摘要
火星环绕器采用3000 N轨控发动机和120 N、25 N姿控发动机进行轨道和姿态控制,良好的温度水平是发动机可靠工作的保障。在复杂深空环境中,3000 N发动机主备份加热区温度控制耦合在一起,且环绕器遥控遥测资源有限,为发动机热控策略设计带来了困难。本文对电磁阀温度适应性进行了仿真分析,阐述了发动机控温回路及控温点设计,分别制定了相应的控温策略,最后给出了真空热试验和在轨飞行试验的温度控制数据。结果表明:热控策略合理可行,可保证发动机温度要求。
The 3000 N orbit-control engine and 120 N,25 N attitude-control engines are used for the orbit and attitude control of Mars orbiter.A good temperature level is the guarantee for the reliable operation of these engines.However,in complex deep space environment,since the temperature control for the primary and backup heating zones of the 3000 N engine is coupled and the telecontrol and telemetry resources are limited,it is difficult to design the engine thermal control strategy for these engines well.In this paper,the temperature adaptability of solenoid valve is simulated and analyzed.The temperature control loops and temperature control points are elaborated,and the corresponding temperature control strategies are formulated,respectively.Finally,the temperature control data of the vacuum thermal test and in-orbit flight test are given.The results show that the thermal control strategies are reasonable and feasible,and can guarantee the temperature requirements of the engines.
作者
赵训友
陈明花
曹伟
杨金
张海
邹亿
谢攀
ZHAO Xunyou;CHEN Minghua;CAO Wei;YANG Jin;ZHANG Hai;ZOU Yi;XIE Pan(Shanghai Institute of Satellite Engineering,Shanghai 201109,China;Shanghai Institute of Space Propulsion,Shanghai 201112,China)
出处
《上海航天（中英文）》
CSCD
2022年第S01期178-185,共8页
Aerospace Shanghai（Chinese&English）
基金
天问一号火星探测任务
关键词
火星
环绕器
发动机
电磁阀
热控
Mars
obiter
engine
solenoid valve
thermal control
作者简介
赵训友(1987—),男,硕士,工程师,主要研究方向为卫星推进系统设计。
