The invention is applicable to the field of spacecrafts, and discloses a thermal control design method of a spacecraft and the spacecraft, and the thermal control design method of the spacecraft comprises the following steps: designing a main body structure of the spacecraft into a polyhedral frame structure with an open top, and processing the main body structure into an integrated structure through an aluminum alloy machining process; white paint is sprayed and/or F46 silver-plated secondary surface mirrors are mounted on all the outer side faces of the main body structure, so that the solar absorptivity of the main body structure is smaller than 0.3, and the infrared emissivity of the main body structure is larger than 0.9; a flexible heat insulation cabin plate matched with the main body structure is designed, the top of the main body structure is covered with the flexible heat insulation cabin plate, and the flexible heat insulation cabin plate comprises a plurality of heat insulation units, double-face aluminized polyester films arranged on the surface layers of the heat insulation units and single-face aluminized polyimide films arranged on the double-face aluminized polyester films; according to the method, the temperature index requirement of spacecraft internal equipment is met, the situation that an external cabin plate wraps multiple layers of heat insulation assemblies can be avoided, the structure of each part is convenient to automatically assemble, and the production efficiency is improved.
本发明适用于航天器领域,公开了航天器的热控设计方法及航天器,航天器的热控设计方法包括:将航天器的主体结构设计成顶部敞开的多面框体结构,并通过铝合金机加工工艺将主体结构加工成一体结构;将主体结构的各个外侧面喷涂白漆和/或贴装F46镀银二次表面镜,使主体结构的太阳吸收比小于0.3,红外发射率大于0.9;设计与主体结构适配的柔性隔热舱板,并将柔性隔热舱板覆盖在主体结构的顶部,柔性隔热舱板包括多个隔热单元、设置在隔热单元表层的双面镀铝聚酯膜和设置在双面镀铝聚酯膜上的单面镀铝聚酰亚胺薄膜;该方法既满足了航天器内部设备的温度指标要求,又能够避免外部舱板包覆多层隔热组件,使得各部分结构便于自动化装配,提升了生产效能。
Thermal control design method for spaceflight and spacecraft
一种航天的热控设计方法及航天器
2023-10-03
Patent
Electronic Resource
Chinese
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