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  • 1
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    Flying NASA's Terminal Configured Vehicle against the Microwave Landing System (1979)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: A prototype Boeing 737 aircraft has been received for use in the Terminal Configured Vehicle (TCV) Program, the aim of which is to develop technology for advanced airborne systems and flight procedures to improve terminal area operations in the future ATC environment. The paper discusses the TCV aircraft, its integrated digital electronic displays and flight controls, and the means by which the pilot interfaces with the aircraft to fly precise curved descending approaches under MLS guidance.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Flying NASA's terminal configured vehicle against the microwave landing system (1979)
    In:  Other Sources
    Details
    Publication Date: 2011-08-17
    Description: Technology for advanced airborne systems and flight procedures to improve terminal-area operations in ATC environment is developed. The terminal configured vehicle (TCV) aircraft, its integrated digital electronic displays and flight controls, and how the pilot interfaces with the aircraft to fly precise curved descending approaches using Microwave Landing System (MLS) guidance are discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: SETP SETP Tech. Rev., Vol. 14, No. 2; p 110-123
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Piloted simulation study of the effects of an automated trim system on flight characteristics of a light twin-engine airplane with one engine inoperative (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A simulation study was conducted to investigate the piloting problems associated with failure of an engine on a generic light twin-engine airplane. A primary piloting problem for a light twin-engine airplane after an engine failure is maintaining precise control of the airplane in the presence of large steady control forces. To address this problem, a simulated automatic trim system which drives the trim tabs as an open-loop function of propeller slipstream measurements was developed. The simulated automatic trim system was found to greatly increase the controllability in asymmetric powered flight without having to resort to complex control laws or an irreversible control system. However, the trim-tab control rates needed to produce the dramatic increase in controllability may require special design consideration for automatic trim system failures. Limited measurements obtained in full-scale flight tests confirmed the fundamental validity of the proposed control law.
    Keywords: AERODYNAMICS
    Type: NASA-TP-2633 , L-16147 , NAS 1.60:2633
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Early flight test experience with Cockpit Displayed Traffic Information (CDTI) (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Coded symbology, based on the results of early human factors studies, was displayed on the electronic horizontal situation indicator and flight tested on an advanced research aircraft in order to subject the coded traffic symbology to a realistic flight environment and to assess its value by means of a direct comparison with simple, uncoded traffic symbology. The tests consisted of 28 curved, decelerating approaches, flown by research-pilot flight crews. The traffic scenarios involved both conflict-free and blunder situations. Subjective pilot commentary was obtained through the use of a questionnaire and extensive pilot debriefing sessions. The results of these debriefing sessions group conveniently under either of two categories: display factors or task performance. A major item under the display factor category was the problem of display clutter. The primary contributors to clutter were the use of large map-scale factors, the use of traffic data blocks, and the presentation of more than a few aircraft. In terms of task performance, the cockpit displayed traffic information was found to provide excellent overall situation awareness.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: NASA-TM-80221 , AVRADCOM-TR-80-B-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Flight investigation of cockpit-displayed traffic information utilizing coded symbology in an advanced operational environment (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Traffic symbology was encoded to provide additional information concerning the traffic, which was displayed on the pilot's electronic horizontal situation indicators (EHSI). A research airplane representing an advanced operational environment was used to assess the benefit of coded traffic symbology in a realistic work-load environment. Traffic scenarios, involving both conflict-free and conflict situations, were employed. Subjective pilot commentary was obtained through the use of a questionnaire and extensive pilot debriefings. These results grouped conveniently under two categories: display factors and task performance. A major item under the display factor category was the problem of display clutter. The primary contributors to clutter were the use of large map-scale factors, the use of traffic data blocks, and the presentation of more than a few airplanes. In terms of task performance, the cockpit-displayed traffic information was found to provide excellent overall situation awareness. Additionally, mile separation prescribed during these tests.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: NASA-TP-1684 , AVRADCOM-TR-80-B-4 , L-13584
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Ground-based and in-flight simulator studies of flight characteristics of a twin-fuselage passenger transport airplane during approach and landing (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Six-degree-of-freedom ground-based and in-flight simulator studies were conducted to evaluate the low-speed flight characteristics of a twin-fuselage passenger transport airplane and to compare these characteristics with those of a large, single-fuselage (reference) transport configuration similar to the Lockheed C-5A airplane. The primary piloting task was the approach and landing task. The results of this study indicated that the twin-fuselage transport concept had acceptable but unsatisfactory longitudinal and lateral-directional low-speed flight characteristics, and that stability and control augmentation would be required in order to improve the handling qualities. Through the use of rate-command/attitude-hold augmentation in the pitch and roll axes, and the use of several turn coordination features, the handling qualities of the simulated transport were improved appreciably. The in-flight test results showed excellent agreement with those of the six-degree-of-freedom ground-based simulator handling qualities tests. As a result of the in-flight simulation study, a roll-control-induced normal-acceleration criterion was developed. The handling qualities of the augmented twin-fuselage passenger transport airplane exhibited an improvement over the handling characteristics of the reference (single-fuselage) transport.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TP-2451 , L-15941 , NAS 1.60:2451
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Results of intravehicular manned cargo-transfer studies in simulated weightlessness (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A parametric investigation was conducted in a water immersion simulator to determine the effect of package mass, moment of inertia, and size on the ability of man to transfer cargo in simulated weightlessness. Results from this study indicate that packages with masses of at least 744 kg and moments of inertia of at least 386 kg-m2 can be manually handled and transferred satisfactorily under intravehicular conditions using either one- or two-rail motion aids. Data leading to the conclusions and discussions of test procedures and equipment are presented.
    Keywords: BIOTECHNOLOGY
    Type: NASA-TN-D-6774 , L-8099
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Flight investigation of manual and automatic VTOL decelerating instrument approaches and landings (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A flight investigation was undertaken to study the problems associated with manual and automatic control of steep, decelerating instrument approaches and landings under simulated instrument conditions. The study was conducted with a research helicopter equipped with a three-cue flight-director indicator. The scope of the investigation included variations in the flight-director control laws, glide-path angle, deceleration profile, and control response characteristics. Investigation of the automatic-control problem resulted in the first automated approach and landing to a predetermined spot ever accomplished with a helicopter. Although well-controlled approaches and landings could be performed manually with the flight-director concept, pilot comments indicated the need for a better display which would more effectively integrate command and situation information.
    Keywords: NAVIGATION
    Type: NASA-TN-D-7524 , L-9311
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Simulation and flight studies of an approach profile indicator for VTOL aircraft (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Simulation and flight investigations were conducted by using a method of providing supplementary information to the pilot in conjunction with a closed-circuit-television display during a VTOL instrument final approach including deceleration and hover. The supplementary information included range, cross range, ground speed, altitude, and rate-of-climb error and was displayed on an instrument called an approach profile indicator. The display was arranged to provide both quasi-command and situation information. Pilot comments indicated that the approach-profile-indicator display concept in conjunction with the closed-circuit television resulted in a decreased pilot workload and an increase in pilot confidence. Also, the results indicated that the approach profile repeatability was significantly improved because of the ground-speed and altitude information provided on the approach profile indicator.
    Keywords: AIRCRAFT INSTRUMENTATION
    Type: NASA-TN-D-8051 , L-10204
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Development and validation of a piloted simulation of a helicopter and external sling load (1979)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A generalized, real time, piloted, visual simulation of a single rotor helicopter, suspension system, and external load is described and validated for the full flight envelope of the U.S. Army CH-54 helicopter and cargo container as an example. The mathematical model described uses modified nonlinear classical rotor theory for both the main rotor and tail rotor, nonlinear fuselage aerodynamics, an elastic suspension system, nonlinear load aerodynamics, and a loadground contact model. The implementation of the mathematical model on a large digital computing system is described, and validation of the simulation is discussed. The mathematical model is validated by comparing measured flight data with simulated data, by comparing linearized system matrices, eigenvalues, and eigenvectors with manufacturers' data, and by the subjective comparison of handling characteristics by experienced pilots. A visual landing display system for use in simulation which generates the pilot's forward looking real world display was examined and a special head up, down looking load/landing zone display is described.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TP-1285 , L-11925
    Format: application/pdf
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