固体火箭发动机振动试验过试验分析与控制  

Analysis and Control of Excessive Level in Vibration Test for Solid Rocket Motor

作　　者：王世辉[1] 张磊[1] 李铁[1] 张昱[1] 云杰[1] 石鹏[1] 

机构地区：[1]中国航天科工集团第六研究院601所,呼和浩特010076

出　　处：《计算机测量与控制》2017年第4期247-250,共4页Computer Measurement &Control

基　　金：军品自主创新项目

摘　　要：针对固体火箭发动机振动试验过程中出现局部过试验情况影响振动试验质量以及由于响应测点分布的局限性导致试验周期延长等问题,采用有限元技术与实际试验方法相结合,构建振动力源、试验夹具和固体火箭发动机一体化有限元模型;应用此模型进行振动试验系统动态力传递特性研究,找出振动力源、试验夹具和发动机之间动态力传递规律,选择合适的控制点与控制策略,改善振动试验局部过试验问题,提高振动试验质量,缩短试验周期。According to local excessive test in vibration test procedure of solid rocket motor impacting test quality as well as measuring points distribution limitations leading to extended response test cycle, combined with finite element and actual test methods, building incen rive source, test fixtures and finite element model of integration for solid rocket motor. Vibration test analysis of dynamic force transmission characteristics using these models, identifying laws of dynamic transitivity between force source, test fixtures and solid rocket motors, then select the appropriate control points and control strategy to ease local excessive experiment problems of vibration test, to improve quality, shorten the period of experiment.

关 键 词：振动与波 固体火箭发动机振动试验过试验传递特性 

分 类 号：V435.6[航空宇航科学与技术—航空宇航推进理论与工程]