Flight Vehicle System Identification

Flight Vehicle System Identification

This valuable volume offers a systematic approach to flight vehicle system identification and exhaustively covers the time domain methodology.

Author: R. Jategaonkar

Publisher: Amer Inst of Aeronautics &

ISBN: UOM:39015064807202

Category: Technology & Engineering

Page: 534

View: 741

This valuable volume offers a systematic approach to flight vehicle system identification and exhaustively covers the time domain methodology. It addresses in detail the theoretical and practical aspects of various parameter estimation methods, including those in the stochastic framework and focusing on nonlinear models, cost functions, optimization methods, and residual analysis. A pragmatic and balanced account of pros and cons in each case is provided. The book also presents data gathering and model validation, and covers both large-scale systems and high-fidelity modeling. Real world problems dealing with a variety of flight vehicle applications are addressed and solutions are provided. Examples encompass such problems as estimation of aerodynamics, stability, and control derivatives from flight data, flight path reconstruction, nonlinearities in control surface effectiveness, stall hysteresis, unstable aircraft, and other critical considerations.
Categories: Technology & Engineering

Flight Vehicle System Identification

Flight Vehicle System Identification

This book offers a systematic approach to flight vehicle system identification and covers the time-domain methodology.

Author: Ravindra V. Jategaonkar

Publisher:

ISBN: 152310080X

Category: Aerodynamics

Page: 627

View: 715

This book offers a systematic approach to flight vehicle system identification and covers the time-domain methodology. It addresses theoretical and practical aspects of parameter estimation methods, including those in the stochastic framework focusing on nonlinear models, cost function, optimization methods, and residual analysis. A pragmatic and balanced account of pros and cons in each case is provided. It presents data gathering and model validation, covering large-scale and high-fidelity modeling. Real-world problems dealing with a variety of flight vehicle applications are addressed, and solutions are provided. Examples include: estimation of aerodynamic stability and control derivatives from flight data; flight-path reconstruction; nonlinearities in control surface effectiveness; stall hysteresis; unstable aircraft; flexible aircraft model integrating rigid-body and structural dynamics; wake vortex encounters; and other critical considerations. --
Categories: Aerodynamics

Flight Vehicle System Identification

Flight Vehicle System Identification

Author: R. Jategaonkar

Publisher: Amer Inst of Aeronautics &

ISBN: UOM:39015064807202

Category: Technology & Engineering

Page: 534

View: 842

This valuable volume offers a systematic approach to flight vehicle system identification and exhaustively covers the time domain methodology. It addresses in detail the theoretical and practical aspects of various parameter estimation methods, including those in the stochastic framework and focusing on nonlinear models, cost functions, optimization methods, and residual analysis. A pragmatic and balanced account of pros and cons in each case is provided. The book also presents data gathering and model validation, and covers both large-scale systems and high-fidelity modeling. Real world problems dealing with a variety of flight vehicle applications are addressed and solutions are provided. Examples encompass such problems as estimation of aerodynamics, stability, and control derivatives from flight data, flight path reconstruction, nonlinearities in control surface effectiveness, stall hysteresis, unstable aircraft, and other critical considerations.
Categories: Technology & Engineering

Scientific and Technical Aerospace Reports

Scientific and Technical Aerospace Reports

FLIGHT VEHICLE SYSTEM IDENTIFICATION : STATUS AND PROSPECTS c05
P. G. Hamel In its System Identification in Vehicle Dynamics 1987 p 51-90 ( For
primary document see N88-26518 20-31 ) Avail : NTIS HC A18 / MF A01 ; DFVLR
 ...

Author:

Publisher:

ISBN: UIUC:30112075701489

Category: Aeronautics

Page:

View: 434

Categories: Aeronautics

Flight Test System Identification

Flight Test System Identification

Maximum likelihood identification of Wiener models. Automatica, 44(11):2697–
2705, February 2008. Cited on page 158. P. G. Hamel and R. V. Jategaonkar.
Evolution of flight vehicle system identification. Journal of Aircraft, 33(1):9–28, ...

Author: Roger Larsson

Publisher: Linköping University Electronic Press

ISBN: 9789176850701

Category: Science

Page: 301

View: 183

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.
Categories: Science

Flight Test Identification and Simulation of a UH 60A Helicopter and Slung Load

Flight Test Identification and Simulation of a UH 60A Helicopter and Slung Load

Mansur , M. H .; and Tischler , M. B .: An Empirical Correction for Improving Off -
Axes Response in Flight Mechanics ... 42. Hamel , P. G .; and Jategaonkar , R. V .
: Evolution of Flight Vehicle System Identification . J. Aircraft , Jan. 1996 43.

Author:

Publisher:

ISBN: NASA:31769000634223

Category:

Page: 98

View: 991

Helicopter slung-load operations are common in both military and civil contexts. Helicopters and loads are often qualified for these operations by means of flight tests, which can be expensive and time consuming. There is significant potential to reduce such costs both through revisions in flight-test methods and by using validated simulation models. To these ends, flight tests were conducted at Moffett Field to demonstrate the identification of key dynamic parameters during flight tests (aircraft stability margins and handling-qualities parameters, and load pendulum stability), and to accumulate a data base for simulation development and validation. The test aircraft was a UH-60A Black Hawk, and the primary test load was an instrumented 8- by 6- by 6-ft cargo container. Tests were focused on the lateral and longitudinal axes, which are the axes most affected by the load pendulum modes in the frequency range of interest for handling qualities; tests were conducted at airspeeds from hover to 80 knots. Using telemetered data, the dynamic parameters were evaluated in near real time after each test airspeed and before clearing the aircraft to the next test point. These computations were completed in under 1 min. A simulation model was implemented by integrating an advanced model of the UH-60A aerodynamics, dynamic equations for the two-body slung-load system, and load static aerodynamics obtained from wind-tunnel measurements. Comparisons with flight data for the helicopter alone and with a slung load showed good overall agreement for all parameters and test points; however, unmodeled secondary dynamic losses around 2 Hz were found in the helicopter model and they resulted in conservative stability margin estimates.
Categories:

Flight Dynamics and System Identification for Modern Feedback Control

Flight Dynamics and System Identification for Modern Feedback Control

Flight dynamics and system identification for modern feedback control provides an in-depth study of the difficulties associated with achieving controlled performance in flapping-wing, avian-inspired flight, and a new model paradigm is ...

Author: Jared A Grauer

Publisher: Elsevier

ISBN: 9780857094674

Category: Technology & Engineering

Page: 160

View: 854

Unmanned air vehicles are becoming increasingly popular alternatives for private applications which include, but are not limited to, fire fighting, search and rescue, atmospheric data collection, and crop surveys, to name a few. Among these vehicles are avian-inspired, flapping-wing designs, which are safe to operate near humans and are required to carry payloads while achieving manoeuverability and agility in low speed flight. Conventional methods and tools fall short of achieving the desired performance metrics and requirements of such craft. Flight dynamics and system identification for modern feedback control provides an in-depth study of the difficulties associated with achieving controlled performance in flapping-wing, avian-inspired flight, and a new model paradigm is derived using analytical and experimental methods, with which a controls designer may then apply familiar tools. This title consists of eight chapters and covers flapping-wing aircraft and flight dynamics, before looking at nonlinear, multibody modelling as well as flight testing and instrumentation. Later chapters examine system identification from flight test data, feedback control and linearization. Presents experimental flight data for validation and verification of modelled dynamics, thus illustrating the deficiencies and difficulties associated with modelling flapping-wing flight Derives a new flight dynamics model needed to model avian-inspired vehicles, based on nonlinear multibody dynamics Extracts aerodynamic models of flapping flight from experimental flight data and system identification techniques
Categories: Technology & Engineering

Rotorcraft System Identification

Rotorcraft System Identification

In cases of high bandwidth model - following flight control system designs ,
accurate mathematical models improve feed - forward control ... 3 , 1989 ( 1.4 ]
Hamel , P. G. Flight Vehicle System Identification - Status and Prospects DFVLR -
Mitt .

Author:

Publisher:

ISBN: MINN:31951D005685921

Category: Helicopters

Page: 273

View: 235

Categories: Helicopters

Flight vehicle Materials Structures and Dynamics assessment and Future Directions Structural dynamics and aeroelasticity

Flight vehicle Materials  Structures  and Dynamics  assessment and Future Directions  Structural dynamics and aeroelasticity

Ahmed Khairy Noor, Samuel L. Venneri. systems ) cause the measurements to
violate the basic linear system equation , generating additional identification
errors . Many uncertainties often occur in testing complex structures , and it is
usually ...

Author: Ahmed Khairy Noor

Publisher:

ISBN: UVA:X002533583

Category: Aeroelasticity

Page: 524

View: 581

The fifth volume of a six-volume monograph, the objective of which is to broaden the awareness among material scientists, engineers, and research workers about the recent developments which can impact future flight vehicles. The present volume, Volume 5, is divided into three parts. The first part h
Categories: Aeroelasticity

AIAA Journal

AIAA Journal

... a systematic approach to flight vehicle system identification and covers
exhaustively the time - domain methodology . ... The book also presents data
gathering and model validation and covers both large - scale systems and high -
fidelity ...

Author: American Institute of Aeronautics and Astronautics

Publisher:

ISBN: UCSD:31822036051662

Category: Aeronautics

Page:

View: 775

Categories: Aeronautics

International Aerospace Abstracts

International Aerospace Abstracts

Teledyne Ayan Aeronautical's Global Hawk is the largest of the new generation
of U.S. unmanned air vehicles ( UAVs ) , having a 116.2 - ft ... AIAA A98-37214 #
Acceleration CFD - based aeroelastic predictions using system identification .

Author:

Publisher:

ISBN: STANFORD:36105021108332

Category: Aeronautics

Page:

View: 350

Categories: Aeronautics

Indian Science Abstracts

Indian Science Abstracts

000656 JATEGAONKAR R V ( Inst of Flight Systems , DLR - German Aerospace
Cent , 38108 Braunschweig , Germany , Email ... The overview presentation
brings out why and what system identification is as applied to flight vehicles .

Author:

Publisher:

ISBN: UOM:39015066008379

Category: Science

Page:

View: 636

Categories: Science

Aerospace America

Aerospace America

The nine new AIAA Library of Flight titles are Rocketdyne : Powering Humans
into Space ( Kraemer ) , Applied Orbit ... Airborne Doppler Radar : Applications ,
Theory , and Philosophy ( Schetzen ) , Flight Vehicle System Identification : A
Time ...

Author:

Publisher:

ISBN: UCSD:31822036025997

Category: Aeronautics

Page:

View: 596

Categories: Aeronautics

NASA SP

NASA SP

Results on system identification related to highly augmented flight vehicles as
well as to high angle-of-attack maneuvers are presented. ESA N88-26525;}
Centre d'Etudes et de Recherches, Toulouse (France). Dept. d'Automatique.

Author:

Publisher:

ISBN: MINN:30000011046509

Category: Aeronautics

Page:

View: 178

Categories: Aeronautics

Aeronautical Engineering

Aeronautical Engineering

1991 - 161 ) p 137 A92 - 16128 An intelligent pilot vehicle interface for a day /
night adverse weather pilotage system ( D / NAPS ) ( AIAA ... the crew - flight
vehicle system p 1133 A92 - 57444 An approach to the organization of an
adaptive man - machine system for flight vehicle ... identification p 274 N92 -
17163 Prediction of aerodynamic phenomena limiting aircraft manoeuvrability p
364 N92 - 18781 ...

Author:

Publisher:

ISBN: STANFORD:36105012119850

Category: Aeronautics

Page:

View: 963

A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA)
Categories: Aeronautics

Choice

Choice

... FORTE ET Aircraft Design : A Conceptual Approach , Fourth Edition Daniel P.
Raymer August 2006 , 923 pages , Hardback , 1-56347-829-3 , $ 105.95 Flight
Vehicle System Identification : A Time Domain Methodology Ravindra
Jategaonkar ...

Author:

Publisher:

ISBN: UCSC:32106019070504

Category: Academic libraries

Page:

View: 871

Categories: Academic libraries