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Nonlinear reconfiguration for asymmetric failures in a six degree-of-freedom F-16
Please use this identifier to cite or link to this item:
http://hdl.handle.net/1860/771
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| Title: | Nonlinear reconfiguration for asymmetric failures in a six degree-of-freedom F-16 |
| Authors: | Thomas, Suba
Kwatny, Harry G.
Chang, Bor-Chin |
| Keywords: | F-16 (Jet fighter plane)--Automatic control--Mathematical models
Machine parts--Failures--Mathematical models |
| Issue Date: | Jun-2004 |
| Publisher: | American Automatic Control Council |
| Citation: | Proceedings, American Control Conference, pp 1823-1828. Retrieved April 2006 from http://www.pages.drexel.edu/~hgk22/OnlinePubs/Thomas%20Kwatny%20Chang%20ACC04%200326_WeP15.6.pdf. |
| Abstract: | In this paper we consider an F-16 fighter aircraft
subject to asymmetric actuator failures. To address nonsymmetric
faults it is not possible to decouple the longitudinal
and lateral dynamics. It is necessary to deal with a full six
degree of freedom airframe. First, we outline an automated
procedure to assemble symbolic and simulation models of
complex aircraft. The symbolic model can be manipulated in
various ways and used for both linear and nonlinear control
system design. In the event of actuator failures, the failed
surfaces not only cease to function as viable inputs but also
impose persistent disturbances on the system. As previously
shown, the problem of designing a reconfigured controller can
be formulated as a nonlinear disturbance rejection problem.
We apply this method to design a controller for the F-16. |
| URI: | http://hdl.handle.net/1860/771 |
| Appears in Collections: | Faculty Research and Publications (MEM)
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