Author: Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 404
Book Description
Parameter Estimation Techniques and Applications in Aircraft Flight Testing
Author: Flight Test Techniques for Aircraft Parameter Estimation in Ground Effect
Author: James Matthew ClarkNASA Technical Note
Author: Scientific and Technical Aerospace Reports
Author: Estimation of Aircraft Dynamic States and Instrument Systematic Errors from Flight Test Measurements Using the Carlson Square Root Formulation of the Kalman Filter
Author: C. A. MartinPublisher:
ISBN: 9780642888693
Category : Aerodynamics
Languages : en
Pages : 24
Book Description
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).
Stability and Control Estimation Flight Test Results for the SR-71 Aircraft With Externally Mounted Experiments
Author: Timothy R. MoesPublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 98
Book Description
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.
Application of Parameter Estimation to Aircraft Stability and Control
Author: Richard E. MainePublisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 190
Book Description
Aircraft Aerodynamic Parameter Estimation from Flight Data Using Neural Partial Differentiation
Author: Majeed MohamedPublisher: Springer Nature
ISBN: 9811601046
Category : Technology & Engineering
Languages : en
Pages : 66
Book Description
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.
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