Research On Dynamic Characteristics Of Excitation Force Source System

Aeroelastic flutter has always been an important problem in the structural design of aerocraft.We always study the flutter problem through experiments,including wind tunnel flutter experiments and flight flutter tests.Using the dry wind tunnel test system is an innovative method which can determine the critical flutter speed and flutter frequency of aircraft structure without wind tunnel.The test is carried out on the real full-scale structure.We exert concentrated force,coming from exciter and is used to simulate the unsteady aerodynamic force in the flight process,to the test object.In this paper,some problems involved in the design of multi input and multi output force controller,when establishing dry wind tunnel test system,are studied.In order to get the data needed to identify the system model,the excitation force source system and sine sweep flutter test technology are studied,the excitation signal,detailed test scheme and specific test operation steps are designed;in order to improve the accuracy of system identification results,three data preprocessing steps are designed;in order to get the state space model of the system,the specific steps and processes of the algorithm are obtained by studying the principle and implementation process of the algorithm;based on the study of single input and single output excitation force source system identification,the identification of multi input and multi output excitation force source system is studied.Finally,the dynamic characteristics of the excitation force source system in the dry wind tunnel test system are studied,and a complete model acquisition method is formed,which lays a solid foundation for the design of multiple input and multiple output force controller.