Structure Optimal Design For Wings Of A Light And Small Composite Unmanned Aerial Vehicle

The characteristics of composite wing unmanned aerial vehicle(UAV)requires the design of lightweight and high stiffness.The structural optimization design of a composite wing of composite wing UAV is conducted in this paper.Firstly,study the performance of the composite laminated plates.The structural mechanics of different laminates is simulated and analyzed,and the corresponding tensile strength and flexural rigidity are obtained,which verifies the accuracy of the finite element model.The adhesive properties between the laminates are simulated and analyzed.In the test,the bonding strength of the bonding structure under different stress conditions is obtained,which provides material parameters and simplified basis for the finite element analysis of the entire wing.Secondly,according to the design requirements of the wing,through the structural mechanics analysis of the aircraft,the layout of the double-beam multi-ribbed wing structure is determined.Lay out the wing components and complete the simplified finite element model of the wing.The finite element analysis of the wing structure under the two conditions of take-off and landing flight,the deformation and stress of the initial wing structure all meet the design requirements.In order to reduce the weight of the wing structure as much as possible,a number of reinforcement structures were deleted.Four scenarios were analyzed in turn under the flat flight condition,and the best solution is chosen.Wing's structural weight is reduced by 3.2%,wing tip deformation is reduced by 12.6%.Thirdly,on the basis of preliminary design of the wing,taking into account the large influence of wing position parameters on the wing stiffness,the wing is parametrically modeled and the response surface method based on Kriging model is used to optimize it.After optimization,the strength of the wing meets the constraint condition,and the wing tip deformation decreases by 37.3%.Finally,the wing static test to verify the simulation results.The results show that the error between the two is 4.7%,which is in line with the engineering requirements.The results show that the wing structure of the light and small composite wing UAV which is optimized fully meets the design requirements.