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).
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).
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).
B23K 26/38 - Removing material by boring or cutting
B23K 26/40 - Removing material taking account of the properties of the material involved
B26D 5/34 - Arrangements for operating and controlling machines or devices for cutting, cutting-out, stamping-out, punching, perforating, or severing by means other than cutting with interrelated action between the cutting member and work feed having the cutting member controlled by scanning a record carrier scanning being effected by a photosensitive device
G05B 19/18 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form
G05B 19/402 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by control arrangements for positioning, e.g. centring a tool relative to a hole in the workpiece, additional detection means to correct position
G05B 19/4093 - Numerical control [NC], i.e. automatically operating machines, in particular machine tools, e.g. in a manufacturing environment, so as to execute positioning, movement or co-ordinated operations by means of programme data in numerical form characterised by part programming, e.g. entry of geometrical information as taken from a technical drawing, combining this with machining and material information to obtain control information, named part programme, for the NC machine
4.
ASYNCHRONOUS TENDERING FOR VARIABLE CHARACTERISTIC ASSETS
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.
G06Q 30/06 - Buying, selling or leasing transactions
G06Q 10/04 - Forecasting or optimisation specially adapted for administrative or management purposes, e.g. linear programming or "cutting stock problem"
A bonding method includes vacuum bagging a second metal plate (12) atop a first metal plate (10), with a thermosetting adhesive (16) in a lap joint (22) therebetween covered in turn by a porous peel ply (28) and a porous breather ply (30); the plates (10, 12) being initially clamped together by applying vacuum through the breather ply (30); and thermally curing the adhesive (16), with the breather and peel plies (30,28) being preselected to capture adhesive seepage (38) from the lap joint (22) and removed with the plies (28,30) to correspondingly reduce cured adhesive flash (40).
B23K 37/08 - Auxiliary devices or processes, not specially adapted for a procedure covered by only one of the other main groups of this subclass for flash removal
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
B32B 15/092 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin comprising epoxy resins
A hybrid frame (18) is fabricated by initially forming a stack of fibrous layers (8) in an annular pattern. An annular metal trim (54) is separately formed to conform with the annular pattern. The trim (54) is trapped in a lower mold (70) having a complementary lower mold channel (74). The stacked layers (8) are trapped atop the trim (54) in the lower mold channel (74). An upper mold (72) is pressed atop the stacked layers (8) for compression co-molding together in the lower mold (74) the stacked layers (8) and trim (54) to co-form the hybrid frame (18).
A thrust reverser nozzle (22) for an engine nacelle (20) includes opposite and asymmetrically pivoting first and second doors (24,26) defining a nacelle aft section (20a), first and second trailing edges (24a, 26a) of the first and second doors (24,26) adjacent to an outlet (28) of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge (24a) is positioned behind the second trailing edge (26a) when the doors are in the deployed position, and the first and second fairings (34,36) attached to the first and second doors in relative fixed positions to the first and second doors respectively Male contour middle portions (38) of the first fairings (34) may complementarily match female contour middle portions (40) of the second fairings (36) and are received within the female contour middle portion when the doors are in the stowed position.
A pair of laminated panels (40) are simultaneously manufactured in a single panel press (10). A thermal band (32) is stacked between two panel sets (42) and then the two panel sets (42) are simultaneously heated and compressed together in a common stack (44) with the band (32), with the band (32) being separately heated.
An erosion shield (54) for an aircraft window (12) includes an annular band (56) having a radially outer brim (58) and a radially inner clip (60). The shield (54) is sized to cover a composite window frame (18) having an outer rim (22) and an inner sash (24) around a central aperture (26) in which is mounted a window pane (20). The clip (60) is asymmetrical around the central aperture (26) to protect the sash (24) and permit assembly of the shield (54) thereto.
An aircraft window frame (18) includes a laminated outer rim (22) and inner sash (24) having a central aperture (26) for receiving a window pane (20). The sash (24) is transversely offset from the rim (22) and they include different layers (1-7) between the opposite inboard and outboard sides (28,20) of the frame (18).
A bonding method includes vacuum bagging a second metal plate (12) atop a first metal plate (10), with a thermosetting adhesive (16) in a lap joint (22) therebetween covered in turn by a porous peel ply (28) and a porous breather ply (30); the plates (10, 12) being initially clamped together by applying vacuum through the breather ply (30); and thermally curing the adhesive (16), with the breather and peel plies (30,28) being preselected to capture adhesive seepage (38) from the lap joint (22) and removed with the plies (28,30) to correspondingly reduce cured adhesive flash (40).
B23K 37/08 - Auxiliary devices or processes, not specially adapted for a procedure covered by only one of the other main groups of this subclass for flash removal
B32B 15/04 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance
B32B 15/092 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin comprising epoxy resins
A thrust reverser nozzle (22) for an engine nacelle (20) includes opposite and asymmetrically pivoting first and second doors (24,26) defining a nacelle aft section (20a), first and second trailing edges (24a, 26a) of the first and second doors (24,26) adjacent to an outlet (28) of the nacelle, the doors being pivotable simultaneously between a stowed position and a deployed position such that the first trailing edge (24a) is positioned behind the second trailing edge (26a) when the doors are in the deployed position, and the first and second fairings (34,36) attached to the first and second doors in relative fixed positions to the first and second doors respectively Male contour middle portions (38) of the first fairings (34) may complementarily match female contour middle portions (40) of the second fairings (36) and are received within the female contour middle portion when the doors are in the stowed position.
An erosion shield (54) for an aircraft window (12) includes an annular band (56) having a radially outer brim (58) and a radially inner clip (60). The shield (54) is sized to cover a composite window frame (18) having an outer rim (22) and an inner sash (24) around a central aperture (26) in which is mounted a window pane (20). The clip (60) is asymmetrical around the central aperture (26) to protect the sash (24) and permit assembly of the shield (54) thereto.
