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  • 1
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    Piloted Simulator Studies Pertaining to the Low-Speed Longitudinal Handling Qualities of a Supersonic Transport Airplane (1963)
    In:  CASI
    Details
    Publication Date: 2010-10-04
    Description: Piloted simulator studies of low-speed longitudinal handling qualities of supersonic transport aircraft
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: AIAA Simulation for Aerospace Flight Conference, A Volume of Technical Papaers Presented August 26-28, 1963, Columbus, Ohio; 35-43
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Simulator Investigations of the Problems of Flying a Swept-Wing Transport Aircraft in Heavy Turbulence (1965)
    In:  CASI
    Details
    Publication Date: 2004-12-03
    Description: An investigation of several factors which may contribute to the problem of piloting jet transport aircraft in heavy turbulence was conducted by using a piloted simulator that included the most significant airplane response and cockpit vibrations induced by rough air. Results indicated that the primary fuselage structural frequency contributed significantly to a distracting cockpit environment, and there was obtained evidence of severely reduced instrument flight proficiency during simulated maneuvering flight in heavy turbulence. It is concluded that the addition of similar rough-air response capabilities to training simulators would be of value in pilot indoctrination in turbulent-flight procedures.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA Conference on Aircraft Operating Problems: A Compilation of the Papers Presented; 137-148
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Part 1: Executive summary (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A workshop was convened by the FAA and NASA for the purpose of providing a forum at which leading designers, manufacturers, and users of helicopter simulators could initiate and participate in a development process that would facilitate the formulation of qualification standards by the regulatory agency. Formal papers were presented, special topics were discussed in breakout sessions, and a draft FAA advisory circular defining specifications for helicopter simulators was presented and discussed. A working group of volunteers was formed to work with the National Simulator Program Office to develop a final version of the circular. The workshop attracted 90 individuals from a constituency of simulator manufacturers, training organizations, the military, civil regulators, research scientists, and five foreign countries. A great amount of information was generated and recorded verbatim. This information is presented herein within the limits of accuracy inherent in recording, transcribing, and editing spoken technical material.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA(FAA Helicopter Simulator Workshop; p 1-11
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Evaluation of two cockpit display concepts for civil tiltrotor instrument operations on steep approaches (1993)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A piloted simulation experiment was conducted using the NASA Ames Research Center Vertical Motion Simulator to evaluate two cockpit display formats designed for manual control on steep instrument approaches for a civil transport tiltrotor aircraft. The first display included a four-cue (pitch, roll, power lever position, and nacelle angle movement prompt) flight director. The second display format provided instantaneous flight path angle information together with other symbols for terminal area guidance. Pilots evaluated these display formats for an instrument approach task which required a level flight conversion from airplane-mode flight to helicopter-mode flight while decelerating to the nominal approach airspeed. Pilots tracked glide slopes of 6, 9, 15 and 25 degrees, terminating in a hover for a vertical landing on a 150 feet square vertipad. Approaches were conducted with low visibility and ceilings and with crosswinds and turbulence, with all aircraft systems functioning normally and were carried through to a landing. Desired approach and tracking performance was achieved with generally satisfactory handling qualities using either display format on glide slopes up through 15 degrees. Evaluations with both display formats for a 25 degree glide slope revealed serious problems with glide slope tracking at low airspeeds in crosswinds and the loss of the intended landing spot from the cockpit field of view.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: Piloting Vertical Flight Aircraft: A Conference on Flying Qualities and Human Factors; p 433-452
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Application of data to piloted simulators (1987)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The application of a further developed analytical model and JAWS data to a piloted simulator is addressed. The Ames simulator provides a facility for the development of piloting procedures, and for the selection of training scenarios. The system is operational with the new wind shear models and comprehensive data output. The use of these models with the simulator is dicussed in detail.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: NASA. Langley Research Center Wind Shear(Turbulence Inputs to Flight Simulation and Systems Certification; p 97-115
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    A proposed definition for a pitch attitude target for the microburst escape maneuver (1990)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: The Windshear Training Aid promulgated by the Federal Aviation Administration (FAA) defines the practical recovery maneuver following a microburst encounter as application of maximum thrust accompanied by rotation to an aircraft-specific target pitch attitude. In search of a simple method of determining this target, appropriate to a variety of aircraft types, a computer simulation was used to explore the suitability of a pitch target equal in numerical value to that of the angle of attack associated with stall warning. For the configurations and critical microburst shears simulated, this pitch target was demonstrated to be close to optimum.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: NASA, Langley Research Center, Airborne Wind Shear Detection and Warning Systems. Second Combined Manufacturers' and Technologists' Conference, Part 1; p 105-121
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Visual and motion cueing in helicopter simulation (1986)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The visual cues presented in the simulator are compared with those of flight in an attempt to identify deficiencies. For the low-amplitude maneuvering tasks normally associated with the hover mode, the unique motion capabilities of the Vertical Motion Simulator (VMS) at Ames Research Center permit nearly a full representation of vehicle motion. Especially appreciated in these tasks are the vertical-acceleration responses to collective control. For larger-amplitude maneuvering, motion fidelity must suffer diminution through direct attenuation through high-pass filtering washout of the computer cockpit accelerations or both. Experiments were conducted in an attempt to determine the effects of these distortions on pilot performance of height-control tasks.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD Flight Simulation; 16 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Flight Calibration of Angle-of-attack and Sideslip Detectors on the Fuselage of a 35 Degree Swept-wing Fighter Airplane (1952)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-A52A04
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    A flight evaluation of the longitudinal stability characteristics associated with the pitch-up of a swept-wing airplane in maneuvering flight at transonic speeds (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-A51I12
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Schlieren Investigation of the Wing Shock-wave Boundary-layer Interaction in Flight (1951)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-RM-A51G09
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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