The invention relates to the field of engines for spacecraft propulsion systems, and provides a spacecraft temperature control and heat preservation device which comprises a heat insulation layer, a heat preservation layer and a heat preservation layer. The heat dissipation plate is arranged on the other surface of the heat insulation layer; and the PTC heater is arranged on the heat dissipation plate. The PTC heater and the heat dissipation plate are combined to form a temperature control heater and a heat dissipation device, the heat insulation layer is combined to block the influence of the external low-temperature environment, and the environment in a cabin and the structural temperature are both within the temperature control range. The scale of the thermal control system is reduced, the operation is simple, the cost is reduced, and the working reliability of the system is improved.
本发明涉及航天器推进系统用的发动机领域,提供了一种航天器控温保温装置,包括:隔热层,一面设置在舱壁内表面上;散热板,设置在所述隔热层另一面;PTC加热器,设置在所述散热板上。本发明采用PTC加热器结合散热板组成控温的加热器和散热器,结合隔热层阻隔外部低温环境影响,使得舱内环境和结构温度均在控制温度范围内,与传统的控温电器盒相比,本发明中的PTC陶瓷片也是加热器,并配置隔热层,使得热控系统规模减小,操作简单,成本降低,同时也提升了系统工作的可靠性。
Spacecraft temperature control and heat preservation device
航天器控温保温装置
2023-09-15
Patent
Electronic Resource
Chinese
IPC: | B64G Raumfahrt , COSMONAUTICS |