B/E Aerospace Patente

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A self-disinfecting partition system is disclosed. The system includes a housing, and an attachment element configured to attach the housing (104) to a surface. The system further includes one or more arms (304a, 304b) configured to deploy from a stored position an extended position. The system further includes a flexible screen (106) coupled to the one or more arms configured to restrict a transmission of microbes. The system further includes a retraction assembly configured to retract the flexible screen into the housing. The system further includes an electromagnetic energy source (216) disposed within the housing configured to emits disinfecting electromagnetic energy onto the flexible screen. A second self-disinfecting partition system is disclosed that includes a housing configured to fit around the headrest and/or seatback of a passenger seat. The system further includes an accordion-folded flexible screen coupled to the housing that deploys from the housing and disinfected via electromagnetic energy.

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A low pressure enclosure (LPE) vehicle can include a hull (101) defining a cabin therein. The hull (101) can be configured to travel within a LPE and the cabin can be configured to be pressurized. The LPE vehicle can include a supplemental oxygen system configured to be activated and/or made accessible to one or more occupants within the cabin in a depressurized state such that a cabin pressure is less than a threshold cabin pressure.

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A construction of commercial aircraft interior monument employs carbon fiber Spread Tow Fabric (STF) as face sheets (skins) surrounding a paper honeycomb or foam core to produce flat pressed panels of high strength and desirable thickness. Each individual panel is joined with other panels to construct a modular rectangular cubic able to be modularly coupled with additional structures to form the aircraft monument. The use individual STF panels offer a desirable weight and footprint of a fabricated structure as a whole. Also usable in conjunction with other composite reinforcements, the individual STF panels produce hybrid lay-ups for both pressed flat panel and tooled composite moldings offering a high strength to weight ratio of the overall monument.

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An additively manufactured strut device including a cylinder body (102) forming a chamber and a piston (108) having a first part disposed in the internal chamber and a second part disposed outside of the chamber. A first deformable element (118) formed as a lattice structure breaks to permit initial withdrawal of the piston (108) when a tensive threshold is met and a second deformable crushes during continued withdrawal of the piston (108). In further embodiments, a third deformable element formed as a lattice structure may be collocated with the second deformable element (122). The strut may be manufactured by an additive manufacturing process. Applications for the energy absorbing strut include aircraft seat frames among other applications.

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A system includes a connector bracket (104). The connector bracket (104) includes a first planar plate section (106-1) defined by a top first planar surface (108-1), a bottom first planar surface (118-1), and first side edges (110-1), wherein the first planar plate section (106-1) includes first holes (112-1) extending between the top first planar surface (108-1) and the bottom first planar surface (118-1). The connector bracket (104) includes a second planar plate section (106-2) defined by a top second planar surface (108-2), a bottom second planar surface (118-2), and second side edges (110-2), wherein the second planar plate section (106-2) includes second holes (112-2) extending between the top second planar surface (108-2) and the bottom second planar surface (118-2). The connector bracket (104) includes a groove section (114) connected between the first planar plate section (106-1) and the second planar plate section (106-2), wherein the groove section (114) is defined by a groove (116) that drops below the top first planar surface (108-1) and the top second planar surface (108-2).

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An illuminated handle (100;200;800) mounted to a surface of a crew work area includes an illuminated portion is disposed on an interior surface. A structural portion (102;202;802;902;1001;1602;1702) is integrated into work area stowage compartments, disposed between two stowage compartments, such that the illuminated portion illuminates the stowage compartments and their contents when opened. The illuminated handle includes an illuminated coat hook (906;1010;1708) protrusion extending from a top portion of the illuminated handle. The illuminated portion of the illuminated coat hook is disposed on an interior surface to further illuminate the stowage compartments and indicate the location of the illuminated coat hook, while the hook extension prevents the illuminated portion from directly illuminating a crew member's face and potentially blinding the crew member momentarily.

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A multi-panel system is disclosed. The multi-panel system includes a drive panel (104) coupled to an actuator and a follower panel coupled to the drive panel (104) via a first latch rotatably coupled to the follower panel. The drive panel (104) and the follower panel translate along a guide rail (300, 304) configured with a latch keeper at a latch position. The drive panel (104) and follower panel are initially stored substantially superposed to each other. Upon translating the drive panel (104) toward a final position, the first latch is configured to couple the first follower panel to the drive panel (104) when the drive panel (104) is translated from the stored position, and 1) couple to the first latch keeper, and 2) uncouple the first follower panel from the drive panel (104) when the first follower panel has translated to the first latch position.

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An aircraft seat may include an integrated control panel (114) at least partially embedded within an armrest of the aircraft seat. The integrated aircraft seat control panel (114) may include at least one signal path for communicatively coupling the user interface device (202) to at least one component of the aircraft seat. The user interface device (202) may generate signals for at least one control function of the at least one component following an input being received. The integrated aircraft seat control panel may include a textile covering coupled to the armrest and positioned above the user interface device, the textile covering including a plurality of icons configured to indicate the location of the at least one control function on a respective portion of the user interface device. At least one icon is configured to illuminate following a receipt by at least one of a power signal or a light source output.