A wing rock model for the F-14A aircraft.
Wright, Steven Roland
Schmidt, Louis V.
Howard, Richard M.
MetadataShow full item record
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.
"Submitted in partial fulfillment of the requirements for the degree of Aeronautical and Astronautical Engineer from the Naval Postgraduate School June 1992"
RightsThis 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.
Showing items related by title, author, creator and subject.
Romano, M.; Agrawal, B. (2004);The dynamics equations of a spacecraft consisting of two bodies mutually rotating around a common gimbal axis are derived by the use of the Newton–Euler approach. One of the bodies contains a cluster of single-gimbal var ...
Giraldo, F.X. (2001);The spectral element method for the two-dimensional shallow water equations on the sphere is presented. The equations are written in conservation form and the domains are discretized using quadrilateral elements obtained ...
The numerical solution and analysis of airplane spin equations modeled in a fixed coordinate system Champoux, Robert Louis (1972-12);Three forms of the airplane spin equations of motion, derived by Buehler in Reference [l], form the basis for the development of a computer program designed to seek dynamically stable equilibrium solutions of a spinning ...