Fast half-loop maneuvers for the F/A-18 fighter aircraft using a singular perturbation feedback control law

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.

Name thesis:degree_name

Master of Science

Level thesis:degree_level

masters

Discipline thesis:degree_discipline

Aerospace Engineering

Department dc:contributor.department

Aerospace Engineering

Grantor dc:publisher

Virginia Tech

Year dc:date.issued

1988

Author dc:creator

• Garrett, Frederick Earl

Chair dc:contributor.committeechair

• Stalford, Harold L.

Committee members dc:contributor.committeemember

• Cliff, Eugene M.
• Lutze, Frederick H. Jr.

Statement dc:rights

• In Copyright

Licence dc:rights.uri

• http://rightsstatements.org/vocab/InC/1.0/

Dc Identifier Other

etd-04122010-083818

OAI identifier oai:identifier

oai:vtechworks.lib.vt.edu:10919/42053