An analytical method was developed for studying the combined effects of rotational coupling and nonlinear aerodynamics on aircraft response for specified control inputs. The method involves the simultaneous solution of two nonlinear equations which are functions of angle attack, roll rate, and control inputs. The method was applied to a number of maneuvers for a fighter-type aircraft. Time history responses verified the usefulness of the analysis for predicting a variety of response characteristics caused by interacting nonlinear aerodynamic and inertial effects, including spin conditions.
Pseudosteady-state analysis of nonlinear aircraft maneuvers
1980-12-01
Report
No indication
English
Nonlinear decoupling control of aircraft maneuvers
British Library Online Contents | 1996
|Nonlinear Decoupling Control and Aircraft Agility Maneuvers
British Library Conference Proceedings | 1994
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