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.
Key words: solar sail space