Aircraft load alleviation by robust yaw-lateral decoupling. (Q1421415)

In an aircraft the pilot reaction is to reduce the yaw rate by a high rudder deflection. But the pilot delay causes high loads at the vertical tail. Here, a new pilot assistance control system is proposed for the yaw disturbance moment compensation. The system is unilaterally decoupled in the sense that the yaw rate reduction is performed robustly and is not observable from the lateral acceleration at the decoupling point. Simulations are presented to show that the system ensures a load alleviation at the vertical tail.