In an example, a method for deorbiting a spacecraft is described. The method includes selecting a target landing site for deorbiting the spacecraft. The method includes determining a range target and a velocity target for reaching a predicted atmospheric entry location. The method includes determining a back-propagated orbit state estimate of the spacecraft. The method includes comparing the back-propagated orbit state estimate to a known orbit state of the spacecraft to determine that the back-propagated orbit state estimate has converged with the known orbit state. The method includes calculating based on determining that the back-propagated orbit state estimate has converged with the known orbit state, (a) an estimated time of ignition for a propulsion system of the spacecraft and (b) an estimated burn velocity vector of the propulsion system using the range target and the velocity target. The method includes performing a burn pulse by the propulsion system.


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    Titel :

    SYSTEMS AND METHODS FOR AUTONOMOUS DEORBITING OF A SPACECRAFT


    Weitere Titelangaben:

    SYSTEMES ET METHODES DE DESORBITATION AUTONOME D'UN ASTRONEF


    Beteiligte:
    EALY JOHN P (Autor:in) / PHAIL BRIAN A (Autor:in) / POLADIAN DAVID (Autor:in)

    Erscheinungsdatum :

    2021-02-28


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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