The invention provides a heat conduction buffer structure of a satellite initiating explosive device. The heat conduction buffer structure comprises mounting screws, mounting feet, an upper buffer heat conduction pad, a middle buffer heat conduction pad and a lower buffer heat conduction pad. The middle buffering heat conduction pad and the upper buffering heat conduction pad are sequentially arranged on the top of the initiating explosive device unlocking and separating device from bottom to top, and the lower buffering heat conduction pad is arranged between the bottom of the initiating explosive device unlocking and separating device and a satellite. The satellite is arranged at the top of the mounting foot, and the mounting screws are used for sequentially fixing the upper buffering heat conduction pad, the middle buffering heat conduction pad, the initiating explosive device unlocking and separating device, the lower buffering heat conduction pad and the satellite to the mounting foot and providing pre-tightening force. The heat conduction buffer structure adopts an upper-layer, middle-layer and lower-layer heat conduction pad structure, heat generated during explosion of the initiating explosive device is better dissipated through superposition of multiple layers of materials, and the thermal shock of explosion of the initiating explosive device on a satellite structure and equipment is effectively reduced.

    本发明提供了一种卫星火工品导热缓冲结构,包括安装螺钉、安装脚、上缓冲导热垫、中缓冲导热垫以及下缓冲导热垫;所述中缓冲导热垫与上缓冲导热垫从下至上依次设置在火工品解锁分离装置的顶部,所述下缓冲导热垫设置在火工品解锁分离装置的底部与卫星之间;所述卫星设置在安装脚的顶部,所述安装螺钉用于依次将上缓冲导热垫、中缓冲导热垫、火工品解锁分离装置、下缓冲导热垫以及卫星固定在安装脚上并提供预紧力。本发明中的导热缓冲结构采用上中下三层导热垫结构,采用多层材料的叠加更好地对火工品爆炸时产生的热量进行散热,有效降低了火工品爆炸对卫星结构和设备的热冲击。


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    Title :

    Satellite initiating explosive device heat conduction buffer structure


    Additional title:

    卫星火工品导热缓冲结构


    Contributors:
    ZHOU HONGWEI (author) / GU LILI (author) / YANG ZHEN (author) / WANG SHUNAN (author) / ZHANG XIAOTONG (author) / ZHANG TINGYAO (author) / ZHU XINZHONG (author) / XI PEILI (author)

    Publication date :

    2025-02-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Chinese


    Classification :

    IPC:    B64G Raumfahrt , COSMONAUTICS



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