目的验证动力系统低温环境适应性要求。方法开展低温试验,模拟火箭运载平台在某使用条件下的环境状态,测量火箭运载平台在各典型测点表面温度数据,将实际温度数据及温度变化情况与关键部组件的使用要求进行对比,分析局部实际温度条件是否满足内部关键部组件的使用要求。结果获得低温条件下关注部位温度数据及温度变化情况。结论通过进行低温条件下的试验,验证了此型火箭在一定低温条件下,重点关注部位的温度能够满足产品设计使用技术要求。此结果为此型火箭动力系统低温环境条件下的使用提供了依据。 Objective To verify the adaptability of low temperature environment of power system. Methods The low temperature test was carried out to simulate the environmental conditions of the rocket carrying platform under certain conditions of use. The surface temperature data of the rocket carrying platform at various typical measuring points were measured. The actual temperature data and temperature changes were compared with those of the key components. Local actual temperature conditions to meet the internal use of key components of the Department. Results The temperature data and the temperature change of the concerned site under the condition of low temperature were obtained. Conclusion Through the test under the condition of low temperature, it is verified that under the condition of certain low temperature, the temperature of the focus area can meet the technical requirements of product design and use. This result provides the basis for the use of this rocket power system in low temperature environment.