摘要
针对上面级动力系统发动机温度需求,设计了发动机热控方案,建立了25、5 000 N发动机热仿真模型,确定了各发动机加热功率及被动包覆方式,解决了加热器尺寸小、电阻值密度大以及热控组件安装方式难等问题,上面级发动机随整箭进行了热试验验证和飞行试验验证。验证结果表明:25 N发动机法兰和5 000 N发动机壳体温度均在5℃以上,发动机温度水平和加热功耗均满足系统要求,验证了热控设计的有效性,可为类似发动机热控研制提供一定参考。
In view of the temperature requirements of upper power system engine,a thermal control scheme is designed,a thermal simulation model for 25 N and 5 000 N engines is established,and the scheme of heating power and passive coating is determined,which solves the problems of small heater size,high resistance density,and difficult installation of thermal control components. The upper stage engine system is verified by thermal tests and flight tests along with the whole rocket. The results show that the temperatures of the 25 N engine flange and 5 000 N engine shell are above 5 ℃,and the temperature level and heating power of engine both meet the requirements of the system,which verifies the effectiveness of the engine thermal control design. The results can provide some references for the development of similar engine thermal control.
作者
叶胜
宁静
陈阳春
YE Sheng;NING Jing;CHEN Yangchun(Shanghai Institute of Space Propulsion,Shanghai 201112,China;Shanghai Engineering Research Center of Space Engine,Shanghai 201112,China)
出处
《上海航天（中英文）》
CSCD
2022年第4期186-191,共6页
Aerospace Shanghai（Chinese&English）
基金
上海市空间发动机工程技术研究中心项目(17DI2280800)。
关键词
上面级
发动机热控
数值计算
热试验
在轨验证
upper stage
engine thermal control
numerical calculation
thermal test
on-orbit verification
