Abstract: A spool valve arrangement comprising a spool arranged for linear movement within a bore to regulate flow of fluid through the bore according to the linear position of the spool relative to the bore, the spool having an end arranged to be engaged, in use, by a drive member to cause the linear movement, the spool valve arrangement further comprising a sliding block component moveably attached to the spool end and arranged to engage with the drive member, in use, such that the drive member engages with the spool end via the sliding block component and the sliding block component moves relative to the spool to compensate for non-linear movement of the drive member.

Abstract: A pressure detection device is mounted within an actuator housing between a piston rod and the housing, to receive fluid leaked past a seal, via a bore in the housing. The pressure detection device is configured to provide an output indicative of the pressure or flow of the leaked fluid in the bore. Thus, the leaked fluid diverted via the bore operates the pressure detection device to provide an output indicative of leakage.

Abstract: A spool valve arrangement comprising a spool arranged for linear movement within a bore to regulate flow of fluid through the bore according to the linear position of the spool relative to the bore, the spool having an end arranged to be engaged, in use, by a drive member to cause the linear movement, the spool valve arrangement further comprising a sliding block component moveably attached to the spool end and arranged to engage with the drive member, in use, such that the drive member engages with the spool end via the sliding block component and the sliding block component moves relative to the spool to compensate for non-linear movement of the drive member.

Abstract: A rotor blade assembly includes a rotor blade and a movable trim tab located along a span of the rotor blade. A linear positioner is located inside the rotor blade and operably connected to the trim tab to move the trim tab thereby reducing rotor blade vibration. A method for reducing vibration of a rotor assembly includes energizing a linear positioner located inside a rotor blade of the rotor assembly and moving an output piston of the linear positioner. A trim tab located at the rotor blade is moved to a selected trim tab angle relative to the rotor blade by the output piston, and the linear positioner is deenergized thereby locking the trim tab at the selected trim tab angle.

Abstract: A rotor blade assembly includes a rotor blade, a rotatable flap portion disposed along a span of the rotor blade. A rotary actuator is located inside the rotor blade and is operably connected to the flap portion to rotate the flap portion about a flap axis. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion disposed along a span of the rotor blade. A rotary actuator located inside the rotor blade and is operably connected to the flap portion to rotate the flap portion about a flap axis. The rotary actuator is absent oil, grease or other fluid lubricant.

Abstract: A rotor blade assembly includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator located inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator positioned inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant.

Abstract: According to an embodiment disclosed herein, a gurney flap assembly includes an actuator, and a flexible body attaching to the actuator, the body having a downwardly depending flap for moving into and out of an airstream in a pressure side of a wing, wherein the flexible body flexes in reaction to motion of the actuator. This increases the lift force of the rotor blade, wing or aerofoil blade.

Abstract: A bearing assembly and a method of forming a bearing assembly is provided including a housing having a bore. The bore has a generally concave inner surface. The bearing assembly also includes a bearing having an inner member. The inner member is movable about a central axis and is dimensioned to fit within the bore. The inner member has a generally convex outer surface complementary to the concave inner surface of the bore. The housing functions as an outer member of the bearing.

Abstract: A gurney flap assembly has an actuator, a flexible or hinged body, the body flexing from a retracted to a deployed position in reaction to motion of the actuator, and a first seal extending along a first edge of the flexible body that flexes from the stowed position. Linear motion of the actuator output is transposed to the gurney flap thereby moving it from a retracted position into the airstream. This trailing edge device will improve airfoil lift.

Abstract: A rotor blade assembly includes a rotor blade, a rotatable flap portion disposed along a span of the rotor blade. A rotary actuator is located inside the rotor blade and is operably connected to the flap portion to rotate the flap portion about a flap axis. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion disposed along a span of the rotor blade. A rotary actuator located inside the rotor blade and is operably connected to the flap portion to rotate the flap portion about a flap axis. The rotary actuator is absent oil, grease or other fluid lubricant.

Abstract: A rotor blade assembly includes a rotor blade and a movable trim tab located along a span of the rotor blade. A linear positioner is located inside the rotor blade and operably connected to the trim tab to move the trim tab thereby reducing rotor blade vibration. A method for reducing vibration of a rotor assembly includes energizing a linear positioner located inside a rotor blade of the rotor assembly and moving an output piston of the linear positioner. A trim tab located at the rotor blade is moved to a selected trim tab angle relative to the rotor blade by the output piston, and the linear positioner is deenergized thereby locking the trim tab at the selected trim tab angle.

Abstract: A hinge for use with movable components is provided including a generally rectangular body. The body includes a bend region, a first flange, and a second flange. The first flange and the second flange are positioned on opposing sides of the bend region. A portion of the bend region has a reduced thickness relative to the first flange and the second flange. A hinge axis is defined within the bend region. The first flange and the second flange rotate about the hinge axis.

Abstract: A bearing assembly and a method of forming a bearing assembly is provided including a housing having a bore. The bore has a generally concave inner surface. The bearing assembly also includes a bearing having an inner member. The inner member is movable about a central axis and is dimensioned to fit within the bore. The inner member has a generally convex outer surface complementary to the concave inner surface of the bore. The housing functions as an outer member of the bearing.

Abstract: A gurney flap assembly has an actuator and a body. The body has a leading edge and a trailing edge and includes a first panel attaching to the actuator proximate the leading edge, and a second panel attaching to a first hinge at the trailing edge. A second hinge attaches the first and second panel. Linear motion of an actuator output is transposed to the gurney flap, thereby causing the gurney flap to expand and deploy into the airstream on the pressure side of the wing.

Abstract: A rotor blade assembly includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator located inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant. A rotary-winged aircraft includes an airframe and a main rotor assembly operably connected to the airframe. The main rotor assembly includes a plurality of rotor blade assemblies rotatable about a rotor assembly axis. At least one rotor blade assembly of the plurality of rotor blade assemblies includes a rotor blade and a rotatable flap portion located along a span of the rotor blade. A linear actuator positioned inside the rotor blade is operably connected to the flap portion to rotate the flap portion about a flap axis and is absent oil, grease or other fluid lubricant.

Abstract: A gurney flap assembly has an actuator, a flexible or hinged body, the body flexing from a retracted to a deployed position in reaction to motion of the actuator, and a first seal extending along a first edge of the flexible body that flexes from the stowed position. Linear motion of the actuator output is transposed to the gurney flap thereby moving it from a retracted position into the airstream. This trailing edge device will improve airfoil lift.

Abstract: According to an embodiment disclosed herein, a gurney flap assembly includes an actuator, and a flexible body attaching to the actuator, the body having a downwardly depending flap for moving into and out of an airstream in a pressure side of a wing, wherein the flexible body flexes in reaction to motion of the actuator. This increases the lift force of the rotor blade, wing or aerofoil blade.

Abstract: A gurney flap assembly has an actuator and a body. The body has a leading edge and a trailing edge and includes a first panel attaching to the actuator proximate the leading edge, and a second panel attaching to a first hinge at the trailing edge. A second hinge attaches the first and second panel. Linear motion of an actuator output is transposed to the gurney flap, thereby causing the gurney flap to expand and deploy into the airstream on the pressure side of the wing.