Simulation experiments demonstrated the ability of the pilot and copilot to fly a night mission at low altitudes, ranging from 50 to 150 feet AGL, in a CH-53D simulation with the night visionics equipment package described previously. Phases I and II HNVS simulation studies indicated that enroute flight profiles over the simulator's rolling terrain can be accomplished at airspeeds ranging from 60 to 80 knots with clearance altitudes averaging 100 feet. This study was conducted with a revised terrain model with improved altitude feedback cues that produced higher clearance altitudes and somewhat lower airspeeds than the prior simulations. The actual speeds and altitudes will be verified in the planned HNVS flight tests. The simulation confirmed the minimum system requirement of a gimballed FLIR with a navigation system and with ancillary hardware such as a symbol generator. Although this experiment required no data be generated on dead reckoning versus navigation system requirements, both pilot performance and opinion data reiterated the reduced crew station workload with Doppler command steering information. Incorporation of the navigation capability of the Control Display Unit also was instrumental in further reducing the navigation workload.
Helicopter Night Vision System Simulation Evaluation
1981
138 pages
Report
No indication
English
Human Factors Engineering , Infrared & Ultraviolet Detection , Helicopters , Night vision devices , Forward looking infrared systems , Helmet mounted displays , Display systems , Flight simulators , Terrain following , Models , Mission profiles , Performance(Human) , Pilots , Human factors engineering , Low altitude , High velocity , Flight paths , Airspeed , Data bases , Computer programming , Flight testing , Navigation , CH-53D aircraft , HNVS(Helicopter Night Vision System) , FLIR(Forward Looking Infrared Systems) , PMDS(Panel Mounted Displays) , Work loads
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