Date of Graduation

12-2021

Document Type

Thesis

Degree Name

Master of Science in Electrical Engineering (MSEE)

Degree Level

Graduate

Department

Electrical Engineering

Advisor/Mentor

McCann, Roy A.

Committee Member

Balda, Juan C.

Second Committee Member

Wu, Jingxian

Keywords

Actuator Failure; Adaptive Control; Aircraft Control; Aircraft Model; LQR; Transport Aircraft

Abstract

Aircraft operate over a wide range of conditions including atmospheric, weight, and center ofgravity changes. This presents a substantial challenge to automatic control system designers. When these operating conditions are merged with a partial or full control surface failure, automatic flight control is near impossible with conventional controllers. Additionally, when pilots experience control failure emergencies during flight, workload and fatigue increase drastically. The continued research of automatic flight control systems that can seamlessly adapt to unmodelled failures will enable a new generation of robust aircraft control. In this paper a 9th order 6 degree of freedom aircraft model is used to evaluate a transport type aircraft’s response to an adaptive controller given unknown actuator failures. A differential thrust transport type aircraft model is developed and modeled in MATLAB and Simulink. A nominal controller is then designed using a linear quadratic regulator (LQR). This generates a model reference response to a perturbed flight condition. An adaptive controller is subsequently implemented as a controller to the linearized aircraft model. This enables the study of convergence to the uninhibited reference output after multiple actuator failures.

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