The invention discloses an automatic temperature control method and device for a thermal vacuum experiment of a spacecraft. The method comprises the steps that an initial temperature control area is divided based on the maximum temperature difference value of the initial temperature control area of the spacecraft, and a plurality of temperature control sub-areas are obtained; determining a first target temperature and a second target temperature of each temperature control sub-region; the first target temperature is the target temperature of the spacecraft in the heating stage and the high-temperature stage, and the second target temperature is the target temperature of the spacecraft in the cooling stage and the low-temperature stage; and for each temperature control sub-region, obtaining a performance parameter of the spacecraft in a high-temperature environment based on the first target temperature and a performance parameter of the spacecraft in a low-temperature environment based on the second target temperature, and determining the performance of the spacecraft according to the obtained performance parameters. By adopting the method, the temperature control precision in each temperature control area in the thermal vacuum test process can be improved.
本申请公开了一种航天器热真空实验自控温方法及装置。所述方法包括:基于航天器的初始控温区域的最大温度差值对初始控温区域进行划分,获得多个控温子区域;确定各控温子区域的第一目标温度和第二目标温度;第一目标温度为航天器在升温阶段和高温阶段的目标温度,第二目标温度为航天器在降温阶段和低温阶段的目标温度;针对每一控温子区域,获取航天器在基于第一目标温度的高温环境下的性能参数以及航天器在基于第二目标温度的低温环境下的性能参数,并根据所获取的性能参数确定航天器的性能。采用本方法能够提高热真空试验过程中各控温区域内的控温精度。
Spacecraft thermal vacuum experiment automatic temperature control method and device
一种航天器热真空实验自控温方法及装置
2023-12-01
Patent
Electronic Resource
Chinese