Real Time Flutter Analysis Of An Active Flutter Suppression System On A Remotely Piloted Research Aircraft
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Real Time Flutter Analysis Of An Active Flutter Suppression System On A Remotely Piloted Research Aircraft
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Author :
language : en
Publisher:
Release Date : 1983
Real Time Flutter Analysis Of An Active Flutter Suppression System On A Remotely Piloted Research Aircraft written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1983 with categories.
Real Time Flutter Analysis Of An Active Flutter Suppression System On A Remotely Piloted Research Aircraft
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Author : National Aeronautics and Space Administration (NASA)
language : en
Publisher: Createspace Independent Publishing Platform
Release Date : 2018-07-20
Real Time Flutter Analysis Of An Active Flutter Suppression System On A Remotely Piloted Research Aircraft 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 2018-07-20 with categories.
Flight flutter-test results of the first aeroelastic research wing (ARW-1) of NASA's drones for aerodynamic and structural testing program are presented. The flight-test operation and the implementation of the active flutter-suppression system are described as well as the software techniques used to obtain real-time damping estimates and the actual flutter testing procedure. Real-time analysis of fast-frequency aileron excitation sweeps provided reliable damping estimates. The open-loop flutter boundary was well defined at two altitudes; a maximum Mach number of 0.91 was obtained. Both open-loop and closed-loop data were of exceptionally high quality. Although the flutter-suppression system provided augmented damping at speeds below the flutter boundary, an error in the implementation of the system resulted in the system being less stable than predicted. The vehicle encountered system-on flutter shortly after crossing the open-loop flutter boundary on the third flight and was lost. The aircraft was rebuilt. Changes made in real-time test techniques are included. Gilyard, G. B. and Edwards, J. W. Armstrong Flight Research Center; Langley Research Center NASA-TM-84901, NAS 1.15:84901 RTOP 505-33-41
Scientific And Technical Aerospace Reports
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Author :
language : en
Publisher:
Release Date : 1992
Scientific And Technical Aerospace Reports written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1992 with Aeronautics categories.
On Subscale Flight Testing
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Author : Alejandro Sobron
language : en
Publisher: Linköping University Electronic Press
Release Date : 2018-11-05
On Subscale Flight Testing written by Alejandro Sobron 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 2018-11-05 with categories.
Downscaled physical models, also referred to as subscale models, have played an essential role in the investigation of the complex physics of flight until the recent disruption of numerical simulation. Despite the fact that improvements in computational methods are slowly pushing experimental techniques towards a secondary role as verification or calibration tools, real-world testing of physical prototypes still provides an unmatched confidence. Physical models are very effective at revealing issues that are sometimes not correctly identified in the virtual domain, and hence can be a valuable complement to other design tools. But traditional wind-tunnel testing cannot always meet all of the requirements of modern aeronautical research and development. It is nowadays too expensive to use these scarce facilities to explore different design iterations during the initial stages of aircraft development, or to experiment with new and immature technologies. Testing of free-flight subscale models, referred to as Subscale Flight Testing (SFT), could offer an affordable and low-risk alternative for complementing conventional techniques with both qualitative and quantitative information. The miniaturisation of mechatronic systems, the advances in rapid-prototyping techniques and power storage, as well as new manufacturing methods, currently enable the development of sophisticated test objects at scales that were impractical some decades ago. Moreover, the recent boom in the commercial drone industry has driven a quick development of specialised electronics and sensors, which offer nowadays surprising capabilities at competitive prices. These recent technological disruptions have significantly altered the cost-benefit function of SFT and it is necessary to re-evaluate its potential in the contemporary aircraft development context. This thesis aims to increase the comprehension and knowledge of the SFT method in order to define a practical framework for its use in aircraft design; focusing on low-cost, short-time solutions that don’t require more than a small organization and few resources. This objective is approached from a theoretical point of view by means of an analysis of the physical and practical limitations of the scaling laws; and from an empirical point of view by means of field experiments aimed at identifying practical needs for equipment, methods, and tools. A low-cost data acquisition system is developed and tested; a novel method for semi-automated flight testing in small airspaces is proposed; a set of tools for analysis and visualisation of flight data is presented; and it is also demonstrated that it is possible to explore and demonstrate new technology using SFT with a very limited amount of economic and human resources. All these, together with a theoretical review and contextualisation, contribute to increasing the comprehension and knowledge of the SFT method in general, and its potential applications in aircraft conceptual design in particular.
Ceas Aiaa Icase Nasa Langley International Forum On Aeroelasticity And Structural Dynamics 1999
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Author :
language : en
Publisher:
Release Date : 1999
Ceas Aiaa Icase Nasa Langley International Forum On Aeroelasticity And Structural Dynamics 1999 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 Aeroelasticity categories.
These proceedings represent a collection of the latest advances in aeroelasticity and structural dynamics from the world community. Research in the areas of unsteady aerodynamics and aeroelasticity, structural modeling and optimazation, active control and adaptive structures, landing dynamics, certification and qualification, and validation testing are highlighted in the collection of papers. The wide range of results will lead to advances in the prediction and control of the structural response of aircraft and spacecraft.
The Shock And Vibration Digest
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Author :
language : en
Publisher:
Release Date : 1983
The Shock And Vibration Digest written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1983 with Shock (Mechanics) categories.
Aeronautical Engineering
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Author :
language : en
Publisher:
Release Date : 1991
Aeronautical Engineering written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1991 with Aeronautics categories.
Real Time Flutter Identification
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Author : R. Roy
language : en
Publisher:
Release Date : 1985
Real Time Flutter Identification written by R. Roy and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1985 with categories.
The techniques and a FORTRAN 77 MOdal Parameter IDentification (MOPID) computer program developed for identification of the frequencies and damping ratios of multiple flutter modes in real time are documented. Physically meaningful model parameterization was combined with state of the art recursive identification techniques and applied to the problem of real time flutter mode monitoring. The performance of the algorithm in terms of convergence speed and parameter estimation error is demonstrated for several simulated data cases, and the results of actual flight data analysis from two different vehicles are presented. It is indicated that the algorithm is capable of real time monitoring of aircraft flutter characteristics with a high degree of reliability.
Aircraft Flight Flutter Testing At The Nasa Ames Dryden Flight Research Facility
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Author :
language : en
Publisher:
Release Date : 1988
Aircraft Flight Flutter Testing At The Nasa Ames Dryden Flight Research Facility written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1988 with categories.
Nasa Sp
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Author :
language : en
Publisher:
Release Date : 1984
Nasa Sp written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1984 with Aeronautics categories.