Abstract
The CH-53A helicopter is approximately the same size but has four times the productivity of its predecessor, the H-37. It has an operational speed with pay load on a par with the existing world's records set by the MIL Mi-6, an aircraft twice the size. As such, it has demanded the application of many new design and analytical techniques. This paper outlines the general approach to the optimization and selection of the fundamental design parameters and discusses areas of particular interest, such as rotor system, airframe dynamic design and analysis, dynamic aspects of the airframe/powerplant marriage, and the need for inherent stability in high-speed helicopters. Looking ahead, the CH-53A program should advance the state of the art in such areas as I 1) the large scale use of titanium in dynamic components designed for fatigue considerations; 2) the efficient design of large asymmetrical airframes, with extensive cutouts, subjected to relatively low-frequency vibration excitation; 3) the operation of high solidity rotors at high disk loadings, advance ratios, and tip Mach numbers; and 4) stability, control, and failure reaction requirements of high-speed rotary wing aircraft.
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