Actuation system for an active rotor control system

• US 6,200,096 B1
• Filed: 04/16/1999
• Issued: 03/13/2001
• Est. Priority Date: 04/16/1999
• Status: Expired due to Fees

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Kohlhepp, Fred W.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, NINH H
• Application Number:
  US09/293,428
• Time in Patent Office: 697 Days
• Field of Search: 416/23, 416/24, 416/158, 92/34, 92/39, 92/92
• US Class Current: 416/24
• CPC Class Codes: B64C 2027/7272 of the electro-hydraulic type
• CPC Class Codes: B64C 27/001 Vibration damping devices
• CPC Class Codes: B64C 27/615 including flaps mounted on blades
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

A flap actuation system for a helicopter rotor blade. The rotor blade includes a root end, a tip end, a trailing edge and a flap hinged to at least a portion of the trailing edge about a pivot axis. The flap actuation system includes at least one supply line mounted within the rotor blade and extending outward from the root end. The supply line is adapted to channel pressurized fluid. At least one actuator fluidly connected to the supply line. The actuator includes a displacement member and a head member. The head member is engaged with the flap and is adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the supply line. In one embodiment of the invention there are two supply lines, each extending outward from the root end and is adapted to channel pressurized fluid. There is at least one actuator fluidly connected to each supply line. The actuator on one of the supply lines is adapted to pivot the flap upward when pressurized, and the actuator on the other supply line is adapted to pivot the flap downward when pressurized.

Claims

1. A flap actuation system for a helicopter rotor blade, the rotor blade having a root end, a tip end, a trailing edge and a flap hinged to at least a portion of the trailing edge, the flap being pivotable about a pivot axis, the flap actuation system comprising:

at least one supply line mounted within the rotor blade and extending outward from the root end, the supply line adapted to channel pressurized fluid;

a valve attached to the at least one supply line for controlling a flow of fluid along the supply line;

a controller adapted to receive signals indicative of the current state of the flap, the controller providing a signal to the valve for controlling the operational state of the valve; and

at least one actuator fluidly connected to the at least one supply line, the actuator having a displacement member and a head member, the head member being engaged with the flap and adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the at least one supply line.

2. A flap actuation system according to claim 1 wherein the displacement member is a bellows which extends outward when supplied with pressurized fluid, and wherein the head member is engaged with the bellows such that extension of the bellows translates the head member in a prescribed direction.

3. A flap actuation system for a helicopter rotor blade, the rotor blade having a root end, a tip end, a trailing edge and a flap hinged to at least a portion of the trailing edge, the flap being pivotable about a pivot axis the flap actuation system comprising:

two supply lines mounted within the rotor blade, each extending outward from the root end and adapted to channel pressurized fluid; and

at least one actuator fluidly connected to each supply line, the actuator having a displacement member and a head member, the head member being engaged with the flap and adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the associated supply line, and wherein the at least one actuator on one of the supply lines is adapted to pivot the flap upward when pressurized, and the actuator on the other supply line is adapted to pivot the flap downward when pressurized.

4. A flap actuation system according to claim 3 wherein when the first supply line is pressurized, the second supply line is depressurized.

5. A rotor blade for a helicopter comprising:

a root end;

a tip end;

a trailing edge;

a flap hinged to at least a portion of the trailing edge, the flap being pivotable about a pivot axis;

a flap actuation system for pivoting the flap about its pivot axis, the flap actuation system including

at least one supply line mounted within the rotor blade and extending outward from the root end, the supply line adapted to channel pressurized fluid;

at least one actuator fluidly connected to the at least one supply line, the actuator having a displacement member and a head member, the head member being engaged with the flap and adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the at least one supply line; and

a valve attached to the at least one supply line for controlling a flow of fluid along the supply line, the valve being controlled by a controller that receives signals regarding the current operational state of the flap.

7. A rotor blade according to claim 5 wherein the at least one fluid supply line is engaged with a hydraulic fluid supply which channels pressurized hydraulic fluid to the supply line.

8. A rotor blade according to claim 5 wherein the displacement member is a bellows which extends outward when supplied with pressurized fluid, and wherein the head member is engaged with the bellows such that extension of the bellows translates the head member in a prescribed direction.

9. A rotor blade according to claim 5 wherein there are two supply lines mounted within the rotor blade, each extending outward from the root end and adapted to channel pressurized fluid, wherein there is at least one actuator fluidly connected to each supply line, the actuator having a displacement member and a head member, the head member being engaged with the flap and adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the associated supply line, and wherein the at least one actuator on one of the supply lines is adapted to pivot the flap upward when pressurized, and the actuator on the other supply line is adapted to pivot the flap downward when pressurized.

10. A rotor blade according to claim 9 wherein when the first supply line is pressurized, the second supply line is depressurized.

6. A rotor blade for a helicopter comprising:

a root end;

a tip end;

a trailing edge;

a flap hinged to at least a portion of the trailing edge, the flap being pivotable about a pivot axis;

wherein the flap is hinged to the trailing edge through a flexible hinge;

a flap actuation system for pivoting the flap about its pivot axis, the flap actuation system including

at least one supply line mounted within the rotor blade and extending outward from the root end, the supply line adapted to channel pressurized fluid; and

least one actuator fluidly connected to the at least one supply line, the actuator having a displacement member and a head member, the head member being engaged with the flap and adapted to pivot the flap about its pivot axis when pressurized fluid is conveyed through the at least one supply line.

11. A flap actuation system for a helicopter rotor blade, the rotor blade having a root end, a tip end, a trailing edge and a flap hinged to at least a portion of the trailing edge, the flap being pivotable about a pivot axis, the flap actuation system comprising:

a first supply line mounted within the rotor blade and extending outward from the root end, the first supply line adapted to channel pressurized hydraulic;

a first set of actuators fluidly connected to the first supply line, the actuators having a displacement member and a head member, the head member being engaged with the flap and adapted to pivot the flap about its pivot axis so that the flap angles upward when pressurized hydraulic fluid is channeled along the first supply line;

a second supply line mounted within the rotor blade and extending outward from the root end, the second supply line adapted to channel pressurized hydraulic; and

a second set of actuators fluidly connected to the second supply line, the actuators having a displacement member and a head member, the head member being engaged with the flap and adapted to pivot the flap about its pivot axis so that the flap angles downward when pressurized hydraulic fluid is channeled along the second supply line.