Design And Research Of Flexible CIGS Thin Film Solar Powered UAV

Small solar UAV has the advantages of long endurance,wide coverage,easy launch and retrieval,and has a broad application prospect in the field of emergency rescue,investigation and inspection.The traditional solar UAV uses monocrystalline silicon solar cell,which is poor in anti deformation and not fit for the high curvature airfoil,since large aspect ratio must be adopted in structure design to obtain enough laying area,which leads to inefficient utilization of the wing leading edge area.In this paper,a small light solar UAV flight platform is designed for CIGS thin film solar cell with high deformation resistance,and the essential structure of UAV is optimized incorporating finite element analysis,which can enrich the design idea and expand the application field of solar UAV.The main research contents are as follows:1.In line with the performance parameters and structural requirements of small CIGS solar UAV,a flight platform with compact structure,large wing area and double vertical tail aerodynamic layout is designed.The MH114 high lift drag ratio airfoil is determined by Profili software after comparing various wing shapes,and the three section approximate trapezoid design is used to improve the wing load performance.2.The finite element analysis of the wing rib is carried out with CATIA software.After several iterations under the constraint conditions,the weight reduction hole distribution of the optimized wing rib is obtained.At 5 °angle of attack,the maximum stress of the optimized wing rib structure is 2.1% higher than that of the traditional circular weight reduction hole,the maximum displacement is 16.7% higher than the original design,the area is reduced by 47.5%,and the structure weight is greatly reduced.Then,the three-dimensional modeling and simulation of the whole aircraft are carried out using Xflr5 software,and the influence of attack angle on the aerodynamic performance of the wing is studied.Furthermore,The self stability of the UAV is verified through the time response analysis of various flight modes of the UAV.3.Based on the research of the influence of parameters matching between units in the CIGS solar cell array on the combined power,the parameters generating the greatest influence on the array matching under different connection modes are determined and the corresponding matching rules are given,which reduce the combined power loss of the array by 8.3%.Finally,the assembly and flight test of the verified UAV are carried out,and the effective endurance is extended by 2 hours and 48 minutes,which provides an important reference for the design of low altitude solar UAV.