Aeroelasticity And Dynamics Analysis On A Folding Wing Morphing Aircraft

The Aeroelastic and Dynamics simulation problems of folding wing, which is an important design configuration for future intelligent morphing aircraft, have gained investigator significant attention. In this thesis, the folding wing is taken as the research object. In order to research its flutter First of all analysis its structural properties. Afterward ,The profound study Dynamics simulation of the folding process dynamics based on ADAMS is also investigated.The models of the folding wing are constructed by finite element analysis technique, the types of the hinge constraints are analyzed and defined.The folding angle and hinge stiffness are considered as the research parameters.By studying the different folding sub-cases and hinge properties of the folding wing, Analysis in folding process above two parameters influence on modality and flutter.Secondly,the dynamics aircraft model is introduced and had a small signal linearization, Establishment system's transfer function.the constitute and control scheme of the longitudinal control system is studied,Then,tranditional PID control is respectively used to design and simulate the laws of pitching pose holding mode and high holding mode.Based on ADAMS platform, Considers the rigid and flexible mixed model ,the folding processes of the folding wing are simulated and the aeroelastic problems of in the folding process are investigated. Developed the ADAMS subroutine to computation the aerodynamics of Folding wing. Constructs the flight control system in ADAMS. In order to provide the theory the reference guide for folding wing vehicle's further research, Dissertate some flight parameter and motin change rule in the flight process .