摘要
火箭发动机热试车试验需要在试车架上进行,但目前采用的试车架存在占地面积大或结构复杂、建设成本高的问题,不适合中小推力火箭发动机试验。为解决这些问题,该文提出一种操作简易、成本低廉的倾斜式中、小推力火箭发动机试车架设计方案。试车架采用简支框架结构设计,通过强度仿真完善设计方案;根据工程经验,选配性能稳定的推力传感器;采用流体仿真(CFD)模拟试验火箭发动机的燃气羽流场来设计与试车架相匹配的燃气导流槽。在试车架安装调试后,进行火箭发动机热试车试验,结果表明火箭发动机的推力轴线偏差满足指标要求,推力传感器测试正常。
Rocket engine hot commissioning tests are conducted in the test frame,but the present test frame has some shortcomings,such as large area,complex and high construction cost,not suitable for small and mediumsized thrust rocket engine test.To solve those problems,a designing scheme for a tilting small and mediumsized thrust rocket engine test frame with simple operation and low cost was proposed.A simply supported frame structure was utilized for the test frame,and the designing scheme was perfected by strength simulating.A thrust sensor equipped with stable performance was matched according to engineering experience.Gas diversion trench that matches the test frame was designed by conducting the fluid simulation(CFD)of rocket engine to stimulate the gas plume flow field.After the installation and debugging of test frame,the rocket engine heat run test was carried out,and the results show that the thrust axis deviation of rocket engine meets the specification,and the thrust sensor test is normal.
作者
佟显义
徐微
胡广
陈祎航
唐学来
高博
汤崭
TONG Xianyi;XU Wei;HU Guang;CHEN Yihang;TANG Xuelai;GAO Bo;TANG Zhan(First Research Studio,Shenyang Aerospace Xinguang Group Co.,Shenyang 110043,China)
出处
《中国测试》
CAS
北大核心
2020年第5期143-147,共5页
China Measurement & Test
基金
装备预研航天科工联合基金项目(6141B070603)。
关键词
火箭发动机
试车架
导流槽
rocket engine
test frame
diversion trench
