PARAMETRIC ANALYSIS AND PRELIMINARY DESIGN OF A SHAFT-DRIVEN ROTOR SYSTEM FOR A HEAVY LIFT HELICOPTER
Final rept., 15 Oct 1965-15 Oct 1966
UNITED TECHNOLOGIES CORP STRATFORD CT SIKORSKY AIRCRAFT DIV
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The primary objective of the program was to select and design a shaft-driven lifting rotor system for a heavy lift helicopter. The selection included a complete parametric analysis of the aircraft, based on three defined missions lifting a 20-ton payload 20 nautical miles, lifting a 12-ton payload 100 nautical miles, and ferrying. Several aircraft configurations were studied, and a single rotor crane arrangement was selected. Included in the study were selection of engines and parametric sizing of all major aircraft component systems. The aircraft defined has a takeoff gross weight for the 20-ton mission of approximately 79,000 pounds, and uses a single lifting rotor 91.6 feet in diameter. Ferry range exceeds 2400 nautical miles. While differing in detail from any existing hardware, the rotor system design follows directly from present practice. Analyses of aircraft stability and control characteristics and rotor system stability for the selected configuration were performed, and the methods and results reported. For all of the properties studied, both the aircraft and the rotor system were shown to meet or exceed the requirements of applicable specifications andor accepted practice.