Really Rigid Rotor

[Dave Jackson]

Based on the assumption that a rotor assembly can be built which is strong enough to have no coning angle and all flapping is handled by feathering: Can anyone suggest aerodynamic or structural reasons why this rotor will not function better than conventional coned rotors?

_______ Considerations for making a rigid rotor ______
 Helicopter has an intermeshing configuration and the load is divided between the 2 rotor assemblies.
 Load is also divided amongst 3 blades per rotor. The rigidity of the rotors should eliminate the 'self stropping' that the Kellett (3-blade intermeshing) experienced.
 Blades to be all composite (carbon) construction
 A high lift asymmetrical airfoil can be used because of the extreme rigidity of the rotor.
 A strong arm (cutout) between the mast and blade root, which can be the mast-to-mast distance.
 The airfoil profile can be thicker toward the root, for extra blade strength.
 Any tendency to cone, at average loading, can be offset by building a small amount of downward cone (anhedral) into the blades.
 Helicopter to utilize lightweight construction, to minimizing the rotor thrust requirements.
 Incorporated a static mast to transmit the moments directly to the fuselage.



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