Application of dynamical systems theory to the high angle of attack dynamics of the F-14
- Creators
- Jahnke, Craig C.
- Culick, Fred E. C.
Abstract
Dynamical systems theory has been used to study the nonlinear dynamics of the F-14. An eight degree of freedom model that does not include the control system present in operational F-14's has been analyzed. The aerodynamic model, supplied by NASA, includes nonlinearities as functions of the angles of attack and sideslip, the rotation rate, and the elevator deflection. A continuation method has been used to calculate the steady states of the F-14 as continuous functions of the control surface deflections. Bifurcations of these steady states have been used to predict the onset of wing rock, spiral divergence, and jump phenomena which cause the aircraft to enter a spin. A simple feedback control system was designed to eliminate the wing rock and spiral divergence instabilities. The predictions were verified with numerical simulations.
Additional Information
© 1990 by Craig C. Jahnke. Published by the American Institute of Aeronautics and Astronautics, Inc. with permission. This work was partly supported by CALTECH funds and partly supported by a grant from the National Aeronautics and Space Administration, Ames Dryden Flight Research Center. The F-14 aerodynamic model was supplied by Joe Gera, Acting Assistant Branch Chief, Vehicle Technical Branch, Ames Dryden Flight Research Center.Attached Files
Published - 341_Jahnke_C_1990.pdf
Files
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Additional details
- Eprint ID
- 21071
- Resolver ID
- CaltechAUTHORS:20101130-140634171
- Caltech
- NASA
- Ames Dryden Flight Research Center
- Created
-
2010-12-03Created from EPrint's datestamp field
- Updated
-
2019-10-03Created from EPrint's last_modified field
- Caltech groups
- Guggenheim Jet Propulsion Center, GALCIT
- Series Name
- AIAA Papers
- Series Volume or Issue Number
- AIAA-90-0221
- Other Numbering System Name
- AIAA
- Other Numbering System Identifier
- 1990-221