Abstract: A window assembly and method for its installation is provided. The window assembly may include multiple transparent panels covering an opening of an aircraft fuselage. A clip member may be utilized to secure one or more of the transparent panels in place. The clip member may be slideably disposed against a retainer member, and may be adapted to lock in place relative to the retainer member in engaged and disengaged positions.

Abstract: 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.

Abstract: A method of installing a window panel in an aircraft. The method includes connecting upper and lower ends of the window panel with upper and lower longerons of the aircraft, and connecting a side end of the window panel with a hoop frame of the aircraft. This method makes it possible to eliminate heavy window support structures and to provide continuous hoop frame support members in an aircraft fuselage.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An apparatus is provided that includes a body having a first wall and a second wall, at least one appending structure extending from an end of the body and at least one actuator positioned between the first and second walls. The actuator includes first end coupled to a portion of the body and a second end coupled to a portion of the appending structure. At least one shape memory alloy (SMA) wire is connected to and extends between the first and second ends of the actuator. The SMA wire is adapted to controllably constrict when activated by heat, whereby the constriction causes the appending structure to move from a first position to a second position.

Abstract: A floor panel assembly, system, and method for assembling a floor panel assembly and one or more floor beams are provided. A floor panel assembly may include a floor panel comprising a pair of opposed surfaces, wherein the floor panel includes at least one key hole slot defined in one of the opposed surfaces. The assembly also includes at least one seat track positioned between the opposed surfaces, wherein the seat track comprises at least one key hole slot defined therein that is substantially aligned with a respective key hole slot defined in the floor panel. In addition, the assembly includes at least one fastener assembly comprising a fastener configured to be positioned through a respective key hole slot defined in the floor panel and the seat track.

Abstract: A floor beam assembly, system, and method for installing 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 and at least one floor beam bracket attached to a respective floor beam. The assembly also includes at least one pivot arm pivotally attached to the structure. In addition, the assembly includes a pad attached to the at least one pivot arm, wherein the at least one pivot arm is configured to pivot the pad to a position proximate to a respective floor beam bracket to be attached thereto.

Abstract: An apparatus is provided that includes a body having a first wall and a second wall, at least one appending structure extending from an end of the body and at least one actuator positioned between the first and second walls. The actuator includes first end coupled to a portion of the body and a second end coupled to a portion of the appending structure. At least one shape memory alloy (SMA) wire is connected to and extends between the first and second ends of the actuator. The SMA wire is adapted to controllably constrict when activated by heat, whereby the constriction causes the appending structure to move from a first position to a second position.

Abstract: In an embodiment, a drill nozzle includes a housing having a bristle brush ring attached. The housing of the drill nozzle may include an air intake, multiple coolant inlets, multiple coolant jets, a vacuum tube, and mounting flanges. The air intake may provide a thrust-vectored down draft into the vacuum tube. The coolant inlets may receive coolant fluid that may be expelled from the coolant jets towards a drill bit. Drilling debris and coolant fluid may be contained inside the bristle brush ring preventing damage and soiling of surrounding structures and areas and may be extracted with the vacuum tube. The drill nozzle may be attached to a drill motor unit of a numerically controlled drill jig, enabling the use of such numerically controlled drill jig for drilling high quality holes effectively into non-flat surfaces, for example, the leading edge extension spar of the F-18 aircraft.

Abstract: A window assembly for an aircraft fuselage comprises an exterior transparent panel and an interior transparent panel positioned in an opening of the fuselage. At least one of the transparent panels may be relatively lightweight and the exterior transparent panel may be spaced apart from and in overlying relationship with the interior transparent panel. To ameliorate pressure build up in the spaced apart area, a pressure modulator, such as a vent, may be provided.

Abstract: Methods for performing surface lapping using a robotic system are provided. In one embodiment, a method for lapping a surface includes providing a lapping assembly having a first base coupled to a second base by a flexible coupling member, and a lapping medium coupled to the second base, the flexible coupling member being configured to flex to allow the lapping medium to at least partially conform to the surface. The lapping medium is moveably applied to the surface using the lapping assembly. In another embodiment, the method further includes pneumatically controlling a pressure applied by the lapping medium to the surface using a pneumatic device operatively coupled to the second base.

Abstract: In one preferred embodiment, a structure is provided that includes a body having a first wall and a second wall. At least one appending component extends from an end of the body and includes a first skin and second skin. The structure additionally includes at least one actuator positioned within a cavity formed in the body first wall and the appending component second skin. The actuator includes at least one shape memory alloy (SMA) wire adapted to constrict when activated to move the first skin of the appending component from a first position to a second position.

Abstract: A drill nozzle includes a housing having a bristle brush ring attached. The housing of the drill nozzle may include an air intake, multiple coolant inlets, multiple coolant jets, a vacuum tube, and mounting flanges. The air intake may provide a thrust-vectored down draft into the vacuum tube. The coolant inlets may receive coolant fluid that may be expelled from the coolant jets towards a drill bit. Drilling debris and coolant fluid may be contained inside the bristle brush ring preventing damage and soiling of surrounding structures and areas and may be extracted with the vacuum tube. The drill nozzle may be attached to a drill motor unit of a numerically controlled drill jig, enabling the use of such numerically controlled drill jig for drilling high quality holes effectively into non-flat surfaces, for example, the leading edge extension spar of the F-18 aircraft.