453results about "Fuselage bulkheads" patented technology

Methods and apparatus for determinant assembly support are disclosed. A disclosed example apparatus to support a panel component for determinant assembly thereof includes a support frame that is releasably couplable to a jig, a first clamp to support the panel component at a first position of the panel component, a first body of the first clamp or the support frame including a nominal clearance opening to receive a first fastener to operatively couple the first clamp to the support frame, and a second clamp to support the panel component at a second position of the panel component different from the first position, a second body of the second clamp or the support frame including a slotted opening to receive a second fastener to operatively couple the second clamp to the support frame, the second fastener movable about the slotted opening to enable the second clamp to reduce forces imparted to the panel component while held by the support frame.

A hydrogen aircraft includes: an airframe including a fuselage and a wing; at least one propulsion system fixed to the airframe; a pressurized chamber disposed inside the fuselage; a pressure bulkhead that is disposed at a rear part of the pressurized chamber and has strength to withstand pressurization of the pressurized chamber; a hydrogen tank that is disposed in an accommodation section and stores liquid hydrogen, the accommodation section being installed behind the pressure bulkhead, outside the pressurized chamber, and inside the fuselage; and a supply line that supplies the liquid hydrogen stored in the hydrogen tank to the propulsion system.

The invention belongs to the technical field of grating stiffened wall plates, and particularly relates to a grating stiffened wall plate for an aircraft structure and a forming mold and method.The grating stiffened wall plate comprises a grating frame, a skin plate is arranged on the grating frame, and the skin plate comprises an outer skin arranged on the bottom face of the grating frame and an inner skin arranged on the grating frame; the grille frame comprises a transverse rib core material and a longitudinal rib core material which are connected with each other, the inner skin is located between the transverse rib core material and the longitudinal rib core material, the connecting position between the transverse rib core material and the longitudinal rib core material is called as a connecting node, and each connecting node is provided with a forming block; the strength and the stability of the grating frame are effectively enhanced through the forming blocks. In addition, the transverse rib core materials and the longitudinal rib core materials are tightly fixed through flanging wrapping of the inner skin, and therefore the strength and the structural efficiency of the grating stiffened wall plate are remarkably improved. And the unique requirements of aircraft wall plate structures such as airplanes and the like on the aspects of transmitting and bearing large loads are met.

Aerogels comprising a hydrophobic polyimide moiety, including hydrophobic polyimide aerogels, as well as methods of manufacture and applications thereof, are generally described.

The present disclosure provides a battery load support structure of a fuselage, the battery load support structure including a battery mount support formed in a longitudinal direction of a floor frame of the fuselage, a battery unit inputted into an opened lower side of the floor frame and fastened to the battery mount support, and a joint unit configured to support the battery mount support and connected to a plurality of framework members that constitutes the floor frame.

An aircraft structure part having a stacked arrangement of layers with the layers being one of an at least first doubler and a basic layer of the outer skin of an aircraft fuselage, with the first doubler and the basic layer being bonded by a first intermediate bond film layer to form a step-shaped configuration of the aircraft structure part, wherein the first doubler includes a first fiber prepreg layer, in particular glass fiber prepreg layer, arranged at the perimeter of the first doubler and wherein the first fiber prepreg layer is bonded to the basic layer by at least one first bond-film segment deposited adjacent to the first fiber prepreg layer in a first wedge-shaped element at least partially incorporating the first fiber prepreg layer. A method is disclosed for providing an aircraft structure part and an aircraft fuselage provided with the aircraft structure part.

The utility model belongs to the technical field of aviation structure design, and relates to a fuselage external protruding component reinforcing structure which is characterized in that two combined frames and two combined longitudinal pieces form a box section combined piece; and the box section assembly is fixedly connected with the fuselage skin. The reinforcing structure is used for the fuselage external protruding component fuselage, and overcomes the defects that a traditional supporting structure is poor in bearing capacity, low in rigidity, large in weight, poor in manufacturability and the like.

An aircraft structure including an outer mold line skin, one or more frames located on an inner surface of the outer mold line skin having an outer flange attached to an inner surface of the outer mold line skin, a first core filler in contact with the outer flange, an inner flange in contact with the first core filler and a web skin, wherein the web skin and the outer flange encapsulate the inner flange and at least a portion of the first core filler, and an arched inner mold line skin located between each frame of the one or more frames, wherein the arched inner mold line skin is in contact with each web skin of the one or more web skins.

A variable fuselage fuel tank structure of a high-speed aircraft comprises a fuselage fixing structure, an external flexible heat insulation skin and an internal skin bearing framework. The machine body fixing structure comprises a lower wall plate and an upper wall plate; the edges of the lower wall plate and the upper wall plate are connected, and the upper wall plate is provided with a fuel circulating hole; the outer flexible heat insulation skin is connected with the edge of the upper wall plate; the external flexible heat-insulating skin comprises a flexible fabric heat-proof outer layer and a microporous aerogel heat-insulating inner layer; the inner skin bearing framework is connected to the inner side of the outer flexible heat insulation skin and comprises reinforcing longitudinal beams, elastic elements and high-temperature-resistant rubber. The longitudinal beams are connected to the inner side of the outer flexible heat insulation skin in the longitudinal direction. A plurality of groups of elastic elements are respectively connected between two adjacent longitudinal beams, are distributed along the longitudinal direction, and are connected to the inner side of the external flexible heat insulation skin; and the high-temperature-resistant rubber is filled between the longitudinal beam and the elastic element, is filled in the elastic element and is adhered to the inner side of the external flexible heat-insulating skin.

The invention discloses a laser processing microstructure electric heating anti-icing and de-icing skin and a using method thereof.The laser processing microstructure electric heating anti-icing and de-icing skin comprises a skin body arranged on the surface of an airplane, the skin body comprises an electric heating microstructure anti-icing and de-icing skin body, a microstructure anti-icing and de-icing skin body and a common skin body, and the input end of the electric heating microstructure anti-icing and de-icing skin body is connected with an airborne power source through a wire; the electric heating micro-structure anti-icing and deicing skin is arranged on the windward side, with the maximum airflow collection coefficient, of the outer surface of the aircraft, the micro-structure anti-icing and deicing skin is arranged on the upstream and downstream of the windward side of the outer surface of the aircraft, and the common skin is arranged on other parts, except the electric heating micro-structure anti-icing and deicing skin and the micro-structure anti-icing and deicing skin, of the outer surface of the aircraft. According to the laser processing microstructure electric heating anti-icing and deicing skin and the using method thereof, through matched arrangement of the electric heating microstructure anti-icing and deicing skin and the microstructure anti-icing and deicing skin, the purposes of being good in anti-icing and deicing effect, low in energy consumption, light in weight and good in maintenance performance can be achieved.

This document describes a system that can be attached to the outer skin of a vehicle, such as an aircraft. A disclosed version of the system comprises an antenna component, a support frame, brackets, and an aerodynamic fairing. The antenna component is connected to the support frame, which has a plurality of clevis mounting features. Each support fitting can be coupled between one of the clevis mounting features and the outer skin of the vehicle. The fairing consists of an upper and a lower part. The upper part has a defined opening. The lower part is configured and arranged to connect to the outer skin of the vehicle. The opening is shaped and dimensioned to accommodate at least a portion of the support frame that is connected to the upper part of the fairing.

Methods and apparatus for determinant assembly support are disclosed. A disclosed example apparatus to support a panel component for determinant assembly thereof includes a support frame that is releasably couplable to a jig, a first clamp to support the panel component at a first position of the panel component, a first body of the first clamp or the support frame including a nominal clearance opening to receive a first fastener to operatively couple the first clamp to the support frame, and a second clamp to support the panel component at a second position of the panel component different from the first position, a second body of the second clamp or the support frame including a slotted opening to receive a second fastener to operatively couple the second clamp to the support frame, the second fastener movable about the slotted opening to enable the second clamp to reduce forces imparted to the panel component while held by the support frame.

The invention relates to the technical field of layered products, and particularly discloses a heat-insulating and wave-absorbing skin material as well as a preparation method and application thereof. The heat-insulating and wave-absorbing skin material is of an integrated layered structure based on an aluminum oxide-mullite system, comprising a functional gradient layer with double gradients of fiber density and aperture, an impedance matching layer with a gradient dielectric constant, a resonance wave absorbing layer with a periodic dot matrix formed by silicon carbide and aluminum oxide core-shell microspheres, and a heat insulation layer with a nano-micron double-scale pore structure. According to the preparation method, a green body is constructed mainly through tape casting and silk-screen printing, and then co-sintering integrated forming is carried out. The material has the excellent characteristics of high temperature resistance, toughness, efficient heat insulation, broadband wave absorption and the like, and is suitable for extreme environments such as hypersonic aircraft skin and the like.

The invention discloses a stringer assembly, a stiffened wall plate, a stiffened wall plate assembling method and an aircraft, and belongs to the technical field of aircraft manufacturing. The stringer assembly comprises a cap-shaped stringer and a forming die, the cap-shaped stringer comprises a stringer main body and a lap joint part, the stringer main body extends in the first direction and is provided with a cavity, the forming die comprises a containing part extending in the first direction, the containing part is provided with a containing groove, and the lap joint part is provided with a lap joint part. The containing groove extends in the first direction and is opened in one side of the second direction, the containing groove and the opening of the cavity face the same direction, the stringer body penetrates through the opening of the containing groove and is installed in the containing groove, the end, in the first direction, of the containing groove is closed, and the lap joint part is in lap joint with the forming mold. The cap-shaped stringer is blocked by the closed end of the containing groove of the containing part, it is guaranteed that the cap-shaped stringer cannot penetrate through the containing part and pass through the net size area in the skin, the influence on the surface quality of the skin is reduced, and the forming die cost is reduced.

An aircraft including a blended wing body aircraft (BWB) having a main body and wings with no clear demarcation between the wings and the main body along a leading edge of the aircraft, a rear spar located within the main body, one or more gear wells located on a lower surface of the rear spar, a landing gear system having at least a main gear the at least a main gear situated in one of the one or more gear wells, and one or more propulsors located directly above the one or more gear wells, wherein at least one propulsor is located over the at least one gear well of the one or more gear wells.

The invention provides a composite fuselage wall plate for an aircraft, which comprises a skin wall plate, a plurality of annular reinforcing frames distributed on the inner surface of the skin wall plate along the heading direction of the aircraft, and a plurality of segmented stringers positioned between the adjacent annular reinforcing frames and distributed along the annular direction of the aircraft, an annular local reinforcing part with a preset thickness is formed at the intersection position of the segmented stringer and the annular reinforcing frame on the inner surface of the skin wallboard, and the end part, extending in the heading direction, of the annular local reinforcing part is overlapped with the end part, close to the annular local reinforcing part, of the segmented stringer.

A partition includes, but is not limited to, a first body comprising a planar, foldable material. The partition further includes a plurality of anti-fold flat substrates. The partition further includes an adhesive. The substrates are adhered to the first body by the adhesive and are arranged in a repeating pattern defining a plurality of columns and rows. Each column and each row is spaced from its adjacent counterparts, defining longitudinal gaps between the columns and lateral gaps between the rows. The first body is folded laterally along the longitudinal gaps in an accordion-like manner and simultaneously folded longitudinally along the lateral gaps in an accordion-like manner. The partition contracts in both the lateral and longitudinal directions when the first body is simultaneously folded laterally and longitudinally. The partition extends in both the lateral and longitudinal directions when the first body is simultaneously unfolded laterally and longitudinally.

The invention provides a honeycomb sandwich wall plate structure and a preparation method thereof, the honeycomb sandwich wall plate structure comprises a first panel, a second panel, a honeycomb core layer, a honeycomb insert block, a heat insulation plate and a fastener, and the first panel and the second panel are oppositely arranged; the honeycomb core layer is arranged between the first panel and the second panel, one side of the honeycomb core layer is connected to the first panel, the other side of the honeycomb core layer is connected to the second panel, and embedded holes are formed in the honeycomb core layer; the honeycomb embedded blocks are arranged in the embedded holes and are connected to the honeycomb core layer; the heat insulation plate is arranged on the side, away from the second panel, of the first panel. And the fastener is connected with the heat insulation plate and the honeycomb insert block. The wallboard structure provided by the invention has the characteristics of high temperature resistance, vibration absorption, high durability, low cost and light weight.

The invention relates to a method for automated docking of a stationary part (1) with a movable part (2) capable of being moved towards the stationary part by a robot (3), the stationary part (1) and the movable part (2) each comprising an end (4, 5), the two ends forming a docking interface (6). The method comprises the steps of positioning of multiple profilometers around the docking interface so that the docking interface is located in the field of view of the profilometers, determination of a target profile of the end of the movable part, measurement of a profile of the end of the movable part by the profilometers, comparison of the target profile and the measured profile, generating a speed setpoint in the measurement space, and movement of the movable part towards the stationary part (1) by the robot (3) on the basis of this speed setpoint.

An integrated stringer panel for an aircraft, including a base panel comprising a sheet-like continuous part; and a stringer panel comprising a sheet-like continuous part, wherein the base panel is bonded to the stringer panel, wherein the stringer panel is corrugated to define two or more stringer channels, and one or more raised areas between the two or more stringer channels, and wherein the one or more raised areas include one or more openings to allow access to the base panel through the stringer panel.

The application provides a flat threshold maintenance passage structure and an operation method. The structure comprises a large opening reinforcing structure assembly 100, a quick-release floor assembly 200, a footboard assembly 300, a door frame assembly 400, a stepping reinforcing assembly 500, a mechanical support rod assembly 600, a bolt locking mechanism 700, a maintenance passage door 800, an external hinge 900 and a boarding handle 1000. The large opening reinforcing structure assembly 100 comprises an upper reinforcing horizontal piece 101, a lower reinforcing horizontal piece 102, a reinforcing front partition frame 103, a reinforcing rear partition frame 104, a horizontal piece outer flange 105, a stretching belt plate 106, an upper horizontal piece inner flange 107, a stretching belt plate 108, a lower horizontal piece inner flange 109, a counter-pulling angle box 110 and a counter-pulling angle piece 111. The quick-release floor assembly 200 comprises an upper panel 201, an aluminum honeycomb 202, a lower panel 203 and a bowl-shaped piece 204. The footboard assembly 300 comprises a foldable cantilever footboard 301, a locking mechanism 302, a bolt 303, a partition frame T-shaped outer flange 304, a support lug 305, a rib 306 and a stepping pedal 307. The door frame assembly 400 comprises a door frame 401 and a skin 402.

An air mobility apparatus and mobility apparatus having a door. The air mobility apparatus includes a fuselage having a first cabin and a second cabin; and a rear door having an inner door partitioning the first cabin and the second cabin, and an outer door partitioning the second cabin and an external space, wherein the inner door and the outer door are independently opened and closed.

This invention provides a hyperelastic flexible structure, forming tooling, and a method for fabricating the hyperelastic flexible structure. The hyperelastic flexible structure includes a first helical wire, a second helical wire, and welded mass microspheres. The length direction of the first helical wire is orthogonal to the length direction of the second helical wire. The welded mass microspheres are positioned at the intersection of the first and second helical wires to connect them. This invention connects the orthogonally arranged first and second helical wires with welded mass microspheres to form a hyperelastic flexible structure. Compared to existing hyperelastic structural materials, it possesses excellent multifunctional mechanical properties such as large deformation recovery elastic deformation and zero Poisson's ratio. It can be used as a skeletal reinforcement for novel multiphase composite hyperelastic structural materials or as a standalone component.

The invention provides an aircraft composite heat insulation plate based on welding forming, a flap lower wall plate and an assembling method, and the aircraft composite heat insulation plate based on welding forming comprises an upper frame and a lower frame which are sequentially stacked to form a frame assembly; the outer edge of the outer skin and the frame assembly are aligned and stacked, the lower surface of the outer skin abuts against the lower frame, and the upper frame, the lower frame and the outer skin are formed at a time in a welding mode; the aerogel layer is arranged on the lower surface of the outer skin and located in the frame assembly. The invention has the beneficial effects that the nano porous structure of the aerogel limits the motion of gas molecules and reduces convective heat transfer, and the complex nano skeleton increases the heat conduction path, improves the heat radiation absorption, reduces the solid heat conduction and radiative heat transfer, and can tolerate the high temperature of 650 DEG C in the jet flow area of an engine.

A method for producing a torsion box for a structure of an airplane. The method includes providing a first component made of a fiber composite material, the first component has a first planar base having a first inner side and a first outer side, first stiffening elements on the first inner side forming a composite with the first base. A second component is provided of a fiber composite material and has a second planar base having a second inner side and a second outer side. Second stiffening elements are on the second inner side and form a composite with the second base. The method includes superimposing the first component and the second component such that the first stiffening elements lie, at least in some areas, on the second inner side and the second stiffening elements lie, at least in some areas, on the first inner side. The methods includes connecting the first stiffening elements to the second base and connecting the second stiffening elements to the first base.

Decompression hatch provided with an elastomer part for an aircraft and internal wall of an aircraft provided with such a decompression hatch.- The decompression hatch (1) comprises a frame (5) provided with an opening (6) and a flap (7) connected to the frame (5) by a connection system (8) comprising at least one elastomer part (13) provided with a plurality of fixing elements (14) fixing together said part (13), the frame (5) and the flap (7), the flap (7) being capable of being brought from a closed position in which it completely closes the opening (6) to an open position (P2) in which it partially releases the opening (6) under the effect of a pressure difference between the two sides of the decompression hatch (1) in the event of rapid decompression, the elastomer part(s) (13) making it possible to obtain an effective decompression hatch (1), simple to produce, not using any complex mechanism and making it possible to return the flap (7) directly to its closed position when the pressure conditions allow it again. Figure for abstract: Fig. 3.

A retainer 16, 18 suitable for use on an aircraft 2 is disclosed. The retainer 16, 18 comprises a first retainer part 16 and a second retainer part 18. The first retainer part 16 comprises a catch and a damper 24; in which the catch comprises one or more magnetic elements 20, 22. The damper 24 comprises a damping material, the damping material damps shock impulses; and the catch is supported on the damper.

The invention discloses a bi-directionally sewed composite longitudinal and transverse stiffened wallboard and a preparation method thereof, the longitudinal and transverse stiffened wallboard comprises a bulkhead, a stringer, a stringer R area filling core material, a stringer crack arrest belt, a bulkhead crack arrest belt and a skin, and the bulkhead is connected with the stringer in an inserted manner; a stringer and a stringer crack arrest belt are arranged at the top of the skin in the Y direction, and a bulkhead and a bulkhead crack arrest belt are arranged at the top of the skin in the X direction; the bulkhead and the wrapping layer on the outer side of the stringer are connected with the skin in a sewing mode through a bulkhead crack arresting belt and a stringer crack arresting belt respectively, and the bulkhead is connected with the bottom of the wrapping layer on the outer side of the stringer in a sewing mode. The transverse ribs keep good continuity, the two-way continuous rib structure enables the stiffened wall plate to have a more efficient stress conduction path, the suture line plays a role in Z-direction reinforcement, interlayer strength and toughness are improved, damage tolerance is improved, the comprehensive performance of the stiffened wall plate is improved, and good practicability is achieved.