Fluid conduit for use with hydraulic actuator
View Patent ↗A fluid conduit is provided for use in a hydraulic actuating system for controlling an instrumentality disposed on a rotating portion of a machine. The fluid conduit transports pressurized fluid between a fluid source disposed on a non-rotating portion of the machine and the instrumentality and comprises a rigid tubular member formed in the shape of a helix having at least about 2 revolutions and a non-constant pitch length. The ends of the tube are adapted to be sealingly connected between the fluid source and the instrumentality. The fluid conduit is used, for example, in an apparatus and system for controlling a hydraulic actuator mounted on a rotating blade.
1. A fluid line for use in an active control device on a rotary wing aircraft having an airframe and a rotor rotatable relative to the airframe, the rotor including a hub and at least one elongated rotor blade connected at one end to the hub and extending radially outwardly therefrom such that when the rotor hub is rotatably driven the rotor blade rotates with the hub, the rotor blade movable relative to the hub about a blade pitch axis extending along its length, and a hydraulic actuation system for moving the blade about the blade pitch axis including a fluid source associated with the hub, means for controlling the position of the rotor blade about the blade pitch axis, and a hydraulic actuator operatively connected to and rotating with the blade for changing the position of the blade about the blade pitch axis in response to a signal from the controlling means, the fluid line comprising:
a rigid member having a substantially helical shape with at least about two revolutions and a non-constant pitch length, said rigid member having a first end and a second end;
a first fluid-tight connector fluidly connecting said first end of said rigid member to the fluid source; and
a second fluid-tight connector fluidly connecting said second end of said rigid member to the hydraulic actuation system;
wherein said first and second connectors are structured and arranged to non-releasably transmit forces generated in said rigid member to the hub and the rotor.
2. A fluid line as recited in claim 1 , wherein the tubular member is formed from a material having a hardness of about Rc 40.
3. A fluid line as recited in claim 1 , wherein the tubular member has a pitch diameter of less than about 3.5 inches.
4. A fluid line as recited in claim 1 , further comprising a second rigid tubular member formed in the shape of a helix having at least about 2 revolutions and a non-constant pitch length, the ends of the tube adapted to be connected between the fluid source and the actuator so that the second rigid tubular member is nested within the first tubular member.
5. A fluid line for use in an active control device on a rotary wing aircraft having an airframe and a rotor rotatable relative to the airframe, the rotor including a hub and at least one elongated rotor blade connected at one end to the hub and extending radially outwardly therefrom such that when the rotor hub is rotatably driven the rotor blade rotates with the hub, the rotor blade comprising a flap attached to and movable relative to the blade about an axis, and a hydraulic actuation system or moving the flap about the axis, the hydraulic actuation system including a fluid source associated with the hub, means for controlling the position of the flap about the axis, and a hydraulic flap actuator operatively connected to the flap for changing the position of the flap with respect to the blade in response to a signal from the controlling means, the fluid line comprising:
a rigid member having a substantially helical shape with at least about two revolutions and a non-constant pitch length, said rigid member having a first end and a second end:
a first fluid-tight connector fluidly connecting said first end of said rigid member to the fluid source; and
a second fluid-tight connector fluidly connecting said second end of said rigid member to the hydraulic actuation system:
wherein said first and second connectors are structured and arranged to non-releasably transmit forces generated in said rigid member to the hub and the rotor.
6. A fluid line as recited in claim 5 , wherein the tubular member is formed from a material having a hardness of about Rc 40.
7. A fluid line as recited in claim 5 , wherein the tubular member has a pitch diameter of less than about 3.5 inches.
8. A fluid line as recited in claim 5 , further comprising a second rigid tubular member formed in the shape of a helix having at least about 2 revolutions and a non-constant pitch length, the end of the tube adapted to be connected between the fluid source and the actuator so that the second rigid tubular member is nested within the first tubular member.
9. An active control device for hydraulically controlling the position of a rotor blade flap on a rotary wing aircraft having an airframe and a rotor rotatable relative to the airframe, the rotor including a hub and at least one elongated rotor blade connected at one end to the hub and extending radially outwardly therefrom such that when the rotor hub is rotatably driven the rotor blade rotates with the hub, the rotor blade flap movably attached to and movable relative to the blade about an axis, the active control device comprising:
a fluid source adapted to be mounted to the airframe;
means for controlling the position of the flap about the axis;
a hydraulic flap actuator adapted to be operatively connected to the flap for changing the position of the flap with respect to the blade in response a signal from the controlling means; and
a rigid member having a substantially helical shape with at least about two revolutions and a non-constant pitch length, said rigid member having a first end and a second end;
a first fluid-tight connector fluidly connecting said first end of said rigid member to said fluid source; and
a second fluid-tight connector fluidly connecting said second end of said rigid member to the hydraulic flap actuator;
wherein said first and second connectors are structured and arranged to non-releasably transmit forces generated in said rigid member to the hub and the rotor blade.
10. A rotary wing aircraft, comprising:
an airframe;
a rotor rotatable relative to the airframe including
a hub,
and at least one elongated rotor blade connected at one end to the hub and extending radially outwardly therefrom such that when the rotor hub is rotatably driven the rotor blade rotates with the hub, the rotor blade comprising a flap attached to and movable relative to the blade about an axis;
a fluid source associated with the airframe;
means for hydraulically controlling the position of the flap about the axis;
a hydraulic flap actuator operatively connected to the flap for banging the position of the flap with respect to the blade in response to a signal from the controlling means; and
a rigid member having a substantially helical shape with at least about two revolutions and a non-constant pitch length, said rigid member having a first end and a second end;
a first fluid-tight connector fluidly connecting said first end of said rigid member to the fluid source; and
a second fluid-tight connector fluidly connecting said second end of said rigid member to the controlling means;
wherein said first and second connectors are structured and arranged to non-releasably transmit forces generated in said rigid member to the hub and the rotor blade.