Flight control system design for a flying-wing aircraft

In this paper, the flight control system of a flying-wing aircraft is designed. Significant dynamic nonlinearity and control redundancy are main problems for a flying-wing aircraft. As the over-actuated system and dynamic nonlinearity, the flight control system is divided into two parts: control laws and control allocation. Nonlinear dynamic inversion is used to design the control laws to generate control moments as the commands of control allocator. Because the relationship between moment and effector deflection is nonlinear, the nonlinear control allocation based on SQP is designed. The nonlinear control allocation can reduce the errors between commands and responses of control moments.