Abstract: A double pulse guidance strategy based on Gaussian perturbation equation is designed for the quick far range rendezvous task after lunar take off. Firstly, the control equation of the orbit correction is derived, and then the double pulse guidance nonlinear equation group is derived by combining the constraint equation of far range rendezvous time. In order to obtain the minimum solution of speed increment, the problem of solving nonlinear equations is transformed into a nonlinear programming problem by designing programming variables, and the optimal solution is solved by sequential quadratic programming algorithm (SQP). In addition, in order to improve the guidance accuracy, the iterative correction method is used to optimize the guidance process. Finally, the correctness of the double pulse guidance strategy based on Gaussian perturbation equation is verified by data simulations, and compared with Lambert double pulse guidance strategy. The simulation results show that the double pulse guidance strategy based on Gaussian perturbation equation can effectively complete the quick far range rendezvous task, and the guidance accuracy and fuel consumption are better than Lambert double pulse guidance strategy.

Key words: quick far range rendezvous of lunar orbits, gaussian perturbation equation, nonlinear programming, lambert guidance