NDLI: Vibration analysis of the sa349/2 helicopter

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Vibration analysis of the sa349/2 helicopter

Content Provider	NASA Technical Reports Server (NTRS)
Author	Heffernan, Ruth Johnson, Wayne Precetti, Dominique
Copyright Year	1991
Description	Helicopter airframe vibration is examined using calculations and measurements for the SA349/2 research helicopter. The hub loads, which transmit excitations to the fuselage, are predicted using a comprehensive rotorcraft analysis and correlated with measuring hub loads. The predicted and measured hub loads are then coupled with finite element models representing the SA349/2 fuselage. The resulting vertical acceleration at the pilot seat is examined. Adjustments are made to the airframe structural models to examine the sensitivity of predicted vertical acceleration to the model. Changes of a few percent to the damping and frequency of specific models lead to large reductions in predicted vibration, and to major improvements in the correlations with measured pilot-seat vertical acceleration.
File Size	3157357
Page Count	104
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19910021764
Archival Resource Key	ark:/13960/t2799301r
Language	English
Publisher Date	1991-01-01
Access Restriction	Open
Subject Keyword	Aeronautics (general) Dynamic Structural Analysis Correlation Helicopters Structural Vibration Dynamic Loads Seats Aircraft Models Finite Element Method Vibration Damping Airframes Research Aircraft Acceleration Physics Fuselages Rotary Wing Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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