観測ロケットを用いた再突入試験における柔軟構造体の空力安定性に関する研究

抄録

A thin-membrane inflatable aeroshell has been developed as one of the innovative reentry technologies. A suborbital reentry demonstration using a sounding rocket was conducted in 2012. Contrary to the result of a preliminary study, the vehicle always had an angle of attack (AoA) during its reentry. In addition, attitude instability such as increase in amplitude of AoA and vertical rotation was observed. To clarify the cause of attitude instability, we numerically investigated the dynamic stability of a forced oscillating vehicle, where a large eddy simulation technique with the standard Smagorinsky model was applied. In the trajectory of the CM with respect to AoA, hysteresis in one cycle was observed. The discussion of detailed stability and the analysis for the subsonic region are future works.