Reconfigurable Flight Control Designs With Application to the X-33 Vehicle
Burken, John J. and Lu, Ping and Wu, Zhenglu (1999) Reconfigurable Flight Control Designs With Application to the X-33 Vehicle. Technical Report NASA TM-1999-206582, 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: | NASA Technical Memorandum |
|---|---|
| Keywords: | Failure control system design, Reconfigurable flight controls, Robust servomechanism design |
| Subjects: | (01 - 09) Aeronautics: (08) Aircraft Stability And Control Aircraft/Project: X-33 |
| ID Code: | 95 |
| Deposited On: | 03 June 2004 |
| Additional Information: | 20 pages. Presented at AIAA Guidance Navigation and Control Conference, Portland, Oregon, August 9–11, 1999, AIAA-99-4134. |
