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Author : Mark S. Smith
Publisher :
ISBN 13 :
Total Pages : 38 pages
Book Rating : 4.:/5 (317 download)
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:
Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
ISBN 13 : 9781723750137
Total Pages : 38 pages
Book Rating : 4.7/5 (51 download)
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
Author : Kenneth W. Iliff
Publisher :
ISBN 13 :
Total Pages : 54 pages
Book Rating : 4.:/5 (317 download)
Download or read book Extraction of Stability and Control Derivatives from Orbiter Flight Data written by Kenneth W. Iliff and published by . This book was released on 1993 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : George G. Steinmetz
Publisher :
ISBN 13 :
Total Pages : 52 pages
Book Rating : 4.:/5 (31 download)
Download or read book Longitudinal Stability and Control Derivatives of a Jet Fighter Airplane Extracted from Flight Test Data by Utilizing Maximum Likelihood Estimation written by George G. Steinmetz and published by . This book was released on 1971 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: "A method of parameter extraction for stability and control derivatives of aircraft from flight test data, implementing maximum likelihood estimation, has been developed and successfully applied to actual longitudinal flight test data from a modern sophisticated jet fighter. The results of this application establish the merits of the estimation technique and its computer implementation (allowing full analyst interaction with the program) as well as provide data for the validation of a portion of the Langley differential maneuvering simulator (DMS). The results are presented for all flight test runs in tabular form and as time history comparisons between the estimated states and the actual flight test data."--Page i
Author : Russel R. Tanner
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (317 download)
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 : Malcolm J. Abzug
Publisher : Cambridge University Press
ISBN 13 : 1107320194
Total Pages : 417 pages
Book Rating : 4.1/5 (73 download)
Download or read book Airplane Stability and Control written by Malcolm J. Abzug and published by Cambridge University Press. This book was released on 2002-09-23 with total page 417 pages. Available in PDF, EPUB and Kindle. Book excerpt: From the early machines to today's sophisticated aircraft, stability and control have always been crucial considerations. In this second edition, Abzug and Larrabee again forge through the history of aviation technologies to present an informal history of the personalities and the events, the art and the science of airplane stability and control. The book includes never-before-available impressions of those active in the field, from pre-Wright brothers airplane and glider builders through to contemporary aircraft designers. Arranged thematically, the book deals with early developments, research centers, the effects of power on stability and control, the discovery of inertial coupling, the challenge of stealth aerodynamics, a look toward the future, and much more. It is profusely illustrated with photographs and figures, and includes brief biographies of noted stability and control figures along with a core bibliography. Professionals, students, and aviation enthusiasts alike will appreciate this readable history of airplane stability and control.
Author :
Publisher :
ISBN 13 :
Total Pages : 996 pages
Book Rating : 4.F/5 ( download)
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1990 with total page 996 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 936 pages
Book Rating : 4.:/5 (334 download)
Download or read book STAR written by and published by . This book was released on 1973 with total page 936 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Adm Nasa
Publisher :
ISBN 13 : 9781730938672
Total Pages : 102 pages
Book Rating : 4.9/5 (386 download)
Download or read book Determination of Stability and Control Derivatives from the NASA F/a-18 Harv from Flight Data Using the Maximum Likelihood Method written by National Aeronautics and Space Adm Nasa and published by . This book was released on 2018-11-07 with total page 102 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report is a compilation of PID (Proportional Integral Derivative) results for both longitudinal and lateral directional analysis that was completed during Fall 1994. It had earlier established that the maneuvers available for PID containing independent control surface inputs from OBES were not well suited for extracting the cross-coupling static (i.e., C(sub N beta)) or dynamic (i.e., C(sub Npf)) derivatives. This was due to the fact that these maneuvers were designed with the goal of minimizing any lateral directional motion during longitudinal maneuvers and vice-versa. This allows for greater simplification in the aerodynamic model as far as coupling between longitudinal and lateral directions is concerned. As a result, efforts were made to reanalyze this data and extract static and dynamic derivatives for the F/A-18 HARV (High Angle of Attack Research Vehicle) without the inclusion of the cross-coupling terms such that more accurate estimates of classical model terms could be acquired. Four longitudinal flights containing static PID maneuvers were examined. The classical state equations already available in pEst for alphadot, qdot and thetadot were used. Three lateral directional flights of PID static maneuvers were also examined. The classical state equations already available in pEst for betadot, p dot, rdot and phi dot were used. Enclosed with this document are the full set of longitudinal and lateral directional parameter estimate plots showing coefficient estimates along with Cramer-Rao bounds. In addition, a representative time history match for each type of meneuver tested at each angle of attack is also enclosed. Napolitano, Marcello R. Unspecified Center...
Author :
Publisher :
ISBN 13 :
Total Pages : 704 pages
Book Rating : 4.:/5 (319 download)
Download or read book NASA Technical Note written by and published by . This book was released on 1976 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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ISBN 13 :
Total Pages : 1286 pages
Book Rating : 4.F/5 ( download)
Download or read book NASA Tech Briefs written by and published by . This book was released on 2006 with total page 1286 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722225872
Total Pages : 42 pages
Book Rating : 4.2/5 (258 download)
Download or read book Extraction of Lateral-Directional Stability and Control Derivatives for the Basic F-18 Aircraft at High Angles of Attack written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-03 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of parameter identification to determine the lateral-directional stability and control derivatives of an F-18 research aircraft in its basic hardware and software configuration are presented. The derivatives are estimated from dynamic flight data using a specialized identification program developed at NASA Dryden Flight Research Center. The formulation uses the linearized aircraft equations of motions in their continuous/discrete form and a maximum likelihood estimator that accounts for both state and measurement noise. State noise is used to model the uncommanded forcing function caused by unsteady aerodynamics, such as separated and vortical flows, over the aircraft. The derivatives are plotted as functions of angle of attack between 3 deg and 47 deg and compared with wind-tunnel predictions. The quality of the derivative estimates obtained by parameter identification is somewhat degraded because the maneuvers were flown with the aircraft's control augmentation system engaged, which introduced relatively high correlations between the control variables and response variables as a result of control motions from the feedback control system. Iliff, Kenneth W. and Wang, Kon-Sheng Charles Armstrong Flight Research Center RTOP 505-68-50...
Author : James LaVern Williams
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
Download or read book Extraction from Flight Data of Longitudinal Aerodynamic Coefficients for F-8 Aircraft with Supercritical Wing written by James LaVern Williams and published by . This book was released on 1974 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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)
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...
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781720525479
Total Pages : 38 pages
Book Rating : 4.5/5 (254 download)
Download or read book Flight Investigation of Prescribed Simultaneous Independent Surface Excitations for Real-Time Parameter Identification written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-31 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Near real-time stability and control derivative extraction is required to support flight demonstration of Intelligent Flight Control System (IFCS) concepts being developed by NASA, academia, and industry. Traditionally, flight maneuvers would be designed and flown to obtain stability and control derivative estimates using a postflight analysis technique. The goal of the IFCS concept is to be able to modify the control laws in real time for an aircraft that has been damaged in flight. In some IFCS implementations, real-time parameter identification (PID) of the stability and control derivatives of the damaged aircraft is necessary for successfully reconfiguring the control system. This report investigates the usefulness of Prescribed Simultaneous Independent Surface Excitations (PreSISE) to provide data for rapidly obtaining estimates of the stability and control derivatives. Flight test data were analyzed using both equation-error and output-error PID techniques. The equation-error PID technique is known as Fourier Transform Regression (FTR) and is a frequency-domain real-time implementation. Selected results were compared with a time-domain output-error technique. The real-time equation-error technique combined with the PreSISE maneuvers provided excellent derivative estimation in the longitudinal axis. However, the PreSISE maneuvers as presently defined were not adequate for accurate estimation of the lateral-directional derivatives.Moes, Timothy R. and Smith, Mark S. and Morelli, Eugene A.Armstrong Flight Research Center; Langley Research CenterAUTOMATIC CONTROL; FLIGHT CONTROL; REAL TIME OPERATION; CONTROL SYSTEMS DESIGN; AIRCRAFT CONTROL; DAMAGE; PARAMETER IDENTIFICATION; AIRCRAFT MANEUVERS; AIRCRAFT STABILITY; ERROR ANALYSIS; FOURIER TRANSFORMATION; TIME DOMAIN ANALYSIS
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
ISBN 13 : 9781722944742
Total Pages : 42 pages
Book Rating : 4.9/5 (447 download)
Download or read book X-29a Lateral-Directional Stability and Control Derivatives Extracted from High-Angle-Of-Attack Flight Data written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-15 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: The lateral-directional stability and control derivatives of the X-29A number 2 are extracted from flight data over an angle-of-attack range of 4 degrees to 53 degrees using a parameter identification algorithm. The algorithm uses the linearized aircraft equations of motion and a maximum likelihood estimator in the presence of state and measurement noise. State noise is used to model the uncommanded forcing function caused by unsteady aerodynamics over the aircraft at angles of attack above 15 degrees. The results supported the flight-envelope-expansion phase of the X-29A number 2 by helping to update the aerodynamic mathematical model, to improve the real-time simulator, and to revise flight control system laws. Effects of the aircraft high gain flight control system on maneuver quality and the estimated derivatives are also discussed. The derivatives are plotted as functions of angle of attack and compared with the predicted aerodynamic database. Agreement between predicted and flight values is quite good for some derivatives such as the lateral force due to sideslip, the lateral force due to rudder deflection, and the rolling moment due to roll rate. The results also show significant differences in several important derivatives such as the rolling moment due to sideslip, the yawing moment due to sideslip, the yawing moment due to aileron deflection, and the yawing moment due to rudder deflection. Iliff, Kenneth W. and Wang, Kon-Sheng Charles Wang Armstrong Flight Research Center RTOP 505-68-50...
Author :
Publisher :
ISBN 13 :
Total Pages : 404 pages
Book Rating : 4.:/5 (31 download)
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:
