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  • 1
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    Drilling test program (1965)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Rock drilling test program and drilling parameters for lunar sampling
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Sampling. (1969)
    In:  Other Sources
    Details
    Publication Date: 2011-08-12
    Description: Bulk, selective particulate and hard rock samplers for landed extraterrestrial geological and biological instruments performing on-site analysis
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Type: ; SEARCH(
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Extendable mast used in one shot soil penetrometer (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-29
    Description: Penetrometer to test soil characteristics has a piercing head with soil instrumentation equipment attached to an expandable mast actuated by compressed air. The penetrometer gives continuous measurements as the mast pushes the piercing head through the soil.
    Keywords: MECHANICS
    Type: JPL-685
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Burst diaphragm protects vacuum vessel from internal pressure transients (1965)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Supported dual-mode burst diaphragm protects vacuum vessels from transient internal pressures. It forms the interface between the vacuum in the vessel and an external pressure.
    Keywords: MECHANICS
    Type: JPL-687
    Format: application/pdf
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  • 5
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    Cold-air investigation of a 4 1/2 stage turbine with stage-loading factor of 4.66 and high specific work output. 2: Stage group performance (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The stage group performance of a 4 1/2 stage turbine with an average stage loading factor of 4.66 and high specific work output was determined in cold air at design equivalent speed. The four stage turbine configuration produced design equivalent work output with an efficiency of 0.856; a barely discernible difference from the 0.855 obtained for the complete 4 1/2 stage turbine in a previous investigation. The turbine was designed and the procedure embodied the following design features: (1) controlled vortex flow, (2) tailored radial work distribution, and (3) control of the location of the boundary-layer transition point on the airfoil suction surface. The efficiency forecast for the 4 1/2 stage turbine was 0.886, and the value predicted using a reference method was 0.862. The stage group performance results were used to determine the individual stage efficiencies for the condition at which design 4 1/2 stage work output was obtained. The efficiencies of stages one and four were about 0.020 lower than the predicted value, that of stage two was 0.014 lower, and that of stage three was about equal to the predicted value. Thus all the stages operated reasonably close to their expected performance levels, and the overall (4 1/2 stage) performance was not degraded by any particularly inefficient component.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TP-1688 , E-315
    Format: application/pdf
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  • 6
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    Cold-air performance of a tip turbine designed to drive a lift fan. 3: Effect of simulated fan leakage on turbine performance (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Performance data were obtained experimentally for a 0.4 linear scale version of the LF460 lift fan turbine for a range of scroll inlet total to diffuser exit static pressure ratios at design equivalent speed with simulated fan leakage air. Tests were conducted for full and partial admission operation with three separate combinations of rotor inlet and rotor exit leakage air. Data were compared to the results obtained from previous investigations in which no leakage air was present. Results are presented in terms of mass flow, torque, and efficiency.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1109 , E-9331
    Format: application/pdf
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  • 7
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    Cold-air performance of a tip turbine designed to drive a lift fan (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Performance was obtained over a range of speeds and pressure ratios for a 0.4 linear scale version of the LF460 lift fan turbine with the rotor radial tip clearance reduced to about 2.5 percent of the rotor blade height. These tests covered a range of speeds from 60 to 140 percent of design equivalent speed and a range of scroll inlet total to diffuser exit static pressure ratios from 2.6 to 4.2. Results are presented in terms of equivalent mass flow, equivalent torque, equivalent specific work, and efficiency.
    Keywords: AERODYNAMICS
    Type: NASA-TP-1126 , E-9293
    Format: application/pdf
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  • 8
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    Research turbine for high temperature core engine application. 1: Cold-airoverall performance of solid scaled turbine (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A solid, half-scale model of a 50.8-cm (20-in) research turbine designed for a high temperature core engine application was investigated over a range of speeds and pressure ratios. The results of this test are presented. The effect of rotor blade twist was also investigated. At the design equivalent speed and specific work output, the total efficiency of the turbine with untwisted rotor blades was 87.1 percent; at the same pressure ratio the efficiency of the turbine with twisted rotor blades was 88.0 percent.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-7557 , E-7592
    Format: application/pdf
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  • 9
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    A survey of actuator shaft sealing techniques for extended space missions (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Actuators for control and articulation aboard Mariner spacecraft have employed output shaft seals to maintain an internal gaseous atmosphere. On future missions, considerably greater expected lifetimes, temperature ranges, and radiation exposures have led to a need to determine the limitations of the present O-ring output shaft seal and to examine other candidate seals. Seals suited both to dynamic and static sealing were examined for potential use in three specific actuator applications and the following candidate seals were selected: (a) O-ring seal, (b) chevron seal, (c) bellows seal (linear actuator only), (d) magnetic fluid seal (rotary actuators only) and as a backup seal to any of the foregoing, (e) the labyrinth seal.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-130927 , JPL-TM-33-587
    Format: application/pdf
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  • 10
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    Burrowing apparatus (1968)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A soil burrowing mole is described in which a housing has an auger blade wound around a front portion. This portion is rotatable about a housing longitudinal axis relative to an externally finned housing rear portion upon operation of driving means to cause an advance through soil and the like. The housing carries a sensor sensitive to deviation from a predetermined path and to which is coupled means for steering the housing to maintain the path.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Format: application/pdf
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