Parameter Estimation Techniques and Applications in Aircraft Flight Testing PDF Download
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Author: Flight Center
Publisher: CreateSpace
ISBN: 9781499161762
Category :
Languages : en
Pages : 394
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Book Description
To provide a forum for discussion of the status and the future of this technology, the NASA Flight Research Center hosted a Symposium on Parameter Estimation Techniques and Application in Aircraft Flight Testing. Technical papers were presented by selected representatives from industry, universities, and various Air Force, Navy, and NASA installations who are actively working in the field.
Author: Flight Center
Publisher: CreateSpace
ISBN: 9781499161762
Category :
Languages : en
Pages : 394
Get Book Here
Book Description
To provide a forum for discussion of the status and the future of this technology, the NASA Flight Research Center hosted a Symposium on Parameter Estimation Techniques and Application in Aircraft Flight Testing. Technical papers were presented by selected representatives from industry, universities, and various Air Force, Navy, and NASA installations who are actively working in the field.
Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 404
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 390
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Herman A. Rediess
Publisher:
ISBN:
Category :
Languages : en
Pages : 385
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Book Description
Author: National Aeronautics and Space Administration. Flight Research Center
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: James Matthew Clark
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Author: Majeed Mohamed
Publisher: Springer Nature
ISBN: 9811601046
Category : Technology & Engineering
Languages : en
Pages : 66
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Book Description
This book presents neural partial differentiation as an estimation algorithm for extracting aerodynamic derivatives from flight data. It discusses neural modeling of the aircraft system. The neural partial differentiation approach discussed in the book helps estimate parameters with their statistical information from the noisy data. Moreover, this method avoids the need for prior information about the aircraft model parameters. The objective of the book is to extend the use of the neural partial differentiation method to the multi-input multi-output aircraft system for the online estimation of aircraft parameters from an established neural model. This approach will be relevant for the design of an adaptive flight control system. The book also discusses the estimation of aerodynamic derivatives of rigid and flexible aircraft which are treated separately. The longitudinal and lateral-directional derivatives of aircraft are estimated from flight data. Besides the aerodynamic derivatives, mode shape parameters of flexible aircraft are also identified in the book as part of identification for the state space aircraft model. Since the detailed description of the approach is illustrated through the block diagram and their results are presented in tabular form with figures of parameters converge to their estimates, the contents of this book are intended for readers who want to pursue a postgraduate and doctoral degree in science and engineering. This book is useful for practicing scientists, engineers, and teachers in the field of aerospace engineering.
Author: J. A. Mulder
Publisher:
ISBN: 9789283507482
Category : Aerodynamics
Languages : en
Pages : 191
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Book Description
Pt. 1 examines the practical application of parameter estimation methodology to the problem of estimating aircraft stability and control derivatives from flight test data. The primary purpose is to present a comprehensive and unified picture of the entire parameter estimation process and its integration into a flight test program. Pt. 2 covers areas such as flight path reconstruction, nonlinear model identification, optimal input design and flight test instrumentation. This approach is referred to as the Two-Step Method (TSM), also known as Estimation Before Modelling (EBM) in the literature. It will be shown that this approach has significant practical advantages over methods which no attempt is made to decompose the joint parameter-state estimation problem. The two-step method is generally applicable to flight vehicles such as fixed wing aircraft and rotorcraft which are equipped with state of the art inertial reference systems.
