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  • 1
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    Design and development of a high-speed bearing test rig (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The development of a high-speed test rig, to be used for compiling an experimental data base of bearing signatures for bearings with known faults, is described. This bearing test rig can be adapted to test oil-film bearings as well as rolling element bearings. This is achieved by mounting the test bearing in one of two special test housings, either of which can be mounted onto a common test shaft which can be driven up to 30,000 rpm. The test bearing housing for rolling element bearings can accommodate proximity displacement transducers, accelerometers, thermocouples, and acoustic emission sensors. The test bearing housing for the fluid-film bearings can accommodate the same instrumentation as well as Bourdon tube-type transducers for measuring oil film pressures around the bearing circumference.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA-CR-199180 , NAS 1.26:199180 , WYLE-TR-61820-01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    An experimental program for the investigation of panel instabilities caused by shock waves (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Experimental methods and apparatus for studying panel instabilities caused by shock waves
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-100354 , TM-68-23
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Experimental study of shock-panel coupling - Preliminary results (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Shock-panel coupling effects of supersonic turbulent flow driven by impedance head
    Keywords: AERODYNAMICS
    Type: NASA-CR-61986 , TM-68-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Vibration response of spacecraft shrouds to in-flight fluctuating pressures (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: Results are presented for the vibration response of a spacecraft shroud to a range of in-flight fluctuation pressures. An Atlas-Agena 15 degree cone-cylinder shroud was analyzed during the present study, and three critical flight Mach numbers were considered. At transonic Mach numbers, the aerodynamic flow over the shroud is complex, involving zones of regular attached flow, separated flow, shock wave oscillation, and modified attached flows induced by local thickening of the boundary layer. The overall shroud vibration levels for a particular Mach number were determined by initially calculating the mean square acceleration levels induced by the fluctuating pressures distributed over an individual zone, and then summing mean square acceleration levels in one-third octave bands over all zones.
    Keywords: SPACE VEHICLES
    Type: Journal of Sound and Vibration; 33; Apr. 22
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Acoustic fatigue and sound transmission characteristics of a ram composite panel design (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental study to determine the acoustic fatigue characteristics of a flat multi-layered structural panel is described. The test panel represented a proposed design for the outer skin of a research application module to be housed within the space shuttle orbiter vehicle. The test specimen was mounted in one wall of the Wyle 100,000 cu ft reverberation room and exposed to a broadband acoustic environment having an overall level of 145 db. The test panel was exposed to nine separate applications of the acoustic environment, each application consisting of 250 seconds duration. Upon completion of the ninth test run, the specimen was exposed to a simulated micrometeoroid impact near the panel center. One additional test run of 250 seconds duration was then performed to complete the overall simulation of 50 flight missions. The experimental results show that no significant fatigue damage occurred until the test specimen was exposed to a simulated micrometeoroid impact. The intermediate foam layer forming the core of the test specimen suffered considerable damage due to this impact, causing a marked variation in the dynamic characteristics of the overall test panel. During the final application of the acoustic environment, the strain and acceleration response spectra showed considerable variation from those spectra obtained prior to impact of the panel. Fatigue damage from acoustic loading however, was limited to partial de-bonding around the edges of the composite panel.
    Keywords: MATERIALS, NONMETALLIC
    Type: NASA-CR-124079 , TM-72-3
    Format: application/pdf
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  • 6
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    Evaluation of acoustic testing techniques for spacecraft systems (1971)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: External acoustic environments, structural responses, noise reductions, and the internal acoustic environments have been predicted for a typical shroud/spacecraft system during lift-off and various critical stages of flight. Spacecraft responses caused by energy transmission from the shroud via mechanical and acoustic paths have been compared and the importance of the mechanical path has been evaluated. Theoretical predictions have been compared extensively with available laboratory and in-flight measurements. Equivalent laboratory acoustic fields for simulation of shroud response during the various phases of flight have been derived and compared in detail. Techniques for varying the time-space correlations of laboratory acoustic fields have been examined, together with methods for varying the time and spatial distribution of acoustic amplitudes. Possible acoustic testing configurations for shroud/spacecraft systems have been suggested and trade-off considerations have been reviewed. The problem of simulating the acoustic environments versus simulating the structural responses has been considered and techniques for testing without the shroud installed have been discussed.
    Keywords: SPACE VEHICLES
    Type: NASA-CR-122450 , WR-71-7
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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