Independent hydraulic control system for rotorcraft secondary rotor

Patent metadata

Field	Value
Publication number	US-9815553-B2
Application number	US-201313932407-A
Country	US
Kind code	B2
Filing date	Jul 1, 2013
Priority date	Jul 1, 2013
Publication date	Nov 14, 2017
Grant date	Nov 14, 2017

Abstract

According to some embodiments, a rotorcraft includes a secondary rotor control system located proximate to the empennage of the rotorcraft. The secondary rotor control system includes at least one hydraulic pump and at least one hydraulic actuator. The at least one hydraulic pump is located proximate to the empennage. The at least one hydraulic actuator is located proximate to the empennage and configured to adjust at least one operating characteristic of the at least one secondary rotor blade.

First claim

What is claimed is:

1. A rotorcraft, comprising:
a body comprising a fuselage and an empennage;
a power train coupled to the body and comprising a power source;
a main rotor system in mechanical communication with the power train and located proximate to the fuselage, the main rotor system comprising a main rotor gear box and at least one main rotor blade in mechanical communication with the main rotor gear box;
a secondary rotor system in mechanical communication with the power train and located proximate to the empennage, the secondary rotor system comprising a secondary rotor gear box and at least one secondary rotor blade in mechanical communication with the secondary rotor gear box;
a main rotor control system located proximate to the fuselage and comprising:
at least one hydraulic pump located proximate to the fuselage; and
at least one hydraulic actuator located proximate to the fuselage and configured to adjust at least one operating characteristic of the at least one main rotor blade; and

a secondary rotor control system located proximate to the empennage and comprising:
at least one hydraulic pump located proximate to the empennage; and
at least one hydraulic actuator located proximate to the empennage and configured to adjust at least one operating characteristic of the at least one secondary rotor blade;

wherein the secondary rotor control system is in fluid communication with the secondary rotor gear-box such that the secondary rotor gear box provides hydraulic fluid to the secondary rotor control system.

2. The rotorcraft of claim 1 , wherein the secondary rotor system comprises an anti-torque rotor system.

3. The rotorcraft of claim 1 , wherein the main rotor control system is not in fluid communication with the secondary rotor control system.

4. The rotorcraft of claim 1 , wherein an operating fluid pressure of the main rotor control system is higher than an operating fluid pressure of the secondary rotor control system.

5. The rotorcraft of claim 1 , wherein the at least one hydraulic actuator of the secondary rotor control system is configured to adjust at least one operating characteristic of the at least one secondary rotor blade by adjusting a pitch angle of the at least one secondary rotor blade.

6. The rotorcraft of claim 1 , further comprising at least one drive shaft extending from the secondary rotor system located proximate to the empennage to the main rotor system located proximate to the fuselage.

7. The rotorcraft of claim 6 , wherein the at least one drive shaft mechanically couples the main rotor gear box and the secondary rotor gear box.

8. The rotorcraft of claim 1 , wherein the secondary rotor control system is not in fluid communication with any components located in the fuselage.

9. A method, comprising:
providing a rotorcraft, comprising:
a body comprising a fuselage and an empennage;
a power train coupled to the body and comprising a power source;
a main rotor system in mechanical communication with the power train and located proximate to the fuselage, the main rotor system comprising a main rotor gear box and at least one main rotor blade in mechanical communication with the main rotor gear box;
a secondary rotor system in mechanical communication with the power train and located proximate to the empennage, the secondary rotor system comprising a secondary rotor gear box and at least one secondary rotor blade in mechanical communication with the secondary rotor gear box;
a main rotor control system located proximate to the fuselage and comprising:
at least one hydraulic pump located proximate to the fuselage; and
at least one hydraulic actuator located proximate to the fuselage; and

a secondary rotor control system located proximate to the empennage and comprising:
at least one hydraulic pump located proximate to the empennage and operable to provide a flow of hydraulic fluid;
at least one hydraulic actuator located proximate to the empennage configured to receive the provided flow of fluid and adjust an operating characteristic of the at least one secondary rotor blade based on the provided flow of hydraulic fluid, wherein the secondary rotor control system is in fluid communication with the secondary rotor gear box such that the secondary rotor gear box provides the flow of hydraulic fluid to the secondary rotor control system;

receiving an instruction to adjust the operating characteristic of the at least one secondary rotor blade of the secondary rotor system; and
changing, based on the received instruction, at least one aspect of the provided flow of fluid such that the at least one hydraulic actuator adjusts the operating characteristic of the at least one secondary rotor blade.

10. The method of claim 9 , wherein receiving the instruction comprises receiving the instruction in the form of an electrical signal.

11. The method of claim 9 , wherein receiving the instruction comprises receiving the instruction in the foal′ of a mechanical input.

12. The method of claim 9 , wherein the secondary rotor system comprises an anti-torque rotor system.

13. The method of claim 9 , wherein the main rotor control system is not in fluid communication with the secondary rotor control system.

14. The method of claim 9 , wherein an operating fluid pressure of the main rotor control system is higher than an operating fluid pressure of the secondary rotor control system.

15. The method of claim 9 , wherein the at least one hydraulic actuator of the secondary rotor control system is configured to adjust at least one operating characteristic of the at least one secondary rotor blade by adjusting a pitch angle of the at least one secondary rotor blade.

Assignees

• Bell Helicopter Textron Inc
• Bell Helicopter Tectron Inc

Inventors

• Mccollough James M
• Fenny Carlos A

Classifications

• B64C27/64

  using fluid pressure, e.g. having fluid power amplification · CPC title

• B64C27/54

  Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement · CPC title

• B64C27/78 Primary

  in association with pitch adjustment of blades of anti-torque rotor · CPC title

• B64C27/82

  characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft · CPC title