Tokai University
Tokyo Institute of Technology
Tokai University
Shizuoka University
Shizuoka University
Tokai University
Japan Aerospace Exploration Agency (JAXA)
Japan Aerospace Exploration Agency (JAXA)
18 June-19 June, 2009, Japan Aerospace Exploration Agency
抄録（英）
The flight speed of space plane or reentry capsule reaches from 8 to 12 km/s and the temperature behind the shock wave become tens of thousands of Kelvin. Due to that, development of heat shield systems is one of the most important tasks. Current main heat shield system is the thermal protection tile and ablator. These systems utilize thermal protective structures for reducing heat flux. These thermal protective methods can not be reusable because thermal protective structures are damaged in one reentry flight. Given this factor, in order to develop a future thermal protection system, we need to consider not only protecting vehicle passively from aerodynamic heating, but also reducing aerodynamic heating actively. To reduce aerodynamic heating actively, the method using magnetic force has been considered. In this method, plasma flow behind the shock wave is controlled by the applied magnetic field through the electric current and Lorentz force. In the present study, using expansion tube, we generated the high enthalpy flow, which approached real flight condition comparatively, around the test model with applied magnetic field. And we visualized density variation around the test model, and search the shock stand-off distance in the varied magnetic field. By evaluating the shock stand-off distance from the images, we confirmed that the shock stand-off distance is increased with increasing magnetic field intensity.
内容記述
形態: カラー図版あり
内容記述（英）
Physical characteristics: Original contains color illustrations
膨張波管を用いた印加磁場による衝撃層拡大効果に関する実験的研究
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