Modeling and Simulation for an Aircraft of Seamless Aeroelastic Wing

The purpose of this paper is to discuss the method of modeling and simulation software design for an aircraft of seamless aeroelastic wing. An aeroelastic wing structure model is established, and then a flight control model is linearized by small disturbance method. The characteristic for aeroelastic wing aerodynamic force varying with the flight speed and the control surface deflection is analyzed through some numerical calculation curves. The analyzing results show that the main challenge is how to achieve a specified rolling rate for the aircraft when the control effectiveness drops down within the flight envelope. In order to resolve this problem, the simulation software integrated dynamics force calculating and control system design is developed and a PID control law is designed. The simulation results show that the control plans are feasible to meet the requirement for rolling control of aeroelastic wing aircraft designed by this paper.