Abstract:
This paper deals with UAVs that are envisaged to fly solely with the help of solar power. The power
required to keep these solar powered UAVs airborne is produced by solar cells. The objective is to design and
analysis of wing structure of solar powered UAV. In this paper power required for solar UAV is estimated and
required solar panel area is estimated. As wing span must be more than the solar panel area to give necessary power
to UAV, wing span is estimated and it is compared with solar panel area. Then wing structural members were set
and composite material is chosen based on weight requirement. Finally, wing structure for solar UAV is designed by
using CATIA software package and analysis is carried out by ANSYS software package. Wing structure load limits,
stress limits and displacement results are discussed.
