A Rapid Low-Thrust Trajectory Design Approach Based on Bi-Impluse Extension

The low-thrust propulsion has broad application prospects in deep space explorations, while it also brings forward a formidable challenge to the low-thrust trajectory design. To determine whether there is a feasible low-thrust trajectory connecting given points and to provide an initial guess for further trajectory optimization, we present a rapid low-thrust trajectory design approach based on bi-impulse extension. The approach employs the bi-impulse obtained by solving the Lambert's problem to indicate the direction of low-thrust and updates the state of spacecraft by numerical integration using low-thrust. After several iterations, a feasible low-thrust trajectory can be obtained by the presented approach. Results show that it is effective for both Venus-flyby mission and Mars-rendezvous mission.