133results about "Aircraft assembly" patented technology

Systems and methods for manufacturing composite structures are disclosed. A system for manufacturing a composite structure includes a layup carrier including a layup support surface configured to support at least one composite material layup. The system includes a carrier transfer device configured to transfer the layup carrier. The system includes a lamination system configured to selectively apply the at least one composite material layup to the layup support surface of the layup carrier. The system includes a transfer system configured to remove the layup carrier from the carrier transfer device and apply the at least one composite material layup to at least a portion of a forming surface of a forming tool. The system includes a forming system configured to form the at least one composite material layup over the at least a portion of the forming surface of the forming tool.

To provide systems and methods for assembly line processing of wing panels of an aircraft.SOLUTION: In a method of inputting wing panels 150 into an assembly line 100, the assembly line 100 has several work stations 120. The wing panels 150 are oriented in a manner so that leading edges 155 are all on a first side 166 of the work stations 120, whereas trailing edges 157 are all on a second side 165 of the work stations 120. A first portion of the work stations 120 is dedicated to wing panel leading edge 155 processing, whereas a second portion of the work stations 120 is dedicated to wing panel trailing edge 157 processing. In the system and the method, the wing panels 150 advance in a processing direction 181 in the assembly line 100.SELECTED DRAWING: Figure 1A

The invention relates to manufacturing curved composite preforms for aircraft by assembly line. Systems and methods for manufacturing curved preforms (146) of fiber-reinforced material (221) are provided. The method includes laying up (804) at least one ply (220) onto a carrier (210) of flexible material at a lamination station (130); loading (806) the carrier (210) onto a rail system (110); routing (808) the carrier (210) to a specific ply-by-ply (PBP) forming station (140) at the rail system (110); separating (810) the at least one ply (220) from the carrier (210); and manufacturing (812) the at least one ply (220) into a preform (146) via the specific PBP forming station (140).

Composite multi-spar aircraft lifting surface comprising an integrated torsion box (1) comprising: - a first portion of a skin (3.1) continuous on the second face (1.2) from a right tip (4.1) to a left tip (4.2), - a second portion of a skin (3.2) continuous on the lateral right side (1.3) of the first face (1.1) from a right tip (4.1) to a first central portion (5), - a third portion of a skin (3.3) continuous on the lateral left side (1.4) of the first face (1.1) from the left tip (4.2) to a second central portion (6), - a cover (7) spanning between the first central portion (5) and the second central portion (6). The spars (2), the first portion of the skin (3.1), the second portion of the skin (3.2) and the third portion of the skin (3.3) being an integrated multi-cell part.

The application discloses a kind of hydrogen storage bottle fuselage integration structure manufacturing method of unmanned plane, the application is by constructing the three-dimensional model of target unmanned plane body and carries out simulation analysis, obtains bearing key area and non-bearing area;Selecting hydrogen storage bottle inner container, the hydrogen storage bottle inner container is divided into pressure-resistant winding area and fuselage combination area, and the inner container partition is wound with different thickness of prepreg, to obtain hydrogen storage bottle;For the installation parameters of three-dimensional model and gas bottle of fuselage, design mould;The bearing key area and non-bearing area are respectively wound with different thickness of prepreg, and the whole structure of hydrogen storage bottle and unmanned plane body integration is formed by mould pressing forming;The application can realize weight reduction while ensuring strength, which is conducive to optimizing unmanned plane load and endurance, integrating space to improve hydrogen storage capacity and startability, simplify process and adapt to large-scale production.The application is suitable for hydrogen energy unmanned plane field.

This invention discloses a composite fuel tank, assembly fixture, and assembly method thereof, relating to the field of integrated fuel tank assembly technology. It includes a mounting frame, on the top of which a main reducer is mounted; the mounting frame is sealed with sealant; and a fuel tank is fixedly installed inside the mounting frame. This invention positions the mounting platform and assembles it with a first side frame, a second side frame, and a skin using adhesive riveting to form an integral structural outer wall. This strengthens the overall integrity and rigidity of the fuel tank while reducing the weight of the fuselage. This invention effectively ensures the load-bearing capacity of the overall fuel tank structure, with a simple assembly process, high efficiency, fewer assembly fixtures, and low manufacturing cost.

The present invention relates to a split rib for securing a leading edge assembly. The rib includes a first rib portion having a first rear mounting portion for attaching the first rib portion to a wing box assembly and further having a front mounting portion opposite the first rear mounting portion. The rib further includes a second rib portion having a second rear mounting portion for attaching the second rib portion to the front mounting portion of the first rib portion.

Disclosed herein is a hoist tool including a hoist frame and a base structure. The hoist frame includes a structural framework having a first end and a second end and at least one first rotation-enabling coupling at the second end of the structural framework. The base structure includes at least one second rotation-enabling coupling configured to engage with the at least one first rotation-enabling coupling of the hoist frame. The at least one second rotation-enabling coupling of the base structure defines a rolling axis. The hoist frame is selectively movable by the hoist to position the at least one first rotation-enabling coupling into engagement with the at least one second rotation-enabling coupling and when coupled and when the assembled structure is coupled to the hoist frame, the hoist frame is selectively rotatable about the rolling axis, relative to the base structure, to enable a rollover of the assembled structure.

The application discloses a kind of for aircraft composite wallboard turnover tool's pose adjusting device and method, include multiple groups of turnover pose adjusting beam and control system, every group of turnover pose adjusting beam includes beam frame, pose adjusting mechanism, protective cover, maintenance cover plate, electrical element, beam frame main body is half-closed long strip plate welding structure, two ends are connected with wallboard turnover tool respectively, two groups of pose adjusting mechanism are embedded and fixed in the middle layer main bearing plate of beam frame, control system controls multiple groups of turnover pose adjusting beam pose adjusting and wallboard suction fixation, multiple groups of turnover pose adjusting beam synchronous turnover will wallboard be turned to required pose.

A remnant extraction tool includes a nosepiece assembly and a vacuum assembly. The nosepiece assembly engages with a robotic manipulator to adjustably align with an exit side of a workpiece during a drilling operation through the workpiece at a predetermined location. The drilling operation includes drilling performed by another robotic manipulator from a drilling side of the workpiece. The vacuum assembly is in fluidic communication with the nosepiece assembly and engages with the robotic manipulator to selectively apply a vacuum to the exit side of the workpiece via the nosepiece assembly and to collect remnants from the drilling operation. A robotic manufacturing system includes a machine drill tool and the remnant extraction tool. The machine drill tool engages with a first robotic manipulator. The remnant extraction tool engages with a second robotic manipulator. Methods for extracting remnants during drilling operations at robotic manufacturing systems are also disclosed.

The present invention is concerned with a system for installing fasteners in an aircraft structure. The system comprises a feeding station 2 comprising one or more fasteners 8, each fastener arranged

Method of assembling an aeronautical panel (10), said panel (10) comprising a curved wall (12) and stiffening elements (14) which are attached and fixed to the wall (12) and which have a stiffness greater than that of the wall (12), in which it comprises the following steps: a) determining deviations between dimensions of the wall (12) in the free state without stress and reference dimensions, b) mounting the wall (12) on a frame (16) which is adjusted to apply on the wall (12) at least one overstress (Σ) such that the wall (12) adopts a shape different from its nominal shape, and c) fixing the stiffening elements (14) to the wall (12), the stiffening elements (14) applying at least one stress (S) to the wall (10) so that it adopts its nominal shape after removal of the panel (10) from the frame (16). Figure for the summary: Figures 3a-3c

This application discloses an inflatable tail fin for an airship made of polyethylene film, characterized by comprising: a spherical membrane made of polyethylene film; reinforcing ribs for securing the spherical membrane; and longitudinally extending partitions welded into the cavity of the spherical membrane, wherein the longitudinal direction refers to the direction from the root of the tail fin to the tip of the tail fin; and multiple partitions arranged laterally within the cavity of the spherical membrane. This application also discloses a method for manufacturing an inflatable tail fin for an airship made of polyethylene film. This solves the problem that polyethylene film cannot withstand high pressure.

To provide systems and methods for assembling a section of a fuselage of an aircraft.SOLUTION: The method includes transferring a half barrel section 24 of a fuselage of an aircraft along a track 110-1, 110-2 in a process direction, utilizing an indexing feature associated with the half barrel section 24 to determine a desired contour 361 for a portion of the half barrel section 24, and enforcing the desired contour 361 on the half barrel section 24 using components that enforce an inner mold line 128 and components that enforce an outer mold line 126 when the contour of the half barrel section 24 is out of tolerance from the desired contour 361.SELECTED DRAWING: Figure 3

The technical scheme of the embodiment of the application discloses a kind of position adjustment method, system, device, equipment and medium of aircraft component, which comprises: the dynamic force data and position coordinates of aircraft component in the process of docking are obtained, wherein the aircraft component is moved along the moving path by mobile robot, and the dynamic force data changes due to the movement of the mobile robot;According to the dynamic force data and position coordinates, the compensation distance is determined;The compensation distance is sent to the mobile robot, so that the mobile robot adjusts the position of the aircraft component according to the compensation distance.The technical scheme provided by the application can accurately calibrate the position of the aircraft component during docking, improve the accuracy of aircraft component docking, and avoid damage caused by abnormal stress of aircraft component.

A method for manufacturing a connecting part between a wing box and a leading edge module. The method comprises performing a three-dimensional scanning of a first representative part of the wing box to obtain a first computer model and performing a three-dimensional scan of a second representative part of the leading edge module in order to obtain a second computer model. The first part comprises a first reference region and a first connecting region, the second part comprises a second reference region and a second connecting region. A relative position of the first reference region is defined with respect to the reference region. From the first and second computer model, the connecting part is configured to connect the first and the second connecting region such that the first and the second reference region are located in said relative position. The connecting part is then manufactured.

A system includes a base. A platform is coupled to the base. A staircase is coupled to the base and the platform. The staircase includes one or more steps leading up to the platform. A head support includes a front cross beam connected to a first arm and a second arm. The first arm and the second arm are pivotally coupled to the platform. The head support is selectively moveable between an upright position in which the front cross beam is above the platform, and a deployed position in which the front cross beam is forward from a front end of the platform.

A method, apparatus, and system for storing a carbon fiber ply. The carbon fiber ply is moved to an electrostatic storage panel. The carbon fiber ply is attached to the electrostatic storage panel using an electrostatic charge generated by the electrostatic storage panel.

This utility model discloses an intelligent trackless lifting and installation transport vehicle, relating to the field of aircraft assembly equipment technology. The utility model includes an AGV intelligent trackless transport vehicle, a lifting unit, a rotating unit, and a gripping unit. In this utility model, through the functions of the hub gripping mechanism, the support strut gripping mechanism, and the adjusting components, the distance between the two first clamping blocks and the distance between the two second clamping blocks can be adjusted to adapt the distance between them to the specifications and dimensions of the landing gear hub and landing gear strut. The first clamping blocks enter the gap near the axle of the landing gear hub, and the second clamping blocks contact the outer wall of the landing gear strut, thus gripping the landing gear hub and landing gear strut. This facilitates the gripping of landing gear hubs and landing gear struts of different specifications, effectively improving the convenience of gripping operations for landing gear hubs and landing gear struts of different specifications, while also increasing the flexibility of the installation vehicle.

This present invention relates to the field of aircraft and discloses an aircraft and a method for connecting a canard to an arm. The connection method is used to couple a canard and an arm. The canard comprises a coupling insertion portion, which comprises a plurality of fixing portions. The arm comprises an arm insertion cavity, and an insertion opening is provided at one end of the arm insertion cavity. The coupling insertion portion is configured to be inserted into the arm insertion cavity through the insertion opening and is fixed within the arm via the fixing portions. In the present invention a detachable structure is enabled between the canard and the arm, allowing the position of the center of lift to be adjusted by exchanging canards featuring different designs, thereby adapting to aircraft cabins with different centers of gravity.

An assembly platform configured to manipulate at least one aircraft lower shell without deforming it with a view to assembly of an aircraft fuselage barrel is disclosed including at least one rectangular chassis, at least two frames having an adjustable trim with respect to the rectangular chassis, at least two setting systems intended to adjust the trim of the frame and at least two cradles fixed onto the frames and intended to receive the lower shell and to hold the lower shell in a desired form. The cradles of the assembly platform make it possible to prevent a deformation of the lower shell during the assembly of the fuselage barrel.

A device for equipping and fitting out fuselage barrels of an aircraft fuselage includes a support structure that carries an assembly platform, the assembly platform including at least one load support and including a frame and at least one actuator rail connected to the frame, wherein at least one actuator carriage can be movably arranged on each of the actuator rails, and wherein the load support is designed to be coupled to a support structure provided on the aircraft fuselage and / or a load introduction point in order to support the assembly platform relative to the aircraft fuselage.

The application provides a quick mounting and dismounting device for optoelectronic products, and belongs to the technical field of aircraft optoelectronic products. The mounting and dismounting device comprises a support assembly, a positioning assembly, an adjusting assembly and a fixing assembly. The support assembly can support the optoelectronic product and adjust the position of the optoelectronic product in the vertical direction, so that the optoelectronic product is moved to its installation position. The positioning assembly can always keep a safe distance between the optoelectronic product shell and the aircraft cabin, effectively avoiding the collision between the optoelectronic product and the aircraft cabin, and saving the mounting and dismounting time. The adjusting assembly can accurately adjust the inclination angle of the optoelectronic product, quickly position the installation interface of the aircraft cabin, and greatly shorten the installation time. The fixing assembly can quickly and accurately align the screw with the fixing hole of the optoelectronic product and the screw hole of the aircraft cabin, save time, and realize the quick mounting and dismounting of the optoelectronic product and the aircraft.

The utility model discloses an aircraft wing rib assembly tool which comprises a bearing mechanism and a positioning mechanism, the bearing mechanism comprises a bearing platform, the bearing platform is provided with an installation opening, and the shape of the installation opening is the same as that of a wing plate of a wing rib; the positioning mechanism comprises a first baffle and two second baffles, the first baffle is arranged on the side of any long edge of the mounting opening and used for abutting against any long edge of a wing plate of a wing rib and a first plate face of a rib strip of the wing rib, and the two second baffles are oppositely arranged on the two sides of two short edges of the mounting opening and used for abutting against any long edge of the wing plate of the wing rib and abutting against a second plate face of a rib strip of the wing rib. The two short edges of the wing plate and the two ends of the rib are connected in an abutting mode respectively. The aircraft wing rib assembly tool has the advantages that wing plates and rib strips of wing ribs of the structure can be rapidly positioned, and the assembly efficiency of the wing plates and the rib strips of the wing ribs of the structure is improved.

The invention relates to a monolithic structure (1) made of composite material, manufactured starting from a fiber-reinforced prepreg material. The structure comprises two walls (6, 7) facing each other and at least one interconnecting element (8) extending transversely between the walls (6, 7) and connected to them, with which each elongated cavity (9) is defined. The walls (6, 7) extend symmetrically on both sides of a direction (B). The interconnecting element (8) is a rib (10) extending transversely to said direction (B), at least one wall (6, 7) having a sandwich structure and comprising two panels (11, 12) facing each other and at least one spar element (13) extending transversely between the panels (11, 12) and connected to them, with which each elongated cavity (14) is defined, extending transversely to the rib (10).

A method for assembling a rotational equipment assembly having a rotational equipment module and a rotational equipment case includes axially supporting the rotational equipment module with a first support assembly, positionally fixing a rotor assembly and a stator assembly of the rotational equipment module together with a second support assembly, coupling a pulling rod assembly with a tooling shaft of the rotational equipment module, and assembling the rotational equipment assembly by positioning the rotational equipment case axially abutting the rotational equipment module and axially pulling the pulling rod assembly to axially fit the rotational equipment module with the rotational equipment case.

The invention relates to a method for manufacturing a fixed-wing aircraft, in particular a drone (100), (200), having the following steps: (i) manufacturing a housing (110), (210), (310) of the fixed-wing aircraft, (ii) manufacturing a support structure (120), (220), (320) of the fixed-wing aircraft, the support structure comprising an upper support structure part (121), (221), (321) and a lower support structure part (122), (222), (322), each comprising at least a support structure for a fuselage (113), (213) of the fixed-wing aircraft and a support structure for a wing (114), (115), (214), (215) of the fixed-wing aircraft, and (iii) joining the housing together with the support structure. The invention also relates to a fixed-wing aircraft, in particular a drone, which is manufactured using the manufacturing method according to the invention, so that a stable fixed-wing aircraft can be manufactured in a simple manner.

A spinner is described that can provide aerodynamic advantages for vertical takeoff and landing (VTOL) aircraft. The spinner can be shaped with multiple faces divided by chines. The chines can run down the edge of the spinner to fairings that can cover rotor blades and / or couplings between rotor blades and the rotor hubs of the aircraft. During forward flight the rotor blades can be folded down into recesses on the spinner. The spinner and fairings can provide aerodynamic advantages in addition to protection for sensitive components within the rotor and blades apparatus. This improves efficiency and allows the aircraft to fly faster.

This utility model discloses a positioning fixture for mounting a drone wing, relating to the field of positioning fixtures. It includes a mounting bracket, on which a positioning support frame and a pressing and fixing structure are fixedly mounted. The pressing and fixing structure is located above the positioning support frame. The positioning support frame consists of a connecting plate, support columns, and a first arc-shaped rubber pad. There are four support columns, all fixedly mounted on the upper end of the connecting plate. There are four first arc-shaped rubber pads, each fixedly mounted on one of the four support columns. By setting a positioning support frame composed of a connecting plate, support columns, and first arc-shaped rubber pads on the mounting bracket, and a pressing and fixing structure composed of a cylinder, mounting plate, Z-shaped plate, mounting rod, buffer spring, anti-detachment plate, arc-shaped plate, and second arc-shaped rubber pads, the drone fuselage can be accurately positioned and securely fixed, ensuring that the fuselage will not shift during the assembly process of the wing and fuselage.