Pseudosteady state analysis of nonlinear aircraft maneuversAn analytical method has been 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 of attack, roll rate, and the control inputs. The method is 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.
Document ID
19800061723
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Young, J. W. (NASA Langley Research Center Hampton, VA, United States)
Schy, A. A. (NASA Langley Research Center Hampton, VA, United States)
Johnson, K. G. (NASA Langley Research Center Hampton, Va., United States)