Optimal orbit control strategy design for low energy moon return

The low energy moon return orbit has evident advantages in the fuel consumption but it´s much sensitive to the initial states of the probe. To solve this problem, in this paper, the problem of accurate orbit control for low energy Moon return mission is studied. Firstly, based on the elliptical four body dynamical model, the dynamical characteristics of the low energy return orbit is analyzed. Then, the covariance analysis method is introduced to clarify the propagation properties of initial orbit errors. Finally, a three maneuvers orbit adjusting strategy is proposed according to the sensitiveness of the constraint against the accuracy of navigation and control impulse. By the simulation results, the strategy is able to guarantee an accurate height of reentry effectively.