The invention belongs to the technical field of satellite thermal protection, and particularly relates to a pneumatic thermal protection structure of an ultra-low orbit aircraft solar cell array. Substrate protection design and single battery protection design are carried out on the front face of the solar cell array, and electric connector and grounding resistor protection design and diode protection design are carried out on the back face of the solar cell array. Through ground test verification and on-orbit verification, the protection effect on the front face and the back face of the solar cell array is remarkable, the solar cell array can be effectively protected against high temperature caused by pneumatic friction in the 160 km to 120 km orbit descending process, and it is guaranteed that the solar cell array can normally work in the ultra-low orbit severe environment.
本发明属于卫星热防护技术领域,特别是一种超低轨道飞行器太阳电池阵的气动热防护结构。对太阳能电池阵正面进行基板防护设计、单体电池防护设计,对太阳能电池阵背面进行电连接器及接地电阻防护设计、二极管防护设计。经过地面试验验证与在轨验证,该专利设计对太阳电池阵正面与背面的防护效果显著,能对太阳能电池阵在160km~120km降轨过程中气动摩擦导致的较高温度进行有效防护,保证太阳能电池阵在超低轨道恶劣环境中能够正常工作。
Aerodynamic thermal protection structure of solar cell array of ultra-low orbit aircraft
一种超低轨道飞行器太阳电池阵的气动热防护结构
2024-01-02
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |
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