固体火箭发动机五分力测量原理及静态误差分析
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摘要
针对某些实际工程中固体火箭发动机绕轴线的旋转力矩M_Z相对很小或者不是测量关注重点的推力矢量测量问题,为避免测量中较为复杂的解耦过程,更简单地实现对推力矢量在各坐标轴上的分力P_X、P_Y、P_Z和对坐标轴的转矩M_X、M_Y的准确测量,在分析了六分力测量模型耦合误差的基础上,忽略发动机绕轴线的旋转力矩,提出了一种动架约束之间只存在线性耦合的五分力试验台模型,并对其进行了误差分析,证实了五分力模型能够实现对推力矢量在各坐标轴上的分力P_X、P_Y、P_Z和对坐标轴的转矩M_X、M_Y的准确测量,并进一步得到了五分力模型的静态误差主要来源于发动机安装误差和标定误差,安装误差中横偏是主要因素的结论。所得结论可为固体火箭发动机五分力试验台研制提供理论基础。
Aiming at the problem that the rotational moment M_Z of solid rocket motor around axes is relatively small or not the focus of measurement in some practical projects,it is important to realize the accurate measurement of the component force P_X,P_Y,P_Z of thrust vectors on each axis and the torque M_X,M_y of coordinate axis. In this paper,on the basis of the six-component force measurement model,neglecting the rotating moment of engine around axis,a five-component force test-bed model with linear coupling between the constraints of the moving frame has been proposed.Moreover,its error analysis has been carried out,which proves the practicability of the five-component force test-bed. This paper may provide a theoretical basis for the solid rocket motor thrust measurement quintuple test-bed.
Aiming at the problem that the rotational moment M_Z of solid rocket motor around axes is relatively small or not the focus of measurement in some practical projects,it is important to realize the accurate measurement of the component force P_X,P_Y,P_Z of thrust vectors on each axis and the torque M_X,M_y of coordinate axis. In this paper,on the basis of the six-component force measurement model,neglecting the rotating moment of engine around axis,a five-component force test-bed model with linear coupling between the constraints of the moving frame has been proposed.Moreover,its error analysis has been carried out,which proves the practicability of the five-component force test-bed. This paper may provide a theoretical basis for the solid rocket motor thrust measurement quintuple test-bed.
引文
[1]李海涛.发件发动机推力矢量测量理论方法与自动测试技术研究[D].长沙:国防科技大学,2005.LI Haitao.Research on theory and automatic test technology of thrust vector measurement for engine[D].Changsha:National University of Defense Technology,2005.
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[9]郑健,周长省,刘锐.固体火箭发动机六分力试验台应用综述[J].江苏航空,2010(增刊):5-8.ZHENG Jian,ZHOU Changxing,LIU Rui.Application summary of six component test bench for solid rocket motor[J].Journal of Jiangsu Aviation,2010(s):5-8.
[10]王颐,雷亚琴.固体火箭发动机多分力测量方法简介[J].固体火箭技术,2000,23(3):70-74.WANG Yi,LEI Yaqin.Introduction of multi component measurement method for solid rocket motor[J].Solid rocket technology,2000,23(3):70-74.
[11]段斌斌.大吨位六分力测量系统原位标定及数据处理方法研究[D].南京:南京理工大学,2009.DUAN Binbin.Research on in situ calibration and data processing method for large tonnage six component measuring system[D].Nanjing:Nanjing University of Science and Technology,2009.
[12]陈萌,兰宝刚.多元非线性拟合在固体火箭发动机多分力试验中的应用[J].金陵科技学院学报,2015,31(2):23-26.CHEN Meng,LAN Baogang.Application of multivariate nonlinear fitting in multi component test of solid rocket motor[J].Journal of Jinling Institute of Technology,2015,31(2):23-26.
[13]甘舜仙.六分力试验台静态误差分析与调整[J].推进技术,1987,12(6):73-81.GAN Shunxian.Static error analysis and adjustment of six component test bench[J].Propulsion Technology,1987,12(6):73-81.
[2]薛群,徐向东.固体火箭发动机测试与试验技术[M].北京:宇航出版社,1994.XUE Qun,XU Xiangdong.Solid rocket motor measurement and test technology[M].Beijing:Aerospace Press,1994.
[3]西安航天动力测控技术研究所.固体火箭发动机试验测试[M].西安:西北工业大学出版社,2016.Xi'an aerospace measurement and control technology research institute.Solid rocket motor measurement[M].Xi'an:Northwestern Polytechnical University Press,2016.
[4]李兆民,李邦,周生国.固体火箭发动机推力偏心试验台的静态检测技术[J].测试技术学报,1994,8(4):211-216.LI Zhaomin,LI Bang,ZHOU Shengguo.Static testing technology of thrust eccentricity test rig for solid rocket motor[J].Journal of Testing Technology,1994,8(4):211-216.
[5]王娟.六分力测试系统误差研究[D].南京:南京理工大学,2004.WANG Juan.Research on the error of six component testing system[D].Nanjing:Nanjing University of Science and Technology,2004.
[6]刘宏璇.六分力测试方法研究[D].南京:南京理工大学2008.LIU Hongxuan.Research on six component testing method[D].Nanjing:Nanjing University of Science and Technology,2008.
[7]鞠玉涛,周长省,王政时.发动机六分力试验台系统误差分析研究[J].导弹与制导学报,2005,25(4):63-68.JU Yutao,ZHOU Changxing,WANG Zhengshi.Research on system error analysis of engine six component test rig[J].Journal of Missiles and Guidance,2005,25(4):63-68.
[8]王栋,余陵,武晓松.火箭发动机六分力试验系统力学和误差特性[J].导弹学报,2009,21(3):23-25.WANG Dong,YU Ling,WU Xiaosong.Mechanics and error characteristics of rocket engine six component test system[J].Journal of Missile,2009,21(3):23-25.
[9]郑健,周长省,刘锐.固体火箭发动机六分力试验台应用综述[J].江苏航空,2010(增刊):5-8.ZHENG Jian,ZHOU Changxing,LIU Rui.Application summary of six component test bench for solid rocket motor[J].Journal of Jiangsu Aviation,2010(s):5-8.
[10]王颐,雷亚琴.固体火箭发动机多分力测量方法简介[J].固体火箭技术,2000,23(3):70-74.WANG Yi,LEI Yaqin.Introduction of multi component measurement method for solid rocket motor[J].Solid rocket technology,2000,23(3):70-74.
[11]段斌斌.大吨位六分力测量系统原位标定及数据处理方法研究[D].南京:南京理工大学,2009.DUAN Binbin.Research on in situ calibration and data processing method for large tonnage six component measuring system[D].Nanjing:Nanjing University of Science and Technology,2009.
[12]陈萌,兰宝刚.多元非线性拟合在固体火箭发动机多分力试验中的应用[J].金陵科技学院学报,2015,31(2):23-26.CHEN Meng,LAN Baogang.Application of multivariate nonlinear fitting in multi component test of solid rocket motor[J].Journal of Jinling Institute of Technology,2015,31(2):23-26.
[13]甘舜仙.六分力试验台静态误差分析与调整[J].推进技术,1987,12(6):73-81.GAN Shunxian.Static error analysis and adjustment of six component test bench[J].Propulsion Technology,1987,12(6):73-81.
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