Abstract: A cut guide includes a first face and an opposed second face. The cut guide further includes a first aperture and a second aperture extending through the cut guide from the first face to the second face. The first and second apertures are configured to guide a surgical tool in cutting a bone. The cut guide further includes a first hole extending through the cut guide from the first face to the second face. The cut guide further includes a second hole extending through the cut guide. A central axis of the second hole is oriented at an acute angle to the second face. The first and second holes are configured to receive a wire to position the guide against the bone.

Abstract: A bone anchor includes a flexible strand defining a first adjustable loop and a friction knot coupled to a proximal end of the first adjustable loop. The friction knot is configured to allow adjustment of the first adjustable loop in a first configuration and is configured to prevent adjustment of the first adjustable loop in a second configuration. A knot capsule includes a body defining an internal knot cavity. The friction knot and a portion of the first adjustable loop are positioned within the internal knot cavity. The internal knot cavity defines one or more impingement surfaces configured to maintain the friction knot in a fixed position within the internal knot cavity when the friction knot is in the second configuration.

Abstract: An apparatus for correcting bunion deformity includes an elongated member, a first arm member extending from a first end to a second end, a second arm member, and a rotation guide. The first arm member has an arm axis and is coupled to the first end of the elongated member so that the arm axis extends in an orthogonal direction from the elongated member. The second arm member includes an attachment portion configured to translatably engage the elongated member and an extension extending in the same orthogonal direction as the first arm member. The rotation guide is coupled to the first arm member such that the rotation guide is configured to rotate with respect to the first arm member about a rotation axis, the rotation guide defining a bore having a longitudinal axis.

Abstract: A clutch assembly for a roller door operator, the clutch assembly providing selective engagement with a drive wheel, the clutch assembly comprising: a rotatable shaft rotatable relative to the drive wheel; a clutch disc supported in a clutch lever and arranged to rotate with the rotatable shaft, the clutch disc and clutch lever configured to rotate relative to one another around the axis of rotation of the shaft; and a clutch cam supported in a clutch base, the clutch base configured to permit operative rotation of the clutch cam around the axis of rotation of the shaft in a first direction; wherein the clutch lever is operatively associated with the clutch cam so that rotational movement of the clutch lever in a second direction opposite to the first direction actuates movement of the clutch disc and the clutch lever axially along the rotatable shaft to engage or disengage the clutch disc with the drive wheel, and subsequent rotational movement of the clutch lever in the first direction actuates rotational m

Abstract: In various embodiments, a targeting guide is disclosed. The targeting guide includes a handle defining a targeting hole and a targeting tower configured to be coupled to the handle. The targeting tower defines at least a first guide hole and a second guide hole. Each of the first and second guide holes are sized and configured to receive a respective first guide pin and second guide pin therethrough. The first and second guide pins are configured to indicate alignment of a k-wire inserted through the targeting hole defined by the handle. Methods of using a targeting guide are also disclosed.

Abstract: A bone anchor includes a flexible strand defining a first adjustable loop and a friction knot coupled to a proximal end of the first adjustable loop. The friction knot is configured to allow adjustment of the first adjustable loop in a first configuration and is configured to prevent adjustment of the first adjustable loop in a second configuration. A knot capsule includes a body defining an internal knot cavity. The friction knot and a portion of the first adjustable loop are positioned within the internal knot cavity. The internal knot cavity defines one or more impingement surfaces configured to maintain the friction knot in a fixed position within the internal knot cavity when the friction knot is in the second configuration.

Abstract: An apparatus for correcting bunion deformity includes an elongated member, a first arm member extending from a first end to a second end, a second arm member, and a rotation guide. The first arm member has an arm axis and is coupled to the first end of the elongated member so that the arm axis extends in an orthogonal direction from the elongated member. The second arm member includes an attachment portion configured to translatably engage the elongated member and an extension extending in the same orthogonal direction as the first arm member. The rotation guide is coupled to the first arm member such that the rotation guide is configured to rotate with respect to the first arm member about a rotation axis, the rotation guide defining a bore having a longitudinal axis.

Abstract: A cut guide includes a first face and an opposed second face. The cut guide further includes a first aperture and a second aperture extending through the cut guide from the first face to the second face. The first and second apertures are configured to guide a surgical tool in cutting a bone. The cut guide further includes a first hole extending through the cut guide from the first face to the second face. The cut guide further includes a second hole extending through the cut guide. A central axis of the second hole is oriented at an acute angle to the second face. The first and second holes are configured to receive a wire to position the guide against the bone.

Abstract: A rotor system for an aircraft includes a rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.

Abstract: A cut guide includes a first face and an opposed second face. The cut guide further includes a first aperture and a second aperture extending through the cut guide from the first face to the second face. The first and second apertures are configured to guide a surgical tool in cutting a bone. The cut guide further includes a first hole extending through the cut guide from the first face to the second face. The cut guide further includes a second hole extending through the cut guide. A central axis of the second hole is oriented at an acute angle to the second face. The first and second holes are configured to receive a wire to position the guide against the bone.

Abstract: A rotor blade retention device for use in an aircraft having a plurality of blades includes an array of cavities, each cavity adapted to receive a portion of a tension-torsion strap therein. Each cavity is oriented such that, when the portion of the tension-torsion strap is received therein, a central plane of the tension-torsion strap is inclined relative to a blade plane of rotation defined by the plurality of blades. The retention device may have a body that defines an aperture adapted to receive a portion of a rotor mast of the aircraft, may comprise a rotor mast of the aircraft, or may comprise first and second plates that cooperate to form the array of cavities and that are adapted to receive a portion of the rotor mast of the aircraft.

Abstract: A rotor assembly has a rotor hub having a unitary structure. The rotor assembly further includes a unitary crosshead having a first upper tab and a first lower tab located vertically below the first upper tab. The first upper tab and the first lower tab define a slot therebetween to accept a first pin of the first rotor blade. A second upper tab and a second lower tab located vertically below the second upper tab define a slot therebetween to accept a second pin of the second rotor blade. A first recess is provided between the first lower tab and the second lower tab so that the crosshead comprises no material directly between at least a portion of the first lower tab and the second lower tab along at least one straight path.

Abstract: In various embodiments, a targeting guide is disclosed. The targeting guide includes a handle defining a targeting hole and a targeting tower configured to be coupled to the handle. The targeting tower defines at least a first guide hole and a second guide hole. Each of the first and second guide holes are sized and configured to receive a respective first guide pin and second guide pin therethrough. The first and second guide pins are configured to indicate alignment of a k-wire inserted through the targeting hole defined by the handle. Methods of using a targeting guide are also disclosed.

Abstract: A method to remove a memory metal orthopedic staple from that is implanted in a bone repair site is disclosed. The orthopedic staple is in its relaxed state and the method includes (a) attaching an inserter tool/cartridge assembly to the orthopedic staple's bridge portion; (b) actuating the inserter tool to change the orthopedic staple from its relaxed state to its insertion state in which the two legs of the orthopedic staple are substantially parallel to each other; and (c) removing the orthopedic staple from the bone repair site.

Abstract: A rotor system for an aircraft includes an open rotor assembly comprising an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast, wherein the rotor assembly is tiltable relative to a wing of the aircraft between a first position corresponding to an airplane mode of the aircraft and a second position corresponding to a helicopter mode of the aircraft; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast. The drive system includes at least one electric motor for generating rotational energy to a motor shaft; and a gearbox connected to receive rotational energy from the at least one electric motor via the motor shaft and to provide rotational energy to the rotor mast via a rotor shaft, wherein the at least one electric motor is fixed relative to the wing of the aircraft.

Abstract: A device for a track- or rail-mounted closure drive assembly can include a lever and cam arrangement configured to drive an engagement member between an engaged position and a disengaged position, the engaged position allowing motor drive of a closure and the disengaged position disconnecting the drive from the motor to the closure; and a rotating body including one or more camming surfaces and one or more peripheral surfaces, the peripheral surfaces including visual indicia to indicate to a user an orientation of the one or more camming surfaces and hence whether the engagement member is in the engaged position or the disengaged position.

Abstract: A computer-implemented method for matching material names from one or more material sources with safety data sheet material names from one or more safety data sheets. The method includes: extracting the material names from the one or more material sources; preprocessing the material names and removing extraneous data from one or more of the material names; selecting one of the material names; comparing the selected material name with the safety data sheet material names; identifying the safety data sheet material names that match the material name; and transmitting an output to a user device to display the material name and the matching safety data sheet material names.

Abstract: In various embodiments, a targeting guide is disclosed. The targeting guide includes a handle defining a targeting hole and a targeting tower configured to be coupled to the handle. The targeting tower defines at least a first guide hole and a second guide hole. Each of the first and second guide holes are sized and configured to receive a respective first guide pin and second guide pin therethrough. The first and second guide pins are configured to indicate alignment of a k-wire inserted through the targeting hole defined by the handle. Methods of using a targeting guide are also disclosed.

Abstract: Embodiments of an expansion joint are provided. The expansion joint is configured to cover a gap between a first architectural surface and a second architectural surface. The expansion joint includes a panel having a first surface and a second surface in which the second surface is opposite the first surface. When the panel covers the gap, the panel is magnetically connected to both of the first architectural surface or the second architectural surface. In specific embodiments, at least one of the magnetic structures that magnetically connect the panel to both of the first architectural surface or the second architectural surface is allowed to move in response to movement of the panel. In more specific embodiments, the movement of the magnetic structure is a tilting movement.

Abstract: A rotor system for an aircraft includes an open rotor assembly comprising a plurality of rotor blades connected to a rotor mast via a yoke, wherein the rotor assembly is tiltable between a first position corresponding to an airplane mode and a second position corresponding to a helicopter mode; and a drive system for providing rotational energy to the open rotor assembly via the rotor mast, the drive system comprising at least one electric motor for providing rotational energy to a drive shaft and a gearbox connected to the drive shaft for receiving rotational energy from the at least one electric motor via the drive shaft and providing rotational energy to the rotor mast via a rotor shaft; wherein the drive system is rotatable relative to the wing about a tilt axis and the rotor shaft is coaxial with the drive shaft.