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Thermoelastic vibration test techniquesThe structural integrity of proposed high speed aircraft can be seriously affected by the extremely high surface temperatures and large temperature gradients throughout the vehicle's structure. Variations in the structure's elastic characteristics as a result of thermal effects can be observed by changes in vibration frequency, damping, and mode shape. Analysis codes that predict these changes must be correlated and verified with experimental data. The experimental modal test techniques and procedures used to conduct uniform, nonuniform, and transient thermoelastic vibration tests are presented. Experimental setup and elevated temperature instrumentation considerations are also discussed. Modal data for a 12 by 50 inch aluminum plate heated to a temperature of 475 F are presented. These data show the effect of heat on the plate's modal characteristics. The results indicated that frequency decreased, damping increased, and mode shape remained unchanged as the temperature of the plate was increased.
Document ID
19910009770
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kehoe, Michael W.
(NASA Ames Research Center Moffett Field, CA., United States)
Snyder, H. Todd
(PRC Kentron, Inc., Edwards CA., United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1991
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
H-1707
NASA-TM-101742
NAS 1.15:101742
Meeting Information
Meeting: International Modal Analysis Conference
Location: Florence
Country: Italy
Start Date: April 14, 1991
End Date: April 18, 1991
Accession Number
91N19083
Funding Number(s)
PROJECT: RTOP 505-66-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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