Attitude control and thrust augmentation system and method for space rockets

摘要

Disclosed is an attitude control and thrust augmentation system (100) for a space rocket including a rocket engine (303) provided with an exhaust nozzle. The nozzle includes an enlarged portion (302) designed to exit the supersonic gas stream through an outlet section defined by a predetermined enlarged angle with respect to the longitudinal axis of the rocket engine. The attitude control and thrust augmentation system (100) is disposed around the exit section and is formed to extend an enlarged portion of the exhaust nozzle and is mechanically separated from the exhaust nozzle, relative to the rocket engine longitudinal axis. It is equipped with flaps (110, 111, 112, 113) that can be actuated to assume different angular positions. The control means (130) also receives an amount indicative of the actual attitude of the space rocket and the ambient static pressure and causes the flaps (110, 111, 112, 113) to provide a predetermined amount with respect to the longitudinal axis of the rocket engine. The neutral angle position to be inclined according to the inclination angle of the expansion angle or more is taken, and the neutral angle position taken by the flaps (110, 111, 112, 113) is controlled according to the ambient static pressure, and one or more flaps (110, 111, 112, 113) is configured to take an angular position different from the neutral angular position according to the actual attitude of the space rocket and the attitude required for the space rocket. [Selection diagram]