固体火箭发动机五分力测量原理及静态误差分析

The theory and static error analysis of solid rocket motor five-component force measurement

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 MZ 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 PX,PY,PZ of thrust vectors on each axis and the torque Mx,My 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.