摘要
为研究和探索火箭发动机地面试验推力室脉动压力测量方法和数据分析技术,介绍了火箭发动机试验中脉动压力测量系统的组成和参数的测量方法;分析了引压导管的动态特性及其对脉动压力参数测量的影响;采用齐平安装的方式,按照所述方法建立脉动压力参数测量系统;结合推力室多个振动测点的数据,分别采用快速傅里叶变换(FFT)和小波包分解两种方法对脉动压力数据进行分析。根据两种方法的分析结果推断发动机在径向和切向产生了不稳定燃烧。对探索和推广脉动压力测量技术在火箭发动机试验和其他组合件试验中的应用具有重要意义。
In order to study and explore the measurement method and data analysis technology of pulsating pressure in the thrust chamber of rocket engine ground test,the composition of pulsating pressure measurement system and the measurement method of parameters in rocket engine test are introduced.The dynamic characteristics of the transmission tube and its influence on the measurement of pulsating pressure parameters are analyzed.The measurement system of fluctuating pressure parameters is established by means of flush installation.Combined with the data of several vibration measurement points in the thrust chamber,two methods of fast Fourier transform(FFT)and wavelet packet decomposition are used to analyze the fluctuating pressure data.According to the analysis results of the two methods,it is inferred that the engine has unstable combustion both in radial and tangential directions.It is of great significance to explore and popularize the application of pulsating pressure measurement technology in rocket engine test and other assembly test.
作者
杨懿
于涛
郭亚男
贾志杰
王永鹏
YANG Yi;YU Tao;GUO Ya-nan;JIA Zhi-jie;WANG Yong-peng(Beijing Institute of Aerospace Testing Technology,Beijing 100074,China)
出处
《宇航学报》
CSCD
北大核心
2021年第7期917-926,共10页
Journal of Astronautics
关键词
火箭发动机
脉动压力
引压导管
FFT
小波包分解
Rocket engine
Fluctuating pressure
Transmission tube
Fourier transform
Wavelet packet decomposition
