Highlights A capture mission scenario of a radially-propelled space-craft is analyzed. The capture parabolic orbit is circularized with modulated radial thrust. The problem is studied in an optimal framework to minimize the flight time. The parameters defining the capture trajectories shape are identified. A test case scenario involving a capture mission around Ceres is discussed.

    Abstract The aim of this paper is to analyze the performance of a radially-accelerated spacecraft in a capture mission scenario, in which a space vehicle transfers from a parabolic approaching trajectory of assigned semilatus rectum to a target circular orbit around a generic celestial body. The radial propulsive acceleration provided by the spacecraft propulsion system can be modulated within a suitable given range, and the radial thrust can be either inward- or outward-directed. The transfer mission performance is analyzed in an optimal framework, by minimizing the total flight time with an indirect approach. In this context, the paper proposes a semi-analytical method to reduce the computation time required to solve the optimal control problem. Using a proper description of the spacecraft dynamics in a dimensionless form, the paper reports a set of graphs and tables that allow the designer to obtain a rapid approximation of the optimal mission performance with an accuracy consistent with that of a preliminary trajectory design. Finally, the proposed approach is used to describe the minimum time capture trajectories in a mission scenario towards Ceres.


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    Title :

    Rapid capture trajectories from parabolic orbit with modulated radial thrust



    Published in:

    Advances in Space Research ; 71 , 3 ; 1700-1710


    Publication date :

    2022-09-30


    Size :

    11 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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