Swashplateless helicopter blade actuation system
AssigneeThe Boeing Company
InventorsFrank M. Rudley, Evhen M. Mychalowycz, Joseph R. Wagner, Jr., Edward J. Glembocki
Life of this patent
Estimating the term…
Abstract
A blade actuation system comprises at least one motor coupled to a rotor blade for changing the pitch angle of the rotor blade. The motor is configured to wirelessly communicate with at least one flight control computer to modulate the pitch angle. At least one generator may be mounted on a rotor shaft to generate power during rotation of the rotor shaft. The generator may provide power to the motor. The flight control computer is operative to provide control signals to at least one of the generators and motors for regulation thereof. The flight control computer, motor and generator may be configured to wirelessly communicate with one another.
Claims20
A blade actuation system, comprising:
- a rotor shaft;
- a rotor hub fixedly connectable to the rotor shaft;
- a plurality of rotor blades connectable to the rotor hub;
- at least one generator configured to rotate with the rotor shaft for generating power;
- a plurality of motors operatively coupled to the rotor blades, the motors being configured to receive power from the generator;
- and
- a plurality of flight control computers operative to provide control signals to the generator and motors for regulation thereof;
- wherein:
- the motors being responsive to the control signals for rotating the rotor blade in order to change a pitch angle thereof;
- the generator and the motors being communicatively coupled to each other and to each one of the flight control computers, the generator, the motors, and the flight control computers being configured to communicate data information to and from each other.
A helicopter, comprising:
- a rotor shaft;
- a rotor hub fixedly connectable to the rotor shaft;
- a plurality of rotor blades connectable to the rotor hub;
- a plurality of generators configured to rotate with the rotor shaft for generating power;
- a plurality of motors operatively coupled to the rotor blades, the motors being configured to receive power from the generators;
- and
- a plurality of flight control computers operative to provide control signals to the generators and motors for regulation thereof;
- wherein:
- the motors being responsive to the control signals for rotating the rotor blade in order to change a pitch angle thereof;
- the generator and motors being communicatively coupled to each other and to each one of the flight control computers, the generator, the motors, and the flight control computers being configured to communicate data information to and from each other.
A blade actuation system for effectuating changes in pitch angle of a rotor blade connected to a rotor hub, comprising:
- at least one generator mounted to the rotor hub and being configured to generate power during rotation of the rotor hub;
- and
- a plurality of motors mounted to the rotor blade and being configured to be powered by the generator for effectuating changes in the rotor blade pitch angle;
- a plurality of flight control computers configured to regulate the operation of the motors;
- the generator and motors being communicatively coupled to each other and to each one of the flight control computers, the generator, the motors, and the flight control computers being configured to communicate data information to and from each other.
A method of individual blade control of a rotor blade, comprising the steps of:
- coupling the rotor blade to a rotor hub mounted to a rotor shaft;
- providing at least one generator, a plurality of motors, and a plurality of flight control computers, the generators, the motors, and the flight control computers being configured to communicate data information to and from each other;
- actuating the motors;
- and
- changing a pitch angle of the rotor blade in response to actuation of the motors.
Dependencies are inferred from the claim text.