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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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  • 2
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    Requirements and test results for the qualification of thermal control coatings (1988)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Paint type coatings are often used as engineering materials in critical satellite temperature control applications. The functional features of coatings used for temperature control purposes must remain stable throughout the satellite manufacturing process and the satellite mission. The selection of a particular coating depends on matching coating characteristics to mission requirements. The use of paint coatings on satellites, although having an extensive history, requires that the paint be qualified to each application on an individual basis. Thus, the qualification process through testing serves to ensure that paint coatings as engineering materials will fulfill design requirements.
    Keywords: NONMETALLIC MATERIALS
    Type: 15th Space Simulation Conference: Support the Highway to Space Through Testing; p 419-436
    Format: application/pdf
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  • 3
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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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  • 4
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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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  • 5
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    Vibronic effects in the predissociation of the C/1/Pi/u state of C2N2 (1979)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: The partitioning of excess photochemical energy as a function of the vibrational energy of the state of C2N2 has been measured. Surprisal theory has been used to analyze the data and it shows that complete randomization does not occur before dissociation. The results are also inconsistent with the predictions of the quasidiatomic theory for photodissociation.
    Keywords: ATOMIC AND MOLECULAR PHYSICS
    Type: Journal of Chemical Physics; 71; Dec. 1
    Format: text
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  • 6
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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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  • 7
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    Simulator study of the effect of visual-motion time delays on pilot tracking performance with an audio side task (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of time delay was determined in the visual and motion cues in a flight simulator on pilot performance in tracking a target aircraft that was oscillating sinusoidally in altitude only. An audio side task was used to assure the subject was fully occupied at all times. The results indicate that, within the test grid employed, about the same acceptable time delay (250 msec) was obtained for a single aircraft (fighter type) by each of two subjects for both fixed-base and motion-base conditions. Acceptable time delay is defined as the largest amount of delay that can be inserted simultaneously into the visual and motion cues before performance degradation occurs. A statistical analysis of the data was made to establish this value of time delay. Audio side task provided quantitative data that documented the subject's work level.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1216 , L-11996
    Format: application/pdf
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  • 8
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    Evaluation of several secondary tasks in the determination of permissible time delays in simulator visual and motion cues (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The effect of secondary tasks in determining permissible time delays in visual-motion simulation of a pursuit tracking task was examined. A single subject, a single set of aircraft handling qualities, and a single motion condition in tracking a target aircraft that oscillates sinusoidally in altitude were used. In addition to the basic simulator delays the results indicate that the permissible time delay is about 250 msec for either a tapping task, an adding task, or an audio task and is approximately 125 msec less than when no secondary task is involved. The magnitudes of the primary task performance measures, however, differ only for the tapping task. A power spectraldensity analysis basically confirms the result by comparing the root-mean-square performance measures. For all three secondary tasks, the total pilot workload was quite high.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1214 , L-12006
    Format: application/pdf
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  • 9
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    Analysis of interface crack branching (1989)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A solution is presented for the problem of a finite length crack branching off the interface between two bonded dissimilar isotropic materials. Results are presented in terms of the ratio of the energy release rate of a branched interface crack to the energy release rate of a straight interface crack with the same total length. It is found that this ratio reaches a maximum when the interface crack branches into the softer material. Longer branches tend to have smaller maximum energy release rate ratio angles indicating that all else being equal, a branch crack will tend to turn back parallel to the interface as it grows.
    Keywords: STRUCTURAL MECHANICS
    Type: NASA-CR-182273 , NAS 1.26:182273
    Format: application/pdf
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  • 10
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    Model for the solution of supersonic viscous interaction effects on blunted cones (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Mar. 197
    Format: text
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