Solar sail analytical optimal control law for earth escape transfer orbit

Aiming at orbit control problem for escaping the earth with solar sail, a new analytical optimal control law is presented. This approach maximizes the instantaneous rate of the increase of the total orbital energy in the process of escaping the earth, so as to ensure the shortest escape time. The equations of motion for the trajectory are expressed in modified equinoctial orbital elements, which are well behaved as the trajectory going from elliptic to hyperbolic during escape. Furthermore, the derivation of escaping the earth optimal control law is given. Simulation analysis shows that the control law has higher computational speed, and can real-timely calculate the attitude control angle according to the state of spacecraft by the simulation analysis, hence the control law is suitable for the application in future on-orbit solar sail autonomous control system.