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  • Other Sources  (6)
  • 1985-1989  (6)
  • 1985  (6)
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  • 1985-1989  (6)
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  • 1
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    Actions for productivity improvement in crew training (1985)
    In:  CASI
    Details
    Publication Date: 2006-02-14
    Description: Improvement of the productivity of astronaut crew instructors in the Space Shuttle program and beyond is proposed. It is suggested that instructor certification plans should be established to shorten the time required for trainers to develop their skills and improve their ability to convey those skills. Members of the training cadre should be thoroughly cross trained in their task. This provides better understanding of the overall task and greater flexibility in instructor utilization. Improved facility access will give instructors the benefit of practical application experience. Former crews should be integrated into the training of upcoming crews to bridge some of the gap between simulated conditions and the real world. The information contained in lengthy and complex training manuals can be presented more clearly and efficiently as computer lessons. The illustration, animation and interactive capabilities of the computer combine an effective means of explanation.
    Keywords: ADMINISTRATION AND MANAGEMENT
    Type: NASA. Johnson (Lyndon B.) Space Center R and D Productivity: New Challenges for the US Space Program; p 425-436
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    The challenging scales of the bird: Shuttle tile structural integrity (1985)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The principal design issues, tests, and analyses required to solve the tile integrity problem on the space shuttle orbiters are addressed. Proof testing of installed tiles is discussed along with an airflow test of special tiles. Orbiter windshield tiles are considered in terms of changes necessary to ensure acceptable margins of safety for flight.
    Keywords: SPACE TRANSPORTATION
    Type: Space Shuttle Tech. Conf., Pt. 1; p 403-413
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Transonic aerodynamic and aeroelastic characteristics of a variable sweep wing (1985)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The flow over the B-1 wing is studied computationally, including the aeroelastic response of the wing. Computed results are compared with results from wind tunnel and flight tests for both low-sweep and high-sweep cases, at 25.0 and 67.5 deg., respectively, for selected transonic Mach numbers. The aerodynamic and aeroelastic computations are made by using the transonic unsteady code ATRAN3S. Steady aerodynamic computations compare well with wind tunnel results for the 25.0 deg sweep case and also for small angles of attack at the 67.5 deg sweep case. The aeroelastic response results show that the wing is stable at the low sweep angle for the calculation at the Mach number at which there is a shock wave. In the higher sweep case, for the higher angle of attack at which oscillations were observed in the flight and wind tunnel tests, the calculations do not show any shock waves. Their absence lends support to the hypothesis that the observed oscillations are due to the presence of leading edge separation vortices and are not due to shock wave motion as was previously proposed.
    Keywords: AERODYNAMICS
    Type: AGARD Unsteady Aerodynamics-Fundamentals and Applications to Aircraft Dynamics; 15 p
    Format: text
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  • 4
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    Transonic aerodynamic and aeroelastic characteristics of a variable sweep wing (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The flow over the B-1 wing is studied computationally, including the aeroelastic response of the wing. Computed results are compared with results from wind tunnel and flight tests for both low-sweep and high-sweep cases, at 25.0 deg. and 67.5 deg., respectively, for selected transonic Mach numbers. The aerodynamic and aeroelastic computations are made by using the transonic unsteady code ATRAN3S. Steady aerodynamic computations compare well with wind tunnel results for the 25.0 deg. sweep case and also for small angles of attack at the 67.5 deg. sweep case. The aeroelastic response results show that the wing is stable at the low sweep angle for the calculation at the Mach number at which there is a shock wave. In the higher sweep case, for the higher angle of attack at which oscillations were observed in the flight and wind tunnel tests, the calculations do not show any shock waves. Their absence lends support to the hypothesis that the observed oscillations are due to the presence of leading edge separation vortices and are not due to shock wave motion as was previously proposed.
    Keywords: AERODYNAMICS
    Type: NASA-TM-86677 , A-85119 , NAS 1.15:86677
    Format: application/pdf
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  • 5
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    Time-resolved laser-induced fluorescence of selected even-parity 7p states of Xe I (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: Lifetimes and self-quenching rates have been measured for excited states of Xe I that were populated using simultaneous two-photon absorption. Lifetimes measured in this study are somewhat shorter than those measured using the broadband-excitation technique. Lifetimes reported here are all faster than 100 nsec. Deactivation rates are approximately 2 x 10 to the -10th cu cm/sec per mol.
    Keywords: ATOMIC AND MOLECULAR PHYSICS
    Type: Optical Society of America, Journal, B: Optical Physics (ISSN 0740-3224); 2; 414-416
    Format: text
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  • 6
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    Diffusion and solubility of oxygen in silver (1985)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: The diffusion and solubility of oxygen in Ag in the temperature range between 412 and 862 C was determined. The following interpolation formula was found for the solubility: L = 8.19.1/100.exp(-11 860/RT)Mol O2/g.At.Ag.at 1/.5. The process obeys the Sieverts square root law within the limits of error. The dissolution of oxygen in Ag may be accompanied by the dissociation of the oxygen molecules into atoms. The tests on Ag-foils reveal that below a temperature of about 500 C a higher solubility is simulated by the adsorption of oxygen. The diffusion coefficient of oxygen in silver obeys the following equation: D = 2.72.1/100.exp(-11 000/RT)sq cm/s. The relatively low activation energy of 11 kcal/g.At suggests that the diffusion of oxygen takes places over interstitial sites.
    Keywords: METALLIC MATERIALS
    Type: NASA-TM-77938 , NAS 1.15:77938
    Format: application/pdf
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