Abstract
The mission to fly high and very long hour is the specific operating condition of High Altitude Long Endurance (HALE) UAV that require high aspect ratio wing up to 30 to obtain high efficiency aerodynamics. The very flexible wing need to be designed so it can satisfy the deformation and strength criteria. In this research the wing structure of initial version of HALE UAV is designed using carbon composite material. The wing structure is modeled and analyzed using finite element to assess its integrity. The concept of load bearing types of the skin are compared in the analysis. Strength and tip deflection criteria are used to evaluate the wing structure design. The result shows the concept of non-load bearing wing skin will significantly reduce the weight while still can satisfy the strength criteria.
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