火箭喷管三维运动测试的校准装置及误差分析

刘博; 叶东; 车仁生

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火箭喷管三维运动测试的校准装置及误差分析

微纳技术与精密机械 | 更新时间：2020-08-12

- 火箭喷管三维运动测试的校准装置及误差分析
- Calibration equipment for rocket nozzle motion testing and its error analysis
- 光学精密工程 2009年17卷第7期页码：1553-1560
- 作者机构：
  
  哈尔滨工业大学自动化测试与控制系,黑龙江哈尔滨,150001
- 作者简介：
- 基金信息：
  
  国家自然科学基金资助项目(No.50275040)()
- DOI：
  中图分类号： V471;V233
- 收稿日期：2008-11-07，
  
  修回日期：2009-02-01，
  
  网络出版日期：2009-07-25，
  
  纸质出版日期：2009-07-25
- 稿件说明：
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刘博, 叶东, 车仁生. 火箭喷管三维运动测试的校准装置及误差分析[J]. 光学精密工程, 2009,17(7): 1553-1560

LIU Bo, YE Dong, CHE Ren-sheng. Calibration equipment for rocket nozzle motion testing and its error analysis[J]. Editorial Office of Optics and Precision Engineering, 2009,17(7): 1553-1560
刘博, 叶东, 车仁生. 火箭喷管三维运动测试的校准装置及误差分析[J]. 光学精密工程, 2009,17(7): 1553-1560 DOI：

LIU Bo, YE Dong, CHE Ren-sheng. Calibration equipment for rocket nozzle motion testing and its error analysis[J]. Editorial Office of Optics and Precision Engineering, 2009,17(7): 1553-1560 DOI：

摘要

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

轴和

轴的摆动

以及

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 m以内。

Abstract

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

and

coordinate axes

lifting on

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 m.

关键词

Keywords

references

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