Publication Date
2021
Document Type
Thesis
Committee Members
Mitch Wolff, Ph.D. (Advisor); Scott Thomas, Ph.D. (Committee Member); James Menart, Ph.D. (Committee Member)
Degree Name
Master of Science in Mechanical Engineering (MSME)
Abstract
A set of guidance control laws is developed for application to a reduced order dynamic aircraft model. A feedback control formulation utilizing a linear quadratic regulator (LQR) is developed, together with methods for easing the design burden associated with gain tuning. Metrics are developed to assess the stability margin of the controller over the full flight envelope of a notional unmanned aerial vehicle (UAV) model. A feedforward control path is then added to the architecture. The performance of the guidance control laws is assessed through time domain step response metrics as well as through execution of a design mission. The thesis closes with a discussion of possible improvements regarding gain optimality and run-time performance of the model.
Page Count
127
Department or Program
Department of Mechanical and Materials Engineering
Year Degree Awarded
2021
Copyright
Copyright 2021, all rights reserved. My ETD will be available under the "Fair Use" terms of copyright law.
