Date of Award

12-1994

Document Type

Thesis

Degree Name

Master of Science in Electrical Engineering

Department

Department of Electrical and Computer Engineering

First Advisor

Constantine H. Houpis, PhD

Second Advisor

Mier Pachter, PhD

Abstract

An aircraft's response to control inputs varies widely throughout its flight envelope. The aircraft configuration also impacts control response through variations in center of gravity and moments of inertia. Designing a flight control system (FCS) to accommodate the full flight envelope and configuration set of an aircraft is clearly a complex undertaking. Quantitative feedback theory (QFT) is a design tool which enables the engineer to attack this task in an efficient way. Although QFT is a robust control design technique, it is an interactive algorithm allowing the engineer full control over compensator order and gain. In this research effort, a full subsonic flight envelope FCS is designed for the VISTA F-16 aircraft using QFT. Four aircraft configurations are considered. The strict control of the compensator order and gain allowed by QFT facilitates the attainment of desired performance while avoiding physical saturations. In addition, flying qualities are imbedded in the longitudinal design through the use of a control parameter which varies with the aircraft's energy state. This parameter is synthesized to closely reflect the actual control desires of the pilot throughout the aircraft flight envelope. Linear simulations with realistically large control inputs are used to validate the design.

AFIT Designator

AFIT-GE-ENG-94D-24

DTIC Accession Number

ADA289221

Comments

The author's Vita page is omitted.

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