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.


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    Title :

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


    Contributors:
    Jiang, Xiaoyong (author) / Lian, Yijun (author) / Zhang, Rui (author) / Zhang, Zhiyong (author)


    Publication date :

    2019-06-01


    Size :

    1427316 byte




    Type of media :

    Conference paper


    Type of material :

    Electronic Resource


    Language :

    English




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