Aeroelastic Modeling And Active Control Of Civil Aircraft With A High Aspect Ratio Flexible Wing

Large civil aircraft is the medium and long-term development planning is one of the sixteen major research projects,this paper focuses on the elastic problem of civil aircraft with high aspect ratio of flexible wing,carry out researches of the flutter suppression and gust load alleviation problem,the specific contents are as follows:1.The aeroelastic model of flexible wing is established.Firstly,the dynamics model of the structure with the trailing edge control surface two yuan wing,introduction of beam element model,the high aspect ratio of flexible wing finite element division,the establishment of a high aspect ratio structure dynamics model of flexible wing.Secondly,based on the quasi steady theory,the expression of 2D wing aerodynamic force and moment was analysed.Finally,the structural dynamic model is coupled with the aerodynamic model,and the aeroelastic model of the 2D wing and the aeroelastic model of the three-dimensional flexible wing are simplified.2.First of all,according to the elastic model of two wing gas second chapter established dynamic design,robust predictive control for active flutter suppression controller based on the Lyapunov stability theorem to prove the stability of the controller,and the feasibility of this method is proved by simulation experiments,improve the flutter critical speed 30%.Secondly,the proposed method is applied to a three dimensional flexible wing aeroelastic model.The simulation results show that the robust predictive controller can achieve active flutter suppression.3.Based on disturbance observer method,the design of gust load alleviation for flexible wing is carried out.Firstly,the design method of disturbance observer is presented.Secondly,combined with the predictive controller design in the third chapter,by using the Lyapunov stability theory,the stability of the overall closed-loop system is proved.The result of simulation shows that the elastic model for two airfoil aerodynamic disturbance observer without static error,gust load alleviation law of 90%;and the elastic model of three-dimensional flexible wing,10% wing tip disturbance observation error,gust load alleviation rate was 47%,the gravity center of gust load relief rate of 87%.Through the study of the above proposition,this paper preliminary implementation for large civil aircraft with high aspect ratio,flexible wing aeroelastic modeling and active control,which laid a theoretical foundation for the design and gas in our country large civil aircraft composite wing aeroelastic control.