固体火箭发动机试验模态分析技术研究  

Solid Propellant Rocket Engine Modal Test and Analysis Technique

作　　者：陶俊强[1] 王翠荣[1] 陈宁芳[1] 翟江源[1] 

机构地区：[1]中国航天科技集团公司四院四○一所,西安710025

出　　处：《固体火箭技术》2001年第2期73-78,共6页Journal of Solid Rocket Technology

摘　　要：将固体火箭发动机划分为 1 4 4个自由度 ,采用锤击法 ,单点激励多点响应 ( SIMO)对其在 4种工况下进行了频率响应的测量 ,应用了多种方法进行模态参数识别和数据拟合 ,并对其结果进行比较 ,获得了发动机在各工况 1 k Hz以内的各阶固有频率、振型和阻尼 。The paper addresses the modal test of solid rocket motor (SRM). The first step is the hammering impact to obtain the frequency response function (FRF) of SRM under four conditions through SIMO(single input/multi output) method. The second step consists of the curve fitting and parameters identifying through different methods, and at last the results are compared under four conditions. As a result, the inherent frequencies, shapes and damps of system within 1kHz are gained. Finally the application of the modal analysis technique to SRM test is presented.

关 键 词：固体推进剂 火箭发动机 试验模态分析 模态参数 频响函数 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]