Static Aeroelasticity Structure Optimization For Composite Wing Structures With Bend-twist Coupling

It has brought a great deal of benefits for static and dynamic performance of wings with bend-twist coupling. With the utilization of the bend-twist couple effect of laminated composites, the structure of aircraft can be designed more light, and meet all kinds of design requirement, such as stiffness, strength and so onFirstly, in this paper, several analysis models, which have been proposed within recent 40 years to conduct the bend-twist coupling design of composite wing structures, are reviewed and evaluated. Their advantages and disadvantages are objectively listed and compared as well as to summarize the achievements of the corresponding study methods. And the worth and shortage of analysis models are raised. Secondly we build the analysis model of composite wing structures with bend-twist coupling based on equivalent plate model. We build the four degrees of freedom DQM to solve the equation of the analysis model. Further more, General Problem Solving of the analysis model with material discontinuity was figured out by four degrees of freedom DQEM. Numerical examples were tested, which show the feasibility and effectiveness of the proposed method. Using the above method, the impact of composite material parameters and bend-twist coupling stiffness on the static and dynamic characteristics of the wing has been further researched. Then two kinds of elastic tailoring methods were introduced. The comparison between the elastic tailoring methods was studied by case studies. At last, the elastic tailoring optimization was carried on the structure layout of forward-swept wing and back-swept wing by the optimizing strategy proposed in this paper. Meanwhile, the comparison between the optimization results of two laminate layouts for its own structure layout was done.