Abstract: An assembly for reacting a thrust load from an engine, the assembly comprising a frame, a pin, an evener bar, and left and right thrust links. The frame includes an upper pin interface and a lower pin interface. The pin extends through the upper pin interface and the lower pin interface and includes an upper end and a lower end. The evener bar engages the lower end of the pin below the lower pin interface and connects the left and right thrust links to the pin. The pin is configured to react the thrust load at the lower pin interface and the upper pin interface thereby forming a distributed force couple between the lower pin interface and the upper pin interface.

Abstract: A system and method for drilling a hole in a vehicle structure and installing a fastener in the hole. A drill plate having openings and associated machine-readable elements is positioned on the structure. A drill gun is positioned in a particular opening and reads hole information from the associated element, and a computer determines whether the drill gun is properly set-up to drill the hole. A fastener insertion gun is positioned in the particular opening and reads fastener information from the element, and the computer determines whether the hole has been drilled and, if so, whether the fastener insertion gun is properly set-up to insert the fastener. A fastener delivery subsystem stores, tracks, and delivers fasteners to the fastener insertion gun. A system computer monitors the drilling of every hole, the insertion of every fastener, and the overall operation of the fastener delivery subsystem.

Abstract: A stiffening element comprises a tension and compression member, a shear member, an attachment member, and a plurality of beads. The tension and compression member is positioned spaced apart from the skin and configured to bear tension or compression forces that stiffen the skin and prevent the skin from buckling or bending. The shear member is connected to the tension and compression member and configured to bear shear forces between the skin and the tension and compression member. The attachment member is connected to the shear member and is configured to connect to the skin. The beads each create out-of-plane feature that is positioned in at least one of the shear member and the attachment member. The beads permit the stiffening element be reshaped to adjust a longitudinal curvature of the stiffening element.

Abstract: An improved system and process for rapidly producing distilled spirits having characteristics associated with a much longer maturation process is provided. The method involves contacting wood with an unmatured distilled spirit under heated conditions and contacting the resulting heat-treated spirit with actinic light. The disclosure provides embodiments where a spirit is sequentially processed through heat and actinic light treatment. The disclosure also provides embodiments where a heat-treated spirit is mixed with a spirit that has been separately treated with light to give characteristics of a mature spirit. Air may also be percolated through a mature spirit in a container with a headspace at a gauge pressure between about ?25 inHg and about ?30 inHg, until the alcohol concentration of the mature spirit is reduced by between about 1% to about 2% by volume, and until the total volume of the mature spirit is reduced by about 10% or less.

Abstract: A system and method for welding thermoplastic components by positioning and moving a heated plate between the components to melt their respective faying surfaces, and as the plate moves, pressing the components together so that the melted faying surfaces bond together as they cool and re-solidify, thereby creating a composite structure. The plate has a heated portion which is positioned between and heated to melt a portion of the first and second faying surfaces. A manipulator mechanism moves the plate along an interface from between the portion to between a series of subsequent portions of the first and second faying surfaces, thereby welding the thermoplastic components along the entire interface to create the composite structure. An injection device may also move behind the plate and reciprocally inject a polymer between the first and second faying surfaces to provide toughness and crack arresting properties.

Abstract: Embodiments of a multi-compartment beverage bottle system and methods of manufacturing the system are disclosed. First and second housing elements are in mutual engagement with one another to at least partially define a fluid vessel with a fluid cavity therein. The fluid cavity includes a first fluid compartment and a second fluid compartment. The first housing element is rotatable between a storage position and a mix position with respect to the second housing element. A shuttle element is disposed within the fluid cavity and axially actuatable along the main axis into and out of a seal position. Rotation of the first housing element toward the storage position actuates the shuttle element toward the seal position. Rotation of the first housing element toward the mix position actuates the shuttle element away from the seal position, thereby placing the first and second fluid compartments into fluid communication with one another for mixing.

Abstract: A system and method for welding thermoplastic components by positioning and moving a heated plate between the components to melt their respective faying surfaces, and as the plate moves, pressing the components together so that the melted faying surfaces bond together as they cool and re-solidify, thereby creating a composite structure. The plate has a heated portion which is positioned between and heated to melt a portion of the first and second faying surfaces. A manipulator mechanism moves the plate along an interface from between the portion to between a series of subsequent portions of the first and second faying surfaces, thereby welding the thermoplastic components along the entire interface to create the composite structure. The heated portion may contact the faying surfaces and melt them through conduction, or may be suspended between them and melt them through radiation and convection.

Abstract: A composite aircraft engine pylon comprising a frame, an aircraft attachment component, and an engine support. The frame includes an outer structural section and an inner structural section configured to at least partially nest with the outer structural section. The outer structural section and the inner structural section sandwich the airframe attachment component and the engine support to form double shear connections between the frame and the aircraft attachment component and between the frame and the engine support.

Abstract: The disclosure discloses apparatus and methods for repairing defects such as porosity and/or edge delamination in composite laminates by infusion of flowable matrix material. In some embodiments, methods disclosed herein comprise infusing the flowable matrix material into a space in the composite laminate through the use of a formed hole extending at least partially through the composite laminate. In some embodiments, methods disclosed herein comprise infusing the flowable matrix material into a space in the composite laminate in a stepwise manner in order to obtain more complete filling of such space.

Abstract: An automated fiber placement (AFP) and in-situ fiber impregnation system includes a feeder, a resin dispenser, and a compaction roller. The feeder feeds a tow of fiber from a fiber supply toward a forming tool. The resin dispenser deposits resin onto the forming tool in front of the compaction roller. The compaction roller moves over the tow along the forming tool so as to press the tow onto the resin such that the compaction roller impregnates the resin into the tow a direction away from the forming tool via compaction forces immediately after the resin is deposited by the resin dispenser.

Abstract: Method of forming composite components such as aircraft stringers and the like, and tooling used to form the same. The method includes stacking plies on a forming tool and conveying the plies and the forming tool through a pressure vessel. The pressure vessel includes an entrance opening and an exit opening, which are sized and shaped to permit a forming tool supporting a plurality of plies to pass through the pressure vessel. The pressure vessel includes an interior chamber housing multiple spheres. The spheres press against the plies as the forming tool is conveyed through the pressure vessel, thereby pressure treating the plies and forming the composite part.

Abstract: A removable spout seal and pour spout assembly is presented. The removeable spout seal generally comprises a cylindrical attachment member attached to a flange with a channel extending distally perpendicular therefrom. The removeable spout seal is coupled to a pour spout to form the pour spout assembly. In use, the removeable spout seal attaches to the connection member of a pour spout to provide a seal that prevents leaking of liquids from a vessel. The vent tube of the pour spout is inserted into the channel of the spout seal apparatus and the cylindrical attachment member of the spout seal is inserted into the connection member of the pour spout to form a leakproof seal. Use of the spout seal allows shipping a vessel with the pour spout in place thus preventing leaking during shipping; prevents contamination of contents; preserves freshness of contents; and prevents accidental spills and leaking.

Abstract: A monolithic skin for an aerodynamic structure is provided. The skin comprises a root end defining a root opening; a tip end opposite to the root end; a trailing-edge portion defining a slot opening extending from the root opening toward the tip end; a leading-edge portion extending spanwise from the root end to the tip end; and a middle portion extending between the trailing edge and the leading-edge portion and at least partially defining an open slot in fluid communication with the slot opening and root opening. The middle portion comprises an interior surface facing the open slot that is graded so that the middle portion decreases in thickness spanwise toward the root end. The middle portion also comprises a first integrated spar section extending from the interior surface to the tip end.

Abstract: A system for inspecting features of an airframe, the system including a feature inspection device configured to measure an aspect of a first feature and a tracking subsystem configured to determine a position of the feature inspection device when the feature inspection device measures the aspect of the first feature. The system is configured to determine a position of the first feature on the airframe via the feature inspection device and the tracking subsystem, the determination of the position of the first feature being independent from the measurement of the aspect of the first feature.

Abstract: A system for inspecting features of an airframe, the system including a feature inspection device configured to measure an aspect of a first feature and a tracking subsystem configured to determine a position of the feature inspection device when the feature inspection device measures the aspect of the first feature. The system is configured to determine a position of the first feature on the airframe via the feature inspection device and the tracking subsystem, the determination of the position of the first feature being independent from the measurement of the aspect of the first feature.

Abstract: An engine support mount including an airframe structure having a first anchor surface and a length extending along an x-axis, with a second axis defined perpendicularly to the x-axis. A support member is fixed to the airframe structure and defines a first aperture and a second aperture. A mounting assembly includes an elongated arm and first and second primary attachment assemblies respectively attaching the arm to the support member at the first and second apertures, the arm having a second anchor surface. A moment arm reduction feature includes a lug fixed to one of the anchor surfaces and a corresponding fastener fixed to the other of the anchor surfaces. The first anchor surface is positioned on the airframe structure outside of the first and second apertures, and the second anchor surface is positioned on the arm outside of the first and second attachment assemblies.