Dave Jackson
19th Jan 2001, 23:44
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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Dave J Project: SynchroLite.com
_______ 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.
------------------
Dave J Project: SynchroLite.com