飞机颤振试飞操纵面脉冲激励响应仿真方法研究  

Simulation Method of Control Surface Impulse Response of Aircraft Flutter Flight Test

作　　者：雷鸣[1] 卢晓东[1] 霍幸莉[1] LEI Ming;LU Xiao-dong;HUO Xing-li(Chinese Flight Test Establishment,Xiʹan 710089,China)

机构地区：[1]中国飞行试验研究院,西安710089

出　　处：《装备环境工程》2020年第9期48-53,共6页Equipment Environmental Engineering

摘　　要：目的实现颤振试飞操纵面脉冲激励响应仿真,预测操纵面脉冲激励结构响应。方法提出一种飞机颤振试飞操纵面脉冲激励响应仿真方法。该方法以飞机结构动力学有限元模型为基础,建立颤振试飞气动力模型和操纵面脉冲激励力模型。结果以上述模型为基础建立的飞机颤振试飞操纵面脉冲激励响应仿真模型,实现了颤振试飞操纵面脉冲激励响应仿真。首先建立了带副翼单机翼模型操纵面脉冲激励响应仿真模型,并实现了激励响应仿真分析,得到了结构响应幅值。结论开展了全机模型操纵面脉冲激励响应仿真分析,并将仿真结果与飞行试验结果进行对比,两者结果基本一致,验证了该方法的有效性。The paper aims to realize the simulation and prediction of the control surface impulse excitation response of flutter flight test.A simulation method of control surface impulse excitation response was proposed.Based on the finite element model of aircraft structure dynamics,the aerodynamic model of flutter flight test and the impulse excitation force model of control surface were established.Based on the above models,the simulation model of control surface impulse excitation response of flutter flight test was established to realize the simulation of control surface impulse excitation response.Firstly,the simulation model of control surface impulse excitation response of single wing with aileron was established.The simulation analysis of excitation response was conducted,and the structural response amplitude was obtained.The simulation analysis of the control surface impulse excitation response of the whole aircraft model is carried out.The simulation results are compared with the flight test results.The two results are basically consistent,verifying the effectiveness of the method.

关 键 词：颤振试飞 操纵面脉冲激励 仿真建模 激励响应仿真 飞行试验 

分 类 号：V216[航空宇航科学与技术—航空宇航推进理论与工程]