作者：王智超，申勋安，胡玉斌，周全宝
单位：北京航天试验技术研究所，北京 100074
中图分类号：V434                
文献标识码：A                
文章编号：1006-883X(2022)02-0006-05
收稿日期：2021-11-25

摘要：燃烧不稳定性是火箭发动机设计中难以消除的不稳定因素，脉动压力测量作为研究燃烧不稳定的重要手段，它的有效准确获取至关重要。文章研究了几种脉动压力测量系统的声振模型及其安装结构固有频率的计算方法，重点分析火箭发动机试验中一种常用的脉动压力测量的声振模型及其安装结构固有频率计算方法，并通过计算分析和标准计量检定得到了不同传压结构的响应频率信息，为发动机脉动压力测量接口设计及脉动压力数据分析提供了依据。研究成果极大地提升了发动机的动态压力测量水平，为发动机可靠性提升提供了准确的依据。
关键词：火箭发动机试验；脉动压力；声振模型；固有频率；实验分析

Natural Frequency Analysis of Installation Structure of Pulsating Pressure Sensor for Liquid Rocket Engine Test
WANG Zhichao, SHEN Xunan, HU Yubin, ZHOU Quanbao
(Beijing institute of aerospace test technology, Beijing 100074, China)
Abstract: Combustion instability is an unstable factor that is difficult to eliminate in the design of rocket engines. Pulsating pressure measurement is one of the important means to study combustion instability. Its effective and accurate acquisition is very important. The paper studies the acoustic and vibration models of several fluctuating pressure measurement systems and the calculation methods of the natural frequencies of their installed structures. It focuses on the analysis of a commonly used acoustic vibration model for pulsating pressure measurement in rocket engine tests and the calculation method of the natural frequency of the mounting structure, and obtains the response frequency information of different pressure transfer structures through calculation analysis and standard measurement verification. It provides a basis for the design of engine pulsating pressure measurement interface and pulsating pressure data analytics. The research results greatly improve the dynamic measurement level of the engine, and provide an accurate basis for the improvement of engine reliability.
Key words: rocket engine test; pulsation pressure; acoustic vibration model; natural frequency; experimental analysis

阅读全文

备注：2022年 第28卷 第02期