JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
title火星突入カプセルの設計における CFD の適用事例 その2: 超音速・亜音速領域での空力解析
Other TitleCFD Application Examples in Design Studies of a Mars Entry Capsule, Part 2: Supersonic/Subsonic Aerodynamics
Author(jpn)松山, 新吾; 藤田, 和央
Author(eng)Matsuyama, Shingo; Fujita, Kazuhisa
Author Affiliation(jpn)宇宙航空研究開発機構(JAXA); 宇宙航空研究開発機構(JAXA)
Author Affiliation(eng)Japan Aerospace Exploration Agency (JAXA); Japan Aerospace Exploration Agency (JAXA)
Issue Date2017-12-27
Publisher宇宙航空研究開発機構(JAXA)
Japan Aerospace Exploration Agency (JAXA)
Publication title宇宙航空研究開発機構特別資料: 第49回流体力学講演会/第35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 49th Fluid Dynamics Conference / the 35th Aerospace Numerical Simulation Symposium
VolumeJAXA-SP-17-004
Start page117
End page122
Publication date2017-12-27
Languagejpn
eng
AbstractThis paper describes CFD application examples to predict supersonic/transonic/subsonic aerodynamics in design studies of a Mars entry capsule for future Japan’s Mars exploration mission. Firstly, an example of the validation study for the JAXA’s in-house CFD code against aerodynamic database obtained by supersonic wind tunnel test is briefly presented. Subsonic, transonic, and supersonic flows around a 70 deg sphere-cone capsule model with support sting are simulated using large-eddy simulation (LES). The static aerodynamic coefficients obtained by LES show good agreement with the wind tunnel data. The obtained solutions by LES revealed the wake flow dynamics and their effects on the capsule aerodynamic characteristic. Secondly, the static aerodynamic simulations of sphere-cone shaped capsule and detached forebody aeroshell are conducted for supersonic and subsonic flight regimes near the parachute deployment point. The results demonstrated the capability of LES to predict the unsteady separated wake flows over sphere-cone shaped capsules. Finally, dynamic stability characteristic of a Mars entry capsule is investigated using LES. The dynamic simulations are conducted for the parachute deployment point at Mach 1.6. To investigate the influence on the dynamic stability characteristics, the moment of inertia is varied from 1 to 100 kg・m2. The preliminary results by the single degree-of-freedom simulations indicate that the dynamic stability characteristics are very sensitive to the moment of inertia.
Description会議情報: 第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム (2017年6月28日-30日. 国立オリンピック記念青少年総合センター), 渋谷区, 東京
形態: カラー図版あり
Meeting Information: 49th Fluid Dynamics Conference /the 35th Aerospace Numerical Simulation Symposium (June 28-30, 2017. National Olympics Memorial Youth Center), Shibuya-ku, Tokyo, Japan
Physical characteristics: Original contains color illustrations
Document TypeConference Paper
JAXA Category特別資料
NASA Subject CategoryFluid Mechanics and Thermodynamics
ISSN(online)2433-2232
SHI-NOAA1730011017
Report NoJAXA-SP-17-004
URIhttps://repository.exst.jaxa.jp/dspace/handle/a-is/865297


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