| Patent application number | Description | Published |
|---|
| 20080213034 | Swivel fitting attachment apparatus - An exemplary, non-limiting swivel fitting attachment apparatus includes a ball fitting and a swivel fitting. The ball fitting includes a base having an attachment portion, such as a flange, arranged for attachment to a structure and a ball attachable to the base. The ball may be removably attachable or fixedly attached to the base. The swivel fitting has a first end having a socket portion that is arranged to receive the ball therein and a second end having an attachment portion that is arranged for attachment to an object. The socket portion of the swivel fitting may be expandable and closeable over the ball, and may include first and second socket portion members that are urgeable toward and away from each other. The second end of the swivel fitting may be couplable to a clevis fitting. | 09-04-2008 |
| 20080216336 | In-Process Non-Contact Measuring Systems and Methods for Automated Lapping Systems - In-process non-contact measurement systems and methods for automated lapping systems are disclosed. In an embodiment, a moveable frame can be controllably positioned proximate to a lapped work product. A control component can provide first control signals to control a movement of the moveable frame relative to the lapped work product. A non-contact measuring device can be coupled to the moveable frame measures a surface of the lapped work product and can transmit measurement data of the surface of the lapped work product to the control component. The control component can further provide second control signals to control a movement of the non-contact measuring device relative to the moveable frame. | 09-11-2008 |
| 20080217479 | Window installation method and apparatus - An exemplary window frame assembly includes a window frame and spring clips. The window frame includes a window frame body, and flanges extend from the window frame body. The spring clips are removably attachable to the flanges. Each flange may define at least one first locking member and each spring clip may define at least one second locking member configured to engage the first locking member. For example, the at least one first locking member may include saw tooth grooves and the at least one second locking member may include a pair of angled tabs. As another example, the at least one first locking member may include a pair of angled tabs and the at least one second locking member may include saw tooth grooves. Each spring clip may further define a release mechanism, such as a tab, that is configured to disengage the spring clip and the flange. | 09-11-2008 |
| 20080241765 | METHODS AND SYSTEMS FOR PROVIDING DIRECT MANUFACTURED INTERCONNECTING ASSEMBLIES - A system of interconnecting structures fabricated utilizing an additive manufacturing process is described. The system includes a first component comprising a first unit of an interconnection mechanism, and a second component comprising a second unit of an interconnection mechanism. The first component and first unit are integrally formed utilizing the additive manufacturing process as are the second component and the second unit. The first unit and the second unit are operable to engage one another to attach the first component to the second component. | 10-02-2008 |
| 20080243455 | METHODS FOR SYSTEM COMPONENT INSTALLATION UTILIZING DIRECT MANUFACTURED COMPONENTS - A method for fabricating a structure to include at least a portion of a conduit retention system is described. The method includes receiving parameters for the structure and the portion of the conduit retention system associated with the structure via a user interface, providing the parameters to a machine configured to fabricate the structure and incorporate the portion of the conduit retention system, the machine using a direct manufacturing process, and operating the machine to integrally fabricate the structure and the portion of the conduit retention system. | 10-02-2008 |
| 20090078822 | LANDING GEAR SYSTEM AND LOAD DISTRIBUTION - In one embodiment, an aircraft comprises a plurality of hoop frame support members and a landing gear enclosure comprising a curved surface. The plurality of hoop frame support members abut against and extend over the curved surface to provide support to the landing gear enclosure. In another embodiment, loads are transferred from a landing gear strut through a strut fitting, through at least one inner surface of the landing gear enclosure, through at least one outer surface of the landing gear enclosure, and into the plurality of hoop frame support members. | 03-26-2009 |
| 20090078823 | Aircraft nose landing gear enclosure - In one embodiment, an aircraft comprises a plurality of hoop frame support members and a landing gear enclosure comprising a curved surface. The plurality of support frame support members abut against and extend over the curved surface to provide support to the landing gear enclosure. In another embodiment, loads are transferred from a landing gear strut through a strut fitting, through at least one inner surface of the landing gear enclosure, through at least one outer surface of the landing gear enclosure, and into the plurality of hoop frame support members. | 03-26-2009 |
| 20090123225 | DETERMINANT ASSEMBLY FEATURES FOR VEHICLE STRUCTURES - A determinant assembly feature for a joint assembly and a method of assembly therefor. The joint assembly includes a structure and a web connected thereto. The structure includes a base, a pair of legs extending from the base to define a channel, and one or more location control receiving elements in either leg. The web includes a thickness control element and one or more location control elements correspondingly matched to the location control receiving elements. The method includes providing a structure comprising a base, a pair of legs extending from the base to define a channel and one or more location control receiving elements in either leg; providing a web comprising one or more location control elements and a thickness control element; and inserting the web into the structure, wherein the one or more location control elements is correspondingly matched to the one or more location control receiving elements. | 05-14-2009 |
| 20090218445 | AIRFRAME ATTACHMENT FITTING - An airframe attachment fitting includes a fitting base having a base attachment surface and a flange attachment surface, at least one attachment post extending from the base attachment surface of the fitting base and at least one attachment flange carried by the flange attachment surface of the fitting base. An aircraft fuselage and a method of attaching a system or subsystem component to an airframe are also disclosed. | 09-03-2009 |
| 20090218777 | TIE ROD ASSEMBLY - A tie rod assembly includes a composite tie rod shaft having a first end and a second end, a first clevis carried by the first end of the tie rod shaft, a clevis adjustment collar carried by the second end of the tie rod shaft and a second clevis carried by and adjustable along the clevis adjustment collar. A method of connecting a fitting to a shaft is also disclosed. | 09-03-2009 |
| 20090236472 | TRUSS NETWORK FOR AIRCRAFT FLOOR ATTACHMENT - A truss network for aircraft floor attachment includes an aircraft fuselage, an aircraft floor disposed in the aircraft fuselage and a three-dimensional truss network comprising at least two truss assemblies each comprising a plurality of tie rod assemblies connecting the aircraft fuselage to the aircraft floor. A method of attaching a floor structure to a honeycomb fuselage structure and an aircraft having a truss network connecting an aircraft fuselage to an aircraft floor are also disclosed. | 09-24-2009 |
| 20090283649 | Utility Brackets for Securing Components to Structures - Utility brackets for attaching system components (e.g. wires or wire bundles) to structures are provided. The utility bracket includes a first portion that supports a product and a second portion for adhering to a support structure. The second portion includes a separation component that separates the second portion from the support structure by a predefined amount. The separation component includes a plurality of ridges or dimples for allowing even application of an adhesive. A nut plate or wire ties secure the product to the first portion. The second portion can include a base plate that is rotatably coupled to the first portion. The bracket can be formed by a molding or extruding process. | 11-19-2009 |
| 20100011777 | MORPHING STRUCTURE AND METHOD - A method of controlling mixing of a flow exiting a nozzle associated with a jet engine. The method may involve pivotally supporting a mixing structure forming a hinge device at a downstream edge of the nozzle. A shape memory alloy (SMA) element may be used to couple to the mixing structure. Heat may be generated by a flow exiting the nozzle to induce a phase change in the SMA element. The phase change may cause an axial length of the SMA element to constrict, to cause a pivoting movement of the mixing structure into a path of the flow exiting the nozzle. | 01-21-2010 |
| 20100029189 | METHODS FOR STIFFENING THIN WALL DIRECT MANUFACTURED STRUCTURES - A method for manufacturing a wall of a thin-walled structure is described. The method includes receiving parameters for the wall and one or more stiffening features associated with the wall via a user interface, providing the parameters to a machine configured to fabricate the wall and incorporate the one or more stiffening features, the machine using a direct manufacturing process and operating the machine to integrally fabricate the wall and the one or more stiffening features. | 02-04-2010 |
| 20100065688 | METHOD AND APPARATUS FOR REINFORCING COMPOSITE STRUCTURES - A computer implemented method and apparatus for creating a structural joint for an aircraft. A first composite component and a second composite component are co-joined to form the structural joint for the aircraft. A hole through the first composite component and the second composite component is created. A composite shear pin is placed through the hole. A composite collar is bonded to the composite shear pin with an adhesive. | 03-18-2010 |
| 20100126101 | FLOOR BEAM SUPPORT ASSEMBLY, SYSTEM, AND ASSOCIATED METHOD - A floor beam assembly, system, and method for supporting floor beams within a structure are provided. According to one embodiment, a floor beam assembly for installing a floor beam within a structure is provided. The assembly includes at least one floor beam, wherein at least a portion of each floor beam comprises a composite material. The assembly also includes at least one support bracket attached to a structure, wherein each support bracket is configured to support at least a portion of a floor beam thereon. In addition, the assembly includes at least one conductive element extending from the at least one support bracket and configured for electrically communicating with the at least one support bracket. | 05-27-2010 |
| 20100133387 | SHAPE CHANGING AIRFOIL SYSTEM - A method and apparatus for an airfoil, a flexible skin, and a shape control system. The flexible skin forms a control surface of the airfoil. The shape control system is capable of changing a shape of the control surface formed by the flexible skin between a plurality of shapes, wherein a gap does not occur during a changing of the shape of the control surface. | 06-03-2010 |
| 20110024564 | INJECTION-MOLDED WINDOW PANEL AND RELATED METHODS - A window panel adapted for installation relative to a structure. The panel includes a single piece of generally transparent injection-molded material configured to span one or more openings in the structure. The panel has panel attachment inserts for attaching the panel relative to the structure. The inserts are embedded in the material alongside at least one edge of the panel. The panel has a curvature that essentially continues a curvature of the structure surrounding the opening(s) when the panel is installed relative to the structure. This panel can be single-pane and can provide an essentially continuous window along an aircraft fuselage. | 02-03-2011 |
| 20110123254 | Determinant Assembly Features for Vehicle Structures - A determinant assembly feature for a joint assembly and a method of assembly therefor. The joint assembly includes a structure and a web connected thereto. The structure includes a base, a pair of legs extending from the base to define a channel, and one or more location control receiving elements in either leg. The web includes a thickness control element and one or more location control elements correspondingly matched to the location control receiving elements. The method includes providing a structure comprising a base, a pair of legs extending from the base to define a channel and one or more location control receiving elements in either leg; providing a web comprising one or more location control elements and a thickness control element; and inserting the web into the structure, wherein the one or more location control elements is correspondingly matched to the one or more location control receiving elements. | 05-26-2011 |
| 20120151899 | MORPHING STRUCTURE AND METHOD - A method of controlling mixing of a flow exiting a downstream end of a primary nozzle associated with a jet engine. The method may involve coupling a shape memory alloy (SMA) element to a mixing structure disposed at the downstream edge of the primary nozzle. An electrical signal may be applied to the SMA element to heat the SMA element and induce a phase change in the SMA element. The phase change may cause an axial length of the SMA element to constrict, to cause movement of the mixing structure into a path of the flow exiting the primary nozzle. | 06-21-2012 |
