Abstract: A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6, 7, 8) defining the outer skins (20,22).

Abstract: An aircraft seating module (20) includes a seating mount (26) having a horizontal mounting rail (28) integrally joined to a vertical mounting post (30) at an adjoining elbow (32). The rail (28) includes a mounting boss (34) longitudinally spaced from the post (30) for attachment to an aircraft cabin seat track (18). Both the rail (28) and post (30) include mounting holes (38) for attaching a passenger seat (22) and appended furniture (24) directly to the seating mount (26) and in turn indirectly to the seat track (18) in the cabin floor (12).

Abstract: Utilities that allow for the asynchronous tendering for variable characteristic assets. In one aspect, a utility for returning a strike price based on the iterative comparison of a received first listing object with a received first offer object, both corresponding to a first variable characteristic asset. At least one of the first listing object and the first offer object may include a time-dependent price such that the iterative comparison may facilitate the determination of a time-dependent price range corresponding to the variable characteristic asset at a given time. In this regard, the strike price may be returned at least partially based on the time-dependent price range. Additionally, the present disclosure includes embodiments related to the verification of a condition-dependent status of the first variable characteristic asset and a generation of comparison metrics associated with the asynchronous tendering.

Abstract: An aircraft seating module (20) includes a seating mount (26) having a horizontal mounting rail (28) integrally joined to a vertical mounting post (30) at an adjoining elbow (32). The rail (28) includes a mounting boss (34) longitudinally spaced from the post (30) for attachment to an aircraft cabin seat track (18). Both the rail (28) and post (30) include mounting holes (38) for attaching a passenger seat (22) and appended furniture (24) directly to the seating mount (26) and in turn indirectly to the seat track (18) in the cabin floor (12).

Abstract: A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

Abstract: A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

Abstract: A method of vending a product (n) in an automated vending machine (28) includes displaying an initial stock (S) of several products (n) on a display shelf (34), and identifying any product (13) removed therefrom by a customer (48) not by detecting the removed product (13) itself, but by comparing images (50,52) of the displayed stock (S) before and after product removal to determine any product (13) missing in the post-image (52) of remaining stock (S-(S-P)), and then charging payment for the missing product (13) to the customer (48).

Abstract: A radome assembly (20) includes a frame (30) conforming in contour with an aircraft fuselage (14) for being fixedly mounted thereto. A radome (32) having an aerodynamically streamlined elongate contour including a central bulb (34) is spaced from the frame (30) to house an antenna (26) therein, the radome (32) being tuned in configuration to define an unobstructed radio-frequency (RF) window (28) diverging outwardly from atop the frame (30). The radome (32) is pivotally mounted atop the frame (30) by a hinge (36,74,78) hidden inside the frame (30) below the RF window (28) when the radome (32) is stowed closed atop the frame (30) and antenna (26).

Abstract: A method of vending a product (n) in an automated vending machine (28) includes displaying an initial stock (S) of several products (n) on a display shelf (34), and identifying any product (13) removed therefrom by a customer (48) not by detecting the removed product (13) itself, but by comparing images (50,52) of the displayed stock (S) before and after product removal to determine any product (13) missing in the post-image (52) of remaining stock (S-(S-P)), and then charging payment for the missing product (13) to the customer (48).

Abstract: A method of machining a cellular core (14) includes mounting the core (14) atop a table (12) in a multi-axis Computerized Numerical Controlled (CNC) machine (10). The machine (10) is operated to self-scan the core (14) and self-recognize individual cells (30) arranged laterally in columns and longitudinally in rows. A machining path (E) is self-generated from the pre-recognized cells (30), and the core (14) is then machined along the self-generated machining path (E).

Abstract: A method of making an aircraft acoustic structural panel (10) begins with preforming a core honeycomb laminate (12) having preformed foam (3) bonded inside cells (14) thereof by a distinct adhesive (2). The preformed honeycomb laminate (12) is then stacked between opposite top and bottom structural outer laminates (16,18). The stacked honeycomb laminate (12) and outer structural laminates (16,18) are then compressed together under heat and pressure into a unitary structural panel (10) having the core honeycomb laminate (12) integrally bonded between outer skins (20,22). The outer laminates (16,18) may include imperforate acoustic septums (4) bounding the core honeycomb laminate (12) followed by an outer honeycomb (5) and structural fiber layers (6,7,8) defining the outer skins (20,22).

Abstract: A radome assembly (20) includes a frame (30) conforming in contour with an aircraft fuselage (14) for being fixedly mounted thereto. A radome (32) having an aerodynamically streamlined elongate contour including a central bulb (34) is spaced from the frame (30) to house an antenna (26) therein, the radome (32) being tuned in configuration to define an unobstructed radio-frequency (RF) window (28) diverging outwardly from atop the frame (30). The radome (32) is pivotally mounted atop the frame (30) by a hinge (36,74,78) hidden inside the frame (30) below the RF window (28) when the radome (32) is stowed closed atop the frame (30) and antenna (26).

Abstract: A method of machining a cellular core (14) includes mounting the core (14) atop a table (12) in a multi-axis Computerized Numerical Controlled (CNC) machine (10). The machine (10) is operated to self-scan the core (14) and self-recognize individual cells (30) arranged laterally in columns and longitudinally in rows. A machining path (E) is self-generated from the pre-recognized cells (30), and the core (14) is then machined along the self-generated machining path (E).

Abstract: A bonding method includes vacuum bagging a second metal plate atop a first metal plate, with a thermosetting adhesive in a lap joint therebetween covered in turn by a porous peel ply and a porous breather ply; the plates being initially clamped together by applying vacuum through the breather ply; and thermally curing the adhesive, with the breather and peel plies being preselected to capture adhesive seepage from the lap joint and removed with the plies to correspondingly reduce cured adhesive flash.

Abstract: A hybrid frame is fabricated by initially forming a stack of fibrous layers in an annular pattern. An annular metal trim is separately formed to conform with the annular pattern. The trim is trapped in a lower mold having a complementary lower mold channel. The stacked layers are trapped atop the trim in the lower mold channel. An upper mold is pressed atop the stacked layers for compression co-molding together in the lower mold the stacked layers and trim to co-form the hybrid frame.

Abstract: A pivot arrangement for a thrust reverser door of a gas turbine engine, the pivot fitting having a base and a shaft projecting from a main side of the base. The shaft receives a preferably curved pivot arm of the door to provide a low profile arrangement which improves performance when the doors are stowed.

Abstract: The thrust reverser comprises sections, such as arms and skins, which may be connected along joints to provide a thrust reverser body. A plurality of fittings may be integrally formed on a surface of each arm.

Abstract: A thrust reverser door provides in one aspect a separation of structural and aerodynamic functions through the provision of individual structures. In some embodiments, an aerodynamic element is adjustable in position, while in other embodiments, the relative positions are fixed. An exemplary aerodynamic element extends radially into the reverser flow to redirect the flow away from the door surface.

Abstract: A pair of laminated panels are simultaneously manufactured in a single panel press. A thermal band is stacked between two panel sets and then the two panel sets are simultaneously heated and compressed together in a common stack with the band, with the band being separately heated.

Abstract: A pair of laminated panels are simultaneously manufactured in a single panel press. A thermal band is stacked between two panel sets and then the two panel sets are simultaneously heated and compressed together in a common stack with the band, with the band being separately heated.