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Author: C. A. Martin Publisher: 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).
Author: C. A. Martin Publisher: 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).
Author: Publisher: ISBN: Category : Research Languages : en Pages : 1012
Book Description
Sections 1-2. Keyword Index.--Section 3. Personal author index.--Section 4. Corporate author index.-- Section 5. Contract/grant number index, NTIS order/report number index 1-E.--Section 6. NTIS order/report number index F-Z.
Author: Roger Larsson Publisher: Linköping University Electronic Press ISBN: 9176850706 Category : Science Languages : en Pages : 326
Book Description
With the demand for more advanced fighter aircraft, relying on unstable flight mechanical characteristics to gain flight performance, more focus has been put on model-based system engineering to help with the design work. The flight control system design is one important part that relies on this modeling. Therefore, it has become more important to develop flight mechanical models that are highly accurate in the whole flight envelope. For today’s modern fighter aircraft, the basic flight mechanical characteristics change between linear and nonlinear as well as stable and unstable as an effect of the desired capability of advanced maneuvering at subsonic, transonic and supersonic speeds. This thesis combines the subject of system identification, which is the art of building mathematical models of dynamical systems based on measurements, with aeronautical engineering in order to find methods for identifying flight mechanical characteristics. Here, some challenging aeronautical identification problems, estimating model parameters from flight-testing, are treated. Two aspects are considered. The first is online identification during flight-testing with the intent to aid the engineers in the analysis process when looking at the flight mechanical characteristics. This will also ensure that enough information is available in the resulting test data for post-flight analysis. Here, a frequency domain method is used. An existing method has been developed further by including an Instrumental Variable approach to take care of noisy data including atmospheric turbulence and by a sensor-fusion step to handle varying excitation during an experiment. The method treats linear systems that can be both stable and unstable working under feedback control. An experiment has been performed on a radio-controlled demonstrator aircraft. For this, multisine input signals have been designed and the results show that it is possible to perform more time-efficient flight-testing compared with standard input signals. The other aspect is post-flight identification of nonlinear characteristics. Here the properties of a parameterized observer approach, using a prediction-error method, are investigated. This approach is compared with four other methods for some test cases. It is shown that this parameterized observer approach is the most robust one with respect to noise disturbances and initial offsets. Another attractive property is that no user parameters have to be tuned by the engineers in order to get the best performance. All methods in this thesis have been validated on simulated data where the system is known, and have also been tested on real flight test data. Both of the investigated approaches show promising results.
Author: R. A. Feik Publisher: ISBN: 9780642877666 Category : Airplanes Languages : en Pages : 32
Book Description
A brief overview of the application of System Identification methodology to the analysis of dynamic flight test data is provided, and the advantages of this approach summarized. Parameter estimation is presented as an important element in the overall process and a number of estimation programs, available on the ARL computer, are described. The advantages and disadvantages of the various procedures, including least squares, maximum likelihood and Kalman filter techniques, are assessed. Suggestions are made on factors to consider in choosing the most suitable method, depending on measurements available, noise levels and model structure. (Author).
Author: R. A. Feik Publisher: ISBN: 9780642096685 Category : Airplanes Languages : en Pages : 14
Book Description
This note considers matters related to the application of instrument compatibility checking techniques to flight test data. A previously developed Maximum Likelihood program has been used to study the effects of the presence of scale errors, accelerometer offsets and measurement time lags using simulated data. Some additional information on the effects of noise levels has also been obtained. The results have led to a suggested method for determination of centre of gravity location from flight data. The effects of measurement lags have been shown to have a major influence on extracted instrument parameters and a systematic procedure for the determination of relative phases has been devised and applied successfully to simulated data. These techniques have also been applied to flight data from a roller-coaster manoeuvre and a set of relative lag values clearly identified. The question of the accuracies of extracted instrument parameters and their dependence on the relative lags will be treated more fully in a subsequent publication. Keywords: Non-linear systems; Data acquisition; Estimation; System identification; Flight path reconstruction; Maximum likelihood estimates; Instrument errors; Time lag(Australia).
Author: Publisher: ISBN: Category : Languages : en Pages : 18
Book Description
In this paper, a bank of Kalman filters is applied to aircraft gas turbine engine sensor and actuator fault detection and isolation (FDI) in conjunction with the detection of component faults. This approach uses multiple Kalman filters, each of which is designed for detecting a specific sensor or actuator fault. In the event that a fault does occur, all filters except the one using the correct hypothesis will produce large estimation errors, thereby isolating the specific fault. In the meantime, a set of parameters that indicate engine component performance is estimated for the detection of abrupt degradation. The proposed FDI approach is applied to a nonlinear engine simulation at nominal and aged conditions, and the evaluation results for various engine faults at cruise operating conditions are given. The ability of the proposed approach to reliably detect and isolate sensor and actuator faults is demonstrated. (7 tables, 4 figures, 17 refs.).
Author: C. A. Martin
Author: C. A. Martin
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Author: Roger Larsson
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Author: R. A. Feik
Author: R. A. Feik
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