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Simulator Investigation of Pilot Aids for Helicopter Terminal Area Operations with One Engine InoperativeTwo recent piloted simulation experiments have investigated advanced display concepts applied to civil transport helicopter terminal area operations. Civil Category A helicopter operations apply to multi-engine helicopters wherein a safe recovery (land or fly out) is required in the event of a single engine failure. The investigation used the NASA Ames Research Center Vertical Motion Simulator, which has a full six degrees of freedom, to simulate the flight task as closely as possible. The goal of these experiments was to use advanced cockpit displays to improve flight safety and enhance the mission performance of Category A terminal area operations in confined areas. The first experiment investigated the use of military display formats to assist civil rotorcraft in performing a Category A takeoff in confined terminal areas. Specifically, it addressed how well a difficult hovering backup path could be followed using conventional instruments in comparison to panel mounted integrated displays. The hovering backup takeoff, which enables pilots to land back to the confined area pad in the event of an engine failure, was chosen since it is a difficult task to perform. Seven NASA and Army test pilots participated in the experiment. Evaluations, based on task performance and pilot workload, showed that an integrated display enabled the pilot to consistently achieve adequate or desired performance with reasonable pilot workload. Use of conventional instruments, however, frequently resulted in unacceptable performance (poor flight path tracking), higher pilot workload, and poor situational awareness. Although OEI landbacks were considered a visual task, the improved performance on the backup portion, in conjunction with increased situational awareness resulting from use of integrated displays, enabled the pilots to handle an engine failure and land back safely. In contrast, use of conventional instruments frequently led to excessive rates of sink at touchdown. A second simulation (in progress - July - August) is being conducted to investigate the use of advanced displays to perform vertical and short takeoffs and landings. One Engine Inoperative trajectories, which were optimized based on safety of flight restrictions, are utilized. Based on comments from the first experiment and further analytic development, appropriate fly out and approach guidance was added. Displays include conventional instruments with raw data, and the following integrated displays: multi-view and side-view hover displays based on the Apache Pilot Night Vision System, and variations of the pathway-in-the-sky displays with a flight-path-vector, a leader and flight director modifications. Panel mounted and head-up displays are being evaluated. Engine modifications have been incorporated to simulate 30 second and 2 minute contingency power ratings. Evaluations are based on task performance and pilot workload. NASA, Army, FAA, and industry test pilots participated. Details concerning the design, conduct, and the results of the experiment will be reported in the proposed paper.
Document ID
20020032306
Acquisition Source
Ames Research Center
Document Type
Conference Paper
Authors
Iseler, Laura
(NASA Ames Research Center Moffett Field, CA United States)
Chen, Robert
(NASA Ames Research Center Moffett Field, CA United States)
Dearing, Munro
(NASA Ames Research Center Moffett Field, CA United States)
Decker, William
(NASA Ames Research Center Moffett Field, CA United States)
Aiken, Edwin W.
Date Acquired
August 20, 2013
Publication Date
January 1, 1995
Subject Category
Man/System Technology And Life Support
Meeting Information
Meeting: AGARD Flight Vehicle Integration Panel Spring 1996 Symposium
Location: Ottawa
Country: Canada
Start Date: May 1, 1996
Sponsors: Advisory Group for Aerospace Research and Development
Funding Number(s)
PROJECT: RTOP 505-59-36
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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