This paper presents a new type of orbit insertion by combining ballistic capture and aerocapture for a spacecraft with capsule configurations. The spacecraft starts from a very distant region from the target body, follows a ballistic capture trajectory by using multi-body dynamics, attains certain periapsis conditions, and performs a single or multiple aerocapture maneuvers for a low orbit around the target. Ballistic capture transfers are constructed by a straightforward algorithm, i.e., manipulating two sets of initial conditions. Aerocapture is utilized to further decelerate the spacecraft. By controlling the aerodynamic lift and drag forces, post-exit targeting conditions are achieved. Aerocapture trim maneuvers are imparted, if necessary, at the apoapsis to aim the next periapsis conditions when at least two aerocapture passes are required. A semi-analytical prediction algorithm is used to estimate the atmospheric diving conditions with a prescribed aerocapture times. A testing case around Mars has proved a substantial mass saving from that of a conventional Hohmann transfer with moderate flight time and flexible insertion period.


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    Title :

    Mars Aero-Ballistic Capture


    Additional title:

    Lect. Notes Electrical Eng.


    Contributors:
    Yan, Liang (editor) / Duan, Haibin (editor) / Deng, Yimin (editor) / Luo, Zong-Fu (author) / Zhou, Chuan-Kai (author)

    Conference:

    International Conference on Guidance, Navigation and Control ; 2024 ; Changsha, China August 09, 2024 - August 11, 2024



    Publication date :

    2025-03-02


    Size :

    10 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English




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