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Optimal design of control systems for prevention of aircraft flight departureControl 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. In the analysis, the general nonlinear flight dynamic equations with nonlinear aerodynamics are numerically integrated; and the dynamic characteristics needed in the optimization process are then identified from the dynamic response. To assure a reasonable solution, the initial input values of the design variables are estimated through a sensitivity analysis. To demonstrate the method, the pitch departure prevention for an F-16 configuration is demonstrated.
Document ID
19940004740
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lan, C. Edward
(Kansas Univ. Lawrence, KS, United States)
Ge, Fu-Ying
(Kansas Univ. Lawrence, KS, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1990
Publication Information
Publication: NASA. Langley Research Center, The Third Air Force(NASA Symposium on Recent Advances in Multidisciplinary Analysis and Optimization
Subject Category
Aircraft Stability And Control
Accession Number
94N71495
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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