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  • AIRCRAFT STABILITY AND CONTROL  (7)
  • NAVIGATION  (7)
  • MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT  (2)
  • 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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    A manual abort guidance technique with concentric-flight-plan rendezvous (1967)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Manual technique using optical device to abort manned lunar landing module in orbits compatible with concentric-flight-plan rendezvous
    Keywords: NAVIGATION
    Type: NASA-TN-D-4089
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    An analytical technique for the analysis of airplane spin entry and recovery (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The dynamic equations of motion for a spinning airplane are simplified to facilitate the analysis of spin entry and recovery maneuvers. Solutions of a nonlinear, first order equation for spin rate enable calculation of spin entry and recovery times and control required for recovery. The analysis is applied to a light airplane for which both aerodynamic data, rotory balance wind tunnel tests, and spin flight test data have been obtained. A comparison of predicted and actual transient spin responses is made which supports the validity of the analytical approach taken but which also illustrates the difficulty in obtaining accurate aerodynamic data for spinning airplanes. Certain normalized parameters of the reduced state spin equation suggest criteria for assessing the transient spin characteristics of light airplanes.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 82-0243 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A decoupled control system for improved flight performance in wind shear (1981)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A fixed-base simulation study has been made to compare the approach and landing performance of a decoupled longitudinal control system and the velocity-vector control-wheel steering (VCWS) system that currently exists on the NASA Terminal Configured Vehicle (TCV). The decoupled control system employed constant prefilter and feedback gains to provide steady-state decoupling of flight-path angle, pitch angle, and forward velocity using symmetric spoilers, throttle, and elevator as active control elements. In severe wind shear, of the Kennedy-type, the decoupled control system improved both approach performance and touchdown performance even when the spoiler deflection was limited to 16 deg. On a 10-point rating scale, three research pilots rated the approach and landing task with decoupled controls as much as 3 to 4 increments better than the use of the VCWS system in severe winds
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: In: Joint Automatic Control Conference; Jun 17, 1981 - Jun 19, 1981; Charlottesville, VA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Study of an aircraft decoupled longitudinal control system for approach and landing (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A series of ground-based and in-flight simulation studies of the application of steady-state decoupled longitudinal controls to a short take-off and landing (STOL) transport have been made. The externally blown flap STOL was selected for study because it was considered to be a worst-case situation from the control viewpoint. The decoupled longitudinal control system used constant prefilter and feedback gains to provide independent control of flight-path angle, pitch angle, and forward velocity during landing approach. The decoupled controls were compared to a more conventional stability augmentation system. The pilots were enthusiastic about the decoupled controls; the pilot workload was reduced and the landing performance significantly improved. The benefit of the decoupled controls was more dramatic during in-flight simulation using a variable stability airplane than was the case with either fixed- or moving-base, ground-based simulators.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Atmospheric Flight Mechanics Conference; Jun 07, 1976 - Jun 09, 1976; Arlington, TX
    Format: text
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    NASA TECHNICAL REPORTS
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