高床载单组元肼发动机冷起动过程仿真研究  

Simulation of Cold Starting Transient Characteristics of High Bed-load Monopropellant Hydrazine Thruster

作　　者：冀鹏 梁树强 肖明杰 雷凡培 JI Peng;LIANG Shu-qiang;XIAO Ming-jie;LEI Fan-pei(Science and Technology on Liquid Rocket Engine Laboratory, Xi’an Aerospace Propulsion Institute, China Aerospace Science and Technology Corporation, Xi’an 710100, China;Academy of Aerospace Propulsion Technology, Xi’an 710100, China;China State Shipbuilding Corporation Limited, Beijing 100044, China)

机构地区：[1]中国航天科技集团有限公司西安航天动力研究所液体火箭发动机重点实验室,西安710100 [2]航天推进技术研究院,西安710100 [3]中国船舶集团有限公司,北京100044

出　　处：《科学技术与工程》2021年第32期13992-13997,共6页Science Technology and Engineering

基　　金：液体火箭发动机技术重点实验室基金(6142704180308)。

摘　　要：为了进一步提高飞行器的变轨稳定性,研究高床载单组元肼发动机的冷起动特性,采用模块化建模思想通过管路输送系统、推力装置等功能模块的数学模型,基于Mworks软件构建了基于冷起动延迟的单组元肼发动机仿真系统,并采用实验数据对冷起动过程压力特性进行有效性验证。在保证发动机的稳态室压和冷起动加速性的情况下,分析了对高床载单组元发动机冷起动压力峰的影响因素,得到其关于毛细管长度、限流圈孔径等结构参数的关系。结果表明:贮箱压力的变化对冷起动过程的影响较小;增加毛细管长度会显著降低发动机的冷起动加速性;选取合适的限流圈孔径来减小瞬时流量是抑制冷起动压力峰较为合理有效的方式。In order to further improve the orbit change stability of the aircraft,the cold start characteristics of high bed monopropellant hydrazine engine were studied.The modular modeling idea was adopted through the mathematical model of functional modules such as pipeline conveying system and thrust device.Monopropellant hydrazine engine simulation system based on cold start delay was constructed based on Mworks software,and the effectiveness of pressure characteristics in cold start process was verified by experimental data.Under the condition of ensuring the steady-state chamber pressure and cold start acceleration of the engine,the influencing factors on the cold starting pressure peak of monopropellant hydrazine thruster were analyzed,and the relationship between the structural parameters such as capillary length and flow limiting ring aperture was obtained.The results show that the tank pressure has little influence on the cold starting process.Increasing capillary length can significantly worsen the starting acceleration of engine.The appropriate flow limited orifice is a reasonable way to restarin the pressure peak of cold starting.

关 键 词：单组元肼催化分解发动机 冷起动过程 结构参数 数值模拟 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]