摘要
为解决传统火箭发动机安装推力线测量方法耗时较长的问题,通过分析推力线偏差因素、构建偏差计算模型,得到工程简化的推力线快速测算方法。将飞行器推力线偏差分为机体结构偏差和发动机自身推力线偏差,在飞行器装配阶段利用现代化雷达或光学测量技术获取飞行器结构偏差,并结合发动机生产阶段自身推力线偏差数据,可快速计算、获取飞行器安装推力线。最后采用激光雷达推力线测量方法进行对比测试,试验表明快速测算方法仅耗时约10 min、且最大误差小于0.1°,从而验证了该方法的便捷性和有效性,可应用于液体或固体火箭动力飞行器推力线的快速获取。
At present,it takes a long time to get measurement result for the traditional digital measurement of thrust line,which becomes the main bottleneck that restrict the fast re-launch of the reusable rocket powered aircraft.In this paper,the deviation of thrust line during the installation of rocket engine was divided into the structural deviation and thrust line deviation of engine itself.The structural deviation can be obtained through the modern optical measurement technology during the assembling stage.Then the structural deviation and the data of engine thrust line were combined,the engineering calculation method for the engine's installed thrust line data can be quickly obtained before re-launch.The convenience and effectiveness of this method can be confirmed by running a comparative test experiment with the laser radar measurement.The fast calculation method only costs 10 minutes and has a maximum error of 0.1°,which can be applied on quickly measuring the thrust line of liquid or solid rocket-powered aircraft.
作者
刘开磊
王垚
王纯
LIU Kailei;WANG Yao;WANG Chun(Chengdu Aircraft Design and Research Institute, Chengdu 610073, China)
出处
《火箭推进》
CAS
2020年第3期62-67,共6页
Journal of Rocket Propulsion
基金
国家十三五专用技术预先研究项目(303010301)。
关键词
推力线测量
飞行器
火箭发动机
快速测量
偏差分析
工程方法
thrust line measurement
aircraft
rocket engine
fast calculation method
deviation analyse
engineering method
