摘要
本文论述了固体火箭发动机0.5%高精度测试系统的设计原则、结构特点和精度分析方法.经长期静态调试和发动机试车考核,航天部正式鉴定,认可系统设计合理,工作运行稳定可靠,稳态推力静标精度达到0.2%,原位校准力值精度达到0.05%,推力相对总不确定度优于0.3%,三年长期稳定性达到0.01%.文中所述机电系统一综合设计思想,AD-1精密数据放大器、模拟信号发生器的研制和应用,人机对话等编程方法的巧妙配合,为建稳定立可靠的高精度测试系统提供了借鉴.
In this paper,the design principle,structure features and the accuracy analysis method of a test system with accuracy of 0.5% for solid rocket engines are introduced. The system shows rational design and stable and reliable operation during a long abjustment at static state and firing tests and has been approved by the Ministry of Aerospace Industry. The accuracies of the system respectively are 0.2% on static thrust calibration, 0.05% on thrust zeroing, less than 0.3% on relative thrust uncertainty and 0.01% on three year stability.
The comprehensive design idea combining electric and mechanic parts, the development and the application of AD-1 precision data amplifier and simulating signal generator, and the programing method including man-machine communication are also discussed in this paper, which will be used to develop the stable, reliable and high precision test system.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1990年第3期68-73,共6页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
推力
测量
测试技术
Solid rocket engine, Thrust measurement, Measuring technique, Development
