Evaluation of the spaceplane maneuverability during combined orbital plane changes

The problem of trajectory optimization of an spaceplane with the help of orbital plane change maneuver using aerodynamic force and engine thrust is considered. Controls are carried out by changing the angle of attack, the air-path roll angle and the propellant flow rate. The optimality criterion is the maximum of the vehicle final mass when the orbital plane rotates by a given angle. On the basis of sequential linearization method, solutions of the optimal problem without and with constraints are obtained. Results of the vehicle motion simulation for given angles of orbital plane rotation are presented and discussed.