A novel trajectory design methodology is proposed in the current work to minimize the state uncertainty in the crucial mission of spacecraft rendezvous. The trajectory is shaped under constraints utilizing a multiple-impulse approach. State uncertainty is characterized in terms of covariance, and the impulse time as the only effective parameter in uncertainty propagation is selected to minimize the trace of the covariance matrix. Furthermore, the impulse location is also adopted as the other design parameter to satisfy various translational constraints of the space mission. Efficiency and viability of the proposed idea have been investigated through some scenarios that include constraints on final time, control effort, and maximum thruster limit addition to considering safe corridors. The obtained results show that proper selection of the impulse time and impulse position fulfills a successful feasible rendezvous mission with minimum uncertainty.


    Access

    Check access

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

    Covariance-Based Multiple-Impulse Rendezvous Design


    Contributors:


    Publication date :

    2019-10-01


    Size :

    2736821 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




    Optimal multiple-impulse orbital rendezvous

    Prussing, J. E. | NTRS | 1967


    Optimal Multiple-Impulse Time-Fixed Rendezvous

    Chen, Y. / Chen, Z. G. / International Federation of Automatic Control et al. | British Library Conference Proceedings | 1997


    Optimization of Multiple-Impulse, Multiple-Revolution, Rendezvous- Phasing Maneuvers

    Ya-zhong Luo / Guo-jin Tang / Yong-jun Li et al. | AIAA | 2007