {宇宙航空研究開発機構特別資料: 第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 47th Fluid Dynamics Conference / the 33rd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第47回流体力学講演会/第33回航空宇宙数値シミュレーション技術シンポジウム (2015年7月2日-3日. 東京大学生産技術研究所), 目黒区, 東京, 47th Fluid Dynamics Conference /the 33rd Aerospace Numerical Simulation Symposium (July 2-3, 2015. Institute of Industrial Science , the University of Tokyo), Meguro-ku, Tokyo, Japan, The authors have proposed the control of aerodynamic heating and flight characteristics in Mars entry flights using Magnetohydrodynamic (MHD) flow control. In this study, numerical simulations of the flow field and the flight dynamics with MHD flow control during a Mars entry flight are conducted, in which the equations of magnetohydrodynamics and flight dynamics are solved in a coupled manner. The initial flight altitude and velocity are set to 60 km and 10 km/s, respectively. The forebody of an entry vehicle is an axisymmetric sphere-cone with a nose radius of 1.0 m. The mass of the vehicle is assumed to be 500 kg regardless of whether MHD flow control is utilized or not. The strength of magnetic field is varied parametrically in a range of 0 to 0.5 T. Numerical results show that MHD flow control can considerably increase a drag force at high flight altitudes such as 60 km with low atmospheric densities even when the strength of magnetic field is small such as 0.1 T. From the result, it is inferred that flight velocities at the altitudes with severe aerodynamic heating environment could be reduced by MHD flow control, which leads to a mitigation in aerodynamic heating in Mars entry flights., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630005025, レポート番号: JAXA-SP-15-013},
 pages = {159--164},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {火星突入におけるMHDパラシュート効果を適用した熱防御に関する数値解析},
 volume = {JAXA-SP-15-013},
 year = {2016}
}