2784results about "Aircraft assembly" patented technology

A method of making a perforated laminate wherein a pliable perforation device having plurality of holes and plurality of perforation pins in the holes is assembled on a laminate; the pins are driven through the uncured laminate to perforate the laminate; the laminate is then staged or cured with pins in place; and the pins are then removed from the cured laminate and pushed back into the perforation device for reuse thereof.

A method and apparatus for manufacturing wings includes a fixture that holds wing panels for drilling and edge trimming by accurate numerically controlled machine tools using original numerical part definition records, utilizing spatial relationships between key features of detail parts or subassemblies as represented by coordination features machined into the parts and subassemblies, thereby making the parts and subassemblies intrinsically determinant of the dimensions and contour of the wing. Spars are attached to the wing panel using the coordination holes to locate the spars accurately on the panel in accordance with the original engineering design, and in-spar ribs are attached to rib posts on the spar using accurately drilled coordination holes in the ends of the rib and in the rib post. The wing contour is determined by the configuration of the spars and ribs rather than by any conventional hard tooling which determines the wing contour in conventional processes.

An airfoil box and associated method are provided. The airfoil box includes two or more half-shell structures. Each half-shell structure is an integral or unitary member that includes at least a portion of the outer skin of the airfoil as well as stiffener members and connection members. For example, the half-shell structures can be integrally formed of composite materials. The half-shell structures can be assembled by connecting the connection members with fasteners such as rivets to form the airfoil box.

Three-dimensional large scale bodies such as jumbo aircraft fuselages (14) are assembled in body sections around a central longitudinal assembly core (1) which itself is mounted at its ends and accessible all around along its length. Robots carrying tools for holding, transporting and precisely positioning preassembled wall shell sections, are movable along the central core (1). First, at least one floor grid (2 or 3) is releasably mounted to the core. Then, side wall shell sections (4, 5) are secured to the floor grids. Then, top and bottom wall shell sections (10, 8) are secured to the side wall shell sections (4, 5) to form a body section (BS) of the large scale body (14). Neighboring body sections are secured to each other along cross-seams. Upon completion, the floor grids are released from the core (1) and the core is removed preferably withdrawn longitudinally from the assembled large component or body.

The invention is directed to an integrated lightning strike protection system adapted for automated placement on a composite structure comprising a surfacing layer consisting of an organic polymer resin, a conductive layer of an expanded metal foil, an isolation/tack layer, and a carrier paper layer. In another embodiment of the invention, there is provided an integrated lightning strike protection system comprising an integrated lightning strike protection material consisting of an expanded metal foil encapsulated in organic polymer resin mounted on a carrier paper, and an automated placement machine suitable for placing the material on an aircraft composite part for protection of the composite part from lightning strikes. In another embodiment of the invention, there is provided a method for fabricating a composite structure with lightning strike protection.

The invention discloses a method for flexibly and automatically adjusting posture of an airframe of an airplane. The method comprises: the spatial position of a target of the airframe is measured through a laser tracking instrument; a measuring result and a digital standard model are subjected to matched analysis to calculate the posture of the airframe; and finally a plurality of three-coordinate positioner units are controlled and driven to realize adjustment of the posture of the airframe. The whole posture adjusting process comprises three stages: a posture adjusting preparation stage, an airframe posture adjusting stage and a posture adjusting result evaluation and analysis stage to realize automatic and non-stress posture adjustment of the airframe. The method has the following advantages: 1, the method can realize digital posture adjustment of the airframe; 2, the airframe is supported by the plurality of the positioner units; and in the posture adjusting process, motion cooperativity of the airframe is monitored in real time to realize non-stress posture adjustment; 3, the method has good flexibility and compatibility and can meet the requirement of posture adjustment of various airplane models; and 4, the method can carry out quantitative evaluation and analysis on the posture adjusting result and obtain the position and posture of the airframe in a scene coordinate system.

A single piece pulsed flow wing assembly method providing for horizontal wing manufacture is accomplished using synchronized automated vehicles guided in a predetermined manner to move and, locate wing structure in a plurality of assembly positions. Multi-axis assembly positioning systems (MAPS) are used at each assembly position to support and index components in the wing structure and determinant assembly techniques are used for indexing of the components. Modular automated manufacturing processes employing magnetic assembly clamping, drilling, fastener insertion, and sealant application are employed.

An apparatus comprises a plurality of mobile robotic machines, a wireless communications system, and a motion control system. The plurality of mobile robotic machines may be capable of moving to a number of locations in an assembly area and performing operations to assemble a structure in the assembly area. The wireless communications system may be capable of providing communications with the plurality of mobile robotic machines within the assembly area. The motion control system may be capable of generating position information for the plurality of mobile robotic machines in the assembly area and communicating the position.

The invention belongs to the technology of airplane abutting, and relates to abutting technological equipment of airplane large components and an abutting method thereof. The abutting technological equipment of the airplane large components disclosed by the invention consists of a fixed part and a movable part, wherein the fixed part comprises a reference flat plate, a main landing gear technological support frame and a plurality of reinforced frame support frames; the movable part comprises a ground rail, a body front section railway car, a locking and positioning device and a centering device, wherein a car body is arranged on the ground rail, the centering device used for preventing the front section from rolling is arranged at the support frame of the car body, and the locking and positioning device is arranged at an abutting surface. When the front section and the middle section of an airplane are abutted via the abutting technological equipment, the position of the middle section is firstly fixed, then the front section is adjusted, and then accurate abutting of the front section and the middle section is realized through railway movement so as to perform subsequent riveting work. According to the abutting technological equipment of the airplane large components and the abutting method thereof, the abutting difficulty and potential safety hazard of the airplane large components are greatly reduced, the manufacturing efficiency and the abutting quality are improved, and the abutting precision of products is effectively ensured.

The invention discloses a method for measuring positioning points based on a laser tracker in a docking process of airplane parts. The method provided by the invention comprises the following steps of 1, establishing a model of transformation between an airplane global coordinate system and a laser tracker measure coordinate system according to common observation points, 2, acquiring current calculating positions of positioning measure points of airplane parts according to a process joint sphere centre position, and 3, controlling and driving a laser tracker to search current accurate positions of the positioning measure points of the airplane parts from the current calculating positions according to a cross helical search method and to carry out automatic measure. The method provided by the invention has the advantages that 1, an advanced laser measure technology is adopted so that the airplane assembling measure precision is improved; and 2, a measure process does not need artificial light introduction and full automatic search measure of a docking assembling process is realized according to an algorithm so that working efficiency and measure precision are greatly improved and working strength of workers is reduced.

The following steps are performed in the method of constructing an aircraft: taking a subassembly comprising two wings that are rigidly fastened together, and fitting it to a fuselage wall; and fastening the subassembly to the wall by means of fastener elements that are distinct from the subassembly and that present main axes that are vertical.

A method and apparatus for performing operations on a workpiece. A first frame in a frame system may be held on the workpiece by applying a vacuum to the first frame. A second frame in the frame system may be detached from the workpiece by applying a pressure to the second frame. The second frame may be moved to a location on the workpiece. The second frame may be attached to the workpiece by applying the vacuum to the second frame. An operation may be performed on the workpiece.

A modularized robot includes a robot platform configured to convey mobility and connectivity to external components to the modularized robot, a robot workhead configured to convey the ability to perform an operational task to the modularized robot, and a robot adapter attached to either the robot platform or the robot workhead and configured to mechanically link the robot platform to the robot workhead. Moreover, a swarm of modularized robots and a robot system include such modularized robots.

Embodiments of the invention relate to a stringer (108) adapted to transport fluid in an aircraft wing (100). For example, the stringer may be adapted to provide venting to one or more fuel tanks (111) in the aircraft wing, or may be adapted to provide fuel to the one or more fuel tanks. To perform this function, the stringer comprises a duct member (120) providing a duct and a structural member (121) providing an attachment surface for attachment of the stringer to a wing panel (112). Typically, the stringer is formed from a composite material such as carbon fibre reinforced plastic. A method of manufacturing the stringer is also disclosed.

A system for handling a first component includes: a main-device and a module-device, the module-device having a pressing section arranged to form an outer surface of the module-device, the module-device configured to releasably receive the first component, such that a connection section of the first component is attachable to the pressing section of the module-device. The module-device is releasably connected to a second component, wherein the main-device includes a grabbing unit adapted for releasably connecting the module-device, such that the pressing section is arranged to form a first outer surface section of the main-device, and wherein the main-device includes a connector for connecting to a handling-unit for arranging the main-device at the second component, such that the connection section of the first component, if attached to the pressing section of the module-device, is at least indirectly attachable to a front surface of the second component.

Provided is an aircraft component digitized flexible assembling measuring method based on a laser tracking measuring technique. The assembling measuring method comprises the following steps of (1) carrying out preparation work of assembling measurement, (2) carrying out work of the assembling measurement, and (3) carrying out parallel collaborative measurement in real time. The aircraft component digitized flexible assembling measuring method based on the laser tracking measuring technique relates to the combination of an assembling technique and the measuring technique, the theoretical position information of engineering data concentrated product digital analogy is compared with the coordinates, obtained by a laser tracking instrument in real time, of reference points of assembly parts to form positional deviation, the positional deviation is transmitted to a movement control system, the movement control system generates tool pose control instructions by analyzing the positional deviation and transmits the tool pose control instructions to a flexible tool, the flexible tool drives a workpiece to adjust poses together, and through the coordinated operation of the movement control system, the flexible tool and the workpiece, a closed loop control system is formed to complete the assembling work. The aircraft component digitized flexible assembling measuring method based on the laser tracking measuring technique has good practical value and wide application prospect in the laser tracking measuring technique and the aircraft digitalized assembling field.

A method and apparatus for performing an assembly operation. A tool may be macro-positioned relative to an exterior of a fuselage assembly. The tool may be micro-positioned relative to a particular location on the exterior of the fuselage assembly. An assembly operation may be performed at the particular location on the panel using the tool.