Results From F-18B Stability and Control Parameter Estimation Flight Tests at High Dynamic Pressures PDF Download
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Author: Timothy R. Moes
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 146
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Book Description
Author: Timothy R. Moes
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 146
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721095339
Category :
Languages : en
Pages : 144
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Book Description
A maximum-likelihood output-error parameter estimation technique has been used to obtain stability and control derivatives for the NASA F-18B Systems Research Aircraft. This work has been performed to support flight testing of the active aeroelastic wing (AAW) F-18A project. The goal of this research is to obtain baseline F-18 stability and control derivatives that will form the foundation of the aerodynamic model for the AAW aircraft configuration. Flight data have been obtained at Mach numbers between 0.85 and 1.30 and at dynamic pressures ranging between 600 and 1500 lbf/sq ft. At each test condition, longitudinal and lateral-directional doublets have been performed using an automated onboard excitation system. The doublet maneuver consists of a series of single-surface inputs so that individual control-surface motions cannot be correlated with other control-surface motions. Flight test results have shown that several stability and control derivatives are significantly different than prescribed by the F-18B aerodynamic model. This report defines the parameter estimation technique used, presents stability and control derivative results, compares the results with predictions based on the current F-18B aerodynamic model, and shows improvements to the nonlinear simulation using updated derivatives from this research. Moes, Timothy R. and Noffz, Gregory K. and Iliff, Kenneth W. Armstrong Flight Research Center RTOP 529-61-14
Author: Thomas R. Yechout
Publisher: AIAA
ISBN: 9781600860782
Category : Aerodynamics
Languages : en
Pages : 666
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Book Description
Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
Author: Robert C. Nelson
Publisher:
ISBN:
Category : History
Languages : en
Pages : 464
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Book Description
This edition of this this flight stability and controls guide features an unintimidating math level, full coverage of terminology, and expanded discussions of classical to modern control theory and autopilot designs. Extensive examples, problems, and historical notes, make this concise book a vital addition to the engineer's library.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 700
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Author: Albion H. Bowers
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 36
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Book Description
Author:
Publisher:
ISBN:
Category : Technology
Languages : en
Pages : 1020
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Book Description
Author: William Tull Suit
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 68
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Book Description
An iterative method, which is characterized as a maximum-likelihood minimum-variance technique, was used to extract the aerodynamic parameters of a Navion airplane from flight data. The purposes were to compare the results with parameters obtained from wind-tunnel tests and with results obtained by analog matching the same data, and to develop techniques for application of the parameter extraction program. Results from the study showed that the parameter-extraction program can produce aerodynamic parameters which will permit close estimation of the aircraft time histories used in the extraction process. The program determined an estimate of the standard deviations of the states and parameters. These estimates were used to indicate how well the calculated states fit the flight data and the confidence in the values of the estimated parameters. The study also showed that the values of the parameters were affected by the data and mathematical model used during the extraction process. Because of the lack of confidence in the parameters extracted by use of some of the sets of data, several parameters were estimated by other methods. By using a combination of methods, a set of parameters which gave a fit to the data was obtained.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 538
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 512
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Book Description
