Download or read book Application of Parameter Estimation to Aircraft Stability and Control written by Richard E. Maine and published by . This book was released on 1986 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Application of Parameter Estimation to Highly Unstable Aircraft written by and published by . This book was released on 1986 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Application of Parameter Estimation to Flight Measurements to Obtain Lateral directional Stability Derivatives of an Augmented Jet flap STOL Airplane written by Jack Dougal Stephenson and published by . This book was released on 1983 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book An Application of Parameter Estimation to the Stability and Control of the BQM 147 Unmanned Aerial Vehicle written by Patrick John Quinn and published by . This book was released on 1993 with total page 121 pages. Available in PDF, EPUB and Kindle. Book excerpt: Parameter estimation methods were used to obtain estimates of stability and control derivatives for the Marine Corps BQM-147 Unmanned Air Vehicle. The results from a simple, PC-based linear model and those from a more robust non-linear model, pEst, were compared. A Cramer-Rao bound was used to assess the accuracy of the estimates for both methods. The bounds were high for both the longitudinal case and the lateral-directional case due to the limited maneuvers tested, high levels of noise in the same general frequency range as the control input, and the lack of body-angle data. The linear model failed to provide estimates for the lateral-directional case. Though the results may be used as starting points for a dynamic model of the aircraft it is recommended that the flight test procedures be modified to address the issues raised concerning noise, recorded signals and the need for repeated maneuvers.
Download or read book Application of Parameter Estimation to Aircraft Stability and Control written by Richard E. Maine and published by . This book was released on 1986 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Download or read book An Application of Parameter Estimation to the Stability and Control of the BQM 147 Unmanned Aerial Vehicle written by Patrick John Quinn and published by . This book was released on 1993 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Parameter estimation methods were used to obtain estimates of stability and control derivatives for the Marine Corps BQM-147 Unmanned Air Vehicle. The results from a simple, PC-based linear model and those from a more robust non-linear model, pEst, were compared. A Cramer-Rao bound was used to assess the accuracy of the estimates for both methods. The bounds were high for both the longitudinal case and the lateral-directional case due to the limited maneuvers tested, high levels of noise in the same general frequency range as the control input, and the lack of body-angle data. The linear model failed to provide estimates for the lateral-directional case. Though the results may be used as starting points for a dynamic model of the aircraft it is recommended that the flight test procedures be modified to address the issues raised concerning noise, recorded signals and the need for repeated maneuvers.
Download or read book NASA Technical Note written by and published by . This book was released on 1974 with total page 936 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Stability and Control Estimation Flight Test Results for the Sr 71 Aircraft with Externally Mounted Experiments written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-11 with total page 96 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. The reduction of directional stability for the experimental configurations is the most significant aerodynamic effect measured and identified as a design constraint for future experimental configurations. This report also shows the significant effects of aircraft flexibility on the stability and control derivatives.Moes, Timothy R. and Iliff, KennethArmstrong Flight Research CenterCONTROLLABILITY; SR-71 AIRCRAFT; MAXIMUM LIKELIHOOD ESTIMATES; DIRECTIONAL STABILITY; AIRCRAFT STABILITY; SUBSONIC SPEED; YAW; MACH NUMBER; ERROR ANALYSIS; AERODYNAMICS
Download or read book Identification of Dynamic Systems Applications to Aircraft Part 2 written by J. A. Mulder and published by . This book was released on 1994 with total page 191 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Comparison of Stability and Control Parameters for a Light Single engine High winged Aircraft Using Different Flight Test and Parameter Estimation Techniques written by and published by . This book was released on 1979 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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...
Download or read book Aircraft Parameter Estimation written by and published by . This book was released on 1987 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Identification of Dynamic Systems written by Richard E. Maine and published by . This book was released on 1986 with total page 167 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Download or read book Determination of Stability and Control Parameters of a General Aviation Airplane from Flight Data written by Imran Abbasy and published by . This book was released on 1983 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt:
