NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Application of numerical optimization techniques to control system design for nonlinear dynamic models of aircraftControl system design for general nonlinear flight dynamic models is considered through numerical simulation. The design is accomplished through a numerical optimizer coupled with analysis of flight dynamic equations. The general flight dynamic equations are numerically integrated and dynamic characteristics are then identified from the dynamic response. The design variables are determined iteratively by the optimizer to optimize a prescribed objective function which is related to desired dynamic characteristics. Generality of the method allows nonlinear effects to aerodynamics and dynamic coupling to be considered in the design process. To demonstrate the method, nonlinear simulation models for an F-5A and an F-16 configurations are used to design dampers to satisfy specifications on flying qualities and control systems to prevent departure. The results indicate that the present method is simple in formulation and effective in satisfying the design objectives.
Document ID
19900013716
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lan, C. Edward
(Kansas Univ. Lawrence, KS, United States)
Ge, Fuying
(Kansas Univ. Lawrence, KS, United States)
Date Acquired
September 6, 2013
Publication Date
December 15, 1989
Publication Information
Publication: JPL, Proceedings of the 3rd Annual Conference on Aerospace Computational Control, Volume 1
Subject Category
Aircraft Stability And Control
Accession Number
90N23032
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
No Preview Available