Publication Date:
2019-07-13
Description:
The 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.
Keywords:
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Type:
NASA-TM-101742
,
H-1707
,
NAS 1.15:101742
,
International Modal Analysis Conference; Apr 14, 1991 - Apr 18, 1991; Florence; Italy
Format:
application/pdf
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