Structure Design Ang Optimization Of A Solar UAV Wine With High Aspect Ratio

Solar UAV is a new energy aircraft that can convert solar energy into electric energy to maintain flight.It has the characteristics of long endurance.Because of the need to collect solar energy,it often needs to fly at high altitude.As a multi-task carrying platform,the development of solar-powered drones has been limited by issues such as solar energy conversion rate,material development,and structural design.It has always been the research focus of aviation powers in the world.This paper uses Ga As thin-film solar cells for solar unmanned aerial vehicles,which have the characteristics of high photoelectric conversion efficiency and high temperature resistance.M55 J high-modulus composite materials are used for the main bearing structure manufacturing,which can not only ensure the strength of the wing but also reduce the structure quality.In this paper,the solar UAV is designed as a dual-wing aerodynamic layout with both front and rear wings in tandem,which is extremely innovative.Then the FX63-137 airfoil with higher lift-to-drag ratio was selected through FLUENT software analysis and comparison.After analyzing several wing structural characteristics and force forms,the double-beam structure layout of variable-diameter tube beams and rectangular beams was designed.The beam is the main load-bearing beam,which is designed as a plug-in type and fixed with pins for easy disassembly.The whole solar UAV is modeled by CATIA,using HYPERMESH to clean up the geometry and divide the mesh,using PATRAN to carry out other finite element pre-processing,using NASTRAN to solve,By modifying the BDF file,the static analysis of the wing under six flight conditions is carried out.In addition,the stress of the connection and the force of the pin are analyzed and checked to ensure the safety and reliability of the connection.Take the climbing condition with the greatest force as the basic model.The Variable Density Method in PATRAN is used to optimize the topology of the wing rib,and the composite layup optimization of the spar is carried out by using ISIGHT optimization platform combined with PATRAN/NASTRAN.The total weight of the wing is reduced by2.46 kg,with a reduction of 23.6%,and the optimized mass meets the design weight.The work of this paper provides theoretical support and reference for subsequent aircraft type.