Reconfigurable Flight Control Designs with Application to the X-33 Vehicle. Meeting Paper AIAA-1999-4134, Research Engineering, NASA Dryden Flight Research Center

Burken, John J. and Lu, Ping and Wu, Zhenglu (1999) Reconfigurable Flight Control Designs with Application to the X-33 Vehicle. Meeting Paper AIAA-1999-4134, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

Two methods for control system reconfiguration have been investigated. The first method is a robust servomechanism control approach (optimal tracking problem) that is a generalization of the classical proportional-plus-integral control to multiple input-multiple output systems. The second method is a control-allocation approach based on a quadratic programming formulation. A globally convergent fixed-point iteration algorithm has been developed to make onboard implementation of this method feasible. These methods have been applied to reconfigurable entry flight control design for the X-33 vehicle. Examples presented demonstrate simultaneous tracking of angle-of-attack and roll angle commands during failures of the right body flap actuator. Although simulations demonstrate success of the first method in most cases, the control-allocation method appears to provide uniformly better performance in all cases.

EPrint Type:	Other
Keywords:	Failure control system design, Reconfigurable flight controls, X-33 vehicle
Subjects:	(01 - 09) Aeronautics: (08) Aircraft Stability And Control Aircraft/Project: X-33
ID Code:	1267
Deposited On:	06 Febuary 2007
Additional Information:	15 pages. American Institute of Aeronautics and Astronautics Guidance, Navigation, and Control Conference and Exhibit, Portland, Oregon, August 9-11, 1999.