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Results From F 18b Stability And Control Parameter Estimation Flight Tests At High Dynamic Pressures
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Book Synopsis Results From F-18B Stability and Control Parameter Estimation Flight Tests at High Dynamic Pressures by : Timothy R. Moes
Download or read book Results From F-18B Stability and Control Parameter Estimation Flight Tests at High Dynamic Pressures written by Timothy R. Moes and published by . This book was released on 2000 with total page 146 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721095339 Total Pages :144 pages Book Rating :4.0/5 (953 download)
Book Synopsis Results from F-18b Stability and Control Parameter Estimation Flight Tests at High Dynamic Pressures by : National Aeronautics and Space Administration (NASA)
Download or read book Results from F-18b Stability and Control Parameter Estimation Flight Tests at High Dynamic Pressures written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-13 with total page 144 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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
Book Synopsis Results from F-18B Stability and Control Parameter Estimation Flight Test at High Dynamic Pressures by : Timothy R. Moes
Download or read book Results from F-18B Stability and Control Parameter Estimation Flight Test at High Dynamic Pressures written by Timothy R. Moes and published by . This book was released on 2000 with total page 134 pages. Available in PDF, EPUB and Kindle. Book excerpt: A maximun-likelihood output-error parameter estimation technique 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 goals 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/ft2. At each test condition, longitudinal and lateral-directional doublets have been performed using an automated onboard excitation system.
Book Synopsis Stability and Control Estimation Flight Test Results for the SR-71 Aircraft With Externally Mounted Experiments by : Timothy R. Moes
Download or read book Stability and Control Estimation Flight Test Results for the SR-71 Aircraft With Externally Mounted Experiments written by Timothy R. Moes and published by . This book was released on 2002 with total page 98 pages. Available in PDF, EPUB and Kindle. Book excerpt: A maximum-likelihood output-error parameter estimation technique is used to obtain stability and control derivatives for the NASA Dryden Flight Research Center SR-71A airplane and for configurations that include experiments externally mounted to the top of the fuselage. This research is being done as part of the envelope clearance for the new experiment configurations. Flight data are obtained at speeds ranging from Mach 0.4 to Mach 3.0, with an extensive amount of test points at approximately Mach 1.0. Pilot-input pitch and yaw-roll doublets are used to obtain the data. This report defines the parameter estimation technique used, presents stability and control derivative results, and compares the derivatives for the three configurations tested. The experimental configurations studied generally show acceptable stability, control, trim, and handling qualities throughout the Mach regimes tested.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781723022715 Total Pages :124 pages Book Rating :4.0/5 (227 download)
Book Synopsis Determination of the Stability and Control Derivatives of the NASA F/A-18 Harv Using Flight Data by : National Aeronautics and Space Administration (NASA)
Download or read book Determination of the Stability and Control Derivatives of the NASA F/A-18 Harv Using Flight Data written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report documents the research conducted for the NASA-Ames Cooperative Agreement No. NCC 2-759 with West Virginia University. A complete set of the stability and control derivatives for varying angles of attack from 10 deg to 60 deg were estimated from flight data of the NASA F/A-18 HARV. The data were analyzed with the use of the pEst software which implements the output-error method of parameter estimation. Discussions of the aircraft equations of motion, parameter estimation process, design of flight test maneuvers, and formulation of the mathematical model are presented. The added effects of the thrust vectoring and single surface excitation systems are also addressed. The results of the longitudinal and lateral directional derivative estimates at varying angles of attack are presented and compared to results from previous analyses. The results indicate a significant improvement due to the independent control surface deflections induced by the single surface excitation system, and at the same time, a need for additional flight data especially at higher angles of attack. Napolitano, Marcello R. and Spagnuolo, Joelle M. Unspecified Center AIRCRAFT CONTROL; AIRCRAFT STABILITY; ANGLE OF ATTACK; F-18 AIRCRAFT; FLIGHT TESTS; LATERAL STABILITY; LONGITUDINAL STABILITY; MAXIMUM LIKELIHOOD ESTIMATES; PARAMETER IDENTIFICATION; AIRCRAFT MANEUVERS; CONTROL SURFACES; EQUATIONS OF MOTION; MATHEMATICAL MODELS; THRUST VECTOR CONTROL...
Book Synopsis Parameter Estimation Techniques and Applications in Aircraft Flight Testing by :
Download or read book Parameter Estimation Techniques and Applications in Aircraft Flight Testing written by and published by . This book was released on 1974 with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781723750137 Total Pages :38 pages Book Rating :4.7/5 (51 download)
Book Synopsis Real-Time Stability and Control Derivative Extraction from F-15 Flight Data by : National Aeronautics and Space Adm Nasa
Download or read book Real-Time Stability and Control Derivative Extraction from F-15 Flight Data written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-09-16 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: A real-time, frequency-domain, equation-error parameter identification (PID) technique was used to estimate stability and control derivatives from flight data. This technique is being studied to support adaptive control system concepts currently being developed by NASA (National Aeronautics and Space Administration), academia, and industry. This report describes the basic real-time algorithm used for this study and implementation issues for onboard usage as part of an indirect-adaptive control system. A confidence measures system for automated evaluation of PID results is discussed. Results calculated using flight data from a modified F-15 aircraft are presented. Test maneuvers included pilot input doublets and automated inputs at several flight conditions. Estimated derivatives are compared to aerodynamic model predictions. Data indicate that the real-time PID used for this study performs well enough to be used for onboard parameter estimation. For suitable test inputs, the parameter estimates converged rapidly to sufficient levels of accuracy. The devised confidence measures used were moderately successful.Smith, Mark S. and Moes, Timothy R. and Morelli, Eugene A.Armstrong Flight Research Center; Langley Research CenterF-15 AIRCRAFT; PARAMETER IDENTIFICATION; REAL TIME OPERATION; STABILITY DERIVATIVES; CONTROL STABILITY; CONTROL SYSTEMS DESIGN; FREQUENCY DOMAIN ANALYSIS; FLIGHT CONDITIONS; INDUSTRIES; NASA PROGRAMS; FOURIER TRANSFORMATION; REGRESSION ANALYSIS; ALGORITHMS; ERROR ANALYSIS; ONBOARD DATA PROCESSING
Book Synopsis A Procedure for Estimating Stability and Control Parameters from Flight Test Data by Using Maximum Likelihood Methods Employing a Real-time Digital System by : Randall D. Grove
Download or read book A Procedure for Estimating Stability and Control Parameters from Flight Test Data by Using Maximum Likelihood Methods Employing a Real-time Digital System written by Randall D. Grove and published by . This book was released on 1972 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Real-Time Stability and Control Derivative Extraction From F-15 Flight Data by : Mark S. Smith
Download or read book Real-Time Stability and Control Derivative Extraction From F-15 Flight Data written by Mark S. Smith and published by . This book was released on 2003 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Flight Physics by : Konstantin Volkov
Download or read book Flight Physics written by Konstantin Volkov and published by BoD – Books on Demand. This book was released on 2018-02-14 with total page 242 pages. Available in PDF, EPUB and Kindle. Book excerpt: The book focuses on the synthesis of the fundamental disciplines and practical applications involved in the investigation, description, and analysis of aircraft flight including applied aerodynamics, aircraft propulsion, flight performance, stability, and control. The book covers the aerodynamic models that describe the forces and moments on maneuvering aircraft and provides an overview of the concepts and methods used in flight dynamics. Computational methods are widely used by the practicing aerodynamicist, and the book covers computational fluid dynamics techniques used to improve understanding of the physical models that underlie computational methods.
Book Synopsis Flight Stability and Automatic Control by : Robert C. Nelson
Download or read book Flight Stability and Automatic Control written by Robert C. Nelson and published by WCB/McGraw-Hill. This book was released on 1998 with total page 441 pages. Available in PDF, EPUB and Kindle. Book excerpt: The second edition of Flight Stability and Automatic Control presents an organized introduction to the useful and relevant topics necessary for a flight stability and controls course. Not only is this text presented at the appropriate mathematical level, it also features standard terminology and nomenclature, along with expanded coverage of classical control theory, autopilot designs, and modern control theory. Through the use of extensive examples, problems, and historical notes, author Robert Nelson develops a concise and vital text for aircraft flight stability and control or flight dynamics courses.
Book Synopsis Introduction to Aircraft Flight Mechanics by : Thomas R. Yechout
Download or read book Introduction to Aircraft Flight Mechanics written by Thomas R. Yechout and published by AIAA. This book was released on 2003 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Estimation of the Longitudinal and Lateral-Directional Aerodynamic Parameters from Flight Data for the NASA F/A-18 Harv by : National Aeronautics and Space Adm Nasa
Download or read book Estimation of the Longitudinal and Lateral-Directional Aerodynamic Parameters from Flight Data for the NASA F/A-18 Harv written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-10-28 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: This progress report presents the results of an investigation focused on parameter identification for the NASA F/A-18 HARV. This aircraft was used in the high alpha research program at the NASA Dryden Flight Research Center. In this study the longitudinal and lateral-directional stability derivatives are estimated from flight data using the Maximum Likelihood method coupled with a Newton-Raphson minimization technique. The objective is to estimate an aerodynamic model describing the aircraft dynamics over a range of angle of attack from 5 deg to 60 deg. The mathematical model is built using the traditional static and dynamic derivative buildup. Flight data used in this analysis were from a variety of maneuvers. The longitudinal maneuvers included large amplitude multiple doublets, optimal inputs, frequency sweeps, and pilot pitch stick inputs. The lateral-directional maneuvers consisted of large amplitude multiple doublets, optimal inputs and pilot stick and rudder inputs. The parameter estimation code pEst, developed at NASA Dryden, was used in this investigation. Results of the estimation process from alpha = 5 deg to alpha = 60 deg are presented and discussed. Napolitano, Marcello R. Ames Research Center...
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 702 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis AGARD Flight Test Techniques Series. Volume 3. Identification of Dynamic Systems - Applications to Aircraft. Part 1. The Output Error Approach by :
Download or read book AGARD Flight Test Techniques Series. Volume 3. Identification of Dynamic Systems - Applications to Aircraft. Part 1. The Output Error Approach written by and published by . This book was released on 1986 with total page 186 pages. Available in PDF, EPUB and Kindle. Book excerpt: This document 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 of the document is to present a comprehensive and unified picture of the entire parameter estimation process and its integration into a flight test program. The document concentrates on the output-error method to provide a focus for detailed examination and to allow us to give specific examples of situations that have arisen in our experience. The document first derives the aircraft equations of motion in a form suitable for application to estimation of stability and control derivatives. It then discusses the issues that arise in adapting the equations to the limitations of analysis programs, using a specific program for an example. The document then addresses the roles and issues relating to mass distribution data, preflight predictions, maneuver design, flight scheduling, instrumentation sensors, data acquisition systems, and data processing. Finally, the document discusses evaluation and use of the analysis results. Keywords: Aerodynamic stability; Flight control; Flight characteristics; Flight maneuvers; Flight tests; Data processing.
Book Synopsis Stability and Control Derivative Estimates Obtained from Flight Data for the Beech 99 Aircraft by : Russel R. Tanner
Download or read book Stability and Control Derivative Estimates Obtained from Flight Data for the Beech 99 Aircraft written by Russel R. Tanner and published by . This book was released on 1979 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781792079962 Total Pages :28 pages Book Rating :4.0/5 (799 download)
Book Synopsis Determination of the Stability and Control Derivatives of the F/A-18 Harv from Flight Data Using the Maximum Likelihood Method by : National Aeronautics and Space Adm Nasa
Download or read book Determination of the Stability and Control Derivatives of the F/A-18 Harv from Flight Data Using the Maximum Likelihood Method written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-12-29 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The research being conducted pertains to the determination of the stability and control derivatives of the F/A-18 High Alpha Research Vehicle (HARV) from flight data using the Maximum Likelihood Method. The document outlines the approach used in the parameter estimation (PID) process and briefly describes the mathematical modeling of the F/A-18 HARV and the maneuvers designed to generate a sufficient data base for the PID research. Napolitano, Marcello R. and Spagnuolo, Joelle M. NASA-CR-191216, NAS 1.26:191216 NCC2-759...
