火箭发动机喷管三维运动参数的测试是对其精确控制的前提,其校准装置是保证测试精度的关键.本文提出了一种能够直接模拟火箭喷管实际运动并提供标准的位置和运动参数的校准装置,用于火箭喷管三维运动测试的静态和动态校准.在分析火箭喷管运动的基础上,设计了一种新型校准装置的结构.该装置主要由基座、升降台、摇摆台以及喷管标准件组成;具有三个自由度,分别为绕X轴和Y轴的摆动,以及Z轴方向的直线移动.应用多体系统运动学误差理论推导了几何误差源影响校准装置的指向误差和摆心位置误差的公式,分析了几何误差的来源.通过仿真得出了指向误差和摆心位置误差在喷管摆动范围内的分布,指出为满足校准精度,对指向误差影响较大的垂直度误差应控制在15″之内,对摆心位置误差影响较大的相交度误差应控制在80 μm以内.%The 3D motion parameter measurement of a rocket motor nozzle is a premiss for accurately controlling the nozzle,and the calibration equipment is the key to ensure motion testing at a high precision.To test accurately 3D motion parameters, this paper proposes a new calibration equipment to directly simulate the actual motion of the rocket motor nozzle and to supply the standard position and motion parameters for static and dynamic calibrations. After analyzing the motion of the rocket motor nozzle, a new mechanism consisting of a base, a lifting table, a swing table and a standard nozzle model is proposed, which concludes three degrees of freedom, rotation on X and Y coordinate axes, lifting on Z coordinate axis. The terminal error expression is derived by the theory of multi-system kinematic error in consideration of the geometric errors effect on pointing errors and nozzle center position errors,then the origin of geometric errors is analyzed. By the simulated results, the distribution states of pointing errors and center position errors in rotation ranges are obtained. On the basis of the obtained results,it suggests that the orthogonality errors mostly influncing pointing errors should be controlled below 15″, and the axis intersection errors mostly influncing center position errors should be controlled below 80 μm.
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