High torque actuation system for an active rotor control system

• US 6,196,796 B1
• Filed: 04/22/1999
• Issued: 03/06/2001
• Est. Priority Date: 04/22/1999
• Status: Expired due to Fees

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Morton, Robert, Lozyniak, Steven A., Hoffman, Lee A., Ferraro, Richard B., Lorber, Peter Frederick, Kohlhepp, Fred W.
• Primary Examiner(s): Look, Edward K.
• Assistant Examiner(s): NGUYEN, NINH H
• Application Number:
  US09/296,737
• Time in Patent Office: 684 Days
• Field of Search: 416/23, 416/24, 416/158, 921/22
• US Class Current: 416/24
• CPC Class Codes: B64C 2027/7272 of the electro-hydraulic type
• CPC Class Codes: B64C 27/615 including flaps mounted on blades
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

An actuation system for pivoting a flap on a helicopter rotor blade to reduce the interaction of the blade with the preceding blade vortex. The actuation system includes a fluid supply which is connected to first and second fluid supply lines. The fluid supply lines convey flows of pressurized fluid from the fluid supply to an actuator. The actuator includes a housing mounted within the rotor blade and having a channel formed in it. A butterfly shaft is pivotally mounted within the channel and has laterally extending arms which separate the channel into four lobes. A first port connects the first fluid supply line with two diametrically opposed lobes in the channel. A second port connects the second fluid supply line with the other two diametrically opposed lobes in the channel. A torque coupling is attached to the butterfly shaft and engaged with the flap such that rotation of the torque coupling produces concomitant rotation of the flap. The pressurization of the first fluid supply line causes the torque coupling to rotate in a first direction. The pressurization of the second supply fluid line causes the torque coupling to rotate in the opposite direction.

Claims

1. An actuator for actuating a flap in an active rotor control system, the flap being mounted on a trailing edge of a helicopter rotor blade, the actuator connected to a first fluid supply line for providing a first flow of pressurized fluid from a fluid supply, and to a second fluid supply line for conveying a second flow of pressurized fluid from the fluid supply, a controller for actively driving the actuator by controlling the supplying of fluid from the fluid supply, the actuator comprising:

a housing mounted within the trailing edge of a rotor blade, the housing having a channel formed within it;

a butterfly shaft pivotally mounted within the channel, the butterfly shaft having laterally extending arms which separate the channel into four lobes;

a first port adapted to receive a flow of fluid from a first fluid supply line, the first port fluidly communicating with two diametrically opposed lobes in the channel; and

a second port adapted to receive a flow of fluid from a second fluid supply line, the second port fluidly communicating with the other two diametrically opposed lobes in the channel.

2. An actuator according to claim 1 further comprising a torque coupling attached to the butterfly shaft and adapted to engage with a flap on the rotor blade such that rotation of the torque coupling produces concomitant rotation of the flap, the torque coupling rotating in a first direction when the first port receives pressurized fluid, and rotating in the opposite direction when the second port receives pressurized fluid.

3. An actuator according to claim 2 wherein the torque coupling is mounted to an end of the butterfly shaft such that rotation of the butterfly shaft about its longitudinal axis causes concomitant rotation of the torque coupling about its longitudinal axis, the torque coupling extending out of the trailing edge and attaching to the flap along its pivot axis for controlling rotation of the flap, and wherein the supplying of pressurized fluid forces the flap to pivot in a desired direction.

4. The actuator of claim 1 wherein the fluid communication between the first port and the two lobes is provided by a manifold.

5. The actuator of claim 1 wherein the fluid communication between the second port and the two lobes is provided by a manifold.

6. An actuator for actuating a flap mounted on a trailing edge of a helicopter rotor blade, the actuator to be connected to a first fluid supply line for providing a first flow of pressurized fluid from a fluid supply, and to a second fluid supply line for conveying a second flow of pressurized fluid from the fluid supply, the actuator comprising:

a housing adapted to be mounted within the rotor blade, the housing having a channel formed within it;

a butterfly shaft pivotally mounted within the channel, the butterfly shaft having laterally extending arms which separate the channel into four lobes;

a first port adapted to receive a flow of fluid from a first fluid supply line, the first port fluidly communicating with two diametrically opposed lobes in the channel;

a second port adapted to receive a flow of fluid from a second fluid supply line, the second port fluidly communicating with the other two diametrically opposed lobes in the channel; and

at least two bearings mounted within the housing which pivotally support the butterfly shaft.

9. The actuation system of claim 6 wherein the fluid communication between the first port and the two lobes is provided by a manifold.

10. The actuation system of claim 6 wherein the fluid communication between the second port and the two lobes is provided by a manifold.

7. An actuation system for actively controlling the pivoting of a flap on a helicopter rotor blade, the system comprising:

a fluid supply;

a first fluid supply line for conveying a first flow of pressurized fluid from the fluid supply;

a second fluid supply line for conveying a second flow of pressurized fluid from the fluid supply;

a controller for controlling the supplying of fluid from the fluid supply along the first and second supply lines; and

an actuator for pivoting a flap on a helicopter rotor blade, the actuator being fluidly connected to the first and second supply lines and including

a housing mounted within the trailing edge of the rotor blade on the side of the flap, the housing having a channel formed within it,

a butterfly shaft mounted within the channel and pivotable about a pivot axis, the butterfly shaft having laterally extending arms which separate the channel into four lobes,

a first port fluidly communicating with the first fluid supply line and two diametrically opposed lobes in the channel, and

a second port fluidly communicating with the second fluid supply line and the other two diametrically opposed lobes in the channel.

8. The actuation system of claim 7 further comprising a torque coupling attached to the butterfly shaft along the pivot axis and engaged with the flap such that rotation of the torque coupling produces concomitant rotation of the flap, the torque coupling rotating in the clockwise direction when the first supply fluid line is pressurized and the second supply line is depressurized, and the torque coupling rotating in the counter-clockwise direction when the second fluid supply line is pressurized and the first fluid supply line is depressurized.

11. An actuation system for pivoting a flap on a helicopter rotor blade, the system comprising:

a fluid supply;

a first fluid supply line for conveying a first flow of pressurized fluid from the fluid supply;

a second fluid supply line for conveying a second flow of pressurized fluid from the fluid supply; and

an actuator for pivoting a flap on a helicopter rotor blade, the actuator being fluidly connected to the first and second supply lines and including

a housing mounted within the rotor blade, the housing having a channel formed within it,

a butterfly shaft pivotally mounted within the channel, the butterfly shaft having laterally extending arms which separate the channel into four lobes,

a first port fluidly communicating with the first fluid supply line and two diametrically opposed lobes in the channel,

a second port fluidly communicating with the second fluid supply line and the other two diametrically opposed lobes in the channel

at least two bearings mounted within the housing which pivotally support the butterfly shaft.

12. An actuation system for actively controlling the pivoting of a flap on a helicopter rotor blade, the system comprising:

a rotor blade having a trailing edge;

a flap mounted adjacent to the trailing edge and pivotable about a pivot axis;

a fluid supply;

a first fluid supply line mounted within the rotor blade for conveying a first flow of pressurized fluid from the fluid supply;

a second fluid supply line mounted within the rotor blade for conveying a second flow of pressurized fluid from the fluid supply;

a controller for controlling the supplying of fluid along the first and second fluid supply lines from the fluid supply;

an actuator mounted within the trailing edge of the rotor blade for pivoting the flap with respect to the trailing edge, the actuator being fluidly connected to the first and second supply lines and including

a housing mounted within the rotor blade, the housing having a channel formed within it,

a butterfly shaft pivotally mounted within the channel, the butterfly shaft having laterally extending arms which separate the channel into four lobes and a longitudinal pivot axis about which the shaft pivots,

a first port formed in the housing, the first port having at least one manifold that extends from the first fluid supply line to two diametrically opposed lobes in the channel,

a second port formed in the housing, the second port having at least one manifold that extends from the second fluid supply line to the other two diametrically opposed lobes in the channel, and

a torque coupling attached to the pivot axis of the butterfly shaft, the torque coupling extending out of the trailing edge and attaching to the flap along the flap'"'"'s pivot axis such that rotation of the torque coupling produces concomitant rotation of the flap, the torque coupling rotating in the clockwise direction when the first supply fluid line is pressurized and the second fluid supply line is depressurized, and the torque coupling rotating in the counter-clockwise direction when the second fluid supply line is pressurized and the first fluid supply line is depressurized.

13. An actuation system for actuating a flap on the trailing edge of a helicopter rotor comprising:

a fluid supply;

a first fluid supply line for providing a first flow of pressurized fluid from a fluid supply;

a second fluid supply line for conveying a second flow of pressurized fluid from the fluid supply;

a controller for actively controlling the supplying of fluid from the fluid supply;

an actuator including

a housing mounted within the trailing edge of a rotor blade, the housing having a channel formed within it;

a butterfly shaft pivotally mounted within the channel, the butterfly shaft having laterally extending arms which separate the channel into four lobes;

a first port adapted to receive a flow of fluid from the first fluid supply line, the first port fluidly communicating with two diametrically opposed lobes in the channel; and

a second port adapted to receive a flow of fluid from the second fluid supply line, the second port fluidly communicating with the other two diametrically opposed lobes in the channel;

wherein the controller controls the supply of pressurized fluid along the first and second fluid lines to control the angle of the flap for improving the rotor blades aerodynamic performance and reducing noise generated by blade vortex interactions.