Estimation of Aircraft Nonlinear Unsteady Parameters From Wind Tunnel Data PDF Download
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Author: Vladislav Klein
Publisher:
ISBN:
Category : Oscillations
Languages : en
Pages : 46
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Book Description
Author: Vladislav Klein
Publisher:
ISBN:
Category : Oscillations
Languages : en
Pages : 46
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Book Description
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781722208226
Category :
Languages : en
Pages : 44
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Book Description
Aerodynamic equations were formulated for an aircraft in one-degree-of-freedom large amplitude motion about each of its body axes. The model formulation based on indicial functions separated the resulting aerodynamic forces and moments into static terms, purely rotary terms and unsteady terms. Model identification from experimental data combined stepwise regression and maximum likelihood estimation in a two-stage optimization algorithm that can identify the unsteady term and rotary term if necessary. The identification scheme was applied to oscillatory data in two examples. The model identified from experimental data fit the data well, however, some parameters were estimated with limited accuracy. The resulting model was a good predictor for oscillatory and ramp input data. Klein, Vladislav and Murphy, Patrick C. Langley Research Center RTOP 522-33-11-05...
Author:
Publisher: DIANE Publishing
ISBN: 1428996788
Category :
Languages : en
Pages : 29
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Book Description
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1152
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Book Description
Author: Vladislav Klein
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 32
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Book Description
Author: M. J. Queijo
Publisher:
ISBN:
Category :
Languages : en
Pages : 60
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Book Description
Author: J. A. Burns
Publisher:
ISBN:
Category : Aerofoils
Languages : en
Pages : 88
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Book Description
This report is concerned with the development of a general mathematical model for the motion of a two-dimensional airfoil in unsteady aerodynamics and with the study of numerical schemes for estimating parameters in this model. The equations of motion are a set of coupled ordinary and functional differential equations. Approximating Wagner functions are used to construct state space models that retain the hereditary nature of unsteady fluid flow. The results of some simple numerical experiments are presented including a preliminary analysis of wind-tunnel data. (Author).
Author:
Publisher:
ISBN:
Category : Oscillations
Languages : en
Pages : 70
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Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 590
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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.
