JAXA Repository / AIREX 未来へ続く、宙(そら)への英知
SA0200033.pdf4.06 MB
titleThe Aerodynamic Data Base for Asteroid Sample Return Capsule
Author(jpn)平木, 講儒; 稲谷, 芳文
Author(eng)Hiraki, Koju; Inatani, Yoshifumi
Author Affiliation(jpn)宇宙科学研究所; 宇宙科学研究所
Author Affiliation(eng)Institute of Space and Astronautical Science (ISAS); Institute of Space and Astronautical Science (ISAS)
Issue Date2003-03
Institute of Space and Astronautical Science
Publication titleThe Institute of Space and Astronautical Science report. S.P.
Aerodynamics, Thermophysics, Thermal Protection, Flight System Analysis and Design of Asteroid Sample Return Capsule
Start page345
End page363
Publication date2003-03
AbstractThe MUSES-C sample return capsule is expected to carry back to earth the collected sample from Asteroid 1998SF36 in 2007. The capsule has a blunted-cone forebody with a semi-apex angle of 45 degree, and has no active equipment for attitude control. Therefore, it should have passive aerodynamic stability all over the reentry flight. For a dispersion analysis of a landing point, it is indispensable the aerodynamic characteristics of the SRC over an entire flight regime, from rarefied gas to low-subsonic regime. The damping characteristics of the capsule over the entire flight is also required for a six-degree-of-freedom motion analysis. In the present study, the data base of the aerodynamic characteristics of the capsule were constructed by a combination of various available techniques. The source of the data were mainly obtained by a series experiments in several types of wind tunnels. Special attention was paid on the transonic damping in pitch, since it is known that a relatively flat-shaped body has a tendency of the dynamic instability in transonic regime. The grown oscillation might result in a failure of the parachute deployment. This damping-in-pitch characteristics were investigated by the special device which enabled the capsule model to rotate freely around the pitch axis in wind tunnels. A series of free-fall tests from balloons was conducted to validate the transonic and subsonic aerodynamic characteristics with emphasis on the damping-in-pitch characteristics. Another attention was paid on the damping-in-roll characteristics to ensure the spin during the reentry. The details of the experiments and the data base were described herein.
Document TypeDepartmental Bulletin Paper
JAXA Category宇宙科学研究所

Items in DSpace are protected by copyright, with all rights reserved, unless otherwise indicated.