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发明授权
CN109533398B 一种用于卫星热控包覆的安装方法和卫星舱板 有权

一种用于卫星热控包覆的安装方法和卫星舱板
摘要：
本申请提供了一种用于卫星热控包覆的安装方法和卫星舱板，其中，该方法的步骤包括：依次叠放预先加工有多个开孔的附加包覆、预先加工有多个开孔的热控包覆和预先加工有多个螺纹孔的卫星舱板板体；将所述附加包覆的每个开孔、热控包覆的每个开孔和卫星舱板板体上的每个螺纹孔对齐；将紧固件依次穿过附加包覆的开孔和设置在热控包覆开孔内的具有通孔的支柱，旋转插入卫星舱板板体的螺纹孔，并将附加包覆和热控包覆固定在所述卫星舱板板体上。
摘要（英）：

The invention provides an installation method used for a satellite thermal control cladding and a satellite cabin. The method includes the following steps that an additional cladding provided with several openings through preprocessing, the thermal control cladding provided with several openings through preprocessing and a satellite cabin board body provided with several thread holes through preprocessing are stacked sequentially; each opening of the additional cladding and each opening of the thermal control cladding are aligned; fastener passes through the opening of the additional claddingand a support column with a through hole in the thermal control cladding, a rotating plate is inserted into a threaded hole of the satellite cabin board body and the additional cladding and the thermal control cladding are fixed on the satellite cabin board body.

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