Deterministic Reconfigurable Control Design for the X-33 Vehicle. Meeting Paper AIAA-1998-4413, Research Engineering, NASA Dryden Flight Research Center

Wagner, Elaine A. and Burken, John J. and Hanson, Curtis E. and Wohletz, Jerry M. (1998) Deterministic Reconfigurable Control Design for the X-33 Vehicle. Meeting Paper AIAA-1998-4413, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

In the event of a control surface failure, the purpose of a reconfigurable control system is to redistribute the control effort among the remaining working surfaces such that satisfactory stability and performance are retained. Four reconfigurable control design methods were investigated for the X-33 vehicle; Redistributed Pseudo-Inverse, General Constrained Optimization, Automated Failure-Dependent Gain Schedule, and an Off-line Nonlinear General Constrained Optimization approach. The Off-line Nonlinear General Constrained Optimization approach was chosen for implementation on the X-33. Two example failures are shown, a right outboard elevon jam at 25 deg. at a Mach 3 entry condition, and a left rudder jam at 30 deg. Note, however, that reconfigurable control laws have been designed for the entire X-33 flight envelope. Comparisons between responses with the nominal controller and reconfigurable controllers show the benefits of reconfiguration. Single jam aerosurface failures were considered, and failure detection and identification is considered accomplished in the actuator controller. The X-33 flight control system will incorporate reconfigurable flight control in the baseline system.

EPrint Type:	Other
Keywords:	X-33 vehicle
Subjects:	Aircraft/Project: X-33
ID Code:	1287
Deposited On:	07 Febuary 2007
Additional Information:	10 pages. AIAA Guidance, Navigation, and Control Conference and Exhibit, Boston, Massachusetts, August 10-12, 1998.