The invention relates to a high-reliability satellite-rocket docking separation test method based on satellite-rocket separation elements. The method comprises the following steps: extracting the satellite-rocket separation elements; designing a plurality of unlocking separation test working conditions according to different combination conditions of the satellite-rocket separation elements, so that the satellite-rocket separation elements are subjected to limit pulling deviation in a direction unfavorable for normal separation, and completing a satellite-rocket separation unlocking margin test; according to the test result and the satellite-rocket separation element state, comparing and judging the influence weight of each satellite-rocket separation element on the separation result; and optimizing the satellite-rocket docking separation test according to the influence weight of each satellite-rocket separation element on the separation result, and setting the satellite-rocket separation element of which the influence weight is higher than a preset threshold to be in a state beneficial to normal separation. According to the method, the problem of high probability of occurrence of test abnormal phenomena caused by a designer system is solved, the satellite-rocket docking separation test method is optimized and improved, and the test reliability is improved.

    本发明涉及基于星箭分离要素的高可靠性星箭对接分离试验方法,包括:提炼星箭分离要素;根据星箭分离要素的不同组合情况设计多种解锁分离试验工况,使星箭分离要素向不利于正常分离的方向进行极限拉偏,完成星箭分离解锁裕度试验;根据试验结果和星箭分离要素状态,对比判断各星箭分离要素对分离结果的影响权重大小;根据各星箭分离要素对分离结果的影响权重大小,对星箭对接分离试验进行优化,将影响权重高于预设门限的星箭分离要素设置为有利于正常分离的状态。本发明解决了设计师系统导致的试验异常现象发生概率高的问题,并对星箭对接分离试验方法进行优化改进,提高试验可靠性。


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    Titel :

    High-reliability satellite-rocket docking and separating test method based on satellite-rocket separating elements


    Weitere Titelangaben:

    基于星箭分离要素的高可靠性星箭对接分离试验方法


    Beteiligte:
    CHEN KE (Autor:in) / LI DAN (Autor:in) / HU WEI (Autor:in) / ZHANG YIPU (Autor:in) / XU QIAN (Autor:in) / LI RUOQUAN (Autor:in) / YU LONG (Autor:in) / LU KAI (Autor:in) / LENG YUE (Autor:in) / ZHANG WEI (Autor:in)

    Erscheinungsdatum :

    13.02.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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