Attitude control and thrust boosting system and method for space launchers

Abstract

An attitude control and thrust boosting system () for a space launcher is disclosed, wherein the space launcher is equipped with a rocket engine () provided with an exhaust nozzle. The exhaust nozzle comprises a divergent portion () so designed as to make a supersonic gas flow exit through an exit section defined by a given angle of divergence with respect to a longitudinal axis of the rocket engine. The attitude control and thrust boosting system () comprises flaps () that are arranged around the exit section, are shaped so as to extend the divergent portion of the exhaust nozzle, are mechanically decoupled from said exhaust nozzle and can be actuated to take different angular positions with respect to the longitudinal axis of the rocket engine. Control means () are also provided to receive quantities indicative of an actual attitude of the space launcher and an ambient static pressure, and to make the flaps () take a neutral angular position where the flaps () are inclined, with respect to the longitudinal axis of the rocket engine, according to an inclination angle greater than, or equal to, the given angle of divergence, in order to control the neutral angular position taken by the flaps () according to the ambient static pressure and to make one or more flaps () take an angular position different than the neutral angular position according to the actual attitude of the space launcher and to a required attitude for said space launcher.