A wing rock model for the F-14A aircraft.
Loading...
Authors
Wright, Steven Roland
Subjects
Wing rock
F-14A
Nonlinear flight mechanics
Aircraft stability
F-14A
Nonlinear flight mechanics
Aircraft stability
Advisors
Schmidt, Louis V.
Date of Issue
1992-06
Date
Jun-92
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
An investigation of inertial coupling and its contribution to wing rock in the F-14A aircraft has been conducted. Wind tunnel data was used to obtain the stability parameters for angles of attack from zero to 25 degrees, after which linear and nonlinear analyses of the equations of motion were completed. The linearized analysis of the uncoupled longitudinal and lateral-directiondl equations was included to provide a baseline for comparison with the fully coupled, nonlinear equations. In both cases, the equations of
motion were solved numerically and time history traces produced to illustrate aircraft response. Results indicate that a stable short period mode can feed damping energy into an unstable dutch roll mode via the coupling of the equations to produce a stable limit cycle very similar to those experienced in the aircraft. Numerous suggestions for follow on research are presented.
Type
Thesis
Description
"Submitted in partial fulfillment of the requirements for the degree of Aeronautical and Astronautical Engineer from the Naval Postgraduate School June 1992"
Series/Report No
Department
Department of Aeronautics and Astronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funding
Format
73 p.;28 cm.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.