Abstract: A rectification structure body 100 of a flying vehicle is provided with a rectification section 30, a heat input control section 20 and a vacuum thermal insulation section 10. The rectification section 30 has a rectification surface 30a and a back surface 30b. The rectification surface 30a rectifies airflow 5 from a travelling direction. The back surface 30b is arranged opposite to the rectification surface 30a. The heat input control section 20 is connected to the back surface 30b. The vacuum thermal insulation section 10 is connected to the heat input control section 20 and its surface is formed of rigid body. In addition, the heat input control section 20 is sandwiched between the back surface 30b and the vacuum thermal insulation section 10.

Abstract: A method of joining first and second layers of polymeric composite material includes disposing a portion of a molded insert having a bottom end into a top surface of a first layer of material and then applying a layer of adhesive between the top surface of the first layer and a bottom surface of a second layer of material to create a bond-line thickness. Next, a top surface of the second layer is pierced with a headless end of a fastener and interlocked into the molded insert. A layer of protective coating is then applied to the top surface of the second layer of material to cover the interlocked fastener.

Abstract: The present disclosure relates to inserts for use with sandwich panels, such as composite panels, and related methods. Presently disclosed inserts may include a retention feature and/or an anti-rotation feature that may be configured to retain the insert in place within a bore formed in the sandwich panel. In this manner, presently disclosed inserts may be secured without the use of adhesive compounds, which may increase efficiency and/or reduce costs in manufacturing apparatus that include one or more sandwich panels having one or more inserts placed therein. Presently disclosed methods of installing an insert into a sandwich panel may include rotating the insert with respect to the sandwich panel as the insert is installed, such that a portion of the insert may be positioned under the skin of the sandwich panel (e.g., a portion of the insert may be positioned between the skin and the core of the sandwich panel).

Abstract: A fastening resin structure includes a preformed resin member, a fastener-receiving part of metal configured to be fastened to another structure, the fastener-receiving part having a portion joined to the preformed resin member, a foam portion provided on and formed integrally with the portion of the fastener-receiving part which is joined to the preformed resin member, and a joining resin interposed between the preformed resin member and the foam portion and impregnated with the foam portion to thereby join the preformed resin member and the fastener-receiving part via the resin-impregnated foam portion.

Abstract: A method and apparatus for associating an edge of a first object with a second object using an insert. In one illustrative embodiment, an apparatus comprises a structure and a number of attachment features associated with the structure. The structure is configured to be inserted within a hollow portion of the first object at an edge of the first object. The structure is further configured to span an entire thickness of the first object at the edge of the first object. The number of attachment features is configured for use in attaching the second object to the structure to attach the second object to the edge of the first object.

Abstract: An internally threaded anchor for use in poured concrete floors having a metal deck or a wood form. The threaded anchor provides quick and easy attachment to threaded support rods that carry racks for utilities, piping, or ceiling grid systems. Each threaded anchor is capable of accepting different diameter rods or bolts with different thread cuts. Each anchor accepts the different diameter threaded rods by a single insertion motion, without the need to thread the rod into the anchor. Full insertion is visually verifiable when the marked end of the rod inserted into the anchor is no longer visible. An authentication tag visible upon full insertion indicates that authorized rod is being used.

Abstract: An apparatus for attaching a member to a honeycomb core-stiffened structure includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of a honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus. A honeycomb core-stiffened structure includes a honeycomb core and an apparatus for attaching a member to the honeycomb core. The apparatus includes a body and one or more elements extending from the body configured to be adhesively bonded to one or more walls of the honeycomb core of the honeycomb core-stiffened structure. The apparatus further includes a fitting for attaching the member to the apparatus.

Abstract: A method and apparatus for associating an edge of a first object with a second object. An insert comprising a structure holding a fastener element may be positioned within a hollow portion at the edge of the first object. The structure may be configured to span an entire thickness of the first object at the edge of the first object. The structure may be adhesively bonded to the first object. The second object may be attached to the edge of the first object using the fastener element.

Abstract: Substrates such as sheet metal components may be kept spaced apart from each other using a molded polymeric spacing device. The spacing device has a main body with a thickness corresponding to the desired minimum spacing between the substrates and, extending from the main body or a base connected to said main body, an attachment member capable of being inserted into an opening in one of the substrates, but resistant to being easily withdrawn from such opening. Noise and vibration that might otherwise be generated or propagated by closely proximate substrates are reduced through the use of such molded polymeric spacing devices, which may be integrally fashioned from a rubber.

Abstract: An insert is configured for anchoring within a cored panel and has a wide flange on one end, a sacrificial cover and threaded pin on its opposite end and a nut captured therein. The panel is prepared by forming a countersunk hole therein and filling or coating such opening with an adhesive. The insert is fitted into the hole such that the flange is positioned against one surface of the panel while the sacrificial cover and threaded pin protrude from the opposite surface. A screw fixture is threaded onto the threaded pin to maintain the insert in place while the adhesive cures. Subsequent removal of the screw fixture and sacrificial cover completes the anchoring process and exposes the nut that is captured within the insert for receipt of an appropriate fastener.

Abstract: A method of fabricating a panel (1) comprising a core (10) made of honeycomb material provided with a plurality of cells (13) and encased by top and bottom outer walls (20, 30), which method comprises, during a preparation stage (P1): fabricating the top outer wall (20); fabricating the bottom outer wall (30); fabricating said core (10), and perforating one internal orifice (11) per fastener element (50) in said core (10) so as to provide a space (12) for receiving said fastener element (50); and then coating at least one layer of a film of an intumescent adhesive (60) on a connection side wall (51) of said fastener element (50) that is to be connected to said core (10). After performing an assembly stage on a bench (70), the assembly comprising the top outer wall (20), the core (10) provided with said fastener element (50), and the bottom outer wall (30) is polymerized in order to obtain said panel (1) provided with said fastener element (50).

Abstract: A rear door structure in which a rear door is openably and closably provided on a rear portion of a vehicle body, including a door panel, wherein: the door panel includes an upper door panel and a lower door panel provided on the lower portion of the upper door panel; and a lower edge portion of the upper door panel and an upper edge portion of the lower door panel mutually overlap so as to form a lateral beam having a closed cross section and extending in a vehicle width direction.

Abstract: Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

Abstract: A molding-furnished glass in which a resin molding is integrally provided to the edge portion of a glass base. A metal molding is attached to the resin molding by connecting the metal molding to the resin molding through the use of a slide piece and a fastener.

Abstract: The present application is directed to systems for controlling the direction of thermal expansion of a composite part during thermal processing. The systems may comprise at least one guiding mechanism capable of being attached to a surface of a tool for fabricating composites and at least one moveable composite insert capable of being attached to a composite part. The moveable composite insert has an opening for receiving the at least one guiding mechanism. The opening is capable of controlling movement of the at least one moveable composite insert in a desired direction during thermal expansion of the composite part, when the guiding mechanism is received by the opening. Methods for controlling the direction of thermal expansion of a composite part during thermal processing are also disclosed.

Abstract: A rigging for moving an aircraft panel relative to an aircraft substructure includes a retaining base attached to a panel interior, and a slider rod held in contact with the substructure and adjustably engaged with the retaining base. The slider rod is manipulable from the panel exterior to adjustably engage the panel in a rigging position along a fair axis. The slider rod may include a tool appurtenance captively positioned within the riser bore that is exteriorly manipulable through a panel access port. Tool appurtenance manipulation may actuate the slider rod to adjustably engage the support hub and to move the panel into the fair position. A fit plate may be attached to the aircraft panel disposed intermediate to the retaining base, and may be adjustably attached to the aircraft panel for moving the aircraft panel into a fit position in a rigging plane.

Abstract: A floating stud assembly system of particular use in attaching insulating material to aircraft structures is described employing a stud extended through a hole in a plate. The plate comprises a pocket or cavity and an end of the stud is configured to reside in the pocket or cavity such that the stud is retained by the plate while still being allowed movement in a plane.

Abstract: A panel includes a core and a fastener receptacle extending into the core. The fastener receptacle has an internal hollow and an opening to the internal hollow. The opening is formed by a lip that can engage and structurally support a push-in fastener.

Abstract: The invention relates to a floor plate for bearing upon a floor framework in an aircraft. The floor framework is formed with a multiplicity of transverse beams which are arranged like a truss, and a multiplicity of longitudinal profiles, especially seat rail profiles, which extend transversely to the transverse beam. At least one sub-assembly, for example a kitchen module and/or a sanitary cell, can be fastened on the floor plate. The floor plate bears upon at least four longitudinal profiles and has at least one connecting point, especially an insert, for fastening of the sub-assembly. In addition, at least one system port is provided for the tool-less, pluggable connecting of the sub-assembly to any on-board systems of the aircraft, especially to electrical systems, to feed-air systems, to exhaust air systems, to fresh-water systems or to waste-water systems.

Abstract: A wall or roof of a trailer are formed from a first panel and a second panel which are joined together by a cap and a strip which interengage. The cap includes a base wall and an interlock provided thereon. The base wall abuts the outer surfaces of the panels. The strip includes a base wall and an interlock provided thereon. The strip and cap are separate members. The base wall of the strip abuts the inner surfaces of the panels. The interlock of the strip and the interlock of the cap mate together to form a joint. The interlocks extend between the panels. The panels may be composite panels or may be from a single sheet or multiple sheets of metal. An adhesive may be provided between the base wall of the cap and the outer surfaces, and an adhesive may be provided between the base wall of the strip and the inner surfaces.

Abstract: These disclosed embodiments relates to a device for fixing a light-weight panel onto a support. Such device includes an insert including at least one flange, such insert being intended for receiving a fixing device of the bolt type. According to the disclosed embodiments, such flange has an outer surface including toothing elements and the device includes a part made of a ductile material including an opening for the passage of the fixing member. The toothing element are intended for cooperating, upon fixing the panel onto the support, with the part made of a ductile material to allow such fixing without causing any deformation of the panel.

Abstract: A device and a method for fastening, clamping, or adjusting a molding part to a body-mounted part are provided. To allow the absorption of large tensile forces, a tensioning element designed as a tension strut is provided, which includes at least one oblong element made of fiber-reinforced plastic. The length of the tensioning element is adjustable between two end positions via a bracing device.

Abstract: Glass roof (1) with at least two glass covers (2, 3), the glass covers (2, 3) being formed with impact edges (6, 27) facing each other and there being a formed-on part (4) along a impact edge (6) on one glass cover (2), the formed-on part (4) extending away from the impact edge (6) below the glass cover (2) and, in order to seal the impact region between the two glass covers (2, 3), the formed-on part (4) accommodating a seal (16) adjacent to the impact edge (6), the seal (16) extending from an upper side wall (10) of the formation (4) in the direction of a lower side of the glass cover and, on the upper side, forming a supporting wall (21) for the second glass cover (3) and, in addition, there is at least one support (35) for the second glass cover (3) and the seal (16), with the supporting wall (21) cut free from the sealing body, rests on the support (35) in such a manner that an intermediate layer is formed between the second glass cover (3) and the support (35).

Abstract: Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

Abstract: A heat shield suitable for motor vehicles and a method for manufacturing the heat shield is provided. The heat shield is intended to protect temperature-sensitive assemblies, components and connection lines from the direct impact of heat radiation and, possibly, acts as insulation. Moreover, the heat shield may also provide advantageous soundproofing properties. The heat shield is comprised of first and second plates that are at least partially deformable and an insulating material positioned between said plates. Preferably, at least a portion of said insulating material is in the form of compacted powder or flakes.

Abstract: A method of installing an insert in a sandwich panel for mounting a fastener includes making a hole in the panel and inserting a spacer having a height greater than the thickness of the panel. An entrance rim of the spacer extends above an upper surface of the panel and a setting tool exerts a force on the entrance rim to force it into the hole and to position an upper edge of the entrance rim flush with the panel surface. The spacer can include an annular groove on an interior wall of the entrance rim to facilitate the cold working deformation during an installation in the panel and a hole engaging surface to align and maintain the spacer within the hole. An outer exterior surface of the entrance rim can be indented and coated with a first sealing compound to ensure a watertight seal with the panel. A second sealant material can be provided within the entrance rim for sealing with a head of any fastener extending through the spacer. An improved floor panel with spacer is accordingly provided for aircraft.

Abstract: A construction is provided for fastening a plurality of members which thermally expand and contract together to a base member with a screw member, in such a manner that those members do not interfere with each other when they thermally expand or contract. An interference that would otherwise be generated between a plurality of members to be fastened together when the respective members thermally expand and contract can be prevented with a simple construction by interposing an interference preventing spacer member between the respective members. The spacer member is positioned in a radial direction relative to a screw portion. With one member, the fastened portion where the members are fastened together functions as a reference point for absorbing the thermal expansion and contraction. With the other member, an elongate hole is used at this fastened portion for absorbing the thermal expansion and contraction. Accordingly, the single fastened portion allows fastening corresponding to the respective members.

Abstract: A method of installing an insert in a sandwich panel for mounting a fastener includes making a hole in the panel and inserting a spacer having a height greater than the thickness of the panel. An entrance rim of the spacer extends above an upper surface of the panel and a setting tool exerts a force on the entrance rim to force it into the hole and to position an upper edge of the entrance rim flush with the panel surface. The spacer can include an annular groove on an interior wall of the entrance rim to facilitate the cold working deformation during an installation in the panel. An outer exterior surface of the entrance rim can be indented and coated with a first sealing compound to ensure a water-tight seal with the panel. A second sealant material can be provided within the entrance rim for sealing with a head of any fastener extending through the spacer. An improved floor panel with spacer is accordingly provided for aircraft.

Abstract: A hollow reinforced structural member has a bulkhead having a layer of thermally expanded resin disposed between opposed side walls. A sleeve is retained within the resin layer and is oriented perpendicular to the longitudinal axis of the reinforce structural member. The sleeve is an alignment with bolt holes in opposite sides of the reinforced structure such that a bolt can be inserted there through. A component can then be bolted to the reinforced structural member at the site of the reinforcement. The invention not only increases the strength of the part, but also reduces vibration and noise transmission.