摘要
返回器再入过程中的烧蚀温度,是防热结构设计和验证的重要参数之一。针对在轨应用的需求,文章设计了一种使用铠装热电偶进行返回器烧蚀温度在轨测量的方法,通过将铠装热电偶埋入安装并进行冷端补偿和误差校准设计,可以准确测量烧蚀温度的变化过程。通过我国探月三期工程再入返回飞行试验器在轨测试,证明了该方法的有效性。
Ablation temperature of reentry vehicle is an important parameter for heat protection structure design and validation. For meeting the requirement of inflight application, a method is proposed, which uses armoured thermocouple to measure the ablation temperature of reentry ve- hicle. By embedded installation, cold junction compensation and error calibration, the changing process of ablation temperature can be precisely measured. Inflight test results of return and reentry flight test vehicle for the 3rd phase of China lunar exploration program demonstrates the ef- fectiveness of the proposed method.
出处
《航天器工程》
北大核心
2015年第2期129-133,共5页
Spacecraft Engineering
关键词
铠装热电偶
返回器
烧蚀温度
在轨测量
armoured thermocouple
reentry vehicle
ablation temperature
inflight measurement
