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Author : Anonim
Publisher : Unknown
Page : 404 pages
File Size : 48,6 Mb
Release : 1974
Category : Airplanes
ISBN : UIUC:30112106886135
Author : Anonim
Publisher : Unknown
Page : 58 pages
File Size : 41,9 Mb
Release : 1979
Category : Electronic
ISBN : NASA:31769000546047
Author : Anonim
Publisher : Unknown
Page : 936 pages
File Size : 54,6 Mb
Release : 1974
Category : Electronic
ISBN : MINN:31951000846498G
Author : Anonim
Publisher : Unknown
Page : 486 pages
File Size : 50,8 Mb
Release : 1991
Category : Aeronautics
ISBN : MINN:31951P00040947T
Author : Richard E. Maine,Kenneth W. Iliff
Publisher : Unknown
Page : 167 pages
File Size : 51,8 Mb
Release : 1986
Category : Aerodynamics
ISBN : 9283515404
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.
Author : Timothy R. Moes
Publisher : Unknown
Page : 98 pages
File Size : 53,6 Mb
Release : 2002
Category : Airplanes
ISBN : NASA:31769000451636
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 : Majeed Mohamed,Vikalp Dongare
Publisher : Springer Nature
Page : 66 pages
File Size : 51,8 Mb
Release : 2021-02-23
Category : Technology & Engineering
ISBN : 9789811601040
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 : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
Page : 98 pages
File Size : 46,6 Mb
Release : 2018-09-24
Category : Science
ISBN : 1723976504
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
Author : Anonim
Publisher : Unknown
Page : 504 pages
File Size : 41,9 Mb
Release : 1977
Category : Astronautics
ISBN : MINN:31951D00023646G
Author : C. A. Martin
Publisher : Unknown
Page : 24 pages
File Size : 51,9 Mb
Release : 1980
Category : Aerodynamics
ISBN : 0642888698
The development of a procedure for estimating aircraft dynamic states and instrument systematic errors from flight test measurements is described. The method has particular application in non-steady performance estimation for reconstructing aircraft flight path and in the estimation of aerodynamic characteristics using the 'equation error' parameter estimation method. The state estimator can be extended to determine systematic measurement errors in the recorded data, giving a set of data which is compatible according to the kinematic equations which relate the measurements. The effectiveness of the procedures cannot be specified in a general way, since the results depend upon the representation of the input and output noise characteristics and on the choice of initial conditions for a given problem. This note has been written to allow users to apply the state estimation procedure to practical problems. A description of the Carlson Square Root Filter and its application to the kinematic equations of aircraft motion is given. The documentation of the computer program for state estimation is also presented. (Author).
Author : Randall D. Grove
Publisher : Unknown
Page : 68 pages
File Size : 45,9 Mb
Release : 1972
Category : Airplanes
ISBN : UIUC:30112106884247
Author : Anonim
Publisher : Unknown
Page : 32 pages
File Size : 52,5 Mb
Release : 1986
Category : Aeronautics
ISBN : MINN:31951P002187617
Author : Anonim
Publisher : Editora E-papers
Page : 365 pages
File Size : 49,6 Mb
Release : 2024-07-02
Category : Electronic
ISBN : 9788576500292
Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 144 pages
File Size : 47,5 Mb
Release : 2018-06-13
Category : Electronic
ISBN : 1721095330
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
Author : R. A. Feik,AERONAUTICAL RESEARCH LABS MELBOURNE (Australia)
Publisher : Unknown
Page : 28 pages
File Size : 52,8 Mb
Release : 1978
Category : Aerodynamics
ISBN : 0642905932
Flight data from a 60 deg. delta wing aircraft have been analysed using a modified Newton-Raphson parameter estimation procedure. The model equations used for the analysis were extended to account for incidence vane errors and non-linearities in the pitching moment curves. Longitudinal derivatives extracted from the data have been compared with wind tunnel measurements and some theoretical estimates and areas of agreement and disagreement identified. The results demonstrate the usefulness of the parameter identification method not only for the validation of aircraft mathematical models and for checking flight results against wind tunnel data but also for obtaining aerodynamic data not easily available through other means. (Author).