A new helicopter rotor concept, designed to reduce complexity and costs through the elimination of all hinges and bearings, has been under development for several years at United Aircraft. The ability to achieve a true bearingless rotor is made possible through the use of the unique
nonisotropic properties of fiber reinforced composite materials. Specifically, the low torsional stiffness of unidirectional composites allows the root section of a helicopter blade to be elastically twisted to achieve blade pitch control while maintaining the necessary bending stiffness.
This paper presents the results of preliminary studies conducted to evaluate the feasibility of this concept. Emphasis is placed on the fundamental design features and the characteristics of composite materials and how they relate to the control and operation of the rotor. Presented also are
results of composite material fatigue tests, wind tunnel tests of a dynamically scaled model rotor, analytical results of a full‐scale design, and an aeroelastic analysis evaluating the rotor dynamic stability characteristics.
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Document Type: Research Article
Aerodynamics Section, Fluid Dynamics Laboratory, United Aircraft Research Laboratories, East Hartford, Connecticut
Publication date: 1972-10-01
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