Modeling and control for near-space vehicles with oblique wing

In this paper, the flight motion model for near-space vehicle with an oblique wing is presented, and the flight control system is developed using dynamic inversion method. Firstly, based on its asymmetry configuration and special aerodynamic characteristic, the six-degree-of-freedom nonlinear equations of flight motion are derived using Newton´s second law and law of inertia via considering the influence of oblique wing. Secondly, the dynamic inversion control scheme is designed for the near-space vehicle with an oblique wing. Finally, simulation results are presented to illustrate the effectiveness of the proposed flight control scheme.