推力矢量测试平台及原位校准方法研究

对于推力可调式固体姿轨控发动机,推力矢量参数是重要的测试物理量,为了研究固体火箭发动机推力矢量测试问题,提出一种推力矢量测试装置和测试系统。设计出一种固体姿轨控发动机推力矢量测试平台,对推力矢量测试平台的基座进行了模态仿真的分析,得出推力矢量测试平台基座的频率响应在390.71~417.92Hz。对所构建的固体姿轨控发动机推力矢量测试平台进行了测试。通过对推力矢量各分量的原位校准系统构建技术的研究,设计出一套满足单个喷管作用力校准的杠杆组,并进行标定,并得出了原位校准力值-砝码值对应表。对推力矢量主推力进行静态原位校准,并计算校准方程和回归方程,结果表明,该测试装置能够较为精确的测量出固体火箭发动机推力矢量,并且校准曲线的非线性与重复性良好,分别为0.45%、0.47%。

Research on thrust vector test platform and in situ calibration method

The thrust vector parameter is an important test physical quantity for the thrust adjustable solid attitude and orbit control motor.In order to study the thrust vector test of solid rocket motor,a thrust vector test device and test system are proposed.A thrust vector test platform for solid attitude and orbit control motor is designed.The modal simulation analysis of the base of the thrust vector test platform is carried out.The frequency response of the thrust vector test platform base is 390.71~417.92 Hz.The thrust vector test platform of solid attitude and orbit control motor is tested.Through the research on the construction technology of the in-situ calibration system for each component of the thrust vector,a set of lever group meeting the force calibration of single nozzle is designed and calibrated,and the corresponding table of force value weight value of in-situ calibration is obtained.The static in-situ calibration of thrust vector main thrust is carried out,and the calibration equation and regression equation are calculated.The results show that the test device can accurately measure the thrust vector of solid rocket motor,and the calibration curve has good nonlinearity and repeatability,which are 0.45%and 0.47%respectively.