2822results about "Aircraft assembly" patented technology

A method of manufacturing a monolithic composite wing without using mechanical fasteners is described. The process begins with the formation of a center wing box in combination with a pair of spars, riblets and a pair of skin-molds including the wrapping and binding of the box by means of resin impregnated composite tapes. Next, additional cells are adjoined contiguously on either side of the current framework and an overlap wrapping and bonding process is continued around the current framework. The overlap wrapping and binding procedure provides increased torsion stiffness and reduced structural weight. All cells up to the leading and trailing edges will be included in the assembly process. Conduits to convey fuel, hydraulic fluid and electrical wiring will also be installed in designated cells. Finally, the completed wing will be cured in an autoclave under uniform pressure and temperature.

The invention discloses an airplane component attitude adjusting and butting system based on four numeric control positioners, attitude adjusting platform and mobile bracket and a corresponding method. The system comprises a mobile bracket, an attitude adjusting platform, numeric control positioners, a numeric control positioner group guide rail, an upper computer, a ball hinge connection mechanism and a laser tracker. The attitude adjusting and butting method includes the following steps: 1) the mobile bracket is fixed onto the attitude adjusting platform and is supported by the numeric control positioner; 2) fuselage is arranged in place; 3) a site assembly coordinate system and a local coordinate system solidified on the fuselage are established; 4) the current attitude of fuselage A is measured and calculated; 5) motion path of the numeric control positioner is planned; 6) the attitude of the fuselage A is adjusted; 7) coordinates of a butt hole are measured and target attitude offuselage B is calculated; 8) the current attitude of fuselage B is calculated; 9) the attitude of the fuselage B is adjusted; 10) fuselage is butted; 11) the system is reset; 12) the mobile bracket is removed. The invention has the advantages that digitalized attitude adjusting and butting of airplane components are realized and adaptability is strong.

A one-piece barrel assembly cart includes a right assembly cart base connected with a left assembly cart base and at least three stabilizer rings that are attached to the assembly cart base. The one-piece barrel assembly cart may be used to stabilize a tapered cured composite barrel, for example the large fuselage barrel of the aft section of a large new generation aircraft, such as a 7E7 Boeing airplane. A modular assembly cart includes at least two identical modules. Each of these modules includes a cart base and a stabilizer ring. The diameter of the inner surface of the stabilizer ring may vary as needed. Other modules including a fuselage support may be added. By providing modular assembly carts any shape and size of a one-piece composite barrel may be stabilized after curing of the composite material.

A method and apparatus for moving a structure. The structure is supported on a carrier. The carrier comprises a platform having a first side and a second side, a movement system associated with the first side and configured to move the platform on a surface, a support system associated with the second side of the platform and configured to support the structure on the platform, and a leveling system configured to substantially maintain the structure in a desired orientation during movement of the platform on the surface. The carrier is moved with the structure over the surface. At least one of the movement system and the support system is adjusted to substantially maintain the structure in the desired orientation.

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.

In accordance with the present invention an aircraft stringerless fuselage structure is provided comprising an impact compliant outer skin having a plurality of resin impregnated skin fibers forming an outer skin surface, an inner stringerless skin surface, and a skin thickness. A plurality of stiffeners is included, each comprising a plurality of resin impregnated stiffener fibers integrated into the inner stringerless skin structure. The plurality of resin impregnated skin fibers are not aligned with the plurality of resin impregnated stiffener fibers.

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.

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.

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.

A robot system for carrying out a plurality of operations during assembly or maintenance of an aircraft or spacecraft includes a first robot having a base portion, a movable robot arm having a first coupling portion, and a first control means for controlling the robot arm, a plurality of second robots having movement means, a drive portion operable to drive the movement means, a tool portion having a tool for carrying out a specific one of the operations, a second coupling portion adapted to be selectively and releasably coupled with the first coupling portion in a predetermined positional relationship, and a second control means for controlling the respective second robot. The first and second control means are adapted to control the drive portion of one of the second robots and the robot arm to couple the first coupling portion and the respective second coupling portion in the predetermined positional relationship.

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.

A method of installing a fixture, such as a bracket, in a fuselage structure of an aircraft includes the steps of: providing or generating a three-dimensional digital model of the fixture; arranging a head of an additive manufacturing apparatus in the fuselage structure; and forming the fixture in situ in the fuselage structure with the head of the additive manufacturing apparatus based upon the digital model of the fixture. The fixture is installed in the fuselage structure by bonding or fusing the fixture to the fuselage structure as the fixture is formed. A fixture, such as a bracket, which is generated in situ in a fuselage structure of an aircraft based upon a three-dimensional digital model, wherein the fixture is bonded or fused to the fuselage structure as the fixture is formed.

A method, apparatus and computer program product are present for performing a manufacturing procedure. A component may be positioned in a work area. A plurality of groups of robots may be operated in parallel and robots of each group of robots of the plurality of groups of robots may be operated in synchronism for performing a plurality of manufacturing operations at a plurality of locations on the component.

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.

The invention provides a posture adjustment assembly system used for butt joint of components of a rocket. The posture adjustment assembly system comprises a posture adjustment system, a test system and a controller, wherein the posture adjustment system comprises first guide rails, beams and guide rail wheels, the guide rail wheels can move along the first guide rails through a horizontal moving mechanism, the posture adjustment system further comprises two posture adjustment devices arranged in parallel, each posture adjustment device is transversely arranged on the upper sides of the two first guide rails and is connected with the top faces of the beams, and each posture adjustment device comprises a supporting beam, a lifting table, a bracket support and an arc-shaped bracket. A posture adjustment method of the posture adjustment assembly system used for butt joint of the components of the rocket includes six steps. The posture adjustment system comprises the two posture adjustment devices, and the test system comprises an optical measurement device, measurement points located at the end of a rocket body and a processor. When only one single posture adjustment device is combined with the first guide rails, the guide rail wheels and the horizontal moving mechanism, four-freedom-degree posture adjustment can be achieved; when the two posture adjustment devices are used in cooperation with each other, six-freedom-degree posture adjustment can be achieved, and the two posture adjustment devices are independent, do not interfere with each other during six-freedom-degree adjustment and are matched with each other during adjustment.

A system and method determine a size and a shape for identical geodesic modules that are used to form a structure. The system and method may include analyzing input data regarding a size and a shape of the structure to be formed, and determining the size and the shape for each of the identical geodesic modules based on the size and the shape of the structure to be formed. The structure may include a framework including the identical geodesic modules. Each of the geodesic modules has a size and a shape that are the same as all of the other of the geodesic modules. A forming system and method position a framework and a covering skin of the structure in relation to a mandrel, and drill and rivet the framework to the covering skin with a plurality of operating heads.

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.

Three-dimensional large scale bodies such as jumbo aircraft fuselages (14) are assembled in body sections around a longitudinal central 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 sections, are movable along the central assembly core (1). First, at least one floor support grid (2 or 3) is releasably mounted to the central assembly core. Then, side wall sections (4, 5) are first secured to the floor support grids. Then, top and bottom wall sections (10, 8) are secured to the side wall 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 support grids are released from the central assembly core (1) and the core is removed preferably withdrawn longitudinally from the assembled large body.

A one-piece barrel assembly cart includes a right assembly cart base connected with a left assembly cart base and at least three stabilizer rings that are attached to the assembly cart base. The one-piece barrel assembly cart may be used to stabilize a tapered cured composite barrel, for example the large fuselage barrel of the aft section of a large new generation aircraft, such as a 7E7 Boeing airplane. A modular assembly cart includes at least two identical modules. Each of these modules includes a cart base and a stabilizer ring. The diameter of the inner surface of the stabilizer ring may vary as needed. Other modules including a fuselage support may be added. By providing modular assembly carts any shape and size of a one-piece composite barrel may be stabilized after curing of the composite material.

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.