Date of Award
12-1990
Document Type
Thesis
Degree Name
Master of Science in Aeronautical Engineering
Department
Department of Aeronautics and Astronautics
First Advisor
Brett Ridgely, Captain, USAF
Abstract
This work follows Capt. R.L. Riddle's 1989 thesis (ADA216147) which compared conventional, H2 and H∞ controlled guided missiles in simulated flyouts against an airborne target. The simulation results did not clearly demonstrate the H2 and H∞ controller advantages. In this study the missile model and simulation were refined. In addition to simulation runs, performance, noise attenuation, and μ (structural singular value) robustness analyses were conducted. Results showed areas where improvement was needed in the H2 and H∞ controllers used in the study. An H2 and H∞ controller redesign is recommended using the μ synthesis design technique. Additional simulation runs are also recommended to examine whether the improved controllers reduce miss distances.
AFIT Designator
AFIT-GAE-ENY-90D-13
DTIC Accession Number
ADA230524
Recommended Citation
Kolbow, Steven R., "Robustness of H2 and H∞ Design Techniques in the Design of a Guided Missile Controller" (1990). Theses and Dissertations. 7849.
https://scholar.afit.edu/etd/7849
Comments
Alternate title on DTIC: Robustness of Hardy Space with Finite 2-Norm and Hardy Space with Finite Infinity-Norm Design Techniques in the Design of a Guided Missile Controller