Design, Fabrication, and Flight Test of the Active Arm External Load Stabilization System for Cargo Handling Helicopters
Final technical rept.
BOEING VERTOL CO PHILADELPHIA PA
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The report discusses the analysis, design, fabrication, and flight test of an experimental active arm external load stabilization system. The purpose of this effort was to achieve the load damping required for helicopter instrument flight rules operations load modal damping ratio greater than 0.25 without imposing excessive power requirements on the helicopter subsystems or unsafe conditions on the helicopter. Flight test of the system on the Boeing Model 347 helicopter demonstrated adequate load dynamic stability characteristics and elimination of pilot-induced oscillation throughout the test flight envelope.