CN101850850B - Layout method of central airframe digital assembly of big plane - Google Patents

Layout method of central airframe digital assembly of big plane Download PDF

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Publication number
CN101850850B
CN101850850B CN2010101367823A CN201010136782A CN101850850B CN 101850850 B CN101850850 B CN 101850850B CN 2010101367823 A CN2010101367823 A CN 2010101367823A CN 201010136782 A CN201010136782 A CN 201010136782A CN 101850850 B CN101850850 B CN 101850850B
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China
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frame
machine
fuselage
layout
shape
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CN2010101367823A
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Chinese (zh)
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CN101850850A (en
Inventor
蒋君侠
柯映林
李江雄
黄小东
邱宝贵
张洪双
樊新田
杨国荣
梁青霄
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浙江大学
西安飞机工业(集团)有限责任公司
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Priority to CN2010101367823A priority Critical patent/CN101850850B/en
Publication of CN101850850A publication Critical patent/CN101850850A/en
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Abstract

The invention discloses a layout method of a central airframe digital assembly of a big plane. The central airframe digital assembly layout of the big plane is divided into two stations of a component assembling station and a processing station, and toolings adopt symmetric layout. The toolings to which the component assembling station relates comprise a wallboard positioner, a main starting intersection frame positioner, a laser tracker, a wallboard shape-preserving rack, a main starting intersection frame shape-preserving rack, a process middle wing, a wing body butt joint frame shape-preserving rack, a process floor, an operation desk and portable minitype high-speed hole processing equipment. The toolings to which the processing station relates comprise an airframe positoner, a multi-lattice flexible adsorption tooling, a laser tracker, main starting intersection hole surface processing equipment, an airframe end face and measuring point hole processing equipment, an airframe process joint and an operation desk. In the invention, the central airframe assembly layout is divided into multiple stations, and an advanced digital production line is constructed; the precision and the accuracy of the central airframe assembly are improved.

Description

A kind of large aircraft middle machine body digitalisation assembling layout method
Technical field
The present invention relates to a kind of large aircraft middle machine body digitalisation assembling layout method.
Background technology
The development large aircraft is the Major Strategic decision-making that the Party Central Committee, State Council make, and also is national people's hopes for many years.China's Aviation Industry has possessed technology and the material base of development large aircraft through the development in more than 50 years.And large aircraft assembling is an extremely important ring in the aircraft manufacturing link, and its labor content accounts for about half of the total labor content of aircraft manufacturing even be more, has determined to a great extent final mass, manufacturing cost and the cycle of aircraft.
Economic, military developed country extremely pays close attention to the aircraft assembly technique, drops into the huge fund research and development and has obtained the effect that attracts people's attention.Set up separately the portable assembling line of airplane digitalization such as major companies such as Boeing, Air Passenger, increased substantially assembly quality and the efficient of aircraft.Compare with Foreign Advanced Lerel, it is at the early-stage that technology is joined in China's airplane digital makeup, also is at present system, process planning stage, and a small amount of assembled begins to adopt semi-automatic equipment, and great majority then still rest on the hand assembly stage.
For a change the tradition of " erect-position of an airplane; the people turns around aircraft " is assembled layout, develop large aircraft industry as important opportunity take China, a kind of large aircraft middle machine body digitalisation assembling layout design method has been proposed, integrated application comprises the various pioneering technologys such as digital coordination technology, digitized simulation simulation technology, laser tracking measurement technology, Digital location technology, Collaborative Control technology, set up the multi-court position Digital production line of large aircraft middle machine body, had very important strategic importance to improving China aircraft industry level
Summary of the invention
The objective of the invention is to overcome the prior art deficiency, a kind of large aircraft middle machine body digitalisation assembling layout method is provided.
Large aircraft middle machine body digitalisation assembling layout method is: large aircraft middle machine body digitalisation assembling layout is divided into and is parts assembling erect-position and two erect-positions of processing erect-position, and frock adopts symmetric configuration; Be provided with 2 three-dimensional stationary work-tables in the parts assembling erect-position, be positioned at the middle machine body both sides, 12 wainscot steady arms are fixed on the three-dimensional stationary work-table along the course, 12 sidewall paneling steady arms are arranged symmetrically in the middle machine body side along the course, 8 lower wall panels steady arms are installed in the tunnel, workshop, symmetrical the putting in the middle machine body bottom along the course, 8 masters play intersection point frame steady arm and are arranged in main frame place, fuselage both sides along the course, 2 laser trackers are arranged on the mill floor, be the diagonal angle and be distributed in the middle machine body end, the wainscot shape-keeping frame, the medial surface of sidewall paneling shape-keeping frame and lower wall panels shape-keeping frame and corresponding wallboard outside face fit, secondary with corresponding wallboard steady arm formation Spherical Joint Motion by the process connection that is consolidated on the shape-keeping frame simultaneously, led intersection point frame shape-keeping frame and led intersection point frame medial surface and link to each other, the technique central wing links to each other with wing body interface frame, mating frame upper end, wing body interface frame, mating frame shape-keeping frame links to each other with wing body interface frame, mating frame lower end, Artistic floor places middle machine body interior floor installation place, 2 movable operation platforms are arranged on the Artistic floor in the fuselage, 2 Artistic floor guide bracket are positioned at the middle machine body end, respectively there is 1 working stand Artistic floor guide bracket side, and 1 portable small-sized high speed hole Fabricating machinery is used for lead reinforced bulkhead and sidewall paneling and joins and do the hole and process; 4 fuselage process connection are installed on the corresponding reinforced bulkhead of middle machine body in the component processing erect-position, 4 fuselage steady arms are arranged in the fuselage both sides, and link to each other with the fuselage process connection that to consist of Spherical Joint Motion secondary, 2 flexible adsorption toolings of multiple dot array are positioned at the middle machine body bottom, 2 laser trackers are arranged in the middle machine body both sides, 2 masters play the crossing point holes face processing equipment and are arranged in main intersection point frame place, fuselage both sides, 2 fuselage end faces and measurement point hole Fabricating machinery are positioned at the middle machine body two end faces, and 4 end face Fabricating machinery operator's stations are arranged in fuselage processing end face both sides.
The kinematic axis of described steady arm adopts closed grating scale, consist of closed-loop control in X, Y, three directions of Z, and then accurate movement and the location of realizing three directions, one group of formation of per 4 steady arms digitalisation attitude-adjusting unit is realized the 6DOF pose adjustment of assembling object based on the posture adjustment principle of work of four-point supporting.Described parts assembling erect-position and processing erect-position adopt many laser trackers to set up the precise digitization field of fitter's shop, realize the accurate location to fuselage parts and on-the-spot tooling device.It is continuous with corresponding steady arm by process connection that described master plays intersection point frame shape-keeping frame, lower wall panels shape-keeping frame, wainscot shape-keeping frame or wing body interface frame, mating frame shape-keeping frame, indirectly realizes support and the pose adjustment of assembling object.The flexible adsorption tooling of described multiple dot array can generate and the on all four absorption dot matrix of fuselage surface geometric shape, and on telescopic unit the setting pressure sensor, control its feeding by the feedback of power.Described master plays crossing point holes face processing equipment and fuselage end face and measurement point hole Fabricating machinery can both realize five-axle linkage, and then satisfies the processing request of associated orifices and face.Described parts assembling erect-position and processing erect-position guide workman's operation by visual panel in the manual assembly link, have realized the emulation of digitalisation pre-assy.
The invention has the advantages that: 1) middle machine body is assembled layout and be divided into parts assembling erect-position and processing erect-position, set up large aircraft middle machine body multi-court position Digital production line; 2) be the constructional feature that waits straight section substantially according to large aircraft middle machine body, frock adopts symmetric configuration, has increased the frock commonality; 3) take into account the general assembly demand during middle machine body assembling topological design, the frocks such as technique central wing, fuselage process connection are shared with general assembly; The part origin reference location point that relates to when 4) middle machine body section fills and measurement point have been implemented the transmission design philosophy based on same data flow to the general assembly transmission; 5) each axle of steady arm all adopts closed grating scale, consists of closed-loop control in X, Y, three directions of Z, and then accurate movement and the location of realizing three directions; 6) one group of formation of per 4 steady arms digitalisation attitude-adjusting unit is realized the 6DOF pose adjustment of assembling object based on the posture adjustment principle of work of four-point supporting; 7) each erect-position is all selected many laser trackers, realizes the accurate location to fuselage parts and on-the-spot tooling device; 8) adopt in a large number on the conformal frock to reduce the distortion of assembling object, raising assembly precision; 9) the flexible adsorption tooling of multiple dot array can generate and the on all four absorption dot matrix of fuselage surface geometric shape, when the parts profile changes, but frock profile and layout Self-adjustment; 10) the flexible adsorption tooling of multiple dot array setting pressure sensor on telescopic unit is controlled its feeding by the feedback of power; 11) according to constructional feature and the process requirements of middle machine body, design multiple automatically processing device, associated end face and crossing point holes have been processed, improved the manufacturing accuracy of parts; 12) automatically processing device can be realized five-axle linkage, and then satisfies the processing request of associated orifices and face; 13) each erect-position guides workman's operation by visual panel in the manual assembly link, has realized the emulation of digitalisation pre-assy; 14) integrated application based on pioneering technologys such as the coordination technique of digital master tooling, digitized simulation simulation technology, laser tracking measurement technology, Digital location technology, Collaborative Control technology, improved precision and the efficient of middle machine body assembling.
Description of drawings
The large aircraft middle machine body of Fig. 1 parts assembling erect-position front view;
The large aircraft middle machine body of Fig. 2 parts assembling erect-position birds-eye view;
The large aircraft middle machine body of Fig. 3 parts assembling erect-position left view (containing movable operation platform in the fuselage);
The large aircraft middle machine body of Fig. 4 parts assembling erect-position left view (containing technique central wing and wing body interface frame, mating frame shape-keeping frame);
The large aircraft middle machine body of Fig. 5 component processing erect-position front view;
The large aircraft middle machine body of Fig. 6 component processing erect-position birds-eye view;
The large aircraft middle machine body of Fig. 7 component processing erect-position left view;
Among the figure: middle machine body 1, laser tracker 2, Artistic floor guide bracket 3, three-dimensional fixing operation platform 4, working stand 5, led intersection point frame shape-keeping frame 6, movable operation platform 7 in the fuselage, sidewall paneling shape-keeping frame 8, sidewall paneling steady arm 9, led intersection point frame steady arm 10, lower wall panels steady arm 11, lower wall panels shape-keeping frame 12, wainscot steady arm 13, wainscot shape-keeping frame 14, technique central wing 15, Artistic floor 16, wing body interface frame, mating frame shape-keeping frame 17, fuselage process connection 18, fuselage steady arm 19, led crossing point holes face processing equipment 20, the flexible adsorption tooling 21 of multiple dot array, end face Fabricating machinery operator's station 22, fuselage end face and measurement point hole Fabricating machinery 23.
The specific embodiment
As shown in Figure 1, large aircraft middle machine body digitalisation assembling layout is divided into and is parts assembling erect-position and two erect-positions of processing erect-position, and frock adopts symmetric configuration.Be provided with 2 three-dimensional stationary work-tables 4 in the parts assembling erect-position, be positioned at middle machine body 1 both sides, 12 wainscot steady arms 13 are fixed on the three-dimensional stationary work-table 4 along the course, 12 sidewall paneling steady arms 9 are arranged symmetrically in middle machine body 1 side along the course, 8 lower wall panels steady arms 11 are installed in the tunnel, workshop, symmetrical the putting in middle machine body 1 bottom along the course, 8 masters play intersection point frame steady arm 10 and are arranged in main frame place, fuselage both sides along the course, 2 laser trackers 2 are arranged on the mill floor, be the diagonal angle and be distributed in middle machine body 1 end, wainscot shape-keeping frame 14, the medial surface of sidewall paneling shape-keeping frame 8 and lower wall panels shape-keeping frame 12 and corresponding wallboard outside face fit, secondary with corresponding wallboard steady arm formation Spherical Joint Motion by the process connection that is consolidated on the shape-keeping frame simultaneously, led intersection point frame shape-keeping frame 6 and led intersection point frame medial surface and link to each other, technique central wing 15 links to each other with wing body interface frame, mating frame upper end, wing body interface frame, mating frame shape-keeping frame 17 links to each other with wing body interface frame, mating frame lower end, Artistic floor 16 places middle machine body interior floor installation place, 2 movable operation platforms 7 are arranged on the Artistic floor 16 in the fuselage, 2 Artistic floor guide bracket 3 are positioned at middle machine body 1 end, Artistic floor guide bracket 3 sides respectively have 5,1 portable small-sized high speeds of 1 working stand hole Fabricating machinery to be used for lead reinforced bulkhead and sidewall paneling to join and do the hole and process; 4 fuselage process connection 18 are installed on the corresponding reinforced bulkhead of middle machine body in the component processing erect-position, 4 fuselage steady arms 19 are arranged in the fuselage both sides, and link to each other with fuselage process connection 18 that to consist of Spherical Joint Motion secondary, 2 flexible adsorption toolings 21 of multiple dot array are positioned at middle machine body 1 bottom, 2 laser trackers 2 are arranged in middle machine body 1 both sides, 2 masters play crossing point holes face processing equipment 20 and are arranged in main intersection point frame place, fuselage both sides, 2 fuselage end faces and measurement point hole Fabricating machinery 23 are positioned at the middle machine body two end faces, and 4 end face Fabricating machinery operator's stations 22 are arranged in fuselage processing end face both sides.
The kinematic axis of steady arm adopts closed grating scale, consist of closed-loop control in X, Y, three directions of Z, and then accurate movement and the location of realizing three directions, one group of formation of per 4 steady arms digitalisation attitude-adjusting unit is realized the 6DOF pose adjustment of assembling object based on the posture adjustment principle of work of four-point supporting.Parts assembling erect-position and processing erect-position adopt many laser trackers 2 to set up the precise digitization field of fitter's shop, realize the accurate location to fuselage parts and on-the-spot tooling device.Lead intersection point frame shape-keeping frame 6, lower wall panels shape-keeping frame 12, wainscot shape-keeping frame 14 or wing body interface frame, mating frame shape-keeping frame 17 continuous with corresponding steady arm by process connection, indirectly realized support and the pose adjustment of assembling object.The flexible adsorption tooling 21 of multiple dot array can generate and the on all four absorption dot matrix of fuselage surface geometric shape, and on telescopic unit the setting pressure sensor, control its feeding by the feedback of power.Lead crossing point holes face processing equipment 20 and can both realize five-axle linkage with fuselage end face and measurement point hole Fabricating machinery 23, and then satisfied the processing request of associated orifices and face.Parts assembling erect-position and processing erect-position guide workman's operation by visual panel in the manual assembly link, have realized the emulation of digitalisation pre-assy.
Should consider following technological problems during large aircraft middle machine body digitalisation assembling topological design: (1) wallboard takes off and can deform from the type frame.Require wainscot, sidewall paneling before undercarriage, to link to each other with shape-keeping frame for this reason.Be lifted into parts assembling erect-position together with shape-keeping frame behind the undercarriage.Linked to each other with shape-keeping frame by four locater and to carry out the pose adjustment; (2) supporting of reinforcement lower wall panels, lower wall panels is the base part that whole middle machine body is installed, and in section's process of assembling, the weight of frock, operating personal and reinforced bulkhead acts directly on the lower wall panels, so not only will accurately locate lower wall panels, and will strengthen by Supporting fixture; (3) the alighting gear longeron is contained in the sidewall paneling outside, assembles complete rear installation at sidewall paneling, its crossing point holes will with lead the coordination of reinforced bulkhead crossing point holes; (4) before wainscot is installed, require to have led the ring-type reinforced bulkhead and carry out pre-assy, guarantee frame position and frame distance; (5) carry out fine limit work to having led crossing point holes and binding face.In addition, assembling the wallboard surplus of finishing rear body section two ends will remove.
According to constructional feature, technological requirement and the assembly sequence of erection of middle machine body, a kind of method of designing of large aircraft middle machine body digitalisation assembling layout is provided, formulated the technological process of middle machine body parts assemblings.The key step of implementing this layout is:
1) middle machine body parts assembling erect-position frock resets; 2) middle machine body back segment lower wall panels, the successively posture adjustment of leading portion lower wall panels and location; 3) whole section mounting process floor of middle machine body; 4) middle machine body rear section side wallboard (containing the conformal frame) is removed after entering position and posture adjustment; 5) led reinforced bulkhead enter the position and posture adjustment after assemble with lower wall panels; 6) wing body interface frame, mating frame (containing shape-keeping frame and technique central wing) assembles with lower wall panels after entering position and posture adjustment; 7) having led reinforced bulkhead and steady arm breaks away from; 8) middle machine body rear section side wallboard (containing the conformal frame) is installed; 9) middle machine body leading portion sidewall paneling (containing the conformal frame) is installed after entering position and posture adjustment; 10) led reinforced bulkhead and steady arm reconnects; 11) lead ring-type reinforced bulkhead pre-assy, behind the whole frame of formation ring-type aiding support has been set, guaranteed frame position and frame distance; 12) middle machine body back segment wainscot (containing shape-keeping frame) and leading portion wainscot (containing shape-keeping frame) are installed after entering position and posture adjustment; 13) with miniature high-speed hole Fabricating machinery to having led reinforced bulkhead and the sidewall paneling bolt connecting hole is processed; 14) having led reinforced bulkhead is connected with sidewall paneling; 15) ring-type reinforced bulkhead aiding support has been led in taking-up; 16) Artistic floor is removed; 17) sidewall paneling, wainscot conformal frock are removed and are hung; 18) alighting gear longeron and fuselage process connection are installed; 19) middle machine body hangs; 20) assembling of middle machine body parts and processing erect-position frock and Fabricating machinery reset; 21) middle machine body lifts into the position; 22) after the middle machine body posture adjustment, the flexible adsorption tooling of multiple dot array participates in supporting; 23) carry out fine limit work with having led the crossing point holes face processing equipment to having led crossing point holes and binding face; 24) fuselage end face and measurement point hole Fabricating machinery are installed and excision middle machine body termination wallboard surplus; 25) middle machine body component processing erect-position frock and Fabricating machinery reset, and hang behind the middle machine body fine limit work.

Claims (7)

1. a large aircraft middle machine body digitalisation assembling layout method is characterized in that, large aircraft middle machine body digitalisation assembling layout is divided into and is parts assembling erect-position and two erect-positions of processing erect-position, and frock adopts symmetric configuration; Be provided with 2 three-dimensional stationary work-tables (4) in the parts assembling erect-position, be positioned at middle machine body (1) both sides, 12 wainscot steady arms (13) are fixed on the three-dimensional stationary work-table (4) along the course, 12 sidewall paneling steady arms (9) are arranged symmetrically in middle machine body (1) side along the course, 8 lower wall panels steady arms (11) are installed in the tunnel, workshop, symmetrical the putting in middle machine body (1) bottom along the course, 8 masters play intersection point frame steady arm (10) and are arranged in main frame place, fuselage both sides along the course, 2 laser trackers (2) are arranged on the mill floor, be the diagonal angle and be distributed in middle machine body (1) end, wainscot shape-keeping frame (14), the medial surface of sidewall paneling shape-keeping frame (8) and lower wall panels shape-keeping frame (12) and corresponding wallboard outside face fit, secondary with corresponding wallboard steady arm formation Spherical Joint Motion by the process connection that is consolidated on the shape-keeping frame simultaneously, led intersection point frame shape-keeping frame (6) and led intersection point frame medial surface and link to each other, technique central wing (15) links to each other with wing body interface frame, mating frame upper end, wing body interface frame, mating frame shape-keeping frame (17) links to each other with wing body interface frame, mating frame lower end, Artistic floor (16) places middle machine body interior floor installation place, 2 movable operation platforms (7) are arranged on the Artistic floor (16) in the fuselage, 2 Artistic floor guide bracket (3) are positioned at middle machine body (1) end, respectively there is 1 working stand (5) Artistic floor guide bracket (3) side, and 1 portable small-sized high speed hole Fabricating machinery is used for lead reinforced bulkhead and sidewall paneling and joins and do the hole and process; 4 fuselage process connection (18) are installed on the corresponding reinforced bulkhead of middle machine body in the component processing erect-position, 4 fuselage steady arms (19) are arranged in the fuselage both sides, and link to each other with fuselage process connection (18) that to consist of Spherical Joint Motion secondary, 2 flexible adsorption toolings of multiple dot array (21) are positioned at middle machine body (1) bottom, 2 laser trackers (2) are arranged in middle machine body (1) both sides, 2 masters play crossing point holes face processing equipment (20) and are arranged in main intersection point frame place, fuselage both sides, 2 fuselage end faces and measurement point hole Fabricating machinery (23) are positioned at the middle machine body two end faces, and 4 end face Fabricating machinery operator's stations (22) are arranged in fuselage processing end face both sides.
2. layout method is assembled in a kind of large aircraft middle machine body digitalisation according to claim 1, it is characterized in that described sidewall paneling steady arm (9), led intersection point frame steady arm (10), lower wall panels steady arm (11), wainscot steady arm (13), the kinematic axis of fuselage steady arm (19) adopts closed grating scale, at X, Y, consist of closed-loop control on three directions of Z, and then accurate movement and the location of realizing three directions, one group of formation of per 4 steady arms digitalisation attitude-adjusting unit is realized the 6DOF pose adjustment of assembling object based on the posture adjustment principle of work of four-point supporting.
3. layout method is assembled in a kind of large aircraft middle machine body digitalisation according to claim 1, it is characterized in that described parts assembling erect-position and processing erect-position adopt many laser trackers (2) to set up the precise digitization field of fitter's shop, realize the accurate location to fuselage parts and on-the-spot tooling device.
4. layout method is assembled in a kind of large aircraft middle machine body digitalisation according to claim 1, it is characterized in that described master plays intersection point frame shape-keeping frame (6), lower wall panels shape-keeping frame (12), wainscot shape-keeping frame (14) or wing body interface frame, mating frame shape-keeping frame (17) continuous with corresponding steady arm by process connection, indirectly realize support and the pose adjustment of assembling object.
5. layout method is assembled in a kind of large aircraft middle machine body digitalisation according to claim 1, it is characterized in that the flexible adsorption tooling of described multiple dot array (21) can generate and the on all four absorption dot matrix of fuselage surface geometric shape, and on telescopic unit the setting pressure sensor, control flexible adsorption tooling (21) feeding of multiple dot array by the feedback of power.
6. layout method is assembled in a kind of large aircraft middle machine body digitalisation according to claim 1, it is characterized in that described master plays crossing point holes face processing equipment (20) and can both realize five-axle linkage with fuselage end face and measurement point hole Fabricating machinery (23), and then satisfy the processing request of associated orifices and face.
7. layout method is assembled in a kind of large aircraft middle machine body digitalisation according to claim 1, it is characterized in that described parts assembling erect-position and processing erect-position guide workman's operation by visual panel in the manual assembly link, have realized the emulation of digitalisation pre-assy.
CN2010101367823A 2010-03-30 2010-03-30 Layout method of central airframe digital assembly of big plane CN101850850B (en)

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