Conceptual Design and Fluid Structure Interaction Analysis of a Solar Powered High-Altitude Pseudo-Satellite (HAPS) UAV Wing Model

High altitude platforms or Pseudo-satellites (HAPS) are unmanned aerial vehicles that can fly above 17 km from sea level. It can take advantage of weak stratospheric winds and solar energy to operate without interfering with current commercial aviation and with enough endurance to provide long-term services as satellites do. The technological innovations and the growing urgency to expand the availability of broadband led to the development of HAPS. Besides that, Earth observation, positioning, astronomy, and science are the main applications of High altitude platforms, or Pseudo-satellites (HAPS). In this paper, the conceptual design of the novel HAPS UAV based on the initial requirements regarding cruising height of 20 km, the cruising velocity of 25 m/s, and payload of 15 kg were performed and described. The HAPS wing was defined and aerodynamically studied in detail. The computed nominal load was used as input parameter for structural analysis of the wing’s inner structure comprising outer shell, main spars, and ribs made of composite and plastic materials. All computations were performed using commercial software package ANSYS. The obtained results are discussed and graphically presented by computed stress and deformation fields