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  • 1
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    A Method for Measuring the Effective Throughput Time Delay in Simulated Displays Involving Manual Control (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The advent and widespread use of the computer-generated image (CGI) device to simulate visual cues has a mixed impact on the realism and fidelity of flight simulators. On the plus side, CGIs provide greater flexibility in scene content than terrain boards and closed circuit television based visual systems, and they have the potential for a greater field of view. However, on the minus side, CGIs introduce into the visual simulation relatively long time delays. In many CGIs, this delay is as much as 200 ms, which is comparable to the inherent delay time of the pilot. Because most GCIs use multiloop processing and smoothing algorithms and are linked to a multiloop host computer, it is seldom possible to identify a unique throughput time delay, and it is therefore difficult to quantify the performance of the closed loop pilot simulator system relative to the real world task. A method to address these issues using the critical task tester is described. Some empirical results from applying the method are presented, and a novel technique for improving the performance of GCIs is discussed.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA. Ames Research Center 20th Ann. Conf. on Manual Control, Vol. 1; p 173-184
    Format: application/pdf
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  • 2
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    Assessment of simulation fidelity using measurements of piloting technique in flight (1984)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: The U.S. Army and NASA joined together on a project to conduct a systematic investigation and validation of a ground based piloted simulation of the Army/Sikorsky UH-60A helicopter. Flight testing was an integral part of the validation effort. Nap-of-the-Earth (NOE) piloting tasks which were investigated included the bob-up, the hover turn, the dash/quickstop, the sidestep, the dolphin, and the slalom. Results from the simulation indicate that the pilot's NOE task performance in the simulator is noticeably and quantifiably degraded when compared with the task performance results generated in flight test. The results of the flight test and ground based simulation experiments support a unique rationale for the assessment of simulation fidelity: flight simulation fidelity should be judged quantitatively by measuring pilot's control strategy and technique as induced by the simulator. A quantitative comparison is offered between the piloting technique observed in a flight simulator and that observed in flight test for the same tasks performed by the same pilots.
    Keywords: RESEARCH AND SUPPORT FACILITIES (AIR)
    Type: AGARD Helicopter Guidance and Control Systems for Battlefield Support; 12 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Assessment of simulation fidelity using measurements of piloting technique in flight. II (1985)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Two components of the Vertical Motion Simulator (presently being used to assess the fidelity of UH-60A simulation) are evaluated: (1) the dash/quickstop Nap-of-the-earth (NOE) piloting task, and (2) the bop-up task. Data from these two flight test experiments are presented which provide information on the effect of reduced visual field of view, variation in scene content and texture, and the affect of pure time delay in the closed-loop pilot response. In comparison with task performance results obtained in flight tests, the results from the simulation indicate that the pilot's NOE task performance in the simulator is significantly degraded.
    Keywords: BEHAVIORAL SCIENCES
    Format: text
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  • 4
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    Training aircraft design considerations based on the successive organization of perception in manual control (1982)
    In:  Other Sources
    Details
    Publication Date: 2016-06-07
    Description: The thesis that pilot skill development in the Navy approach and landing task is very strongly tied to the aircraft closure rate and, therefore, that pilot training for this task should be based on an appropriate progression closure rate is considered. A rational and explicit determination of design point approach speeds as well as other important aerodynamic features for training aircraft is also considered. Two keys are discussed: recognition of the significance of transitioning from a purely compensatory control loop technique to one involving a pursuit crossfeed between throttle and pitch attitude, and addressing the terminal flight path adjustment in terms of range-to-go.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA. Ames Research Center 16th Ann. Conf. on Manual Control; p 119-126
    Format: text
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  • 5
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    Mission-oriented requirements for updating MIL-H-8501. Volume 1: STI proposed structure (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The structure of a new flying and ground handling qualities specification for military rotorcraft is presented. This preliminary specification structure is intended to evolve into a replacement for specification MIL-H-8501A. The new structure is designed to accommodate a variety of rotorcraft types, mission flight phases, flight envelopes, and flight environmental characteristics and to provide criteria for three levels of flying qualities, a systematic treatment of failures and reliability, both conventional and multiaxis controllers, and external vision aids which may also incorporate synthetic display content. Existing and new criteria were incorporated into the new structure wherever they could be substantiated.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-CR-177331-VOL-1 , NAS 1.26:177331-VOL-1 , USAAVSCOM-TR-84-A-6-VOL-1 , STI-TR-1194-1-1
    Format: application/pdf
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  • 6
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    Manual and automatic control of surface effect ships (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A recent investigation of crew performance in the motion environment of a large generic high speed surface effect ship by means of a motion base simulation addressed some of the helmsman's control task with an external forward visual field of the seascape and navigation and steering displays in the pilot house. In addition to the primary steering control task, a subcritical speed tracking task provided a secondary surrogate for trimming the water speed of the craft. The results of helsmen's steering describing function measurements are presented, and some suggestions for their interpretation are offered. The likely steering loop closures comprise heading and lateral displacement for the course keeping task investigated. Also discussed is the manner in which these loop closures were implemented for automatic steering of the surface effect ship. Regardless of the influence of workload, steering technique, water speed and sea state, the helmsmen apparently adopted a disturbance regulation bandwidth of about 0.2 rad/sec for lateral displacement.
    Keywords: MAN/SYSTEM TECHNOLOGY AND LIFE SUPPORT
    Type: NASA. Ames Res. Center 11th Ann. Conf. on Manual Control; p 693-710
    Format: text
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  • 7
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    A theory of human error (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Human error, a significant contributing factor in a very high proportion of civil transport, general aviation, and rotorcraft accidents is investigated. Correction of the sources of human error requires that one attempt to reconstruct underlying and contributing causes of error from the circumstantial causes cited in official investigative reports. A validated analytical theory of the input-output behavior of human operators involving manual control, communication, supervisory, and monitoring tasks which are relevant to aviation operations is presented. This theory of behavior, both appropriate and inappropriate, provides an insightful basis for investigating, classifying, and quantifying the needed cause-effect relationships governing propagation of human error.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166313 , NAS 1.26:166313 , STI-TR-1156-1
    Format: application/pdf
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  • 8
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    Functional requirements for the man-vehicle systems research facility (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The NASA Ames Research Center proposed a man-vehicle systems research facility to support flight simulation studies which are needed for identifying and correcting the sources of human error associated with current and future air carrier operations. The organization of research facility is reviewed and functional requirements and related priorities for the facility are recommended based on a review of potentially critical operational scenarios. Requirements are included for the experimenter's simulation control and data acquisition functions, as well as for the visual field, motion, sound, computation, crew station, and intercommunications subsystems. The related issues of functional fidelity and level of simulation are addressed, and specific criteria for quantitative assessment of various aspects of fidelity are offered. Recommendations for facility integration, checkout, and staffing are included.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166315 , NAS 1.26:166315 , TR-1156-3
    Format: application/pdf
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  • 9
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    Technical approaches for measurement of human errors (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Human error is a significant contributing factor in a very high proportion of civil transport, general aviation, and rotorcraft accidents. The technical details of a variety of proven approaches for the measurement of human errors in the context of the national airspace system are presented. Unobtrusive measurements suitable for cockpit operations and procedures in part of full mission simulation are emphasized. Procedure, system performance, and human operator centered measurements are discussed as they apply to the manual control, communication, supervisory, and monitoring tasks which are relevant to aviation operations.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-166314 , NAS 1.26:166314 , STI-TR-1156-2
    Format: application/pdf
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  • 10
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    Vehicle design considerations for active control application to subsonic transport aircraft (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The state of the art in active control technology is summarized. How current design criteria and airworthiness regulations might restrict application of this emerging technology to subsonic CTOL transports of the 1980's are discussed. Facets of active control technology considered are: (1) augmentation of relaxed inherent stability; (2) center-of-gravity control; (3) ride quality control; (4) load control; (5) flutter control; (6) envelope limiting, and (7) pilot interface with the control system. A summary and appraisal of the current state of the art, design criteria, and recommended practices, as well as a projection of the risk in applying each of these facets of active control technology is given. A summary of pertinent literature and technical expansions is included.
    Keywords: AIRCRAFT
    Type: NASA-CR-2408 , TR-2037-1
    Format: application/pdf
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