Abstract: There is disclosed a flow control nozzle for controlling the flow of an incompressible fluid, the flow control nozzle having a flow area and comprising a deformable element comprising a shaped memory alloy (SMA) material wherein within a range of operating temperatures the SMA material is configured to reduce the flow area of the flow control nozzle as the operating temperature increases. The flow control nozzle is thus able to dynamically compensate for changes in operating temperature in order to maintain a constant flow.

Abstract: An electrohydraulic spool valve, comprising: a spool, axially movable within a manifold; a position feedback system provided at a first end of the spool; and an end cap provided on said first end so as to form a first high pressure reservoir between the end cap and the first end of the spool. The end cap provided on the end of the spool partly defines the high pressure reservoir by containing the high pressure fluid in the vicinity of the spool end.

Abstract: A gurney flap arrangement comprises: an airfoil with an opening in a surface of the airfoil; a gurney flap having a first position in which at least a portion of the gurney flap extends through the opening and projects outwardly from the airfoil surface, and a second position in which the gurney flap does not project from the airfoil surface or projects outwardly from the airfoil surface to a lesser extent; and a seal disposed about the opening to seal a gap in the opening between the gurney flap and the airfoil.

Abstract: A roller bearing comprises inner and outer rings defining a toroidal inner raceway rotatable about a bearing axis (A). A plurality of concave rolling elements is arranged in a single row between the outer and inner rings. Each of the plurality of concave rolling elements is a symmetrical cylindrical roller having circular ends, a roller axis passing through the center of the circular ends, and a concave side profile that extends continuously between the circular ends. The toroidal inner and outer raceways each have a convex race surface that continuously engages the concave side profile between the circular ends of each concave rolling element with a first radius and extends axially beyond the circular ends of each concave rolling element with a second radius that is less than the first radius.

Abstract: A spool for a hydraulic spool valve, comprising: a pressure chamber for connecting a pressure line to a hydraulic cylinder; at least one return chamber for connecting the hydraulic cylinder to a reservoir; and an actuator slot for receiving a drive lever; wherein the spool further comprises a fluid path connecting said pressure chamber to said actuator slot and a pressure plate movably mounted in the slot such that in use it is disposed between the fluid path and the drive lever.

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 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 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.