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  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (7)
  • AIRCRAFT STABILITY AND CONTROL  (7)
  • NAVIGATION  (7)
  • MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT  (2)
Collection
Keywords
Years
  • 1
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    IONIZATION OF NITROGEN MOLECULE STATIONARITY CONDITIONS FOR A CERTAIN PERIODIC RANDOM PROCESS (1961)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Ionization of nitrogen molecules by nitrogen molecules
    Keywords: NAVIGATION
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    FAST MOLECULAR NITROGEN BEAM (1961)
    In:  CASI
    Details
    Publication Date: 2006-10-26
    Description: Fast molecular nitrogen beam
    Keywords: NAVIGATION
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A 99 percent purity molecular sieve oxygen generator (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Molecular sieve oxygen generating systems (MSOGS) have become the accepted method for the production of breathable oxygen on military aircraft. These systems separate oxygen for aircraft engine bleed air by application of pressure swing adsorption (PSA) technology. Oxygen is concentrated by preferential adsorption in nitrogen in a zeolite molecular sieve. However, the inability of current zeolite molecular sieves to discriminate between oxygen and argon results in an oxygen purity limitations of 93-95 percent (both oxygen and argon concentrate). The goal was to develop a new PSA process capable of exceeding the present oxygen purity limitations. A novel molecular sieve oxygen concentrator was developed which is capable of generating oxygen concentrations of up to 99.7 percent directly from air. The process is comprised of four absorbent beds, two containing a zeolite molecular sieve and two containing a carbon molecular sieve. This new process may find use in aircraft and medical breathing systems, and industrial air separation systems. The commercial potential of the process is currently being evaluated.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA, Washington, Technology 2001: The Second National Technology Transfer Conference and Exposition, Volume 1; p 523-535
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    A simplified guidance scheme for aborting lunar landings (1964)
    In:  CASI
    Details
    Publication Date: 2019-05-23
    Description: Aborting technique for lunar landing
    Keywords: NAVIGATION
    Type: NASA-TN-D-2504
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Visual simulation of lunar orbit establishment using a simplified guidance technique (1966)
    In:  CASI
    Details
    Publication Date: 2019-05-30
    Description: Visual simulation of lunar orbit establishment using simplified guidance technique
    Keywords: NAVIGATION
    Type: NASA-TN-D-3524
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Simulator evaluation of the effects of reduced spoiler and thrust authority on a decoupled longitudinal control system during landings in wind shear (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The effect of reduced control authority, both in symmetric spoiler travel and thrust level, on the effectiveness of a decoupled longitudinal control system was examined during the approach and landing of the NASA terminal configured vehicle (TCV) aft flight deck simulator in the presence of wind shear. The evaluation was conducted in a fixed-base simulator that represented the TCV aft cockpit. There were no statistically significant effects of reduced spoiler and thrust authority on pilot performance during approach and landing. Increased wind severity degraded approach and landing performance by an amount that was often significant. However, every attempted landing was completed safely regardless of the wind severity. There were statistically significant differences in performance between subjects, but the differences were generally restricted to the control wheel and control-column activity during the approach.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-83188 , L-14652
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Simulator study of the effect of control-system time delays on the occurrence of pilot-induced oscillations and on pilot tracking performance with a space-shuttle-orbiter configuration (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Using a six degree-of-freedom motion-base simulator, the effect of control-system time delays on the occurrence of pilot-induced oscillations (PIO's) on the vehicle handling qualities and on pilot tracking performance for a landing-approach configuration of the Space Shuttle orbiter was studied. A linearized math model was employed which represented a 300-knot orbiter with almost all time delays removed. Additional time delays were then inserted following the pilot's hand-controller signals. Only pitch and roll commands were used for vehicle control. The simulation employed an air to air tracking task as a means of emphasizing PIO tendencies. Two astronauts, two research pilots, and one simulation engineer served as test subjects. Results showed that PIO's occurred when the amount of added time delay approximated that existing for the orbiter configuration flown in the approach and landing tests. Increasing the amount of delay increased PIO occurrences and resulted in degraded tracking performance. Decreasing the amount of time delay eliminated the PIO's.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1588 , L-13131
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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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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    NASA TECHNICAL REPORTS
  • 9
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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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    NASA TECHNICAL REPORTS
  • 10
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    Comparison of analytical predictions of longitudinal short period pilot-induced oscillations with results from a simulation study of the space shuttle orbiter (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An analytical analysis of conditions producing pilot induced oscillations (PIO's) was made for the space shuttle orbiter in a landing approach configuration for the task of milling the elevation angle of the line of sight to a target vehicle. The analysis yielded a value of PIO frequency and a value for the amount of total system time delay (pilot + control system) that can be tolerated before instability results. Calculations were performed showing the effect of varying the range to the target and of varying the handling qualities of the orbiter vehicle. Analytical predictions were compared with simulation results obtained using a visual motion simulator.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-83267 , L-14847 , NAS 1.15:83267
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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