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Estimation Of The Longitudinal Aerodynamic Coefficients From Flight Data For The F A 18 Harv Using The Maximum Likelihood Method With Kalvistes Dynamic Modeling
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Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722377526 Total Pages :52 pages Book Rating :4.3/5 (775 download)
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 Administration (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 Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-06 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...
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722344450 Total Pages :100 pages Book Rating :4.3/5 (444 download)
Book Synopsis Determination of Stability and Control Derivatives from the NASA F/A-18 Harv from Flight Data Using the Maximum Likelihood Method by : National Aeronautics and Space Administration (NASA)
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 Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-08 with total page 100 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 :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...
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...
Book Synopsis Practical Aspects of Using a Maximum Likelihood Estimation Method to Extract Stability and Control Derivitives from Flight Data by : Kenneth W. Iliff
Download or read book Practical Aspects of Using a Maximum Likelihood Estimation Method to Extract Stability and Control Derivitives from Flight Data written by Kenneth W. Iliff and published by . This book was released on 1976 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aircraft Aerodynamic Parameter Estimation from Flight Data Using Neural Partial Differentiation by : Majeed Mohamed
Download or read book Aircraft Aerodynamic Parameter Estimation from Flight Data Using Neural Partial Differentiation written by Majeed Mohamed and published by Springer Nature. This book was released on 2021-02-23 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Inclusion of Unsteady Aerodynamics in Longitudinal Parameter Estimation from Flight Data by : M. J. Queijo
Download or read book Inclusion of Unsteady Aerodynamics in Longitudinal Parameter Estimation from Flight Data written by M. J. Queijo and published by . This book was released on 1979 with total page 62 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781726171601 Total Pages :50 pages Book Rating :4.1/5 (716 download)
Book Synopsis Active Aeroelastic Wing Aerodynamic Model Development and Validation for a Modified F/A-18a Airplane by : National Aeronautics and Space Administration (NASA)
Download or read book Active Aeroelastic Wing Aerodynamic Model Development and Validation for a Modified F/A-18a Airplane written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-08-27 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt: A new aerodynamic model has been developed and validated for a modified F/A-18A airplane used for the Active Aeroelastic Wing (AAW) research program. The goal of the program was to demonstrate the advantages of using the inherent flexibility of an aircraft to enhance its performance. The research airplane was an F/A-18A with wings modified to reduce stiffness and a new control system to increase control authority. There have been two flight phases. Data gathered from the first flight phase were used to create the new aerodynamic model. A maximum-likelihood output-error parameter estimation technique was used to obtain stability and control derivatives. The derivatives were incorporated into the National Aeronautics and Space Administration F-18 simulation, validated, and used to develop new AAW control laws. The second phase of flights was used to evaluate the handling qualities of the AAW airplane and the control law design process, and to further test the accuracy of the new model. The flight test envelope covered Mach numbers between 0.85 and 1.30 and dynamic pressures from 600 to 1250 pound-force per square foot. The results presented in this report demonstrate that a thorough parameter identification analysis can be used to improve upon models that were developed using other means. This report describes the parameter estimation technique used, details the validation techniques, discusses differences between previously existing F/A-18 models, and presents results from the second phase of research flights.Cumming, Stephen B. and Diebler, Corey G.Armstrong Flight Research Center; Kennedy Space CenterF-18 AIRCRAFT; AEROELASTIC RESEARCH WINGS; FLIGHT TESTS; AIRCRAFT MODELS; LEADING EDGE FLAPS; CONTROL SURFACES; DEFLECTION; AIRCRAFT MANEUVERS; SIMULATION; PARAMETER IDENTIFICATION; MAXIMUM LIKELIHOOD ESTIMATES; MACH NUMBER...
Book Synopsis An Evaluation Technique for an F/A-18 Aircraft Loads Model Using F/A-18 Systems Research Aircraft Flight Data by : Candida D. Olney
Download or read book An Evaluation Technique for an F/A-18 Aircraft Loads Model Using F/A-18 Systems Research Aircraft Flight Data written by Candida D. Olney and published by . This book was released on 2000 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: A limited evaluation of the F/A-18 baseline loads model was performed on the Systems Research Aircraft at NASA Dryden Flight Research Center (Edwards, California). Boeing developed the F/A-18 loads model using a linear aeroelastic analysis in conjunction with a flight simulator to determine loads at discrete locations on the aircraft. This experiment was designed so that analysis of doublets could be used to establish aircraft aerodynamic and loads response at 20 flight conditions. Instrumentation on the right outboard leading edge flap, left airleron, and left stabilator measured the hinge moment so that comparisons could be made between in-flight-measured hinge moments and loads model-predicted values at these locations. Comparisons showed that the difference between the loads model-predicted and in-flight-measured hinge moments was up to 130 percent of the flight limit load. A stepwise regression technique was used to determine new loads derivatives. These derivatives were placed in the load model, which reduced the error to within 10 percent of the flight limit load. This paper discusses the flight test methodology, a process for determining loads coefficients, and the direct comparisons of predicted and measured hinge moments and loads coefficients.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722163938 Total Pages :70 pages Book Rating :4.1/5 (639 download)
Book Synopsis Aerodynamic Parameters of High-Angle-Of Attack Research Vehicle (Harv) Estimated from Flight Data by : National Aeronautics and Space Administration (NASA)
Download or read book Aerodynamic Parameters of High-Angle-Of Attack Research Vehicle (Harv) Estimated from Flight Data written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-02 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic parameters of the High-Angle-of-Attack Research Aircraft (HARV) were estimated from flight data at different values of the angle of attack between 10 degrees and 50 degrees. The main part of the data was obtained from small amplitude longitudinal and lateral maneuvers. A small number of large amplitude maneuvers was also used in the estimation. The measured data were first checked for their compatibility. It was found that the accuracy of air data was degraded by unexplained bias errors. Then, the data were analyzed by a stepwise regression method for obtaining a structure of aerodynamic model equations and least squares parameter estimates. Because of high data collinearity in several maneuvers, some of the longitudinal and all lateral maneuvers were reanalyzed by using two biased estimation techniques, the principal components regression and mixed estimation. The estimated parameters in the form of stability and control derivatives, and aerodynamic coefficients were plotted against the angle of attack and compared with the wind tunnel measurements. The influential parameters are, in general, estimated with acceptable accuracy and most of them are in agreement with wind tunnel results. The simulated responses of the aircraft showed good prediction capabilities of the resulting model. Klein, Vladislav and Ratvasky, Thomas R. and Cobleigh, Brent R. Langley Research Center...
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 The Theory and Practice of Estimating the Accuracy of Dynamic Flight-determined Coefficients by : Richard E. Maine
Download or read book The Theory and Practice of Estimating the Accuracy of Dynamic Flight-determined Coefficients written by Richard E. Maine and published by . This book was released on 1981 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Adm Nasa Publisher :Independently Published ISBN 13 :9781729383001 Total Pages :48 pages Book Rating :4.3/5 (83 download)
Book Synopsis Aerodynamic Parameter Estimation Via Fourier Modulating Function Techniques by : National Aeronautics and Space Adm Nasa
Download or read book Aerodynamic Parameter Estimation Via Fourier Modulating Function Techniques written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2018-11 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: Parameter estimation algorithms are developed in the frequency domain for systems modeled by input/output ordinary differential equations. The approach is based on Shinbrot's method of moment functionals utilizing Fourier based modulating functions. Assuming white measurement noises for linear multivariable system models, an adaptive weighted least squares algorithm is developed which approximates a maximum likelihood estimate and cannot be biased by unknown initial or boundary conditions in the data owing to a special property attending Shinbrot-type modulating functions. Application is made to perturbation equation modeling of the longitudinal and lateral dynamics of a high performance aircraft using flight-test data. Comparative studies are included which demonstrate potential advantages of the algorithm relative to some well established techniques for parameter identification. Deterministic least squares extensions of the approach are made to the frequency transfer function identification problem for linear systems and to the parameter identification problem for a class of nonlinear-time-varying differential system models. Pearson, A. E. Unspecified Center NAG1-1065; RTOP 505-64-52-01...
Book Synopsis The Determination of Aerodynamic Stability Coefficients from Rocket Flight Test Data by : A. C. Bustamante
Download or read book The Determination of Aerodynamic Stability Coefficients from Rocket Flight Test Data written by A. C. Bustamante and published by . This book was released on 1961 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method by which aerodynamic stability coefficients can be determined from rocket flight test data, through the use of accelerometer and gyroscope measurements, is presented. This analysis is intended to be used as a program on the 704 IBM computer.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722380052 Total Pages :48 pages Book Rating :4.3/5 (8 download)
Book Synopsis Modeling of Aircraft Unsteady Aerodynamic Characteristics/Part 3 - Parameters Estimated from Flight Data. Part 3; Parameters Estimated from Flight Data by : National Aeronautics and Space Administration (NASA)
Download or read book Modeling of Aircraft Unsteady Aerodynamic Characteristics/Part 3 - Parameters Estimated from Flight Data. Part 3; Parameters Estimated from Flight Data written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-05 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: A nonlinear least squares algorithm for aircraft parameter estimation from flight data was developed. The postulated model for the analysis represented longitudinal, short period motion of an aircraft. The corresponding aerodynamic model equations included indicial functions (unsteady terms) and conventional stability and control derivatives. The indicial functions were modeled as simple exponential functions. The estimation procedure was applied in five examples. Four of the examples used simulated and flight data from small amplitude maneuvers to the F-18 HARV and X-31A aircraft. In the fifth example a rapid, large amplitude maneuver of the X-31 drop model was analyzed. From data analysis of small amplitude maneuvers ft was found that the model with conventional stability and control derivatives was adequate. Also, parameter estimation from a rapid, large amplitude maneuver did not reveal any noticeable presence of unsteady aerodynamics. Klein, Vladislav and Noderer, Keith D. Langley Research Center RTOP 505-64-52-01...
Book Synopsis A Maximum Likelihood Program for Non-linear System Identification with Application to Aircraft Flight Data Compatibility Checking by : R. A. Feik
Download or read book A Maximum Likelihood Program for Non-linear System Identification with Application to Aircraft Flight Data Compatibility Checking written by R. A. Feik and published by . This book was released on 1982 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Fortran program has been developed for the Maximum Likelihood Estimation of parameters in non-linear systems. The program structure uses subroutines to describe the problem and define problem-specific elements, while the main program is designed to be problem-independent as far as possible. In the present note an application of the program to compatibility checking of aircraft dynamic flight test data has been studied. Using simulated time histories of longitudinal manoeuvres, the conditions for satisfactory performance have been identified. It has been shown that for a practical manoeuvre shape, record length and sampling rate and for reasonable noise levels on the measured data, instrument errors can be identified to good accuracy and a set of compatible time histories reconstructed. (Author).
Book Synopsis Matrix Method of Determining the Longitudinal-stability Coefficients and Frequency Response of an Aircraft from Transient Flight Data by : James J. Donegan
Download or read book Matrix Method of Determining the Longitudinal-stability Coefficients and Frequency Response of an Aircraft from Transient Flight Data written by James J. Donegan and published by . This book was released on 1951 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is presented for obtaining the over-all longitudinal-stability coefficients and frequency response of an aircraft from an analysis of arbitrary maneuvers in which simple instrumentation is used. Although the method presented deals entirely with the aircraft, it is equally applicable to other problems which can be expressed by second-order differential equations.
