DESIGN AND ANALYSIS OF HIGH ALTITUDE PSEUDO SATELLITE (HAPS)

The objective of this project is to develop technologies for the unmanned aerial vehicle (UAV) to achieve a long endurance and other applications with the readily available renewable energy source. The air plane is driven by electric-based propulsion system with power supplied continuously by the endless solar energy. Suitable airfoil is selected in the design level and drag coefficient is estimated, the series of analysis are made with the existing airfoil regarding pressure distribution, flow analysis and other parameters. Unlike conventional aircrafts, a vehicle was designed with consideration of equipping more number of solar cells on the surface to generate sufficient electric power for flight and consequently enhance our main objective. Main priority is given to designing a wing, since it's the main lifting body, thus it should have moderate aspect ratio for better aerodynamic performance, capable of large number of solar cells accommodation and large volume for holding the payload near the center of gravity