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  • MACHINE ELEMENTS AND PROCESSES  (46)
  • LUNAR AND PLANETARY EXPLORATION
  • ASTROPHYSICS
  • 1975-1979
  • 1970-1974  (47)
  • 1972  (47)
Collection
Years
  • 1975-1979
  • 1970-1974  (47)
Year
  • 1
    Publication Date: 2016-06-07
    Description: The primary objective of the remote nuclear teleoperator study program was to define in detail a program plan which would provide a qualified operational space teleoperator system by about 1980. The concept and philosophy presented provides a product considered to be an advanced teleoperator when compared to today's state-of-the-art. The teleoperator concept is formulated to meet NERVA requirements.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA, Washington Proc. of the Natl. Symp. on Nat. and Manmade Radiation in Space; p 277-279
    Format: application/pdf
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  • 2
    Publication Date: 2019-06-27
    Description: An analysis is presented for compressible fluid flow across shaft face seals and narrow slots. The analysis includes fluid inertia, viscous friction, and entrance losses. Subsonic and choked flow conditions can be predicted and analyzed. The model is valid for both laminar and turbulent flows. Results agree with experiment and with solutions which are more limited in applicability. Results show that a parallel film can have a positive film stiffness under choked flow conditions.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-TN-D-6668 , E-6819
    Format: application/pdf
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  • 3
    Publication Date: 2019-06-27
    Description: The technology developed in defining a facility to be used on the Skylab mission for electromagnetic suspension of small, molten spheres in the weightless space environment is described. The technologies discussed include: four-coil optimization, four-coil versus six-coil configuration comparison, four-coil position servocontrol, four-coil breadboard, position sensing and servosystem, two-color pyrometer, and specimen toration mode analysis.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-124134
    Format: application/pdf
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  • 4
    Publication Date: 2019-06-27
    Description: A method for predicting the operating film thickness of self-acting seals is described. The analysis considers a 16.76-cm mean diameter seal that is typical of large gas turbines for aircraft. Four design points were selected to cover a wide range of operation for advanced engines. This operating range covered sliding speeds of 61 to 153 m/sec, sealed pressures of 45 to 217 N/sq cm abs, and gas temperatures of 311 to 977 K. The force balance analysis revealed that the seal operated without contact over the operating range with gas film thicknesses ranging between 0.00046 to 0.00119 cm, and with gas leakage rates between 0.01 to 0.39 scmm.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-TN-D-6568 , E-6458
    Format: application/pdf
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  • 5
    Publication Date: 2019-07-13
    Description: The results are presented of a program to demonstrate the processes for fabricating complementary MISFET beam-leaded circuits, which, potentially, are comparable in quality to available bipolar beam-lead chips that use silicon nitride passivation in conjunction with a platinum-titanium-gold metal system. Materials and techniques, different from the bipolar case, were used in order to be more compatible with the special requirements of fully passivated complementary MISFET devices. Two types of circuits were designed and fabricated, a D-flip-flop and a three-input NOR/NAND gate. Fifty beam-leaded chips of each type were constructed. A quality and reliability assurance program was performed to identify failure mechanisms. Sample tests and inspections (including destructive) were developed to measure the physical characteristics of the circuits.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-123742
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  • 6
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2019-07-13
    Description: Work is reported for fabricating and testing the fiberglass overwrapped titanium pressure vessel for cryogenic service. Difficulties encountered in the tank liner fabrication phase involved explosive forming, vacuum annealing, chemical milling and electron beam welding. While each of these processes and the nondestructive test methods employed are normally considered to be individually reliable, the combination of poor material together with fabrication and development reversals prevented the full achievement of the desired end results. Eight tanks plus a prototype and tool proofing article were produced. Six of the vessels failed during the hydrostatic sizing operation. One of the remaining tanks was hydrostatically pressurized to burst and the other was pressurized repeatedly at 75 F from 100 psi to the operating pressure until failure occurred. As a result, it is not possible to draw firm conclusions as to the true value of the design concept due to the problems encountered in the program.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-CR-120888
    Format: application/pdf
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  • 7
    Publication Date: 2005-11-30
    Description: A radiation source holder was developed to permit controlled exposure of biological material to a gamma-emitting radiation source during flight in a recoverable earth-orbiting satellite. A unique spring drive mechanism, activated by real time commands from the ground station, moved the Sr-85 source from a shielded position to the exposed position and then back to the shielded condition before reentry and recovery. A fail-safe feature utilized the reentry deceleration force to ensure that the source would be in a shielded position during the recovery operations. The device was successfully flown on Biosatellite 2.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: 6th Aerospace Mech. Symp.; p 9-12
    Format: text
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  • 8
    facet.materialart.
    Unknown
    In:  Other Sources
    Publication Date: 2011-08-16
    Description: Brief discussion of the historical background, variety range, chemistry, physics, and other properties of solid lubricants, and review of their current uses. The widespread use of solid lubricants did not occur until about 1947. At present, they are the object of such interest that a special international conference on their subject was held in 1971. They are used at temperatures beyond the useful range of conventional lubricating oils and greases. Their low volatility provides them with the capability of functioning effectively in vacuum and invites their use in space applications. Their high load carrying ability makes them useful with heavily loaded components. Solid lubricants, however, do lack some of the desirable properties of conventional lubricants. Unlike oils and greases, which have fluidity and can continuously be carried back into contact with lubricated surfaces, solid lubricants, because of their immobility, have finite lives. Also, oils and greases can carry away frictional heat from contacting surfaces, while solid lubricants cannot.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: Chem Tech; May 1972
    Format: text
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  • 9
    facet.materialart.
    Unknown
    In:  CASI
    Publication Date: 2016-06-07
    Description: Titanium fasteners are used in large quantities throughout the aircraft industry. Most of this usage is in aluminum structure; where titanium structure exists, titanium fasteners are logically used as well. Titanium fasteners offer potential weight savings to the designer at a cost of approximately $30 per pound of weight saved. Proper and least cost usage must take into consideration type of fastener per application, galvanic couples and installation characteristics of protective coatings, cosmetic appearance, paint adhesion, installation forces and methods available and fatigue performance required.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA. Langley Res. Center Proc. of the Symp. on Welding, Bonding, and Fastening; 16 p
    Format: application/pdf
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  • 10
    Publication Date: 2019-06-27
    Description: An ultrasonic scanning system used to inspect and evaluate in-place brazed tube joints is considered. The system was designed, developed, and built especially for nondestructive testing and was selected because of its known response to brazing defects not associated with material density changes. The scan system is capable of scanning brazed joints in union, tee, elbow and cross configuration of 3/16-inch through 5/8-inch diameters. It is capable of detecting brazed defects as small as 0.008 by 0.010-inch, which exceeds the 0.015-inch diameter defect resolution required by specification.
    Keywords: MACHINE ELEMENTS AND PROCESSES
    Type: NASA-TM-X-64702
    Format: application/pdf
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