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Structureborne noise in aircraft: Modal testsAs part of an investigation to develop measurement techniques for structureborne noise, three modal surveys have been conducted on an OV-10A aircraft and the results have been presented. The purpose of the modal surveys was to identify suitable locations for mounting accelerometer and strain gages in subsequent tests in which transfer functions relating wing vibration to interior noise were to be determined. These surveys are as follows:(1) wing/fuselage modal survey utilizing one shaker under the right wing; (2) complete wing modal survey utilizing two shakers, one under each wing; and (3) fuselage side panel modal survey utilizing a small instrumented hammer. The predominant frequencies and damping ratios for each analysis were listed in tables. The primary mode shapes at the lower frequencies and at frequencies near the expected engine driving frequencies have been shown for each survey.
Document ID
19860021867
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Clevenson, S. A. (NASA Langley Research Center Hampton, VA, United States)
Metcalf, V. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
July 1, 1986
Subject Category
Acoustics
Report/Patent Number
USAAVSCOM-TM-86-B-3
NASA-TM-87739
NAS 1.15:87739
Accession Number
86N31339
Funding Number(s)
PROJECT: RTOP 535-03-11-03
PROJECT: DA PROJ. 1L1-61102-AH-45
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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