轨/姿控火箭发动机推力矢量动态测试系统测量原理与动态性能  

Measurement Principle and Dynamic Performance of Pulse Thrust Vector Measuring System for Attitude/Orbit Rocket

作　　者：任宗金[1] 孙宝元[1] 张军[1] 钱敏[1] 

机构地区：[1]大连理工大学精密与特种加工教育部重点实验室,辽宁大连116024

出　　处：《航空学报》2009年第11期2037-2044,共8页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(50475152;50675026)

摘　　要：基于国防和航天对轨/姿控火箭发动机脉冲推力矢量动态测试的重大需求,以压电石英为力敏,研制了压电式推力矢量动态测试系统。在探讨推力矢量描述参数及计算的基础上,提出了一种推力矢量测量方案。根据静力平衡原理,推导了求解推力矢量的一般方程。改进了非线性模态分析方法,以所获取的实际动态响应曲线为基础,建立了测试系统的理论动力学模型,利用拉普拉斯变换与逆变换、卷积定理,研究了系统的动态性能和脉冲推力测量性能。针对脉冲推力测量过程中所产生的误差,提出了一种基于理论动力学模型的加速度补偿算法。实验结果证明了测量方案和加速度补偿算法的可行性。To meet the need to improve the control precision of rocket engines, a piezoelectric measurement system is developed with quartz crystal as the force-sensitive element for measuring the dynamic thrust vector of an attitude/orbit rocket. After introducing and calculating the describing parameters of the thrust vector, this article puts forward a measurement scheme. According to the static balance principle, the general equations for solving the describing parameters are derived and proved reliable. The nonlinear modal analysis is improved to build a theoretical dynamic model based on actual frequency response and phase response. The dynamic performance and the pulse measurement performance are obtained by Laplace transform and the inverse and convolution theorem. In studying the pulse measurement, dynamic error is produced, mainly by acceleration. A compensation algorithm for acceleration is advanced based on the theoretical dynamic model. Finally, the experimental results prove that the measurement scheme and the compensation algorithm are feasible and reasonable.

关 键 词：推力测量 模态分析 动态响应 加速度 

分 类 号：V412.1[航空宇航科学与技术—航空宇航推进理论与工程] TH823[机械工程—仪器科学与技术]