The primary purpose of this study is to develop a nonlinear feedback control law for the F / A-I8 fighter aircraft that performs a fast half-loop maneuver. This feedback law is developed using a singular perturbation approach. A secondary purpose of this study is to establish a baseline for time optimal half-loop maneuvers. The singular perturbation approach makes it possible to develop a state feedback control law which rotates the velocity vector through one hundred and eighty degrees at a maximum equilibrium pitch rate with a nearly constant angle of attack. The response of the aircraft to the control law is compared to simulations of half-loop maneuvers generated at NASA Langley Research Center. / Master of Science
| Identifer | oai:union.ndltd.org:VTETD/oai:vtechworks.lib.vt.edu:10919/42053 |
| Date | 12 April 2010 |
| Creators | Garrett, Frederick Earl |
| Contributors | Aerospace Engineering, Stalford, Harold L., Cliff, Eugene M., Lutze, Frederick H. Jr. |
| Publisher | Virginia Tech |
| Source Sets | Virginia Tech Theses and Dissertation |
| Detected Language | English |
| Type | Thesis, Text |
| Format | xix, 223 leaves, BTD, application/pdf, application/pdf |
| Rights | In Copyright, http://rightsstatements.org/vocab/InC/1.0/ |
| Relation | OCLC# 18959249, LD5655.V855_1988.G377.pdf |
Page generated in 0.0026 seconds