Flying-wing type UAV design optimization by incorporating flight stability constraints

A flying wing aircraft is a type of aircraft that has no empennage and fuselage. This type of configuration has smaller drag and radar cross section in comparison to conventional aircraft configurations. Flying wing aircraft has a number of difficulties related to stability and control. 4.6kg UAV model equipped with winglets was designed previously. The goal of this research is to design statically and dynamically stable flying wing aircraft without use of winglets. SQP optimization algorithm with athena vortex lattice (AVL) software were implemented to optimize the aircraft. Feasible solution has been found and verified using 6DOF simulation.