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US 12,179,907 B1Granted
Electrically driven blade control for rotorcraft
AssigneeOrbital Research Inc.
InventorsMatthew C. Birch, Zak Sowle
Life of this patent
Estimating the term…
Abstract
Multiple redundant harmonic drive motors on a rotor head actuate the angle of attack of rotor blades at the rotor blade roots, providing collective control that, in combination with a system for providing cyclic control on the rotor blades, eliminates the need for a swashplate, thereby advantageously reducing the weight and maintenance cost of a helicopter, increasing its reliability, and reducing its vulnerability to ballistic attack.
Claims20
An unmanned aerial vehicle (UAV) or rotorcraft comprising:
- at least one electrically-driven actuator comprising at least one electric motor;
- at least one rotor blade;
- at least one torque-limiting coupling;
- at least one zero-backlash transmission configured to communicate torque from the at least one electrically-driven actuator to the at least one rotor blade to change the at least one rotor blade's angle of attack with respect to a rotor head;
- and
- a mechanical disconnection mechanism configured for disconnecting at least one of the at least one electric motor, the at least one torque-limiting coupling, and/or the at least one zero-backlash transmission from the rotor head so as to not supply torque or friction.
3 more elements
An unmanned aerial vehicle (UAV) or rotorcraft comprising:
- at least one electrically-driven actuator comprising at least one electric motor;
- at least one rotor blade;
- at least one torque-limiting coupling;
- at least one mechanical transmission configured to communicate torque from the at least one electrically-driven actuator to the at least one rotor blade producing an angular displacement of the at least one rotor blade about the at least one rotor blade's longitudinal axis that is limited to an angular displacement range;
- and
- a mechanical disconnection mechanism configured for disconnecting at least one of the motor, coupling, and/or transmission from a rotor head so as to not supply torque or friction,
- wherein the at least one mechanical transmission has an amount of backlash that is less than 0.5% of the angular displacement range of the at least one rotor blade.
4 more elements
An unmanned aerial vehicle (UAV) or rotorcraft comprising:
- at least one electrically-driven actuator comprising at least one electric motor,
- at least one rotor blade;
- at least one torque-limiting coupling,
- at least one zero-backlash transmission configured to communicate torque from the electrically-driven actuator to the at least one rotor blade to change the at least one rotor blade's angle of attack with respect to a rotor head;
- and
- a mechanical disconnection mechanism configured for disconnecting at least one of the motor, coupling, and/or transmission from the rotor head so as to not supply torque or friction,
- wherein the actuator is configured to be mounted to and rotate along with the helicopter or rotorcraft rotor head, and can be modularly replaced without the disconnection of any rotor blade from the rotor head.
4 more elements
Dependencies are inferred from the claim text.