The invention relates to a system and a method for autonomous deorbital of a spacecraft. 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-propagatedorbit 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.

    本公开涉及用于航天器自主脱轨的系统和方法。具体地,在一个示例中,描述了用于使航天器脱轨的方法。该方法包括选择用于使航天器脱轨的目标着陆地点。该方法包括确定用于到达预测大气进入位置的范围目标和速度目标。该方法包括确定航天器的后向传播的轨道状态估计。该方法包括将后向传播的轨道状态估计与航天器的已知轨道状态进行比较,以确定后向传播的轨道状态估计已经与已知轨道状态趋于一致。该方法包括使用范围目标和速度目标基于确定后向传播的轨道状态估计已经与已知轨道趋于一致而计算(a)航天器的推进系统的估计点火时间以及(b)推进系统的估计燃烧速度矢量。该方法包括通过推进系统执行燃烧脉冲。


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    Title :

    Systems and methods for autonomous deorbit of spacecraft


    Additional title:

    用于航天器自主脱轨的系统和方法


    Contributors:

    Publication date :

    2021-03-05


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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