Nonlinear Receding Horizon Control of an F-16 Aircraft
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Nonlinear Receding Horizon Control of an F-16 Aircraft
Published Date
2002
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American Institute of Aeronautics and Astronautics
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Article
Abstract
The application of receding horizon control (RHC) with the linear, parameter varying (LPV) design methodology to a high-fidelity, nonlinear F-16 aircraft model is demonstrated. The highlights are 1) use of RHC to improve upon the performance of a LPV regulator; 2) discussion on details of implementation such as control space formulation, tuning of RHC parameters, computation time and numerical properties of the algorithms; and 3) simulated response of nonlinear RHC and LPV regulator.
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Reprinted with permission of the American Institute of Aeronautics and Astronautics, Inc. See http://www.aiaa.org/content.cfm?pageid=2 for more information.
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Previously Published Citation
Bhattacharya, R., Balas, G. J., Kaya, M. A., and Packard, A. (2002). "Nonlinear Receding Horizon Control of an F-16 Aircraft." Journal of Guidance, Control, and Dynamics. 25(5), 924-931.
Suggested citation
Bhattacharya, Raktim; Balas, Gary J.; Kaya, M. Alpay; Packard, Andy. (2002). Nonlinear Receding Horizon Control of an F-16 Aircraft. Retrieved from the University Digital Conservancy, https://hdl.handle.net/11299/37102.
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