Sliding mode control applied to reconfigurable flight control design

Sliding mode control is applied to the design of a flight control system capable of operating with limited bandwidth actuators and in the presence of significant damage to the airframe and/or control effector actuators. Although inherently robust, sliding mode control algorithms have been hampered by their sensitivity to the effects of parasitic dynamics, such as those associated with control surface actuators. It is known that asymptotic observers can alleviate this sensitivity while still allowing the system to exhibit significant robustness. This approach is demonstrated. The selection of the sliding manifold, as well as the interpretation of the linear design that results after introduction of a boundary layer, is accomplished in the frequency domain. The design technique is exercised on a pitch-axis controller for a simple short-period model of the high angle of attack F-18 vehicle via computer simulation. Stability and performance are compared to that of a system incorporating a controller designed by classical loop-shaping technique.