The invention discloses a low-impact ejection mechanism for releasing and recovering tethered satellites. The low-impact ejection mechanism comprises at least one ejection assembly. The catapulting assembly comprises a child star, a catapulting module, a locking module, a tether winding and unwinding module and a speed limiting module. According to the invention, ejection release and recovery locking of the child satellite can be realized, the device can be repeatedly used for ground simulation experiments of release and recovery of tethered satellites, and the posture of the child satellite can be adjusted to complete recovery; the child satellites can be catapulted and separated according to a certain speed, too large resistance cannot be generated during recycling and locking, and catapulting-recycling experiments can be autonomously and repeatedly carried out through a control system; the speed limiting module can be automatically locked according to a set acceleration value so as to avoid impact when the child satellite is released.

    本发明公开了一种用于绳系卫星释放和回收的低冲击弹射机构,包括至少一个弹射组件;弹射组件包含子星、弹射模块、锁止模块、系绳收放模块、以及限速模块。本发明能够实现子星的弹射释放和回收锁定,可以重复用于绳系卫星释放和回收的地面仿真实验,并且有助于调整子星姿态,完成回收;本发明能将子星按照一定的速度弹射分离,在回收锁定时又不会产生太大的阻力,并能通过控制系统自主反复进行弹射‑回收实验;限速模块能根据设定的加速度值自动锁止,以避免子星释放时的冲击。


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    Titel :

    Low-impact ejection mechanism for releasing and recovering tethered satellites


    Weitere Titelangaben:

    一种用于绳系卫星释放和回收的低冲击弹射机构


    Beteiligte:
    JIN DONGPING (Autor:in) / SHENG GUOCHEN (Autor:in) / LI XINYUAN (Autor:in)

    Erscheinungsdatum :

    21.11.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Chinesisch


    Klassifikation :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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