The problem of trajectory optimization for spacecraft close proximity is addressed in this paper. The proposed algorithm aims to find a fuel-optimal trajectory while subject to line-of-sight constraint, glide slope constraint and control magnitude constraint, etc. Because line-of-sight constraint and glide slope constraint are coupled with the position and attitude motions of the spacecraft, and the dual quaternion can uniformly represent the relative position and attitude between coordinate systems. Therefore, dual quaternions were used to describe the motion of the spacecraft. Secondly, the sequential convex optimization is used to solve the fuel-optimal trajectory established by dual quaternions. Finally, the calculation time and energy consumption of the proposed method are given by numerical simulations.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Trajectory Optimization for Spacecraft Close Proximity Based on Dual Quaternions


    Additional title:

    Springer Aerospace Techn.


    Contributors:
    Liu, Zishun (editor) / Li, Renfu (editor) / He, Xiaodong (editor) / Zhu, Zhenghong (editor) / Wang, Qian (author) / Zhai, Hongmin (author) / Li, Shunli (author)

    Conference:

    International Conference on Advanced Unmanned Aerial Systems ; 2023 ; Harbin, China July 14, 2023 - July 16, 2023



    Publication date :

    2024-02-01


    Size :

    16 pages





    Type of media :

    Article/Chapter (Book)


    Type of material :

    Electronic Resource


    Language :

    English