Quantification of Helicopter Vibration Ride Quality Using Absorbed Power Measurements PDF Download
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Author: D. D. Hollenbaugh
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Book Description
The absorbed power concept offers certain advantages over pure acceleration for helicopter ride quality evaluation. First, it takes into account multi-frequency, multi-axial vibration across a broad frequency range. Second, it provides proper weighting functions for all frequencies and axes according to body response. Third, it is applicable to random as well as periodic accelerations. A larger data base and further experimentation is required for full validation of absorbed power as a means for quantifying helicopter vibration ride quality. Further in-flight data will be collected to expand the vibration/noise environment data base, repeating measurements on the aircraft mentioned here, and add further aircraft. Already underway is a program to take measurements on US Navy air craft types. Data have been recorded on a Sikorsky RH-53D and a Kaman SH-2F. The subjective response experiments will be continued for correlation and validation of the absorbed power and NASA Ride Comfort Model.
Author: D. D. Hollenbaugh
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Book Description
The absorbed power concept offers certain advantages over pure acceleration for helicopter ride quality evaluation. First, it takes into account multi-frequency, multi-axial vibration across a broad frequency range. Second, it provides proper weighting functions for all frequencies and axes according to body response. Third, it is applicable to random as well as periodic accelerations. A larger data base and further experimentation is required for full validation of absorbed power as a means for quantifying helicopter vibration ride quality. Further in-flight data will be collected to expand the vibration/noise environment data base, repeating measurements on the aircraft mentioned here, and add further aircraft. Already underway is a program to take measurements on US Navy air craft types. Data have been recorded on a Sikorsky RH-53D and a Kaman SH-2F. The subjective response experiments will be continued for correlation and validation of the absorbed power and NASA Ride Comfort Model.
Author:
Publisher:
ISBN:
Category : Shock (Mechanics)
Languages : en
Pages : 600
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Author:
Publisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 778
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 204
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 892
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Author:
Publisher:
ISBN:
Category : Shock (Mechanics)
Languages : en
Pages : 598
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Author: J. D. Leatherwood
Publisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 52
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This paper presents the results of a simulator study conducted to compare and validate various ride quality prediction methods for use in assessing passenger/crew ride comfort within helicopters. Included are results quantifying 35 helicopter pilots' discomfort responses to helicopter interior noise and vibration typical of routine flights, assessment of various ride quality metrics including the NASA ride comfort model, and examination of possible criteria approaches. Results of the study indicated that crew discomfort results from a complex interaction between vibration and interior noise. Overall measures such as weighted or unweighted root-mean-square acceleration level and A-weighted noise level were not good predictors of discomfort. Accurate prediction required a metric incorporating the interactive efefcts of both noise and vibration. The best metric for predicting crew comfort to the combined noise and vibration environment was the NASA discomfort index. (Author).
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 614
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Author: American Helicopter Society
Publisher:
ISBN:
Category : Helicopters
Languages : en
Pages : 638
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 700
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