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The Effects Of Structural Flap Lag And Pitch Lag Coupling On Soft Inplane Hingeless Rotor Stability In Hover Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of The Effects Of Structural Flap Lag And Pitch Lag Coupling On Soft Inplane Hingeless Rotor Stability In Hover book. This book definitely worth reading, it is an incredibly well-written.
Author : Anonim
Publisher : DIANE Publishing
Page : 72 pages
File Size : 43,5 Mb
Release : 2024-07-01
Category : Electronic
ISBN : 9781428916777
Author : National Aeronautics and Space Adm Nasa
Publisher : Unknown
Page : 74 pages
File Size : 43,5 Mb
Release : 2018-11-12
Category : Electronic
ISBN : 1731157169
A 1.62-m-diameter rotor model was tested in hover to examine the effects of structural flap-lag and pitch-lag coupling on isolated rotor blade lead-lag stability. Flap-lag coupling was introduced by inclining the principal axes of the blade structure up to 60 degrees. Pitch-lag coupling was obtained either alone or in combination with flap-lag coupling through the use of skewed flexural hinges. The principal results confirm the predictions of theory, and show that both structural flap-lag and pitch-lag coupling when used separately are beneficial to blade stability. Moreover, when the couplings are combined, the lead-lag damping is significantly greater than it would be if the individual contributions were superimposed. Pitch-flap coupling is shown to have only a minor effect on blade lead-lag damping. Differences between theory and experiment observed at zero blade pitch and flexure angles during the initial testing were determined in a second test to be caused by stand flexibility. Other differences between theory and experiment warrant further investigation. Bousman, William G. Ames Research Center...
Author : William G. Bousman
Publisher : DIANE Publishing
Page : 72 pages
File Size : 45,5 Mb
Release : 1990
Category : Aeroelasticity
ISBN : UIUC:30112106709733
Author : Anonim
Publisher : Unknown
Page : 84 pages
File Size : 40,7 Mb
Release : 1990
Category : Science
ISBN : STANFORD:36105024798683
Author : United States. National Aeronautics and Space Administration
Publisher : Unknown
Page : 380 pages
File Size : 50,9 Mb
Release : 1990
Category : Aeronautics
ISBN : UOM:39015022359130
Author : Anonim
Publisher : Unknown
Page : 178 pages
File Size : 55,6 Mb
Release : 1991
Category : Aeronautics
ISBN : NASA:31769000660350
Author : Anonim
Publisher : Unknown
Page : 556 pages
File Size : 55,7 Mb
Release : 1993
Category : Aeronautics
ISBN : STANFORD:36105029368243
Author : Anonim
Publisher : Unknown
Page : 180 pages
File Size : 55,7 Mb
Release : 1987
Category : Aeronautics
ISBN : IND:30000089367167
Author : Wayne Johnson
Publisher : Courier Corporation
Page : 1122 pages
File Size : 43,7 Mb
Release : 2012-03-07
Category : Technology & Engineering
ISBN : 9780486131825
Monumental engineering text covers vertical flight, forward flight, performance, mathematics of rotating systems, rotary wing dynamics and aerodynamics, aeroelasticity, stability and control, stall, noise, and more. 189 illustrations. 1980 edition.
Author : Anonim
Publisher : Unknown
Page : 518 pages
File Size : 45,9 Mb
Release : 1985
Category : Electronic
ISBN : NASA:31769000467491
Author : American Helicopter Society
Publisher : Unknown
Page : 320 pages
File Size : 48,8 Mb
Release : 2003
Category : Helicopters
ISBN : UVA:X006157668
Author : Earl H. Dowell
Publisher : Springer Nature
Page : 828 pages
File Size : 47,6 Mb
Release : 2021-10-16
Category : Technology & Engineering
ISBN : 9783030742362
This book is the sixth edition. It is suitable for one or more courses at the advanced undergraduate level and graduate level to cover the field of aeroelasticity. It is also of value to the research scholar and engineering practitioner who wish to understand the state of the art in the field. This book covers the basics of aeroelasticity or the dynamics of fluid–structure interaction. While the field began in response to the rapid development of aviation, it has now expanded into many branches of engineering and scientific disciplines and treats physical phenomena from aerospace engineering, bioengineering, civil engineering, and mechanical engineering in addition to drawing the attention of mathematicians and physicists. The basic questions addressed are dynamic stability and response of fluid structural systems as revealed by both linear and nonlinear mathematical models and correlation with experiment. The use of scaled models and full-scale experiments and tests play a key role where theory is not considered sufficiently reliable.
Author : Anonim
Publisher : Unknown
Page : 124 pages
File Size : 48,9 Mb
Release : 1989
Category : Electronic
ISBN : NASA:31769000587462
An isolated, hingeless rotor with discrete flap and lead-lag flexures and relatively rigid blades was tested in the Aeroflightdynamics Directorate's 7- by 10-Foot Wind Tunnel. The purpose of the test was to determine experimentally the lead-lag stability of a structurally simple rotor configuration in forward flight. The model tested had no cyclic pitch control, and was therefore operated untrimmed at several collective pitch angles, at shaft angles from 0 to -20, and at advance ratios as high as 0.55. Two inplane natural frequencies, 0.61/rev and 0.72/rev, were tested for configuration both with and without structural flap lag coupling. Concomitant hover testing of the model was also conducted. Representative plots of the frequency and damping data are presented to show general trends, and complete tabular data and model properties information are included for use in detailed correlation exercises. The most prominent feature of the forward flight data is an abrupt increase in damping with advance ratio at certain high-speed, high shaft-angle conditions, with high flapping loads. The hover data are consistent with previous experimental and theoretical results for hingeless rotors without kinematic couplings. Overall, the data quality is very good and the data are expected to be useful in the development and validation of rotor aeroelastic stability analyses.
Author : Robert A. Ormiston
Publisher : Unknown
Page : 60 pages
File Size : 44,8 Mb
Release : 1974
Category : Electronic
ISBN : NASA:31769000530785
Author : Anonim
Publisher : Unknown
Page : 740 pages
File Size : 45,9 Mb
Release : 1993
Category : Aerodynamics
ISBN : PSU:000023545366