Structural analysis of a blended wing body composite aircraft

Abstract

This Master's thesis consists in the structural analysis of a fixed-wing composite unmanned aerial vehicle. The analysis of the aircraft is done in a few steps. The carbon fiber composite used for the skin of the plane is studied thanks to a three point bending test and a finite element model. Then a finite element model of the whole aircraft is developed and is verified thanks to an experimental test. The behavior of the drone performing a resource is studied to ensure that it resists to the load. In order to do that, an estimation of the aerodynamic loads is performed and a panel method software is used to find the distribution of the pressure all over the aircraft. The results show that the skin of the wing is undergoing small stresses compared to its resistance and a new thickness of the skin is proposed. This paper describes all of the methodology used as well as the material and the tools used and an interpretation of the results.