摘要
飞行器伺服弹性地面试验是测试飞行控制系统与机体之间的动力耦合特性,为飞行器伺服弹性分析模型验证和气动伺服弹性分析提供依据。本文主要介绍了伺服弹性地面试验的原理及方法,以及通过伺服弹性试验同时获得结构模态参数的方法。以某型导弹为对象,介绍了试验的准备、测试过程、伺服弹性及模态参数的测试结果。
Ground servo-elasticity test,which can provide support for the model verification of servo-elasticity analysis and pneumatic servo-elasticity simulation of aircraft,is used to obtain the dynamic coupling characteristics between flight control system and aircraft structure.The theory and method of servo-elasticity ground test of aircraft are introduced in the paper.The acquisition method of modal parameter in servo-elasticity test is also recommended.The test preparation,test process,the test results of servo-elasticity and modal parameter are introduced with a real missile.
出处
《工程与试验》
2017年第4期14-16,90,共4页
Engineering and Test
关键词
伺服弹性
地面试验
开环频率响应试验
闭环稳定性试验
模态参数
servo-elasticity
ground test
open loop frequency response test
closed loop stabilitytest
modal parameter