In this paper we analyze the influence of flight control law on the spin dynamics of an aerodynamically asymmetric aircraft. The control law evaluated with aircraft model consists of globally nonlinear controller obtained from gain-scheduling of linear controllers. High fidelity aerodynamic model, in the form of lookup tables, is developed from static, coning and oscillatory coning rotary balance wind tunnel tests. Prediction of all attainable steady spin modes is done by solving three degrees-of-freedom aircraft model and influence of high alpha yawing moment asymmetry on spin equilibria shape is analyzed. Numerical simulations of fully developed spins in open-loop and closed-loop configurations are performed to investigate affect of control law on the dynamic characteristics of aircraft spin. It is found that large amplitude oscillations in angle of attack and sideslip, observed in open-loop left and right flat spins, are significantly damped by the control law. The control law also effectively reduces the recovery time of left flat spins; however recovery of right flat oscillatory spins, which exist across the entire range of aileron deflections and for all elevator settings, is not accelerated when control law is employed.
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