Abstract: Trailing edge device catchers and associated systems and methods are disclosed. A system in accordance with one embodiment includes a wing having a wing support, a trailing edge device carried by and movable relative to the wing and having a device support, and a coupling connected between the wing and the trailing edge device. The coupling can include a pivot joint that includes a pivot element aligned along a pivot axis and connected between the wing support and the device support. The coupling can further include an actuator coupled between the wing and the trailing edge device, with the actuator having a first position in which the trailing edge device is stowed, and a second position in which the trailing edge device is deployed, with an air flow gap located between the wing and the trailing edge device when the trailing edge device is in the second position. A cam track is carried by one of the wing and the trailing edge device and has opposing cam track surfaces fixed relative to each other.

Abstract: Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.

Abstract: Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.

Abstract: Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.

Abstract: Aircraft wing assemblies having both composite and metal panels are disclosed. In one embodiment, a wing assembly includes a support structure, an upper panel assembly formed from a metal material and coupled to the support structure, and a lower panel assembly formed from a composite material and coupled to the support structure. The metal material may be aluminum, titanium, or any other suitable metal, and the composite material may be a carbon fiber reinforced plastic (CFRP) material or other suitable composite material. In another embodiment, the upper panel assembly includes a downwardly depending first web portion, and the lower panel assembly includes an upwardly depending second web portion, the second web portion being proximate the first web portion, and an interface member of an isolating material is disposed between the first and second web portions.

Abstract: Aerodynamic seals for use with control surfaces on aircraft are described herein. In one embodiment, a seal assembly for use with an aircraft includes a first seal member and a second seal member. The first seal member has a first proximal portion configured to be attached to a fixed airfoil portion of the aircraft, and a first distal portion configured to extend outwardly from the fixed airfoil portion toward a movable control surface. The second seal member has a second proximal portion configured to be attached to the movable control surface, and a second distal portion configured to extend outwardly from the control surface toward the fixed airfoil portion. In this embodiment, the second distal portion is further configured to movably contact the first distal portion to at least partially seal the gap between the fixed airfoil portion and the movable control surface as the control surface moves relative to the fixed airfoil portion.

Abstract: Aircraft trailing edge devices, including devices with non-parallel motion paths, and associated methods are disclosed. A device in accordance with one embodiment includes a wing and an inboard trailing edge device coupled to the wing and movable relative to the wing between a first stowed position and a first deployed position along a first motion path. An outboard trailing edge device can be coupled to the wing outboard of the inboard trailing edge device, and can be movable relative to the wing along a second motion path that is non-parallel to the first motion path. An intermediate trailing edge device can be coupled between the inboard and outboard trailing edge devices and can be movable along a third motion path that is non-parallel to both the first and second motion paths. Each of the trailing edge devices can open a gap relative to the wing when moved to their respective deployed positions.

Abstract: Aircraft trailing edge devices, including devices having forwardly positioned hinge lines, and associated methods are disclosed. An aircraft system in accordance with one embodiment of the invention includes a wing and a trailing edge device coupled to the wing. The trailing edge device can be movable relative to the wing between a stowed position and a deployed position, with the trailing edge device having a leading edge, a trailing edge, an upper surface, and a lower surface. The upper surface can have an intersection point with the wing when the trailing edge device is in the stowed position. The motion of the trailing edge device relative to the wing can include rotational motion about a hinge line positioned forward of the intersection point, and a gap can be positioned between the trailing edge of the wing and the leading edge of the trailing edge device when the trailing edge device is in the deployed position.

Abstract: A method, system, and apparatus for attaching a fairing to a body or aircraft wing are disclosed. A plurality of attach anchors is disposed on the body or aircraft wing to which the fairing is to be attached. Disposed in the fairing is a plurality of core pockets that are alignable with the plurality of attach anchors, and each of the core pockets defines a channel. The fairing is placed over the body or the aircraft wing such that the heads of the attach anchors are received in the core pockets. The fairing is then slid across the body or the aircraft wing with the channels sliding along the heads of the attach anchors such that the fairing is prevented from being lifted away from the body or aircraft wing.

Abstract: A method, system, and apparatus for attaching a fairing to a body or aircraft wing are disclosed. A plurality of attach anchors is disposed on the body or aircraft wing to which the fairing is to be attached. Disposed in the fairing is a plurality of core pockets that are alignable with the plurality of attach anchors, and each of the core pockets defines a channel. The fairing is placed over the body or the aircraft wing such that the heads of the attach anchors are received in the core pockets. The fairing is then slid across the body or the aircraft wing with the channels sliding along the heads of the attach anchors such that the fairing is prevented from being lifted away from the body or aircraft wing.

Abstract: An apparatus for centering semiconductor loading and unloading arms is described. The apparatus comprises a cap and a ring. The cap comprises a first plate, substantially in the shape of an electrode, a lip affixed to the edge of the first plate for holding the first plate stationary in a lateral direction, and a pin affixed to a top of the first plate such that the pin is perpendicular to the first plate. The ring comprises a second plate substantially in the shape of a semiconductor material to be placed on the electrode, an aperture in the second plate, the diameter of the aperture being the same as the diameter of the pin, and a collar surrounding the aperture, wherein the collar is for holding the second plate.

Abstract: A test fixture for sputter targets used in the manufacture of semiconductor devices and a method of testing sputter targets. The test fixture comprises a specially shaped piece of material which is adapted to receive a sputter target. The test fixture generally conforms to the shape of the sputter target. The interface between the test fixture and the sputter target is carefully manufactured so as to maintain an airtight seal. A passageway is disposed within one sidewall of the test fixture. A vacuum tubing is disposed within the passageway and valve is connected to the tubing so that the cavity within the test fixture can be evacuated. The size of the cavity is kept small so that it may be quickly evacuated. The present invention provides an efficient and cost effective method of testing sputter targets prior to their being placed in the sputter machine.