Accession Number : ADA189848
Title : Multivariable Control Law Design for the AFTI/F-16 with a Failed Control Surface Using a Parameter-Adaptive Controller.
Descriptive Note : Master's thesis,
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Velez, Julio E
PDF Url : ADA189848
Report Date : Dec 1987
Pagination or Media Count : 183
Abstract : Multivariable control laws are designed for the Advanced Fighter Technology Integration F-16 (AFTI/F-16). Both fixed gain and adaptive Proportional plus Integral (PI) controllers are designed for a plant were the number of outputs are not equal to the number of inputs (rectangular plant). Simulations are conducted for a healthy and a failed aircraft model. The failure consists of reducing the left elevator by 50%. When the fixed gain controller is used for the flight control system, the simulation reveals the fact that the aircraft failure causes the output responses to diverge. If provided with a persistently exciting input the adaptive controller prevents the aircraft failure simulation from diverging and going unstable. However, additional testing and/or tuning of the adaptive controller is required to determine and enhance the stability of the adaptive controller.
Descriptors : *ADAPTIVE CONTROL SYSTEMS, *CONTROL THEORY, *FLIGHT CONTROL SYSTEMS, *AERODYNAMIC CONTROL SURFACES, AIRCRAFT MODELS, CONTROL, CONTROL SURFACES, FAILURE, GAIN, MULTIVARIATE ANALYSIS, OUTPUT, RESPONSE, COMPUTERIZED SIMULATION, THESES, TUNING, ATTITUDE CONTROL SYSTEMS, FEEDBACK, INPUT OUTPUT PROCESSING, ALGORITHMS, JET FIGHTERS, ELEVATORS, PARAMETERS, REGULATORS, TRANSONIC FLIGHT, REGRESSION ANALYSIS
Subject Categories : Flight Control and Instrumentation
Distribution Statement : APPROVED FOR PUBLIC RELEASE