Monte-Carlo simulation and genetic algorithm were employed to achieve the optimal correction strategy during Lambert transfer from the view of probability. The Lambert trajectory associated J2 perturbation was generated from differential correction algorithm that was used to yield the periodic orbit in circular restricted three body problem (CR3BP). So the correction maneuvers dealt with just the residual errors from navigation and controller. Then the linear and nonlinear strategies were derived from the monodromy matrix of differential correction algorithm, and then the Monte-Carlo simulation and genetic algorithm were employed to minimize the rendezvous errors from the view of probability. Quite different from the traditional strategies, the correction developed is universal for its robustness to measure errors.
Spencer D B,Kim Y H.Optimal spacecraft rendezvous using genetic algorithms[J].Journal of Spacecraft and Rockets.2002,39(6):859-865
��ͳ,������.�����Ŵ��㷨������Lambert˫����ת��[J].�������պ����ѧѧ��,2007,33(3):273-274 Chen Tong,Xu Shijie.Optimal Lambert two-impulse transfer using genetic algorithm[J].Journal of Beijing University of Aeronautics and Astronautics,2007,33(3):273-274(in Chinese)
Xu Ming,Xu Shijie.Trajectory and correction maneuver during the transfer from Earth to Halo orbit [J].Chinese Journal of Aeronautics.2008,21(3):200-206
Xu Ming,Xu Shijie.Nonlinear dynamical analysis for displaced orbits above a planet [J].Celestial Mechanics and Dynamical Astronomy.2008,102(4):327-353
Xu Ming,Xu Shijie.Structure-preserving stabilization for Hamiltonian system and its applications in solar sail [J].Journal of Guidance,Control and Dynamics.2009,32(3):997-1004