空间低冰点推进剂发动机宽温域工作特性研究  

Wide temperature range working characteristics of space low freezing point propellant engine

作　　者：施浙杭 王世成 陈泓宇 姚锋 赵婷 刘昌国 SHI Zhehang;WANG Shicheng;CHEN Hongyu;YAO Feng;ZHAO Ting;LIU Changguo(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8期26-34,共9页Journal of Propulsion Technology

基　　金：国防基础科研项目;国家自然科学基金(U21B2088)。

摘　　要：空间双组元发动机采用MON-25/MMH低冰点推进剂具有低温环境工作优势。对深空探测40 N低冰点推进剂发动机开展地面热试车,研究了不同推进剂温度(-35~25℃)和室压(1.6~2 MPa)下的发动机工作特性,并与NTO/MMH常规推进剂进行比较。结果表明,在推进剂宽温域内,发动机能在额定工况下(混合比=1.65,室压=1.8 MPa)正常地稳态和脉冲自燃点火工作,其燃烧室效率和喉部温度随着推进剂温度降低而轻微地下降。发动机以12~60 ms脉宽持续脉冲工作时产生平均室压冲量为0.021~0.127 MPa·s,各室压波形完整、一致性较好,且基本不受推进剂温度变化影响。与常规推进剂相比,低冰点发动机的燃烧室效率降低了约1%,开机响应时间延长了近3 ms,且存在室压波动幅度增大现象,由于高饱和蒸气压的MON-25喷注气化引起雾化和燃烧过程脉动。室压波动特征频率在150~350 Hz内变化,通过提高室压、降低推进剂温度等抑制气化的方法能有效地减弱波动幅度至常规推进剂水平,并使特征频率消失。Space bi-propellant engine using the low freezing point propellant of MON-25/MMH has the ad⁃vantage of operating in low temperature environment.Ground hot firing test of the 40 N low freezing point propel⁃lant engine for deep space exploration was carried out,and the engine working characteristics at different propel⁃lant temperature(-35~25℃)and chamber pressures(1.6~2 MPa)were studied,which compared with the con⁃ventional propellant of NTO/MMH.Results indicated that,for the propellant over a wide temperature range,the engine can work normally by hypergolic ignition in steady-state and pulsed modes at the rated condition(mixing ratio=1.65,chamber pressure=1.8 MPa).Its combustion chamber efficiency and throat temperature slightly de⁃crease as the propellant temperature decreases.The engine constantly pulsed operation with the pulse width of 12~60 ms produces the averaged chamber pressure impulse of 0.021~0.127 MPa·s,and each chamber pressure waveform is complete and consistent,which are largely unaffected by the change of propellant temperature.Com⁃pared with the conventional propellant,the combustion chamber efficiency of low freezing point engine is reduced by about 1%,and the startup response time increases by near 3 ms.The phenomena of an increase in the fluctua⁃tion amplitude of chamber pressure occurs,as MON-25 with the high saturated vapor pressure will vaporize dur⁃ing the injection,which results in pulsating atomization and combustion processes.The characteristic frequency of chamber pressure fluctuation varies in the range of 150~350 Hz.The fluctuation amplitude can be effectively reduced to the level of conventional propellant by the means of inhibiting vaporization such as raising the chamber pressure and decreasing the propellant temperature,which make the characteristic frequency disappear.

关 键 词：空间双组元发动机 低冰点推进剂 低温 工作特性 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]