Multivariable Flight Control Design with Parameter Uncertainty for the AFTI/F-16
Abstract
Quantitative Feedback Theory (QFT) techniques are used in the design of a multivariable flight control law for the AFTI/F-16. The techniques were developed by Professor Isaac Horowitz, University of California, Davis, California. The flight control problem involves a multiple input-multiple output (MIMO) plant requiring regulation and control in the presence of parameter uncertainty and disturbances. Based on frequency response fundamentals, the technique uses feedback to achieve closed-loop system response within performance tolerances despite plant uncertainty. The range of uncertainty and the output performance specifications are quantitative parameters in the design process. The MIMO control problem is restructured into a set of two input - single output (multiple input - single output (MISO)) problems where one input is a command input to the system and the other is a disturbance input to be attenuated. The control laws for the MISO problems taken together form the solution of the MIMO problem. To obtain a point of comparison between various design techniques, the identical aircraft model previously developed by Mr. A. Finley Barfield is used in this study. The state space form of the model is converted to the transfer function relationships between the plant input and output variables. A single design is performed over the range of flight conditions investigated. The approach used along with evaluations of the final control laws is presented. Recommendations for further study and discussion of the results obtained are provided. Keywords: F-16 Aircraft, AFTI/F-16 Aircraft.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1989
- Accession Number
- ADA206068
Entities
People
- Brian J. Pawlowski
Organizations
- Air Force Institute of Technology