System and method for magnetically and aerodynamically optimized control of rotorhead
A rotorcraft having an operational range and a plurality of rotor blades, each rotor blade capable of assuming an angular pitch, utilizes a control apparatus a mechanism for independently controlling an angular pitch value of each of the plurality of rotor blades wherein a collective sum of the angular pitch values of the plurality of rotor blades is not constant over the operational range of the rotorcraft.
1. In a rotorcraft having an operational range and a plurality of rotor blades, each rotor blade capable of assuming an angular pitch, a control apparatus comprising:
a mechanism for independently controlling an angular pitch value of each of the plurality of rotor blades;
wherein a collective sum of the angular pitch values of the plurality of rotor blades is not constant over the operational range of the rotorcraft.
2. In a rotorcraft having a rotor blade secured to a rotor hub, a control apparatus disposed at a rotor end of the rotor blade, the control apparatus comprising:
a motor having a rotatable shaft extending therefrom;
a shaft array of permanent magnets disposed about a free end of the rotatable shaft;
a stationary array of permanent magnets disposed about the shaft array;
a ring disposed intermediate the shaft array and the stationary array for selectively passing an electromagnetic field generated by the shaft array to the stationary array; and
a rotating stator array disposed about the stationary array.
3. The rotorcraft of claim 2 without a swashplate.
4. The rotorcraft of claim 2 without direct or indirect mechanical linkages between rotor blades.