Aircraft separation´s control law simulation based on real time aerodynamics of unsteady flow-field

Modeling aerodynamics of the separation aircraft is important for the controlling the separation aircraft. Using unstructured dynamic mesh method, coupled with Euler equation solver, unsteady flow-field solve give the real time aerodynamics to control model. Controlled by control law, the control surfaces as single moving bodies can deflect for attitude control. In time domain, through this simulate system, user can design and adjust the control law for separation aircraft. Considering the inertia of control system, the real time aerodynamics is delayed for control system. At the same time, control surfaces´ deflection angle and angle velocity saturation are considering. The result of simulation indicated that the generic control law for aircraft flight is not suit to controlling separation. The reason for this phenomena is severity unsteady interfere aerodynamics action on separation aircraft. Additional exciter is introduced by control surfaces´ deflection angle and angle velocity saturation. The exciter brings on control motion´s oscillatory and divergence. Appropriate reduced the parameter of control law and increased pass band of control law, we can improve separation aircraft´s control system performance.