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[1]王宏亮,晏 卓,李志勋,等.发动机矢量推力测量与校准系统设计研究[J].火箭推进,2018,44(01):75-80.
　WANG Hongliang,YAN Zhuo,LI Zhixun,et al.Design research on thrust vector measurement and calibration system for rocket engine[J].Journal of Rocket Propulsion,2018,44(01):75-80.
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发动机矢量推力测量与校准系统设计研究

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 44 期数: 2018年01期 页码: 75-80 栏目: 测控与试验 出版日期: 2018-02-28
Title:
Design research on thrust vector measurement and calibration system for rocket engine
文章编号:
1672-9374(2018)01-0075-06
作者:
王宏亮;  晏 卓;  李志勋;  刘丽宁;  王朋军
西安航天动力试验技术研究所, 陕西 西安 710100
Author(s):
WANG Hongliang;  YAN Zhuo;  LI Zhixun;  LIU Lining;  WANG Pengjun
Xi'an Aerospace Propulsion Test Technology Institute, Xi'an 710100, China
关键词:
火箭发动机;  矢量推力;  测量校准系统;  设计研究
Keywords:
rocket engine;  vector thrust;  measurement and calibration system;  design research
分类号:
V433.9-34
文献标志码:
A
摘要:
矢量推力作为火箭发动机关键性能参数,对飞行器的飞行轨道精度控制具有重要意义。对火箭发动机工作产生的矢量推力进行准确测量成为目前发动机试验推力测量中亟待解决的问题。介绍了国内外目前矢量推力测量技术的进展和矢量推力测量与校准系统原理组成,分析了系统设计的关键技术,建立了发动机矢量推力测量与原位校准系统。基于矢量推力的解耦算法,开发了矢量推力测量与校准软件。针对某型号姿控发动机进行矢量推力试验测量,成功获得了发动机的矢量推力数据。测得的发动机的矢量力数据中主推力的测量不确定度低于1%,侧向力的不确定度低于5%。
Abstract:
As the key performance parameter of rocket engine, vector thrust is very important for orbit precision control of the spacecraft.How to accurately measure the vector thrust produced by rocket engine has become an important problem of thrust measurement in engine test at present.The progress of vector thrust testing technology in China and foreign countries, as well as working principle and composition of the vector thrust measurement and calibration system are introduced.The key technologies of system development are analyzed.The vector thrust measurement and in-situ calibration system was established.The vector thrust measurement and calibration software was developed.The vector thrust test data were successfully achieved by the vector thrust measurement and calibration system in the process of an altitude control engine test.The measured data showed that the testing uncertainty of the main trust is less than 1% and the testing uncertainty of the lateral thrust is less than 5%.

参考文献/References:

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备注/Memo

收稿日期:2017-10-06; 修回日期:2017-12-20 基金项目:国防科工局技术基础科研项目(JSJL2015203B029) 作者简介: 王宏亮(1979—),男,博士,研究领域为液体火箭发动机试验技术

更新日期/Last Update: 1900-01-01