Parameter Identification Flight Test Maneuvers For Closed Loop Modeling Of The F 18 High Alpha Research Vehicle Harv
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Parameter Identification Flight Test Maneuvers For Closed Loop Modeling Of The F 18 High Alpha Research Vehicle Harv
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Author :
language : en
Publisher:
Release Date : 1996
Parameter Identification Flight Test Maneuvers For Closed Loop Modeling Of The F 18 High Alpha Research Vehicle Harv written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
Piloted Parameter Identification Flight Test Maneuvers For Closed Loop Modeling Of The F 18 High Alpha Research Vehicle Harv
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Author :
language : en
Publisher:
Release Date : 1996
Piloted Parameter Identification Flight Test Maneuvers For Closed Loop Modeling Of The F 18 High Alpha Research Vehicle Harv written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
Flight Test Maneuvers For Closed Loop Lateral Directional Modeling Of The F 18 High Alpha Research Vehicle Harv Using Forebody Strakes
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Author : E. A. Morelli
language : en
Publisher:
Release Date : 1996
Flight Test Maneuvers For Closed Loop Lateral Directional Modeling Of The F 18 High Alpha Research Vehicle Harv Using Forebody Strakes written by E. A. Morelli and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
Flight test maneuvers are specified for the F-18 High Alpha Research Vehicle (HARV). The maneuvers were designed for closed loop parameter identification purposes, specifically for lateral linear model parameter estimation at 30, 45, and 60 degrees angle of attack, using the Actuated Nose Strakes for Enhanced Rolling (ANSER) control law in Strake (S) model and Strake/Thrust Vectoring (STV) mode. Each maneuver is to be realized by applying square wave inputs to specific pilot station controls using the On-Board Excitation System (OBES). Maneuver descriptions and complete specification of the time/amplitude points defining each input are included, along with plots of the input time histories.
Piloted Parameter Identification Flight Test Maneuvers For Closed Loop Modeling Of The F 18 High Alpha Research Vehicle Harv
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Author : National Aeronautics and Space Adm Nasa
language : en
Publisher: Independently Published
Release Date : 2018-10-17
Piloted Parameter Identification Flight Test Maneuvers For Closed Loop Modeling Of The F 18 High Alpha Research Vehicle Harv written by National Aeronautics and Space Adm Nasa and has been published by Independently Published this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-10-17 with Science categories.
Flight test maneuvers are specified for the F-18 High Alpha Research Vehicle (HARV). The maneuvers were designed for closed loop parameter identification purposes, specifically for longitudinal and lateral linear model parameter estimation at 5, 20, 30, 45, and 60 degrees angle of attack, using the NASA 1A control law. Each maneuver is to be realized by the pilot applying square wave inputs to specific pilot station controls. Maneuver descriptions and complete specifications of the time/amplitude points defining each input are included, along with plots of the input time histories. Morelli, Eugene A. Langley Research Center NAS1-19000; RTOP 505-64-52-01
Flight Test Maneuvers For Closed Loop Lateral Directional Modeling Of The F 18 High Alpha Research Vehicle Harv Using Forebody Strakes
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-03
Flight Test Maneuvers For Closed Loop Lateral Directional Modeling Of The F 18 High Alpha Research Vehicle Harv Using Forebody Strakes written by National Aeronautics and Space Administration (NASA) and has been published by Createspace Independent Publishing Platform this book supported file pdf, txt, epub, kindle and other format this book has been release on 2018-07-03 with categories.
Flight test maneuvers are specified for the F-18 High Alpha Research Vehicle (HARV). The maneuvers were designed for closed loop parameter identification purposes, specifically for lateral linear model parameter estimation at 30, 45, and 60 degrees angle of attack, using the Actuated Nose Strakes for Enhanced Rolling (ANSER) control law in Strake (S) model and Strake/Thrust Vectoring (STV) mode. Each maneuver is to be realized by applying square wave inputs to specific pilot station controls using the On-Board Excitation System (OBES). Maneuver descriptions and complete specification of the time/amplitude points defining each input are included, along with plots of the input time histories. Morelli, E. A. Langley Research Center NAS1-19000; RTOP 505-64-52-01...
Nasa Technical Memorandum
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Author :
language : en
Publisher:
Release Date : 1997
Nasa Technical Memorandum written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1997 with Aeronautics categories.
Performance Validation Of Version 152 0 Anser Control Laws For The F 18 Harv
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Author : Michael D. Messina
language : en
Publisher:
Release Date : 1996
Performance Validation Of Version 152 0 Anser Control Laws For The F 18 Harv written by Michael D. Messina and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
The Actuated Nose Strakes for Enhanced Rolling (ANSER) Control Laws were modified as a result of Phase 3 F/A-18 High Alpha Research Vehicle (HARV) flight testing. The control law modifications for the next software release were designated version 152.0. The Ada implementation was tested in the Hardware-In-the-Loop (HIL) simulation and results were compared to those obtained with the NASA Langley batch Fortran implementation of the control laws which are considered the 'truth model.' This report documents the performance validation test results between these implementations for ANSER control law version 152.0.
Performance Validation Of Version 154 0 Anser Control Laws For The F 18 Harv
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Author : Michael D. Messina
language : en
Publisher:
Release Date : 1996
Performance Validation Of Version 154 0 Anser Control Laws For The F 18 Harv written by Michael D. Messina and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1996 with categories.
A new software release designated version 154.0 has been developed and tested for use on the F/A-18 High Angle-of-Attack Research Vehicle (HARV). This software release incorporates all software changes to the Actuated Nose Strakes for Enhanced Rolling (ANSER) control laws through version 153.0 with the following exceptions. The first exception is a modification of the On-Board Excitation System (OBES) which replaces the OBES load in version 153.0 with 17 new maneuvers. The second exception is to change the symmetric strake deployment schedule back to the original schedule in ANSER control law version 151.1. The final change replaces two instrumentation parameters. These three modifications make up the new software release for use in the Research Flight Control System (RFCS) flight control computer. This report documents the batch versus Hardware-in-the-Loop Simulation test results for version 154.0.
Identification Des Syst Mes Pour Le D Veloppement Int Gr Des A Ronefs Et Les Essais En Vol
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Author :
language : en
Publisher:
Release Date : 1999
Identification Des Syst Mes Pour Le D Veloppement Int Gr Des A Ronefs Et Les Essais En Vol written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1999 with Airplanes categories.
Flight Test System Identification
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Author : Roger Larsson
language : en
Publisher: Linköping University Electronic Press
Release Date : 2019-05-15
Flight Test System Identification written by Roger Larsson and has been published by Linköping University Electronic Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2019-05-15 with Science categories.
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.