4 edition of A worst-case approach for on-line flutter prediction found in the catalog.
A worst-case approach for on-line flutter prediction
1998 by National Aeronautics and Space Administration, National Technical Information Service, distributor in [Washington, D.C, Springfield, Va .
Written in English
|Other titles||Worst case approach for on line flutter prediction., Worst case approach for online flutter prediction.|
|Statement||Rick C. Lind and Martin J. Brenner.|
|Series||[NASA technical memorandum] -- 207056.|
|Contributions||Brenner, Martin J., United States. National Aeronautics and Space Administration.|
|The Physical Object|
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Get this from a library. A worst-case approach for on-line flutter prediction. [Rick C Lind; Martin J Brenner; United States. National Aeronautics and Space Administration.]. – R. Lind and M. Brenner, “A Worst-Case Approach for On-Line Flutter Prediction” International Forum on Aeroelasticity and Structural Dynamics, Rome Italy, JuneVol.
2, pp. – R. Lind, M. Brenner and L. Freudinger, “Improved Flight Test Procedures for Flutter Clearance” International Forum on AeroelasticityCited by: 4.
Lind and M. Brenner, "A Worst-Case Approach for On-Line Flutter Prediction," International Forum on Aeroelasticity and Structural Dynamics, Rome, Italy, JuneVolume 2, pp. Lind, M. Brenner and L. Freudinger, "Improved Flight Test Procedures for Flutter Clearance," International Forum on Aeroelasticity and Structural Dynamics.
On-Line Robust Modal Stability Prediction using Wavelet Processing A Worst-Case Approach for On-Line Flutter Prediction. Worst-case flutter. An approach for computing worst-case flutter margins has been formulated in a robust stability framework.
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Papcostas N4 = Continue reading "Noise Library". The approach and first results (indicating a near ⁰ TT path for the final hours of the flight) were introduced here on the blog back in March The present document is a first full write-up shared hoping to stimulate discussion, and that possible errors or inaccuracies in the underlying analysis can be reported by critical readers.
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Summary Files Reviews Support Wiki Code Tickets Discussion Blog Code Code Menu Browse Commits. Worst case, results are inefficient, incomplete, and disorganized, resulting in dubious outcomes, and in the best case are so labor intensive they can be inaccurate because they are based on outdated stale data.
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The calculation depends only on the time of the closest approach relative to andand then it is a matter of geometry. The curvature of the arcs can be completely ignored. I agree that if the time of the closest approach wasthen the speed works out at close to knots.
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This paper demonstrates the implementation of an adaptive feedforward controller to reduce structural vibrations on a wing typical section. The aeroelastic model includes a structural nonlinearity, which is modelled in a polynomial form.
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