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  • 1
    Publication Date: 2011-08-24
    Keywords: STRUCTURAL MECHANICS
    Type: Journal of Aircraft (ISSN 0021-8669); 29; 6; p. 1130-1136.
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  • 2
    Publication Date: 2011-08-24
    Description: Data from a sonic fatigue test of a blade-stiffened carbon/carbon panel is analyzed to determine the progression of damage to failure. The reduction in stiffness, as observed from acceleration measurements taken during the test, is correlated with the physical damage. Damage was measured through visual inspection, thermographic measurements, and through the novel use of vibration data collected using a scanning laser vibrometer.
    Keywords: COMPOSITE MATERIALS
    Type: In: International Congress on Experimental Mechanics, 7th, Las Vegas, NV, June 8-11, 1992, Proceedings. Vol. 2 (A94-12901 02-39); p. 1348-1355.
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  • 3
    Publication Date: 2011-08-10
    Description: Prelaunch & flight vibration measurements on thor vehicles
    Keywords: SPACE SCIENCES
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  • 4
    Publication Date: 2011-08-16
    Description: Dynamic field measurements often involve large quantities of continuous data, which must be analyzed and interpreted to obtain meaningful information. The processing can often be accomplished by tape-recording the data in analog form, performing off-line digitalization, and using the result as an input to statistical programs on a digital computer. A time series analysis was used to obtain power spectral density (PSD) curves to identify dominant frequencies. Representative PSD plots were obtained for STOL aircraft during cruise. Vibrational energy was clearly concentrated below 0.1 Hz, and was much higher in the vertical than in the lateral direction.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Instruments and Control Systems; 46; Sept
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  • 5
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    In:  Other Sources
    Publication Date: 2011-08-11
    Description: Fatigue life of aluminum alloy specimens for aircraft and launch vehicles under various random loading spectra
    Keywords: STRUCTURAL MECHANICS
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  • 6
    Publication Date: 2011-08-17
    Description: A series of experimental studies utilizing approximately 2200 test subjects has led to the development of a general empirical model for the prediction of passenger ride discomfort in the presence of complex noise and vibration inputs. The ranges of vibration and noise stimuli used to derive the model included the amplitudes and frequencies that are known to most influence passenger comfort. The ride quality model accounts for the effects of combined axis vibrations (up to three axes simultaneously) and includes corrections for the effect of vibration duration and interior noise. Output of the model consists of an estimate of the passenger discomfort produced by a given noise and/or vibration environment. The discomfort estimate is measured along a continuous scale that spans the range from below discomfort threshold to values of discomfort that are far above discomfort threshold
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: Human Factors; 22; June 198
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  • 7
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    In:  Other Sources
    Publication Date: 2011-08-12
    Keywords: unknown
    Type: NRL THE SHOCK AND VIBRATION BULL., NO. 35, PT. 2 JAN. 1966 (SEE N68-80442)
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  • 8
    Publication Date: 2011-08-17
    Description: A laboratory investigation was directed at the development of criteria for the prediction of ride quality in a noise-vibration environment. The stimuli for the study consisted of octave bands of noise centered at 500 and 2000 Hz and vertical floor vibrations composed of either 5 Hz sinusoidal vibrations, or random vibrations centered at 5 Hz and with a 5 Hz bandwidth. Results indicated that the total subjective discomfort response could be divided into two subjective components. One component consisted of subjective discomfort to vibration and was found to be a linear function of vibration acceleration level. The other component consisted of discomfort due to noise which varied logarithmically with noise level (power relationship). A model of subjective discomfort that accounted for the interdependence of noise and vibration was developed. The model was then used to develop a set of criteria (constant discomfort) curves that illustrate the basic design tradeoffs available between noise and vibration.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Acoustical Society of America; vol. 65
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  • 9
    Publication Date: 2011-08-18
    Description: 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 are presented. 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 effects of both noise and vibration. The best metric for predicting crew comfort to the combined noise and vibration environment was the NASA discomfort index.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: American Helicopter Society, Journal (ISSN 0002-8711); 29; 11-18
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  • 10
    Publication Date: 2018-12-01
    Description: Testing method for spacecraft response during environmental testing equivalent to its response to excitation by sinusoidal transients in flight
    Keywords: STRUCTURAL MECHANICS
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