Multiple Timescale Flight Control Using Reconfigurable Sliding Modes

Abstract

Adual-timescaleaircrafte ight-controlproblemisaddressedviacontinuoussliding-modecontrol.Sliding-surface boundary-layer recone guration is used to account for actuator dynamics, dee ection limits, and rate limits. A recone gurable sliding-mode e ight controller is designed that achieves robust, high-accuracy tracking of outerloop command angles before and after damage to an aircraft. Angular rate commands are robustly tracked in an inner loop. The recone gurable e ight-control strategy is based on a continuous sliding-mode controller with direct boundary-layer adaptation for recone guration. On-line explicit system or damage identie cation is not required. Therecone gurablesliding-modee ight-controltechniqueisapplied to anonlineare ight-dynamicsmodelofan F-16 aircraft. Computer simulations demonstrate stability and high-accuracy tracking performance without violation of actuator limits.