Jahnke, Craig C. and Culick, Fred E. C. (1988) Application of dynamical systems theory to nonlinear aircraft dynamics. AIAA Papers, AIAA-88-4372 . American Institute of Aeronautics and Astronautics . http://resolver.caltech.edu/CaltechAUTHORS:20101203-102240185
- Published Version
See Usage Policy.
Use this Persistent URL to link to this item: http://resolver.caltech.edu/CaltechAUTHORS:20101203-102240185
Dynamical systems theory has been used to study nonlinear aircraft dynamics. A six degree of freedom model that neglects gravity has been analyzed. The aerodynamical model, supplied by NASA, is for a generic swept wing fighter and includes nonlinearities as functions of the angle of attack. A continuation method was use to calculate the steady states of the aircraft, and bifurcations of these steady states, as functions of the control deflections. Bifurcations were used to predict jump phenomena and the onset of periodic motion for roll coupling instabilities and high angle of attack maneuvers. The predictions were verified with numerical simulations.
|Item Type:||Report or Paper (Report)|
|Additional Information:||© 1988 American Institute of Aeronautics and Astronautics. This work was partly supported by Caltech funds and partly by a grant from the National Aeronautics and Space Administration, Ames Dryden Flight Research Center.|
|Group:||Guggenheim Jet Propulsion Center|
|Other Numbering System:|
|Official Citation:||Application of dynamical systems theory to nonlinear aircraft dynamics CULICK, FRED E. C., California Institute of Technology, Pasadena AIAA-1988-4372 AIAA Atmospheric Flight Mechanics Conference, Minneapolis, MN, Aug 15-17, 1988.|
|Usage Policy:||No commercial reproduction, distribution, display or performance rights in this work are provided.|
|Deposited By:||Ruth Sustaita|
|Deposited On:||03 Dec 2010 22:36|
|Last Modified:||25 Mar 2014 04:32|
Repository Staff Only: item control page