结构模态耦合试验稳定性裕度研究及应用  

STUDY AND APPLICATION OF STABILITY MARGIN IN SERVO-STRUCTURE MODAL COUPLING TEST

作　　者：戴亚光[1] 沈恩楠 苍峰[1] 胡家亮[1] 王标[1] DAI Yaguang;SHEN Ennan;CANG Feng;HU Jialiang;WANG Biao(Shenyang Aircraft Design and Research Institute,Shenyang 110016,China)

机构地区：[1]沈阳飞机设计研究所,沈阳110016

出　　处：《力学与实践》2023年第4期783-792,共10页Mechanics in Engineering

摘　　要：针对某型验证机纵向伺服弹性稳定性裕度不足的问题,建立了基于结构模态耦合试验和仿真的分析方法。通过比较原型机与验证机之间传感器幅值裕度和响应曲线,初步判定传感器安装结构响应过大为此次裕度不足的主要原因。通过控制律仿真环节和机体动力学仿真环节建立了结构模态耦合仿真模型,模拟试验输入信号,获得传感器响应数据。通过结构模态耦合仿真,验证了倍频现象是导致传感器安装结构响应过大的原因,进而导致纵向稳定性裕度不足。提出了一种传感器支持系统可调频率动态控制装置,可有效提升结构模态耦合试验稳定性裕度。For the problem of insufficient longitudinal stability margin of a certain type of aircraft,an analysis method based on servo-structure modal coupling test and simulation is established.By comparing the sensor amplitude margin and response curve between the prototype and the verifier,it is preliminarily determined that the excessive response of the mounting structure is the main reason of the insufficient margin.The structural modal coupling simulation model is established through the control law simulation and the organism dynamics simulation,and the sensor response data is obtained by simulating the input signal of the test.Through the structural modal coupling simulation,it is proved that the double frequency phenomenon is the cause of the large response of the sensor installation structure,which leads to the lack of longitudinal stability margin.An adjustable frequency dynamic control device of sensor support system is proposed to effectively improve the stability margin of structural modal coupling test.

关 键 词：结构模态耦合试验 气动伺服弹性 稳定性分析 

分 类 号：V216.2[航空宇航科学与技术—航空宇航推进理论与工程]