CN103303491A - Abutting technological equipment of airplane large components and abutting method thereof - Google Patents
Abutting technological equipment of airplane large components and abutting method thereof Download PDFInfo
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- CN103303491A CN103303491A CN2012100607778A CN201210060777A CN103303491A CN 103303491 A CN103303491 A CN 103303491A CN 2012100607778 A CN2012100607778 A CN 2012100607778A CN 201210060777 A CN201210060777 A CN 201210060777A CN 103303491 A CN103303491 A CN 103303491A
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- 238000004519 manufacturing process Methods 0.000 claims abstract description 22
- 238000003032 molecular docking Methods 0.000 claims description 54
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- 238000005096 rolling process Methods 0.000 abstract 1
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- 229910000831 Steel Inorganic materials 0.000 description 1
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Abstract
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.
Description
Technical field
The invention belongs to the aircraft docking technique, relate to the production tooling and the docking calculation thereof that dock between a kind of Large Aircraft Components.
Background technology
Each model aircraft of producing in the past, the fuselage production breakdown interface all designs on the frame position.The production breakdown interface design in nosing, stage casing is designed with a circle butt hole at 13 frame places at nosing 13 frames and middle fuselage 13 circle edge, utilizes it to dock.During nosing, stage casing docking, middle fuselage is placed on the carriage of stage casing, with crane, hang nosing is sling, makes nosing and stage casing involutory.The position, hole of butt hole guarantees by the docking flat board, when the butt hole on the 13 circle edge one by one after the correspondence, uses connecting bolt is linked together nosing, stage casing, before the fuselage, the docking in stage casing namely finishes.
In recent years certain type machine of development, before the fuselage, design is not on the frame position for the production breakdown interface in stage casing, design is on the transversal surface at 250mm place behind 17 frames, and docking front, the stage casing changes riveted joint into by being spirally connected.When nosing, stage casing docking, leading portion, identical long purlin, stage casing overlap with aluminium section bar, are lined with band plate between long purlin and outer skin, are coated with sealant between long purlin, covering and band plate, then rivet, and make leading portion, stage casing to integrator.Owing to adopting riveting, adopt in the past and hang the form of docking and be easy to make and dock unsuccessfully, can't satisfy the demand that leading portion, stage casing dock.
Summary of the invention
The objective of the invention is: quick, the accurate centering of energy between a kind of aircraft two large parts is provided, realizes the production tooling of riveting method docking.
In addition, the present invention also provides a kind of method of Large Aircraft Components docking.
Technical scheme of the present invention: a kind of production tooling of Large Aircraft Components docking, it is comprised of fixed part and moving part, and its described fixed part comprises and is fixed on ground and 41 frame benchmark corresponding with the aircraft corresponding site are dull and stereotyped, main landing gear process support rods bracing frame and some reinforced bulkhead shearss; Described moving part comprises ground rail, nosing rail vehicle, locking positioning device, screw pull rod mechanism, aligning gear and surveyors' staff, wherein, described nosing rail vehicle for mobile nosing is arranged on the ground rail, be used for preventing that the aligning gear of nosing roll is arranged on the cradle of nosing rail vehicle, the locking positioning device that is used for locking nosing course position is arranged on nosing rail vehicle 9 and closes on the docking location place.
Described 41 frame benchmark are dull and stereotyped for being arranged on middle fuselage and fuselage rear burbling area place.
Described main landing gear process support rods bracing frame top is equipped with the V-type groove, and the groove bottom of V-type groove is 155 ± 0.5mm with respect to the diff-H in the horizontal reference hole of benchmark flat board.
Described reinforced bulkhead comprises 19 frames, 25 frames, 33 frames, 38 frames.
Described nosing rail vehicle comprises nosing rail bed, 6 frame shearss, 16 frame shearss and flatcar wheel and guiding wheel, wherein, the wheel rim of guiding wheel is V-type flute profile formula, the V-type groove is stuck on the ground rail, and two groups of wheels are symmetrical along the trailer line of centers respectively, described 6 frames, 16 frames, two place's carriages are arranged on the vehicle frame of nosing rail vehicle, and each carriage is supported by 4 carrying rollers, and carriage is symmetrically installed with the spiral adjusting mechanism along aircraft diad both ends of the surface.
Described locking positioning device is arranged on the ground that is equivalent to 300mm place behind 17 frames, which is provided with tapered end.The dead bolt of screw pull rod mechanism rushes open the tapered end of catch gear, can be with nosing rail vehicle locking positioning.
Described screw pull rod mechanism connects firmly at the nosing rail vehicle closes on the docking location place.Its pulling nosing rail vehicle slowly moves to the stage casing and carries out trace adjustment.
Described 16 frame carriage symmetrical center line places are designed with mesopore, zero vertical place is equipped with technique to center tap under nosing 16 frames, when nosing was placed on the nosing rail vehicle, technique was inserted with aligning gear to after involutory to mesopore on the hole on the center tap and the 16 frame shearss.
A kind of process of Large Aircraft Components docking, it comprises the steps:
Step 1: the airframe stage casing is in place
Product lifting in airframe stage casing to fixed part station place front, stage casing butt-joint process equipment, is made dull and stereotyped applying of 41 frame benchmark of fuselage 41 circle planes and butt-joint process equipment;
Step 2: the airframe middle section position is adjusted
2.1 the process support rods on the alighting gear mounting hole drops on respectively the V-type groove on the main landing gear process support rods bracing frame top that is positioned at fuselage 30 frame arranged on left and right sides;
2.2 then adjust 19 frame shearss or 38 frame shearss, make butt hole on fuselage 41 frames and the datum hole centering on the 41 frame benchmark flat boards, then insert the centering latch;
2.3 rise 38 frame shearss or 19 frame shearss, 25 frame shearss, 33 frame shearss, each carriage and middle fuselage are fitted fully, at this moment, the standard location status of docking is definite, then, unclamps crane;
Step 3: the front fuselage position is in place
The nosing lifting is extremely front, that the stage casing butt-joint process is equipped moving part station place;
Step 4: the nosing position is adjusted
When nosing is placed on the nosing rail vehicle, adjust the product attitude, make under 16 frames zero vertical place technique to involutory to mesopore on the hole on the center tap and the 16 frame shearss, then fixing aligning gear prevents that nosing from rail vehicle roll occuring;
Step 5: the docking of nosing and middle fuselage
5.1 the nosing rail vehicle of propelling loading product moves to middle fuselage along the ground rail, at this moment, the termination dead bolt of screw pull rod mechanism rushes open the tapered end of locking positioning device, the leading portion rail vehicle is locked at this moment, and registration device tightly pins and Primary Location, guarantees that nosing is consistent with the middle fuselage symmetrical center line;
5.2 under the Primary Location state, have certain gap between the involutory surface of nosing and middle fuselage, at this moment, adjust 6 frame shearss, 16 frame shearss, make that two place's carriages are done respectively vertically, the movement of short transverse, adjust the attitude of nosing;
5.3 when the docking attitude in nosing, stage casing meets the fuselage docking technique and requires, shake the handle of screw pull rod mechanism, make slowly and fully applying close to middle fuselage of nosing, screw the leg of nosing rail vehicle, at this moment, just the riveting work in nosing, stage casing can have been carried out.
Beneficial effect of the present invention: adopt the butt-joint process equipment to carry out the docking in aircraft leading portion, stage casing, reduce difficulty and the potential safety hazard of Large Aircraft Components docking, improved manufacturing efficient, effectively guaranteed the product merging precision.Every series aircraft of developing at fortune 8 certain type machine platform all can be equipped the mating operation that carry out leading portion, stage casing at this butt-joint process, perhaps adds the mating operation that the worker just can carry out leading portion, stage casing.Its to transport 8 family machine leading portions, the stage casing docking technique has carried out large innovation, has changed the docking calculation of in the past transporting 8 family machine leading portions, stage casing.
Description of drawings
Fig. 1 is 41 frame benchmark slab construction schematic diagrams
Fig. 2 is the fixed part structural representation
Fig. 3 is the moving part structural representation
Fig. 4 is screw pull rod mechanism and nosing rail vehicle position relationship schematic diagram
Fig. 5 is spiral adjusting mechanism structural representation
Fig. 6 is locking positioning device and screw pull rod mechanism working state schematic representation
Fig. 7 is the lock bolt structure schematic diagram in the screw pull rod mechanism
Fig. 8 is the lock head structure schematic diagram on the locking positioning device
Fig. 9 is the aligning gear structural representation
Wherein, 1-41 frame benchmark flat board, 2-centering latch, 3-19 frame shears, 4-25 frame shears, 5-main landing gear process support rods bracing frame, 6-33 frame shears, 7-38 frame shears, 8-ground rail, 9-nosing rail vehicle, 10-6 frame shears, 11-16 frame shears, 12-spiral adjusting mechanism, 13-locking positioning device, 14-screw pull rod mechanism, 15-aligning gear, 16-surveyors' staff.
The specific embodiment
Below in conjunction with accompanying drawing and instantiation the present invention is described in further detail:
The production tooling of Large Aircraft Components docking of the present invention is take certain model transport plane as platform, and it is comprised of fixed part and moving part two parts.
The fixed part of the production tooling of Large Aircraft Components docking of the present invention comprises 41 frame benchmark flat boards 1, main landing gear process support rods bracing frame 5,19 frame shearss 3,25 frame shearss 4,33 frame shearss 6,38 frame shearss 7, wherein, 41 frames are interface frame, mating frame, main landing gear process support rods bracing frame is support place of main landing gear process support rods, and 19 frames, 25 frames, 33 frames, 38 frames are reinforced bulkhead.
See also Fig. 1, it is the structural representation of 41 frame benchmark flat boards 1.Be designed with the datum hole of 10 φ 8.5 on this 41 frame benchmark flat board, the horizontal reference hole coordinates to make according to 41 frames docking dressing plate, they lay respectively at 0 long purlin, about 14 long purlins, about place, 22 long purlins, correctly locate to realize the end-face hole on the 41 circle edge.
See also Fig. 2, it is the fixed part schematic diagram that supports the aircraft stage casing.Main landing gear process support rods bracing frame 5 tops in the anchor fitting in this support aircraft stage casing are equipped with V-block, and the groove bottom of V-block is 155 ± 0.5mm with respect to the diff-H in the horizontal reference hole of 41 frame benchmark flat boards 1, satisfies the structural requirement of airplane design.Described 19 frames, 25 frames, 33 frames, 38 frames all adopt leading screw, handwheel devices, are Liftable bracket, and its underframe and ground are fixed, and realize the safety supports in aircraft stage casing.
When middle fuselage lifts on the fixed part of equipping to butt-joint process, fitted with the 41 frame benchmark that dock car dull and stereotyped 1 in fuselage 41 circle planes, process support rods on the alighting gear mounting hole (diameter phi 80) drops on respectively the V-block on main landing gear process support rods bracing frame 5 tops that are positioned at fuselage 30 frame arranged on left and right sides, the temporary transient middle fuselage that supports separately.Then adjust 19 frame shearss 3 (or 38 frame shearss 7), make on butt hole on fuselage 41 frames and the 41 frame benchmark flat boards 1 datum hole centering, then insert fastening screw 2.Rise 38 (or 19 frames), 25 frames, 33 frames, 38 frame shearss, at this moment, crane unclamps the stage casing to be hung, and these four frames and the main landing gear process support rods bracing frame 5 common middle fuselages that hold up have guaranteed the correct docking attitude of middle fuselage on the butt-joint process equipment.When nosing, stage casing docking, middle fuselage is the standard of docking.
See also Fig. 4, it is the moving part structural representation that supports the aircraft leading portion.This moving part structure comprises ground rail 8, nosing rail vehicle 9, locking positioning device 13, screw pull rod mechanism 14, aligning gear 15 and surveyors' staff 16.
Described ground rail 8 is two parallel steel rails, long 10m, and gauge is 2500 ± 1mm, buries underground on the ground, and rail upper surface 25mm above ground level, nosing rail vehicle 9 are placed on the ground rail 8, and car body can move forward and backward along the fuselage course; Baffle plate is equipped with on ground at ground rail leading portion (near near burbling area place 17 frames), prevent nosing rail vehicle 9 slip away rail.
Described nosing rail vehicle 9 comprises nosing rail bed, 6 frame shearss 10,16 frame shearss 11 and flatcar wheel and guiding wheel.Wherein, the wheel rim of guiding wheel is V-type flute profile formula, and the V-type groove is stuck on the ground rail 8, makes trailer move forward and backward Shi Buhui along the fuselage course and produces cross travel, and two groups of wheels are symmetrical along the trailer line of centers respectively.Be provided with 6 frames, 16 frames, two place's shearss above the base of nosing rail vehicle 9, and each carriage supports by 4 carrying rollers, realize the movement that two place's carriages are laterally adjusted, in addition, each carriage liftable is adjusted to do up and down.
See also Fig. 5, it is spiral adjusting mechanism structural representation.Carriage is symmetrically installed with spiral adjusting mechanism 12 along aircraft diad two end faces, guarantees that two place's carriages can both conveniently realize horizontal adjustment.
See also Fig. 6, it is locking positioning device and screw pull rod mechanism working state schematic representation.Be provided with screw pull rod mechanism 14 in the termination of trailer chassis, place, the ground at 300mm place is provided with locking positioning device 13 behind 17 frames.As shown in Figure 5, between the two structural relation.
See also Fig. 7, it is dead bolt 21 structural representations in the screw pull rod mechanism.Dead bolt 21 rushes open the tapered end 22 on the locking positioning device 13, nosing rail vehicle 9 location can be pinned.
See also Fig. 8, it is tapered end 22 structural representations on the locking positioning device.Pin the dead bolt 21 in the screw pull rod mechanism 14.Nosing rail vehicle 9 location can be pinned.
See also Fig. 9, it is aligning gear 15 structural representations.Be designed with mesopore at 16 frame shears symmetrical center line places, zero vertical place is equipped with technique to center tap under nosing 16 frames, when nosing is placed on the nosing rail vehicle, technique is to after involutory to mesopore on the hole on the center tap and the 16 frame shearss, insert aligning gear 15, prevented that nosing from nosing rail vehicle 9 roll occuring, thereby the basic guarantee nosing is in the tram substantially.
The below provides the docking calculation in airframe leading portion of the present invention and stage casing, and its process is as follows:
Step 1: the airframe stage casing is in place
To fixed part station place front, stage casing butt-joint process equipment, the 41 frame benchmark dull and stereotyped 1 of fuselage 41 circle planes and butt-joint process equipment are fitted;
Step 2: the airframe middle section position is adjusted
2.1 the process support rods on the alighting gear mounting hole drops on respectively the V-type groove on main landing gear process support rods bracing frame 5 tops that are positioned at fuselage 30 frame arranged on left and right sides;
2.2 then adjust 19 frame shearss 3 or 38 frame shearss 7, make butt hole on fuselage 41 frames and the datum hole centering on the 41 benchmark flat boards 1, then insert fastening screw 2;
2.3 rise 38 frame shearss 7 or 19 frame shearss 3,25 frame shearss 4,33 frame shearss 6, each carriage and middle fuselage are fitted fully, at this moment, the standard location status of docking is definite, then, unclamps crane;
Step 3: the front fuselage position is in place
The nosing lifting is extremely front, that the stage casing butt-joint process is equipped moving part station place;
Step 4: the nosing position is adjusted
When nosing is placed on the nosing rail vehicle 9, adjust the product attitude, make under 16 frames zero vertical place technique to involutory to mesopore on the hole on the center tap and the 16 frame shearss, then fixing aligning gear 15 prevents that nosing from rail vehicle 9 roll occuring;
Step 5: the docking of nosing and middle fuselage
5.1 the nosing rail vehicle 9 of propelling loading product moves to middle fuselage along ground rail 8, at this moment, the termination dead bolt of screw pull rod mechanism 14 rushes open the tapered end of locking positioning device 13, leading portion rail vehicle 9 is locked at this moment, and registration device 13 tightly pins and Primary Location, guarantees that nosing is consistent with the middle fuselage symmetrical center line;
5.2 under the Primary Location state, has certain gap between the involutory surface of nosing and middle fuselage, at this moment, shake the lifting handwheel on the handwheel, 6 frame shearss 10,16 frame shearss 11 of spiral adjusting mechanism 12, make that two place's shearss are done respectively vertically, the adjustment of short transverse, adjust the attitude of nosing;
5.3 when the docking attitude in nosing, stage casing meets the fuselage docking technique and requires, shake the handle of screw pull rod mechanism 14, make slowly and fully applying close to middle fuselage of nosing, screw the leg of nosing rail vehicle, at this moment, just the riveting work in nosing, stage casing can have been carried out.
In addition, on the symmetrical center line of two ground rails, be equivalent on the ground at 250mm place surveyors' staff 16 is housed respectively before the 20mm and 19 frames behind 1 frame, can check nosing, when the stage casing is involutory, whether the relative position of nosing, stage casing fuselage axis of symmetry line satisfies the manufacturing requirement.
41 frame benchmark of fixed part are dull and stereotyped, two ground rails of triangular support bracket, 19 frames, 25 frames, 33 frames, 38 frame shearss and the moving part of 30 frame both sides, when surveyors' staff 16 is installed on ground, all adopt theodolite to carry out measurement and positioning, thereby guarantee the tram between the aircraft butt-joint process equipment components.
When the present invention adopted the butt-joint process equipment to carry out the docking in aircraft leading portion, stage casing, the airframe leading portion was adjusted in the position in first fastening aircraft stage casing then, again by rail moving, realized that nosing accurately docks with middle fuselage, to carry out follow-up riveting work.The present invention has significantly reduced difficulty and the potential safety hazard of Large Aircraft Components docking, has improved manufacturing efficient and joint quality, has effectively guaranteed the product merging precision.And by this docking platform, can realize the in batches mating operation of aircraft, every series aircraft or its improved type of developing at fortune 8 certain type machine platform, all can carry out at this butt-joint process equipment the mating operation in leading portion, stage casing, perhaps add the mating operation that the worker just can carry out leading portion, stage casing, therefore have larger actual application value.
Claims (10)
1. the production tooling of Large Aircraft Components docking, it is comprised of fixed part and moving part, it is characterized in that: described fixed part comprises and is fixed on ground and 41 frame benchmark corresponding with the aircraft corresponding site dull and stereotyped [1], main landing gear process support rods bracing frame [5] and some reinforced bulkhead shearss; Described moving part comprises ground rail [8], nosing rail vehicle [9], locking positioning device [13], screw pull rod mechanism [14], aligning gear [15] and surveyors' staff [16], wherein, described nosing rail vehicle [9] for mobile nosing is arranged on ground rail [8], be used for preventing that the aligning gear [15] of nosing roll is arranged on the cradle of nosing rail vehicle [9], the locking positioning device [13] that is used for locking nosing course position is arranged on nosing rail vehicle [9] and closes on the docking location place.
2. the production tooling of Large Aircraft Components according to claim 1 docking, it is characterized in that: described 41 frame benchmark are dull and stereotyped for being arranged on middle fuselage and fuselage rear burbling area place.
3. the production tooling of Large Aircraft Components according to claim 2 docking, it is characterized in that: described main landing gear process support rods bracing frame top is equipped with the V-type groove, and the groove bottom of V-type groove is 155 ± 0.5mm with respect to the diff-H in the horizontal reference hole of benchmark flat board.
4. the production tooling of Large Aircraft Components according to claim 3 docking, it is characterized in that: described reinforced bulkhead comprises 19 frames, 25 frames, 33 frames, 38 frames.
5. the production tooling that docks to 3 each described Large Aircraft Components according to claim 1, it is characterized in that: described nosing rail vehicle [9] comprises nosing rail vehicle base, 6 frame shearss [10], 16 frame shearss [11] and flatcar wheel and guiding wheel, wherein, the wheel rim of guiding wheel is V-type flute profile formula, the V-type groove is stuck on the ground rail [8], and two groups of wheels are symmetrical along the trailer line of centers respectively, described 6 frames, 16 frames, two place's carriages are arranged on the vehicle frame of nosing rail vehicle [9], each carriage is supported by 4 carrying rollers, and carriage is symmetrically installed with longitudinal spiral adjusting mechanism [12] along aircraft diad both ends of the surface.
6. the production tooling of Large Aircraft Components according to claim 5 docking, it is characterized in that: described after being equivalent to 17 frames the ground at 300mm place be provided with locking positioning device [13], which is provided with tapered end, the dead bolt of screw pull rod mechanism [14] rushes open the tapered end of catch gear [22], with nosing rail vehicle [9] locking positioning.
7. the production tooling of Large Aircraft Components according to claim 6 docking is characterized in that: describedly close on the docking location place at nosing rail vehicle [9] and be provided with and can drive that nosing rail vehicle [9] is slowly mobile to the stage casing to carry out the screw pull rod mechanism [14] that trace is adjusted.
8. the production tooling of Large Aircraft Components according to claim 7 docking, it is characterized in that: described 16 frame shears symmetrical center line places are designed with mesopore, zero vertical place is equipped with technique to center tap under nosing 16 frames, when nosing is placed on the nosing rail vehicle, technique is inserted with aligning gear [15] to after involutory to mesopore on the hole on the center tap and the 16 frame shearss.
9. the production tooling of Large Aircraft Components according to claim 8 docking, it is characterized in that: described symmetrical center line at ground rail [8] 20mm behind 1 frame that boards a plane, be equipped with respectively on the ground, 250mm place before 19 frames be used to check when involutory before the fuselage, whether the fuselage axis of symmetry line in stage casing satisfy the surveyors' staff [16] of docking requirement.
10. the process of a Large Aircraft Components docking is characterized in that, comprises the steps:
Step 1: the airframe stage casing is in place
To fixed part station place front, stage casing butt-joint process equipment, the 41 frame benchmark dull and stereotyped [1] of fuselage 41 circle planes and butt-joint process equipment are fitted;
Step 2: the airframe middle section position is adjusted
2.1 the process support rods on the alighting gear mounting hole drops on respectively the V-type groove on main landing gear process support rods bracing frame [5] top that is positioned at fuselage 30 frame arranged on left and right sides;
2.2 then adjust 19 frame shearss [3] or 38 frame shearss [7], make the datum hole centering on butt hole on fuselage 41 frames and 41 benchmark dull and stereotyped [1], then insert fastening screw [2];
2.3 rise 38 frame shearss [7] or 19 frame shearss [3], 25 frame shearss [4], 33 frame shearss [6], each carriage and middle fuselage are fitted fully, at this moment, the standard location status of docking is definite, then, unclamps crane;
Step 3: the front fuselage position is in place
The nosing lifting is extremely front, that the stage casing butt-joint process is equipped moving part station place;
Step 4: the nosing position is adjusted
When nosing is placed on the nosing rail vehicle [9], adjust the product attitude, make under 16 frames zero vertical place technique to involutory to mesopore on the hole on the center tap and the 16 frame shearss, then fixing aligning gear [15] prevents that nosing is in rail vehicle [9] generation roll;
Step 5: the docking of nosing and middle fuselage
5.1 the nosing rail vehicle [9] of propelling loading product moves to middle fuselage along ground rail [8], at this moment, the termination dead bolt of screw pull rod mechanism [14] rushes open the tapered end of locking positioning device [13], leading portion rail vehicle this moment [9] is locked, and registration device [13] tightly pins and Primary Location, guarantees that nosing is consistent with the middle fuselage symmetrical center line;
5.2 under the Primary Location state, have the gap between the involutory surface of nosing and middle fuselage, at this moment, adjust 6 frame shearss [10], 16 frame shearss [11], make two place's carriages do respectively laterally, vertically, the movement of short transverse, adjust the attitude of nosing;
5.3 when the docking attitude in nosing, stage casing meets the fuselage docking technique and requires, shake the handle of screw pull rod mechanism [14], make slowly and fully applying close to middle fuselage of nosing, screw the leg of nosing rail vehicle, at this moment, just the riveting work in nosing, stage casing can have been carried out.
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2370083A (en) * | 1942-04-13 | 1945-02-20 | Cons Aircraft Corp | Method of assembling airplane fuselages and the like |
| US6257522B1 (en) * | 1997-03-31 | 2001-07-10 | The Boeing Company | Multi-beam method and apparatus for removing and replacing major structural components while converting an airplane to efficiently carry freight |
| US20060180704A1 (en) * | 2005-02-01 | 2006-08-17 | The Boeing Company | Mandrel segment loader |
| US20090261201A1 (en) * | 2008-04-17 | 2009-10-22 | The Boening Company | Line transfer system for airplane |
| CN101583536A (en) * | 2007-02-28 | 2009-11-18 | 波音公司 | Method for fitting part assemblies |
| DE102008062026A1 (en) * | 2008-12-12 | 2010-06-17 | Dürr Systems GmbH | Assembly device for structural assembly i.e. lining or wing assembly, of airplane, has positioning units including joints indirectly connected with sections of main part, where one of sections is connected with rail through one of joints |
| CN102001451A (en) * | 2010-11-12 | 2011-04-06 | 浙江大学 | Airplane component attitude adjusting and butting system based on four numeric control positioners, attitude adjusting platform and mobile bracket and corresponding method |
| CN102249006A (en) * | 2011-05-11 | 2011-11-23 | 西安飞机工业（集团）有限责任公司 | Movement butt joint device for large body part of airplane general assembly |
-
2012
- 2012-03-09 CN CN201210060777.8A patent/CN103303491B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2370083A (en) * | 1942-04-13 | 1945-02-20 | Cons Aircraft Corp | Method of assembling airplane fuselages and the like |
| US6257522B1 (en) * | 1997-03-31 | 2001-07-10 | The Boeing Company | Multi-beam method and apparatus for removing and replacing major structural components while converting an airplane to efficiently carry freight |
| US20060180704A1 (en) * | 2005-02-01 | 2006-08-17 | The Boeing Company | Mandrel segment loader |
| CN101583536A (en) * | 2007-02-28 | 2009-11-18 | 波音公司 | Method for fitting part assemblies |
| US20090261201A1 (en) * | 2008-04-17 | 2009-10-22 | The Boening Company | Line transfer system for airplane |
| DE102008062026A1 (en) * | 2008-12-12 | 2010-06-17 | Dürr Systems GmbH | Assembly device for structural assembly i.e. lining or wing assembly, of airplane, has positioning units including joints indirectly connected with sections of main part, where one of sections is connected with rail through one of joints |
| CN102001451A (en) * | 2010-11-12 | 2011-04-06 | 浙江大学 | Airplane component attitude adjusting and butting system based on four numeric control positioners, attitude adjusting platform and mobile bracket and corresponding method |
| CN102249006A (en) * | 2011-05-11 | 2011-11-23 | 西安飞机工业（集团）有限责任公司 | Movement butt joint device for large body part of airplane general assembly |
Non-Patent Citations (1)
| Title |
|---|
| 荆道艳: "《大部件对接的数控定位器技术研究》", 《航空制造技术》 * |
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Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: Box 34, Hanzhong City, Shaanxi Province, 723213 Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |