CN118220520B - Aircraft rear fuselage section assembly equipment and method - Google Patents
Aircraft rear fuselage section assembly equipment and method Download PDFInfo
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- CN118220520B CN118220520B CN202410643995.7A CN202410643995A CN118220520B CN 118220520 B CN118220520 B CN 118220520B CN 202410643995 A CN202410643995 A CN 202410643995A CN 118220520 B CN118220520 B CN 118220520B
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- 238000000034 method Methods 0.000 title claims abstract description 13
- 241000252254 Catostomidae Species 0.000 claims abstract description 10
- 230000000712 assembly Effects 0.000 claims description 13
- 238000000429 assembly Methods 0.000 claims description 13
- 238000004080 punching Methods 0.000 claims description 7
- 238000003780 insertion Methods 0.000 claims description 3
- 230000037431 insertion Effects 0.000 claims description 3
- 238000003754 machining Methods 0.000 claims description 2
- 241000196324 Embryophyta Species 0.000 claims 1
- 230000001681 protective effect Effects 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 21
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 238000003825 pressing Methods 0.000 description 5
- 238000004140 cleaning Methods 0.000 description 3
- 210000001503 joint Anatomy 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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Abstract
The application provides equipment and a method for assembling a rear fuselage section of an aircraft, which belong to the technical field of aircraft manufacturing, and comprise the following steps: the main frame comprises a middle shaft track, a radial track, a first stand and a second stand; the movable bottom frame is respectively and slidably connected to the middle shaft track or the radial track; the upper skin lifting appliance comprises a frame and suckers, wherein a plurality of suckers are arranged at the inner side of the frame and correspond to the bottom of the upper skin, and the suckers can open an opening at the bottom of the upper skin; the positioning assembly is respectively provided with a positioning pin corresponding to the rear fuselage section; the fixed component is detachably arranged on the movable bottom frame. Utilize slide rail and mounting platform cooperation, utilize the guide pillar to realize the installation accuracy of setting element and platform, make operating personnel can operate the inside of complicated back fuselage section, utilize hold-down pin and bolt, realize setting element quick detach installation, promote installation effectiveness, and guarantee the installation accuracy.
Description
Technical Field
The application belongs to the technical field of aircraft manufacturing, and particularly relates to equipment and a method for assembling a rear fuselage section of an aircraft.
Background
The back fuselage of aircraft is long 4462mm, and the inner space is complicated, and operating space is little, and the joint quantity that is connected with other positions is many along with the increase of aircraft function moreover, and the oil circuit needs the leakproofness, and the back fuselage adopts the birdcage design, and operating space is not enough. In order to ensure good tightness, a whole skin structure is adopted at present, but the installation difficulty is high, and particularly, the internal structure is difficult to enter into operation, so that the operation difficulty of operators is high, and the assembly efficiency is low.
Through searching, a coordinated assembly method of an unmanned fixed wing aircraft fuselage, such as the one with the application publication number of CN 108557111A, is found, and the fuselage skin of the rear fuselage section is seen to adopt a left and right structure, so that the unmanned fixed wing aircraft fuselage is a common assembly structure in the prior art, the installation of the structure is simpler, the assembly fixture is also more common, but the tightness of the skins of the left and right structures is difficult to ensure, and the unmanned fixed wing aircraft fuselage is not suitable for a model with high tightness requirements.
Disclosure of Invention
Based on the defects of the prior art, the application provides the equipment and the method for assembling the rear fuselage section of the airplane, which can complete the assembly of the upper and lower structural skins of the rear fuselage section and improve the assembly efficiency.
An aircraft aft fuselage section assembly device comprising:
The main frame comprises a central shaft track, radial tracks, a first vertical frame and a second vertical frame, wherein the central shaft track is horizontally and transversely arranged in the middle of the main frame, and the radial tracks are symmetrically arranged on two sides of the middle of the central shaft track; a first stand and a second stand are oppositely arranged on the middle shaft rails at the front side and the rear side of the radial rail;
The movable bottom frame comprises a plurality of specifications, and the movable bottom frames with the plurality of specifications are respectively and slidably connected to the middle shaft track or the radial track and can move along the middle shaft track or the radial track in a guiding way;
The upper skin lifting appliance comprises a frame and a sucker, the size of the frame is matched with that of the upper skin, and an upper skin positioning structure is arranged on the inner side of the frame;
The positioning assembly is respectively provided with a positioning pin corresponding to the rear fuselage section structure and comprises a plurality of specifications, and the positioning assembly is detachably arranged on one or a plurality of movable underframes;
the fixed assembly is detachably mounted on the movable bottom frame and comprises a right frame fixed assembly and a left frame fixed assembly, and the right frame fixed assembly and the left frame fixed assembly are used for riveting the machined rear fuselage section.
By adopting the technical scheme, the rear machine body part to be processed is accommodated in the main frame in a limiting manner, the movable bottom frame which can be moved and positioned accurately is arranged in the main frame, the positioning component is carried by the movable bottom frame to move in the main frame, the processing position can be positioned accurately, and the positioning component or the fixing component on the movable bottom frame is replaced according to the process steps for processing; the equipment adopts the upper skin lifting tool with the outer protection frame to move the upper skin, can prop up and sleeve the upper skin with a large size at the upper frame position, can set the propping up size of the upper skin lifting tool according to the requirement, effectively ensures that the installation procedure is carried out smoothly, can realize the skin installation of the upper and lower structures through the equipment, and ensures that the product has good waterproof performance.
Preferably, the upper skin lifting appliance comprises a top frame, an outer protection frame, top sucking discs, side sucking discs, an ear plate, a positioning bolt and a tightening belt, wherein the top frame is of a rectangular frame structure arranged in the horizontal direction, and a plurality of groups of top sucking discs are arranged in the middle of the lower end of the top frame at intervals and used for sucking the skin from the top;
the lower end of the top frame is provided with a plurality of ear plates, the ear plates are connected with positioning bolts, and the positioning bolts are used for connecting corresponding ear pieces on the skin so as to position the upper skin;
the lower ends of the two long sides of the top frame are respectively connected with an outer protection frame, and a plurality of groups of suckers are oppositely arranged on the outer protection frame and used for sucking the outer side of the skin from the side surface, so that the bottom of the skin can be unfolded;
the top frame is also provided with a plurality of tightening belts at intervals for assisting in fixing the positions of the skins and preventing the skins from falling off in moving.
By adopting the technical scheme, the upper skin lifting appliance adopts the positioning pins to correspondingly connect the ear plates of the upper skin, and the ear plates are fixed at the positions of the upper skin, so that the positioning is accurate, the side sucker structure is adopted to prop open the bottom opening of the skin, the skin is safe and reliable, no damage is caused to the skin, and the sucker can be provided with a telescopic structure, so that the prop-open size can be adjusted as required; the equipment can solve the difficulty of skin installation on a large scale, improve the installation efficiency, ensure the installation quality, and adopt a large scale skin structure, thereby improving the waterproof performance of the product.
Preferably, the top frame is connected with the outer frame by a quick-release structure.
Through adopting above-mentioned technical scheme, can demolish the outer frame of protecting of going up the skin hoist after accomplishing the installation of skin, be convenient for follow-up installation.
Preferably, the middle shaft movable bottom frame comprises a sliding block and a movable platform, the upper end of the movable platform is provided with a mounting hole for connecting and positioning, the lower end of the movable platform is fixedly provided with the sliding block, and the sliding block is in guiding sliding connection with the middle shaft rail; the inner side of the middle shaft track is provided with a plurality of groups of positioning plates with positioning holes at intervals on the corresponding underframe, the inner side of the mobile platform is provided with positioning columns, and the positioning columns can be embedded into the positioning holes for positioning.
Through adopting above-mentioned technical scheme, axis removal underframe sliding connection is provided with the reference column on the axis track of well frame, and the axis removes the underframe, and the axis track inboard sets up a plurality of locating plates, and the axis removes the underframe and removes to corresponding position and can insert the reference column in the locating plate to the locking position realizes moving platform's accurate location.
Preferably, the first stand and the second stand are both provided with a positioning plate, on which a plurality of positioning pins and a pressing pin are mounted, the positioning pins are used for positioning the end parts of the rear fuselage section, and the pressing pins are used for positioning the structure of the rear fuselage section from the side edges.
By adopting the technical scheme, the first stand and the second stand are used for positioning and supporting the rear machine body product to be processed from the front end and the rear end, the positioning pin is used for positioning the product from the axial direction, and the pressing pin is used for positioning the product from the radial direction.
Preferably, auxiliary rails are respectively arranged on the underframe at two lateral sides of the radial rail, the direction of each auxiliary rail is parallel to the middle shaft rail, positioning plates are arranged on the underframe at the outer side of each auxiliary rail at intervals, and insertion holes are formed in the positioning plates; the auxiliary rail is connected to the bottom of the first stand or the second stand in a sliding manner, and positioning columns matched with the positioning plates are respectively arranged at the lower ends of the first stand and the second stand.
Through adopting above-mentioned technical scheme, the interval position of first grudging post and second grudging post can be adjusted to cooperate product processing better, and, first grudging post and second grudging post all can adopt the mode locking of reference column.
A method for assembling a rear fuselage section of a large aircraft comprises the following steps:
s1, adjusting a main frame, and positioning and placing an upper frame to be processed on the main frame;
S2, moving an upper skin to a main frame by adopting an upper skin lifting tool, wherein the upper skin lifting tool supports the upper skin, and the upper skin is sleeved on the upper frame; positioning and connecting the upper skin and the upper frame, and punching;
S3, removing the upper skin and part of the upper frame mechanism out of the main frame by using an upper skin lifting appliance, and separating and cleaning the upper skin and the upper frame;
s4, installing the lower frame, and positioning and installing the lower frame in the main frame by adopting a corresponding positioning assembly for positioning;
s5, installing the lower skin, positioning the lower skin and the lower frame by adopting corresponding positioning assemblies, and splitting the lower skin and the lower frame after the positioning assemblies are used for performing punching treatment;
s6, repeating the steps S1 to S2, positioning and installing the upper skin and the upper frame in the main frame, and positioning, connecting and fixing;
s7, the lower frame is installed again, the lower frame is installed in the main frame in a positioning mode by adopting the corresponding positioning assembly again, and the lower frame is connected with the upper frame by adopting the fixing assembly;
S8, installing the lower skin, positioning and moving the lower skin to a machining position in the main frame by adopting a corresponding positioning assembly, positioning and installing the lower skin, and completing assembly;
S9, removing the positioning assembly, lifting the whole rear fuselage section out by using an upper skin lifting tool, and taking down the whole rear fuselage section.
By adopting the technical scheme, the upper skin and the upper frame with large sizes are preinstalled in sequence, the lower skin and the lower frame are preinstalled, and the upper skin and the lower frame are split, polished and cleaned after positioning and punching processing respectively; then install the preinstallation position again and adopt, install covering and upper frame earlier, then connect the lower frame, the covering is installed down, and operating is reasonable, guarantees the installation accuracy and guarantees installation effectiveness.
Preferably, the upper skin sling comprises a top frame and an outer protecting frame,
When the upper skin lifting appliance moves to the upper frame position, the side sucking discs of the outer protecting frame act, and the bottom of the upper skin is sucked from two sides and simultaneously stretched outwards, so that the lower end opening of the upper skin is propped up;
After the upper skin is sleeved on the upper frame, the outer protecting frame is removed;
the top sucker of the top frame and the locating pin keep locating the upper skin.
Through adopting above-mentioned technical scheme, go up the open suit of covering in the jumpers can be with the upper cover of jumbo size outside the frame to can realize the installation and the structure of upper and lower formula covering of jumbo size, make the product have good waterproof performance, outer protecting frame can be demolishd, the follow-up installation of being convenient for.
In summary, the present application includes at least one of the following beneficial technical effects:
1. The application provides assembly equipment suitable for a rear fuselage section of a large-sized aircraft, which can adopt an upper skin installation structure and a lower skin installation structure, solves the problem of difficult installation of the whole skin, and can ensure the tightness of the skin structure.
2. According to the application, the sliding rail is matched with the mounting platform, the mounting precision of the positioning piece and the platform is realized by utilizing the guide post, so that an operator can operate the inside of the complex rear machine body section, the quick-dismantling mounting of the positioning piece is realized by utilizing the compression pin and the bolt, the mounting efficiency is improved, and the mounting precision is ensured.
Drawings
Fig. 1 is a schematic diagram of the overall apparatus.
Fig. 2 is a schematic view of an upper skin spreader structure.
Fig. 3 is a partial enlarged view of the portion a in fig. 2.
Fig. 4 is a schematic view of the main frame structure.
Fig. 5 is an enlarged schematic view of part B of fig. 4.
Fig. 6 is a partially enlarged schematic view of the structure of fig. 4.
Fig. 7 is a partial schematic view of a main frame showing a first set of lower end fixing assemblies.
Fig. 8 is a partial schematic view of a main frame showing a second set of lower end fixing assemblies.
Fig. 9 is a partial schematic view of a main frame showing a third set of lower end fixing assemblies.
Fig. 10 is a partial schematic view of a main frame showing a fourth set of lower end fixing assemblies.
Fig. 11 is a partial schematic view of a main frame showing a fifth set of lower end fixing assemblies.
Reference numerals: 1. an upper skin lifting appliance; 101. a top frame; 102. a top sucker; 103. tightening the belt; 104. an external protection frame; 105. a side sucker; 106. an auxiliary bracket; 107. a quick-release structure; 108. ear plates; 109. positioning bolts;
2. a right frame fixing assembly; 3. a right skin positioning assembly; 4. a right frame positioning assembly; 5. a third movable bottom frame; 6. a fourth movable bottom frame; 7. a fifth moving bottom frame; 8. a left frame positioning assembly; 9. a left skin positioning assembly; 10. a left frame fixing assembly;
11. A main frame; 111. a second stand; 112. a central shaft rail; 113. a radial track; 114. a first stand; 115. a chassis;
12. moving the bottom frame left;
13. A second movable bottom frame; 131. a mobile platform; 132. a slide block;
14. A first movable bottom frame;
15. A lower end positioning assembly; 151. an upper frame positioning assembly; 152. the skin lug positioning and supporting assembly; 153. a lower joint positioning assembly; 154. a lower frame positioning assembly; 155. a lower skin positioning assembly;
16. Right moving the bottom frame;
17. a positioning pin; 18. a hold-down pin; 19. a positioning plate; 20. positioning columns; 21. a positioning plate; 22. and an auxiliary rail.
Detailed Description
The present application will be described in further detail with reference to the accompanying drawings.
Referring to fig. 1, an aircraft rear fuselage section assembly device comprises a main frame 11, a movable underframe, an upper skin lifting tool 1, a positioning assembly and a fixing assembly, wherein a plurality of movable underframes are slidably connected to the main frame 11, the movable underframe can move on the main frame 11 in a guiding manner, and a plurality of guide pillar structures are correspondingly arranged on the movable underframe and the main frame 11 and are used for fixing the position of a movable base on the main frame 11;
the upper end of the movable bottom frame is detachably provided with a plurality of positioning components or fixing components;
An upper skin lifting appliance 1 is hung above the main frame 11, and the upper skin lifting appliance 1 can be matched with a positioning assembly to effectively position and support a rear fuselage section to be processed. The upper skin sling 1 can move to the outer side of the main frame 11, so that the upper skin is convenient to disassemble and assemble.
The rear fuselage section of the embodiment comprises an upper frame, a lower frame, an upper skin and a lower skin, wherein the upper skin and the lower skin are of semi-cylindrical structures, the upper skin and the lower skin are in butt joint and enclose to form a complete outer skin, and the radian of the upper skin is larger than that of the lower skin; the upper frame is a cage-shaped framework matched with the upper skin in shape, and the lower frame is a cage-shaped framework matched with the lower skin in shape; the upper frame with the upper skin secured thereto and the lower frame with the lower skin secured thereto are assembled to form an integral aft fuselage section.
Referring to fig. 2, the upper skin lifting appliance 1 comprises a top frame 101, an outer protecting frame 104, suckers, lugs, a positioning bolt 109 and a tightening belt 103, wherein the top frame 101 is of a rectangular frame structure arranged in the horizontal direction, the size of the top frame 101 is matched with that of the upper skin, a plurality of groups of top suckers 102 are arranged in the middle of the lower end of the top frame 101 at intervals, and the top suckers 102 are used for sucking the skin from the top; the lower ends of two long sides of the top frame 101 are detachably connected with an outer protection frame 104, a plurality of groups of side sucking discs 105 are oppositely arranged on the outer protection frame 104, and the side sucking discs 105 are used for sucking the outer side of the skin from the side face and can prop open the bottom of the skin. The top sucker 102 and the side sucker 105 are connected with vacuum generators, and the working states of the suckers can be controlled in groups.
The top frame 101 is further provided with a plurality of tightening bands 103 at intervals, which are used for assisting in fixing the skin position and preventing falling off in moving.
Referring to fig. 3, a plurality of ear plates 108 are provided at the lower end of the top frame 101, and positioning bolts 109 are connected to the ear plates 108, and the positioning bolts 109 are used for connecting corresponding fixing lugs on the skin so as to accurately position the skin.
Referring to fig. 3, the top frame 101 is detachably connected with the outer protecting frame 104, and a quick-dismantling structure 107 composed of a positioning bolt 109 and a positioning plate 21 is mounted at the upper end of the outer protecting frame 104; the side of the top frame 101 is provided with a positioning plate 21 which is matched with the positioning bolt 109 of the outer protecting frame 104.
Referring to fig. 4, the main frame 11 includes a bottom frame 115, a central shaft rail 112, radial rails 113, a first stand 114 and a second stand 111, the upper end of the bottom frame 115 is horizontally and transversely provided with the central shaft rail 112, the bottom frames 115 on two sides of the middle part of the central shaft rail 112 are symmetrically provided with the radial rails 113, and the radial rails 113 are perpendicular to the central shaft rail 112; on both lateral sides of the radial rail 113, a first and a second upright 114, 111 are provided for supporting the aft fuselage section, respectively.
Referring to fig. 5, the first stand 114 and the second stand 111 span the central shaft rail 112, and a positioning disc 19 is fixed at the middle of opposite sides of the first stand 114 and the second stand 111, and the positioning discs 19 are coaxially arranged at intervals front and back; the positioning disc 19 is provided with a plurality of positioning pins 17 corresponding to the front end structure and the rear end structure of the upper frame and the lower frame, and the positioning pins 17 are positioned along the end shapes of the upper frame and the lower frame; a pressing pin 18 is also connected to the upper end of the positioning plate 19 for pressing the upper end of the upper skin.
Referring to fig. 6, auxiliary rails 22 are respectively arranged on the underframe 115 at two lateral sides of the radial rail 113, the direction of the auxiliary rails 22 is parallel to the middle shaft rail 112, positioning plates 21 are arranged on the underframe 115 at the outer side of the auxiliary rails 22 at intervals, and insertion holes are arranged on the positioning plates 21; the auxiliary rail 22 is slidably connected to the bottom of the first stand 114 or the second stand 111, the lower ends of the first stand 114 and the second stand 111 are respectively provided with a positioning column 20, and when the positioning column 20 is embedded into the jack of the corresponding positioning plate 21, the positions of the first stand 114 and the second stand 111 are locked.
Referring to fig. 6, the bottom frame for moving the middle shaft comprises a sliding block 132 and a moving platform 131, wherein the upper end of the moving platform 131 is provided with a mounting hole for connecting and positioning, the lower end of the moving platform 131 is fixedly provided with the sliding block 132, and the sliding block 132 is in guiding sliding connection on the middle shaft rail 112;
In order to position the bottom frame of the middle shaft, a plurality of groups of positioning plates 21 provided with positioning holes are arranged on the corresponding bottom frame 115 on the inner side of the middle shaft track 112 at intervals, positioning columns 20 are arranged on the inner side of the mobile platform 131, and the positioning columns 20 can be embedded into the positioning holes, so that the position of the mobile platform 131 is locked.
Referring to fig. 1, the moving base includes a left moving base 12, a right moving base 16, and a plurality of center shaft moving bases, and the corresponding lower end positioning assemblies 15 are mounted on one or more center shaft moving bases according to the selection of the process steps;
The plurality of middle shaft moving bottom frames are arranged on the middle shaft track 112 in a guiding and moving way, and the middle shaft moving bottom frames are used for supporting the lower end positioning assembly 15; the bottom bracket of the present embodiment includes a first moving bottom bracket 14, a second moving bottom bracket 13, a third moving bottom bracket 5, a fourth moving bottom bracket 6 and a fifth moving bottom bracket 7, and the first moving bottom bracket 14, the second moving bottom bracket 13, the third moving bottom bracket 5, the fourth moving bottom bracket 6 and the fifth moving bottom bracket 7 are sequentially disposed on the bottom bracket rail 112.
The left moving bottom frame 12 and the right moving bottom frame 16 are symmetrically arranged on radial rails 113 on both sides, and can move along the radial rails 113, and the left moving bottom frame 12 and the right moving bottom frame 16 are used for supporting a positioning assembly or a fixing assembly.
Referring to fig. 1, the positioning assemblies include a left skin positioning assembly 9, a right skin positioning assembly 3, a left frame positioning assembly 8, a right frame positioning assembly 4 and a lower end positioning assembly 15, wherein the lower end positioning assemblies 15 are various, and the corresponding lower end positioning assemblies 15 are selected according to the process steps and are mounted on one or more middle shaft moving bottom frames; the left skin positioning assembly 9 and the left frame positioning assembly 8 can be installed on the left moving bottom frame 12 in a split manner, and the right skin positioning assembly 3 and the right frame positioning assembly 4 can be installed on the right moving bottom frame 16 in a split manner; the right frame positioning assembly 4 and the left frame positioning assembly 8 are used for positioning an upper frame or a lower frame of the rear fuselage, and the right skin positioning assembly 3 and the left skin positioning assembly 9 are used for positioning an upper skin or a lower skin;
the fixed assembly comprises a right frame fixed assembly 2 and a left frame fixed assembly 10, wherein the right frame fixed assembly 2 and the left frame fixed assembly 10 are used for assembling an upper frame fixed with an upper skin and a lower frame fixed with a lower skin into a whole rear fuselage section.
Referring to fig. 7 to 11, the lower end positioning assembly 15 includes an upper frame positioning assembly 151, a skin tab positioning support assembly 152, a lower joint positioning assembly 153, a lower frame positioning assembly 154, and a lower skin positioning assembly 155, which are respectively mounted on the corresponding center shaft moving bottom frame.
Referring to fig. 7, an upper frame positioning assembly 151 is coaxially disposed between the first stand 114 and the second stand 111, and the upper frame positioning assembly 151 is matched with the left frame positioning assembly 8 and the right frame positioning assembly 4 for use to jointly position an upper frame;
Referring to fig. 8, the skin tab positioning and supporting component 152 includes a plurality of skin tab positioning and supporting components 152 disposed at intervals, wherein the plurality of skin tab positioning and supporting components 152 are coaxially disposed between the first stand 114 and the second stand 111 at intervals, and the skin tab positioning and supporting components 152 are provided with a plurality of tab positioning pins 17 matched with tab structures at the lower parts of two sides of the upper skin, and the tab positioning and supporting components are respectively used for connecting skin tabs to limit the positions of the sides of the skin;
referring to fig. 9, a lower joint positioning assembly 153 is coaxially disposed between the first and second uprights 114 and 111, the lower joint positioning assembly 153 being for mounting a joint;
referring to fig. 10, a lower frame positioning assembly 154 is coaxially disposed between the first stand 114 and the second stand 111, and the lower frame positioning assembly 154 is used for positioning the lower frame;
Referring to fig. 11, a lower skin positioning assembly 155 is coaxially disposed between the first stand 114 and the second stand 111, and the lower skin positioning assembly 155 is used for supporting the lower skin for mounting the lower skin to the lower frame.
The working method of the aircraft rear fuselage section assembly equipment comprises the following steps:
s1, installing an upper frame on a main frame for positioning, wherein the specific steps are as follows:
the upper frame positioning assembly is mounted on a third movable bottom frame, and the third movable bottom frame moves to a using position along a middle shaft track;
the left frame positioning assembly and the right frame positioning assembly are respectively arranged on the left moving bottom frame and the right moving bottom frame, the left moving bottom frame and the right moving bottom frame are moved to the using positions along the corresponding radial tracks, and connecting rods are arranged between the left frame positioning assembly and the right frame positioning assembly for fixing; the upper frame of the rear machine body is installed from the top, stringers of the rear machine body on two sides are respectively fixedly installed on the outer sides of the upper frame, and the upper frame is assembled;
s2, installing an upper skin outside an upper frame, wherein the concrete steps are as follows:
the skin lug positioning support assembly is mounted on the first moving bottom frame, the second moving bottom frame and the fourth moving bottom frame; moving the skin lug positioning assembly to a use position, and supporting the framework by the positioner;
Removing the left frame positioning assembly and the right frame positioning assembly, and placing the left frame positioning assembly and the right frame positioning assembly back on the stored bracket; the left skin positioning component and the right skin positioning component are respectively arranged on the left moving bottom frame and the right moving bottom frame;
The upper skin is installed in an upper skin lifting appliance, the upper skin is positioned by matching a top sucker and a locating pin lug plate with lug holes on the skin, and the binding belt prevents the skin from falling off during transportation; the upper skin lifting appliance moves to a using position, the side sucking discs on two sides prop up the bottom of the skin, and the upper frame is arranged;
Removing the outer protecting frames at two sides of the upper skin lifting appliance, and connecting skin lugs to the skin lug positioning and supporting assembly;
s3, assembling an upper skin and an upper frame, wherein the concrete steps are as follows:
the left skin positioning assembly and the right skin positioning assembly are moved to the using positions, and the suckers of the left skin positioning assembly and the right skin positioning assembly absorb the skins on the two sides of the skins; removing the upper skin lifting appliance, and riveting the upper skin and the upper frame;
Removing the skin lug positioning support assembly, and repairing and riveting the blocking position of the upper skin; installing the joint outside the skin to complete the upper skin structure assembly;
Removing the upper skin structure assembly, removing the left skin positioning assembly and the right skin positioning assembly, and placing the left skin positioning assembly and the right skin positioning assembly on a bracket; removing the upper skin part by using an upper skin lifting appliance; after the upper skin structure assembly is removed, cleaning the upper skin to remove scraps generated by punching;
S4, installing a bottom plate and connectors corresponding to the bottom plate, wherein the specific steps are as follows:
The left frame fixing assembly and the right frame fixing assembly are arranged on the left moving bottom frame and the right moving bottom frame, the left moving bottom frame and the right moving bottom frame are moved to the using positions along the corresponding radial tracks, and the positioning pieces of the left moving bottom frame and the right moving bottom frame are positioned and locked with the rivet holes on the edges of the lower frame from two sides; the bottom plate is positioned by lug holes on two sides and riveted;
Removing the skin lug positioning support assembly, and mounting the lower frame positioning assembly on the second movable bottom frame; moving the lower frame positioning assembly, the first movable bottom frame, the fourth movable bottom frame and the fifth movable bottom frame to a use position, moving the lower joint positioning assembly to a processing position, installing a joint on a bottom plate, and moving out the fourth movable bottom frame and the fifth movable bottom frame after the joint is installed;
S5, installing a lower frame, wherein the concrete steps are as follows: installing the lower frame positioning assembly on the fourth movable bottom frame, moving to a using position, installing the lower frame, dismantling the upper frame positioning assembly after the lower frame positioning assembly is completed, and installing a cabin door structural member; removing the lower frame positioning assembly and the third movable bottom frame after the lower frame positioning assembly and the third movable bottom frame are moved out;
S6, installing a lower skin, wherein the concrete steps are as follows:
the lower skin positioning assembly is mounted on the second movable bottom frame, the third movable bottom frame and the fourth movable bottom frame, the lower skin is mounted on the positioning assembly and then moved to a using position, the lower skin is mounted on the lower frame, and positioning and punching are carried out;
removing the left frame fixing assembly and the right frame fixing assembly, and decomposing and cleaning the lower frame and the lower skin;
S7, repeating the steps S1 to S3:
S8, installing a bottom plate and a lower frame, wherein the concrete steps are as follows:
the bottom plate is installed according to the previous hole position, then the skin lug positioning and supporting component is removed, and the lower frame positioning component is installed on the second movable bottom frame;
Moving the lower frame positioning assembly, the first moving bottom frame, the fourth moving bottom frame and the fifth moving bottom frame to a using position, installing the lower joint positioning assembly on the main frame, and installing joints; after the installation is completed, the fourth movable bottom frame and the fifth movable bottom frame are moved out;
the lower frame positioning assembly is installed on the fourth movable bottom frame and moved to a using position, the lower frame is installed, and the lower frame is connected with the upper frame in a positioning way;
Dismantling the upper frame positioning assembly and installing a cabin door;
after the cabin door is installed, the lower frame positioning assembly and the fourth movable bottom frame are removed, and then the lower frame positioning assembly is removed;
s9, installing a lower skin, wherein the concrete steps are as follows: the lower skin positioning assembly is mounted on the second movable bottom frame, the third movable bottom frame and the fourth movable bottom frame, the lower skin is mounted on the lower skin positioning assembly and then moved to a using position, and the lower skin is mounted;
removing the joint positioning assembly; the upper frame positioning component is disassembled and placed on the bracket;
the product is bound to the lifting appliance by a binding belt, and the whole product is laterally taken out of the lower frame.
The above embodiments are not intended to limit the scope of the present application, so: all equivalent changes in structure, shape and principle of the application should be covered in the scope of protection of the application.
Claims (7)
1. An aircraft aft fuselage section assembly apparatus, comprising:
The main frame (11), the main frame (11) comprises a central shaft track (112), radial tracks (113), a first vertical frame (114) and a second vertical frame (111), the central shaft track (112) is horizontally and transversely arranged in the middle of the main frame (11), and the radial tracks (113) are symmetrically arranged on two sides of the middle of the central shaft track (112); a first stand (114) and a second stand (111) are oppositely arranged on the middle shaft rails (112) at the front side and the rear side of the radial rail (113);
the movable bottom frame comprises a plurality of specifications, and the movable bottom frames with the plurality of specifications are respectively and slidably connected to the middle shaft track (112) or the radial track (113) and can move along the middle shaft track (112) or the radial track (113) in a guiding way;
The upper skin lifting appliance (1) comprises a frame and a sucker, the size of the frame is matched with that of the upper skin, and an upper skin positioning structure is arranged on the inner side of the frame; the upper skin lifting appliance (1) comprises a top frame (101), an outer protection frame (104), top end sucking discs (102), side sucking discs (105), ear plates (108), positioning bolts (109) and tightening belts (103), wherein the top frame (101) is of a rectangular frame structure arranged in the horizontal direction, and a plurality of groups of top end sucking discs (102) are arranged in the middle of the lower end of the top frame (101) at intervals and used for sucking the skin from the top;
The lower end of the top frame (101) is provided with a plurality of lug plates (108), the lug plates (108) are connected with positioning bolts (109), and the positioning bolts (109) are used for connecting corresponding lugs on the skin so as to position the upper skin;
The lower ends of two long sides of the top frame (101) are respectively connected with an outer protection frame (104), and a plurality of groups of suckers are oppositely arranged on the outer protection frame (104) and used for sucking the outer side of the skin from the side surface, so that the bottom of the skin can be unfolded;
A plurality of tightening belts (103) are also arranged on the top frame (101) at intervals and are used for assisting in fixing the positions of the skins to prevent falling in moving;
the positioning assembly is respectively provided with a positioning pin (17) corresponding to the rear fuselage section structure and comprises a plurality of specifications, and the positioning assembly is detachably arranged on one or a plurality of movable underframes;
The fixed assembly is detachably mounted on the movable bottom frame and comprises a right frame fixed assembly (2) and a left frame fixed assembly (10), and the right frame fixed assembly (2) and the left frame fixed assembly (10) are used for riveting the machined fuselage section.
2. An aircraft aft fuselage section assembly plant according to claim 1, wherein the roof frame (101) is connected to the outer frame by a quick release structure (107).
3. The aircraft rear fuselage section assembly device according to claim 1, wherein the central shaft moving bottom frame comprises a sliding block (132) and a moving platform (131), the upper end of the moving platform (131) is provided with a mounting hole for connecting and positioning, the lower end of the moving platform (131) is fixedly provided with the sliding block (132), and the sliding block (132) is in guiding sliding connection with the central shaft rail (112); a plurality of groups of positioning plates (21) provided with positioning holes are arranged on the underframe (115) corresponding to the inner side of the middle shaft track (112) at intervals, positioning columns (20) are arranged on the inner side of the mobile platform (131), and the positioning columns (20) can be embedded into the positioning holes for positioning.
4. An aircraft aft fuselage section fitting apparatus according to claim 1, wherein the first and second uprights (114, 111) are each provided with a positioning disc (19) on which positioning discs (19) a plurality of positioning pins (17) and a hold-down pin (18) are mounted, the positioning pins (17) being used for positioning the end of the connecting aft fuselage section, the hold-down pins (18) being used for sideways positioning the structure of the aft fuselage section.
5. An aircraft aft fuselage section assembly device according to claim 4, wherein the radial rails (113) are provided with auxiliary rails (22) on the underframe (115) on both lateral sides thereof, the auxiliary rails (22) being parallel to the central shaft rail (112), positioning plates (21) being provided at intervals on the underframe (115) outside the auxiliary rails (22), and insertion holes being provided on the positioning plates (21); the auxiliary rail (22) is slidably connected to the bottom of the first stand (114) or the second stand (111), and positioning columns (20) matched with the positioning plates (21) are respectively arranged at the lower ends of the first stand (114) and the second stand (111).
6. A method of assembling a rear fuselage section of a large aircraft, characterized by using an aircraft rear fuselage section assembly apparatus according to claim 1, comprising the steps of:
s1, adjusting a main frame (11), and positioning and placing an upper frame to be processed on the main frame (11);
S2, an upper skin lifting appliance (1) is adopted to move the upper skin to a main frame (11), the upper skin lifting appliance (1) stretches the upper skin, and the upper skin is sleeved on the upper frame; positioning and connecting the upper skin and the upper frame, and punching;
S3, an upper skin lifting appliance (1) is used for removing the upper skin and an upper frame part mechanism out of the main frame (11), and the upper skin and the upper frame are split and cleaned;
s4, installing a lower frame, and positioning and installing the lower frame in the main frame (11) by adopting a corresponding positioning assembly for positioning;
S5, installing the lower skin, positioning the lower skin and the lower frame by adopting corresponding positioning assemblies, and splitting the lower skin and the lower frame after the positioning assemblies are used for performing punching treatment;
s6, repeating the steps S1 to S2, positioning and installing the upper skin and the upper frame in the main frame (11), and positioning, connecting and fixing;
S7, the lower frame is installed again, the lower frame is installed in the main frame (11) in a positioning mode by adopting a corresponding positioning assembly, and the lower frame is connected with the upper frame by adopting a fixing assembly;
S8, installing the lower skin, positioning and moving the lower skin to a machining position in the main frame (11) by adopting a corresponding positioning assembly, positioning and installing the lower skin, and completing assembly;
s9, removing the positioning assembly, lifting the whole rear fuselage section out by using an upper skin lifting tool (1), and taking down the whole rear fuselage section.
7. A method of assembling a rear fuselage section of a large aircraft according to claim 6, wherein the upper skin sling (1) comprises a top frame (101) and an outer protective frame (104),
When the upper skin lifting appliance (1) moves to the upper frame position, the side sucking discs (105) of the outer protecting frame (104) act, and the bottom of the upper skin is sucked from two sides and simultaneously stretched outwards, so that the lower end opening of the upper skin is propped up;
after the upper skin is sleeved on the upper frame, the outer protecting frame (104) is removed;
The top sucker of the top frame (101) and the locating pin (17) keep locating the upper skin.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410643995.7A CN118220520B (en) | 2024-05-23 | 2024-05-23 | Aircraft rear fuselage section assembly equipment and method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410643995.7A CN118220520B (en) | 2024-05-23 | 2024-05-23 | Aircraft rear fuselage section assembly equipment and method |
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| CN118220520A CN118220520A (en) | 2024-06-21 |
| CN118220520B true CN118220520B (en) | 2024-08-06 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742044A (en) * | 2017-01-22 | 2017-05-31 | 艾雷奥特（江苏）飞机工业有限公司 | Small General Aircraft Assembling Production management method |
| CN107538042A (en) * | 2017-10-19 | 2018-01-05 | 南京航空航天大学 | The circular orbit punching system and its operation method of a kind of rigid flexible system |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11655019B2 (en) * | 2020-05-27 | 2023-05-23 | The Boeing Company | Method and system for coupling a vertical stabilizer to an aircraft fuselage |
| CN113386070B (en) * | 2021-07-20 | 2022-07-19 | 中航沈飞民用飞机有限责任公司 | Automatic flexible frock of bow-shaped cardboard formula |
| CN115302790A (en) * | 2022-06-29 | 2022-11-08 | 中航西安飞机工业集团股份有限公司 | A clamping and positioning device for butt joint of composite long truss skin and using method |
| CN117125264A (en) * | 2023-09-08 | 2023-11-28 | 清华大学 | Helicopter middle body assembling and positioning system and control method thereof |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106742044A (en) * | 2017-01-22 | 2017-05-31 | 艾雷奥特（江苏）飞机工业有限公司 | Small General Aircraft Assembling Production management method |
| CN107538042A (en) * | 2017-10-19 | 2018-01-05 | 南京航空航天大学 | The circular orbit punching system and its operation method of a kind of rigid flexible system |
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| CN118220520A (en) | 2024-06-21 |
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