小冲量推力器深空探测工作性能地面模拟实验研究  

Ground-based experimental study of operating performance of a small impulse thruster for deep space exploration

作　　者：余鹏 邬二龙 赵婷 陈泓宇 孙迎霞 徐辉 王东 刘锋 YU Peng;WU Erlong;ZHAO Ting;CHEN Hongyu;SUN Yingxia;XU Hui;WANG Dong;LIU Feng(Shanghai Institute of Space Propulsion,Shanghai 201112,China;Shanghai Engineering Research Center of Space Engine,Shanghai 201112,China)

机构地区：[1]上海空间推进研究所,上海201112 [2]上海空间发动机工程技术研究中心,上海201112

出　　处：《推进技术》2024年第12期291-300,共10页Journal of Propulsion Technology

基　　金：中国航天科技集团推进技术自主研发项目(2023Tm·YY5329Fc);国防科技基础加强计划技术领域基金。

摘　　要：对应用于我国宇航领域深空天体探测重大工程的小冲量推力器进行高空模拟热试车研究,考察小冲量推力器稳态及脉冲工作性能和在轨局部高温环境对推力器脉冲性能的影响规律。结果表明,单氧燃互击对-氧燃同向旋流液膜冷却构型的小冲量推力器稳态工作过程可分为四个阶段,旋流液膜行为对发动机推力性能影响较小,但对推力器温度分布有极其重要的影响。4 ms脉宽下推力器实测脉冲冲量为24.7 mN·s,这与国际上同量级先进推力器脉冲性能持平且脉冲重复性良好,1σ脉冲一致性为5%。地面模拟天体高温环境对小冲量推力器脉冲性能影响研究表明,推力器在轨工作脉宽(4 ms及8 ms)下,推进剂温度在25~85℃内变化时其对推力器脉冲冲量的影响极其有限,而当管路局部高温超过入口压力下氧化剂沸点时其脉冲冲量降至额定水平的1/3。推进剂供应温度对小冲量推力器脉冲冲量的影响机制与推力器电磁阀响应时间及温度对推进剂物性的影响规律密切相关。在短脉宽(4 ms及8 ms)下,推力器脉冲冲量受电磁阀响应时间及推进剂初始相态控制;从12 ms脉宽开始脉宽延长为“温度-推进剂物性-脉冲性能”作用链路提供可能。与25℃推进剂工况相比,60℃下脉冲性能小幅下降与推进剂密度下降有关,85℃下脉冲性能下降主要与氧化剂在喷注器内流动过程中发生气化行为有关,105℃下脉冲性能明显下降主要与氧化剂初始相态为气态有关。The small impulse thruster,which should be used for the major project of deep space object ex⁃ploration in China’s aerospace field,was subjected to a simulated high-altitude thermal commissioning study to investigate the steady-state and impulse performance of the engine and the influence of local high-temperature environment in orbit on the impulse performance of the thruster.The results show that the steady-state operating process of the small-impulse thruster with one impingement pair and the co-rotating liquid film cooling configura⁃tion can be divided into four stages.The behavior of the swirling liquid film has little effect on the thrust perfor⁃mance of the engine.However,it has an extremely important effect on the temperature distribution in the thruster.The impulse of the thruster under the 4 ms pulse width is 24.7 mN·s,which is in line with the pulse performance of the internationally advanced thrusters in the same class and has good pulse repeatability(the 1σpulse consis⁃tency is only 5%).The pulse performance test of the small impulse thruster in the high temperature environment near a small celestial body simulated on the ground shows that under the on-orbit pulse width of the thruster(4 ms and 8 ms),the propellant temperature change in the range of 25~85℃has an extremely limited effect on the thruster impulse.When the oxidant temperature exceeds its boiling point,the thruster impulse drops to 1/3 of the rated level.The mechanism of propellant temperature on the impulse of the small impulse thruster is closely related to the response time of the solenoid valve and the influence of temperature on the physical property of the propellant.For short pulse widths(4 ms and 8 ms),the thruster impulse is controlled by the solenoid valve re⁃sponse time and the initial phase state of the propellant.Starting with 12 ms pulse width,the extension of the pulse width allows the influence of the‘temperature-physical properties of the propellant-impulse performance’mechanism.Compared to the 25℃pr

关 键 词：小冲量空间推力器 推进剂温度 脉冲特性 脉冲一致性 MMH-NTO 高空模拟热试车 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]