火箭推进

矢量推力作为火箭发动机关键性能参数,对飞行器的飞行轨道精度控制具有重要意义。对火箭发动机工作产生的矢量推力进行准确测量成为目前发动机试验推力测量中亟待解决的问题。介绍了国内外目前矢量推力测量技术的进展和矢量推力测量与校准系统原理组成,分析了系统设计的关键技术,建立了发动机矢量推力测量与原位校准系统。基于矢量推力的解耦算法,开发了矢量推力测量与校准软件。针对某型号姿控发动机进行矢量推力试验测量,成功获得了发动机的矢量推力数据。测得的发动机的矢量力数据中主推力的测量不确定度低于1%,侧向力的不确定度低于5%。

As the key performance parameter of rocket engine, vector thrust is very important for orbit precision control of the spacecraft.How to accurately measure the vector thrust produced by rocket engine has become an important problem of thrust measurement in engine test at present.The progress of vector thrust testing technology in China and foreign countries, as well as working principle and composition of the vector thrust measurement and calibration system are introduced.The key technologies of system development are analyzed.The vector thrust measurement and in-situ calibration system was established.The vector thrust measurement and calibration software was developed.The vector thrust test data were successfully achieved by the vector thrust measurement and calibration system in the process of an altitude control engine test.The measured data showed that the testing uncertainty of the main trust is less than 1% and the testing uncertainty of the lateral thrust is less than 5%.

引言
1 矢量推力测量与校准系统设计
2 发动机试验矢量推力测量
3 结论

图1 推力偏心示意<br/>Fig.1 Schematic diagram of thrust eccentricity definition

图1 推力偏心示意
Fig.1 Schematic diagram of thrust eccentricity definition

图2 真空舱试验系统<br/>Fig.2 Testing system for vacuum chamber

图2 真空舱试验系统
Fig.2 Testing system for vacuum chamber

图3 矢量推力测量与校准系统原理<br/>Fig.3 Schematic diagram of vector thrust measurement and calibration system

图3 矢量推力测量与校准系统原理
Fig.3 Schematic diagram of vector thrust measurement and calibration system

图4 矢量推力测量与校准系统<br/>Fig.4 Vector thrust measurement and calibration system

图4 矢量推力测量与校准系统
Fig.4 Vector thrust measurement and calibration system

图5 矢量推力测量解耦软件<br/>Fig.5 Decoupling software for vector thrust measurement and calibration

图5 矢量推力测量解耦软件
Fig.5 Decoupling software for vector thrust measurement and calibration

图6 发动机高模试车<br/>Fig.6 High altitude simulation test of rocket engine

图6 发动机高模试车
Fig.6 High altitude simulation test of rocket engine

表1 管路带压主系数对比<br/>Tab.1 Caparison of main coefficients in pressure state of pipe

表1 管路带压主系数对比
Tab.1 Caparison of main coefficients in pressure state of pipe

表2 试验测量发动机矢量推力数据<br/>Tab.2 Vector thrust data measured in test of rocket engine

表2 试验测量发动机矢量推力数据
Tab.2 Vector thrust data measured in test of rocket engine

[1] 郭霄峰,李耀华.液体火箭发动机试验[M].北京:中国宇航出版社,2009.
[2] 庄杰,李建勋.490N喷管发动机轴向推力测试系统精度分析[J].微型电脑应用,2010, 1(26):51-54.
[3] ZHANG Jun, SUN Baoyuan, REN Zongjin, et al. Research on the measurement of thrust vector for a liquid-propellant rocket motor based on piezoelectric quartz [C]// Proceedings of 2009 International Conference on Measuring Technology and Techtronic's Automation. [S.l.]:[s.n.], 2009.
[4] 刘伟亮,吴建军.机电一体化推力测量系统的研制及应用.火箭推进[J],2004,30(6):50-54.
[5] TAKAHASHI K, LAFLEUR T, CHARLES C, et al. Direct thrust measurement of a permanent magnet helicon double layer thruster [J]. Applied physics letters, 2011, 98(14):141503-1～141503-3.
[6] CUBBIN E A, ZIEMER J K, CHOUEIRI E Y, et al. Pulsed thrust measurements using laser interferometry [J]. Review of Scientific Instruments, 1997, 68(6), 2339-2345.
[7] ERIKSSON A B, LINDEGREN Robert, KOHLER Johan. A dynamic millinewton thrust vector measurement system in silicon [C]// Proceedings of The 13th International Conference on Solid-state Sensors, Actuators and Microsystems. Seoul, Korea: [s.n.], 2007.
[8] 岑乐观,毕毓秀,罗胜初,张贻恭.小推力姿控发动机的推力测量[J]. 光学机械,1982(6):55-62
[9] 颜雄雄,耿卫国.小发动机推力矢量的测量.推进技术[J],2000,21(3):86-88.
[10] 费业泰. 误差理论与数据处理[M]. 北京:机械工业出版社, 1995.

备注

引言

1 矢量推力测量与校准系统设计

2 发动机试验矢量推力测量

3 结论

期刊信息