抄録
The fly-back system of CAMUI (CAscaded MUltistage Impinging-jet) hybrid rocket has been developed. At the first stage, we conducted the gliding test of a Space-shuttle type winged vehicle. In the test, the winged vehicle was carried by a radio-controlled (RC) airplane, separated at the altitude of 250 m, glided and landed. The launching test of the vehicle was carried out by using a model rocket engine. At the second stage, we developed a delta wing to install to the CAMUI hybrid rocket. The aerodynamic characteristics of a hybrid rocket with the delta wing were investigated by a wind tunnel, and the flight performance of the winged vehicle was checked by using water rocket. The launching and fly-back test of the CAMUI hybrid rocket assembled with the delta wing was conducted successfully. At the third stage, we have developed a low drag winged CAMUI hybrid rocket to reach to the 60 km altitude. The avionics for the fly-back system has been also developed, and the performance has been confirmed by the autonomous control test of a motor glider and by the launching and fly-back test of the winged CAMUI hybrid rocket.
