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Application of dynamical systems theory to the high angle of attack dynamics of the F-14Dynamical 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-14s 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.
Document ID
19900035129
Document Type
Conference Paper
Authors
Jahnke, Craig C. (California Inst. of Tech. Pasadena, CA, United States)
Culick, Fred E. C. (California Institute of Technology Pasadena, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
AIRCRAFT STABILITY AND CONTROL
Report/Patent Number
AIAA PAPER 90-0221
Distribution Limits
Public
Copyright
Other