The problem of optimum low-thrust collision avoidance between two objects in circular orbits is investigated. The thrust vector of the maneuvered satellite, applied continuously for a given time span, is held constant in magnitude as a consequence of Pontryagin’s maximum principle while its orientation is controlled following the solution of an optimal control problem using the indirect method written in B-plane coordinates. In addition, a simple, fully analytical solution for a tangential maneuver is derived and compared with the controlled solution. Results show that the analytical solution is sufficiently accurate and adequate for a preliminary design of the maneuver. The influence of environmental perturbations is also addressed and shown to be negligible.


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    Title :

    Low-Thrust Collision Avoidance in Circular Orbits


    Contributors:

    Published in:

    Publication date :

    2021-01-25


    Size :

    13 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English





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