Structural Design,Manufacturing and Verification of Composite Material Wing Beam for Solar-Powered UAV
Solar-powered drones are equipped with wings that possess typical characteristics of low wing loading,high flexibility,and high aspect ratio.As the main load-bearing structure of the wing,the wing spar has very strict requirements on its load capacity and weight.The key technical issues in the research of solar-powered drone spar structures were how to improve the load efficiency of the spar structure,achieve a comprehensive balance between load capacity and weight,and realize the integrated design and manufacturing of large-scale composite material spars.This paper proposes a fast structural configuration selection and optimization design method for the composite material spar design of solar-powered drones.This method determines the design parameters by calculating the load capacity of the spar cross-section,and considers the ply symmetry,strain constraint,and stability constraint at the same time.It can avoid building a full-scale finite element model and performing iterative calculations at the scheme stage,thus improving the design efficiency of the spar structure.Secondly,for the large-scale composite material tubular spar structure,a dedicated molding method is proposed,which realizes the integrated manufacturing of the spar and ensures the quality of the molded parts,providing a reference for the manufacturing process of similar large-scale composite material structures.Finally,a static test of a 2 m-scale tubular spar is carried out,and the strain results of the typical cross-section are within 10%error of the design results,verifying the applicability of this fast optimization design method.
Composite materialsWing sparSolar-powered UAVStructural designFinite element methodLay up
万方数据
维普
