The NASAlArmy Rotorcralt Aircrew Systems Concepts Airborne Laboratory (RASCAL) UHdOA Black Hawk helicopter was used to test the feasibility of using operational techniques to alleviate helicopter noise during approach to landing. Decelerating approaches were flown using multi-segment glidepaths. The approaches were designed to avoid flight conditions known to generate noise due to blade-vortex-interaction (BVI). A Local Dilferential Global Positioning System (LDGPS) was used for precision navigation, and guidance calculations were performed in an on-board computer. Steering commands were presented to the pilot using the existing electromechanical flight instruments olthe UH-60A. Operational aspects of the noise abatement approaches mere evaluated by pilots from NASA, FAA, and the helicopter industry. The methodology used to design the noise abatement trajectories is described, and navigation system and flight technical error data are reported.
A sequence of ground-and flight-simulation experiments was conducled at the Ames Research Center as part of a joint NASA/FAA program to investiyate helicopter instrument-flieht-rules (IFR) airworthiness criteria. This paper describes the first six of these experiments and summarizes major results. Five of the experiments were conducled a n large-amplitude motion base simulators at Ames Research Center; the NASA-Army V/STOLAND UH-IH variable-stability helicopter was used in the flight experiment. Among the results shown for instrument operations are a requirement for some level of artificial stability and control, the adequacy of neutral longitudinal control position gradients, a limited advantage of including flight directors in the display, and the necessity for pitch and roll altitude stabilization to achieve ratings of satisfactory for the approach tasks considered.
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