Active counterweight for main rotor
An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.
1. A rotorcraft, comprising:
a power train comprising an engine coupled to a gearbox;
a main rotor blade having a mast coupled to the power train;
a control input linkage in communication between a pilot input device and the main rotor blade, the control input linkage configured to communicate a control input force from the pilot input device to the main rotor blade; and
a counterweight system connected to an output shaft of the gearbox and in connection with the control input linkage and the power train, the counterweight system configured to apply a centrifugal force to the control input linkage.
2. The rotorcraft of claim 1 , wherein the output shaft rotating at a greater speed than the main rotor blade.
3. The rotorcraft of claim 1 , wherein the output shaft is generally orthogonal to the mast.
4. The rotorcraft of claim 3 , wherein the output shaft rotates at a higher speed than the mast.
5. The rotorcraft of claim 1 , wherein the control input linkage is in communication with the main rotor blade to change a pitch of the main rotor blade in response to the control input force.
6. The rotorcraft of claim 1 , wherein the pilot input device is a collective.
7. The rotorcraft of claim 1 , further comprising a hydraulic boost actuator in connection with the control input linkage.
8. The rotorcraft of claim 1 , wherein the counterweight system comprises a beam having a central pivot and weights located on opposite ends;
the beam is attached to the output shaft of the gearbox such that the beam and the central pivot rotate with the output shaft, wherein the central pivot is orthogonal to the output shaft; and
the control input linkage is connected to the beam.
9. The rotorcraft of claim 8 , wherein the output shaft is oriented generally orthogonal to the mast.
10. The rotorcraft of claim 8 , further comprising a swashplate connected between the control input linkage and the main rotor blade, wherein the swashplate is located between the main rotor blade and the counterweight system.
11. The rotorcraft of claim 10 , wherein the output shaft is oriented generally orthogonal to the mast.
12. The rotorcraft of claim 8 , further comprising a hydraulic boost actuator in connection with the control input linkage.
13. The rotorcraft of claim 8 , further comprising a hydraulic boost actuator in connection with the control input linkage; and
a swashplate connected between the control input linkage and the main rotor blade, wherein the swashplate is located between the main rotor blade and the counterweight system.
14. A rotorcraft comprising:
a power train comprising an engine coupled to a gearbox;
a main rotor blade having a mast coupled to the power train;
a control input linkage in communication between a pilot input device and the main rotor blade, the control input linkage configured to communicate a control input force from the pilot input device to the main rotor blade;
a swashplate connected between the control input linkage and the main rotor blade; and
a counterweight system in connection with the control input linkage and the power train, the counterweight system configured to apply a centrifugal force to the control input linkage.
15. The rotorcraft of claim 14 , wherein the swashplate is located between the main rotor blade and the counterweight system.
16. A method of controlling rotorcraft flight, comprising:
receiving at a swash plate a control input force from a pilot input device via an input linkage; and
applying a centrifugal force produced by a counterweight system to the input linkage to boost the control input force.
17. The method of claim 16 , further comprising changing a pitch angle of a rotor blade in response to receiving the boosted control input force.
18. The method of claim 16 , wherein the applying the centrifugal force comprises rotating the counterweight system at a greater speed than a rotor blade; and
further comprising changing a pitch angle of the rotor blade in response to receiving the boosted control input force.
19. The method of claim 18 , wherein the rotor blade is connected to a mast and the counterweight system is rotated about an axis, wherein the axis is generally orthogonal to the mast.