Abstract:

The new overload constraint is  used for a lunar return vehicle with low lift to drag ratio in the skip and  long range reentry, on this basis the load relief problem is described. Based on the analysis of the factors affecting the Kepler phase flight range in the skip reentry trajectory, the component of the aerodynamic lift in the direction of the radius vector of the Earth is equivalent to small perturbation force of the universal gravitation, and an effective overload relief method combined with the corrector predictor guidance law is derived. The simulation demonstrates that the algorithm can restrain the overload effectively without affecting the landing accuracy. The Monte Carlo Simulation results for dispersed cases show the practicability and robustness of the algorithm.

Key words: Lunar return vehicle; , Low lift to drag ratio; , Skip reentry; , Kepler phase; , Monte Carlo Simulation