The invention relates to a micro-nano satellite-oriented structure thermal control integrated design method, which comprises the following steps of: firstly, comprehensively considering constraint conditions of a micro-nano satellite, including bearing force, size, quality, mechanical interface, external heat flow and internal heat source, and integrally designing a micro-nano satellite structure subsystem and a thermal control subsystem; designing the micro-nano satellite configuration and layout; a mechanical interface and a thermal interface of the micro-nano satellite are designed in parallel; designing a heat dissipation mode of the micro-nano satellite; and finally, designing a micro-nano satellite isothermal mode. Structural components of the micro-nano satellite are made of heat conduction materials, and thermal control coatings, surface treatment of structural parts, heat insulation gaskets and multiple layers of heat insulation materials are integrated, so that miniaturization and light weight of the micro-nano satellite are achieved, and thermal control efficiency and structural stability are improved. The method is suitable for efficient thermal control requirements of micro-nano satellites, the mass of the micro-nano satellites is remarkably reduced, and the in-orbit reliability of the micro-nano satellites is enhanced.
本发明涉及一种面向微纳卫星的结构热控一体化设计方法,首先综合考虑微纳卫星的约束条件,包括:承力、尺寸、质量、机械接口、外热流及内热源,将微纳卫星结构分系统与热控分系统,进行一体化设计;然后设计微纳卫星构型与布局;接着并行设计微纳卫星的机械接口与热接口;再设计微纳卫星的散热方式;最后设计微纳卫星等温化方式。本发明中微纳卫星的结构组件为导热材料,并集成热控涂层、结构件的表面处理、隔热垫片及多层隔热材料,实现微纳卫星的小型化和轻量化,提高热控效率与结构稳定性。本发明适用于微纳卫星的高效热控需求,显著减轻了微纳卫星的质量,并增强了微纳卫星的在轨可靠性。
Structure thermal control integrated design method for micro-nano satellite
一种面向微纳卫星的结构热控一体化设计方法
2025-03-28
Patent
Electronic Resource
Chinese
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