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Accession Number:
ADA151771
Title:
Flight Control System Reconfiguration Design Using Quantitative Feedback Theory.
Descriptive Note:
Master's thesis,
Corporate Author:
AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING
Report Date:
1984-12-01
Pagination or Media Count:
253.0
Abstract:
Quantitative theory is used to develop control laws for the AFTIF-16 with a reconfigurable flight control system. Compensators are synthesized to control pitch rate and roll rate through individually controlled elevators and flaperons. Robust control of these variables is required over a larger portion of the flight envelope despite flight control surface failures. Linearized aerodynamic data are used to develop the aircraft model in state-variable format. The longitudinal and lateral-directional equations are coupled in the control matrix. Individual control of the elevators and flaperons is obtained by dividing the dimensionalized control derivatives for a control surface pair in half and assigning each surface of the pair one-half of the total derivative value. The system with individually controlled surfaces represents a four input-two output system which is transformed into an equivalent two input-two output system for each control surface configuration and flight condition. Quantitative feedback theory is then applied to the equivalent systems. Originator-supplied keywords included Inherent Reconfiguration Loop Transmission Flight control Systems Quantitative Feedback Theory Control Systems Computer Programs Theses.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE
