CN205426649U - Flexible inspection jig of aircraft wing peening wallboard covering - Google Patents
Flexible inspection jig of aircraft wing peening wallboard covering Download PDFInfo
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- CN205426649U CN205426649U CN201520785084.4U CN201520785084U CN205426649U CN 205426649 U CN205426649 U CN 205426649U CN 201520785084 U CN201520785084 U CN 201520785084U CN 205426649 U CN205426649 U CN 205426649U
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Abstract
The application discloses flexible inspection jig of aircraft wing peening wallboard covering supports inspection unit, two sets of borders unit, control system and laser system including base member, multiunit, the base member contains the main part skeleton, X is the U type groove structure on parallel ground to rack and X to bull grating chi, main part skeleton to guide rail, X, and the X of two sets of parallels of each other lays respectively at main part skeleton U type tank bottom and notch upper surface to bull grating chi (1) to rack (2) and X to guide rail (2), X, support inspection unit includes that support chassis, multiunit support inspection subassembly, 2 Y of group to border supporting component, X to servo reducing gear, y -directional guide rail, Y to rack, steering mechanism, Y to bull grating chi, branch accuse case, the border unit includes that support chassis, multiunit X are to border supporting component, 2 Y of group to border supporting component, X to servo reducing gear, y -directional guide rail, Y to rack, steering mechanism, Y to bull grating chi, branch accuse case.
Description
Technical field
The application relates to aircraft inspection jig and manufactures and designs field, the flexible testing fixture of a kind of aircraft wing shot-peening wall panel skin.
Background technology
Owing to shot-peening molding has structure-reinforced effect to plate part, at present, Domestic Aircraft wing wallboard eyelid covering uses shot-peening molding in a large number.But profile is controlled not to be fine by blasting technology, there is the deformation locally exceeding 0.5mm, need wallboard is carried out school shape again, so needing special fixture the most qualified to the shot-peening wall panel skin checking it to produce, at present, to the inspection of shot-peening wall panel skin mainly by framework model inspection jig.
The wing wing shot-peening wallboard plate eyelid covering framework model inspection jig that domestic air mail frock maker manufactures and designs is the stand-alone type single product single frock of correspondence stand-alone type, and Fixture Design, manufacturing cycle are the longest.When facing different types of machines multiple product, a large amount of framework model inspection jigs that structure is similar inside final result often Factory Building, are piled with.When particularly new machine is developed, the design cycle requires tight, and task amount is big, and the limitation of conventional inspection frock constrains the development process of Aircraft Tools to a great extent.
According to tradition Fixture Design manufacturing philosophy, a kind of type wing wing shot-peening wall panel skin inspection jig needs totally 4～6, and size floor space is from 10m～20mX2m.These inspection jig structures are similar to, and floor space is big, and quantity is more, but due to the feature of tradition frock, it is impossible to and use, need to expend and substantial amounts of manufacture and design time and cost.But also to take substantial amounts of hall space resource.Existing tradition stringer inspection frock, design complexity, quantity is more, and manufacturing cost is higher, and utilization rate is the highest, uses loaded down with trivial details error-prone.
Traditional method is when wing wallboard eyelid covering is checked, allowing to apply certain orthopedic external force forces skin morph to reach shape requirement, the orthopedic external force applied is generally the sandbag of fixed weight, weight and degree of deformation controlled quentity controlled variable accuracy are low, and for bigger wallboard, may whole upper surface be all sandbag, workload be big, troublesome poeration.It addition, the Edge position control of wall panel skin is also a difficult problem, different wallboards is required to corresponding special tooling, and handling location is the most complex.
In the world, Flexible Manufacturing Technology always is relatively advanced field, and the flexible Position Research of profile is more, also has some special verifying benches, but the research of the flexible testing of aircraft target ship eyelid covering is less, actual application almost without.Retrieving result according to patent and non-patent literature, relation technological researching is little at home, currently without having practicality and the research of productive value meaning.For reducing space hold efficiency, reducing cost, raising production work efficiency, it is necessary to develop a kind of flexible testing fixture meeting the inspection of all wing wallboard eyelid covering series products.
Summary of the invention
The purpose of the application is a kind of flexible testing fixture of inspection offer for aircraft wing shot-peening wall panel skin, this fixture can carry out automatic flexible inspection to all kinds of aircraft wing eyelid coverings, and fixture has inspection automatically, the automatically orthopedic external force of applying, can be automatically positioned edge, without auxiliary mould, advantage easy and simple to handle.
For reaching object above, the application adopts the following technical scheme that and is achieved:
A kind of aircraft wing shot-peening wall panel skin flexible testing fixture, supports verification unit, two groups of boundary elements, control system and laser system including matrix, many groups；Matrix comprises main body framework, X direction guiding rail, X to tooth bar and X to bull grating scale, main body framework is the U-shaped trough body structure on parallel ground, and two groups of X direction guiding rails parallel to each other (2), X are laid at the bottom of main body framework U-type groove and notch upper surface to tooth bar (2) and X to bull grating scale (1) respectively；Support verification unit and include that support frame, many groups support inspection assembly, support component, X are propped up to servo deceleration gear, Y-direction guide rail, Y-direction tooth bar, steering mechanism, Y-direction bull grating scale, sub-control box in 2 groups of Y-direction borders；Boundary element includes support frame, X props up support component to many groups to border, support component, X are propped up to servo deceleration gear, Y-direction guide rail, Y-direction tooth bar, steering mechanism, Y-direction bull grating scale, sub-control box in 2 groups of Y-direction borders.
Support frame comprise skeleton, decussation roller axle ring connection end, guide rails assembling face, grating scale mounting groove, by groove, tooth bar installed surface.Skeleton generally trench structure, two ends lower surface is steering mechanism's connection end, upper surface is guide rails assembling face, side is grating scale mounting groove, centre arranges and supports inspection assembly and support component is propped up on border passes through groove, tooth bar installed surface is set by groove side, guide rails assembling face, grating scale mounting groove, is parallel to each other by groove, tooth bar installed surface.
Steering mechanism by connecting plate, base plate, turn to guide rail, intermediate plate, decussation roller axle ring etc. to form.Connecting plate, base plate are by guideway and X direction guiding rail sliding connection；Be arranged parallel to Y-direction on base plate turns to guide rail, turn to the guideway sliding connection intermediate plate on guide rail, it is spirally connected fixing with decussation roller axle ring outer shroud on the upside of connecting plate, intermediate plate, is spirally connected on the downside of decussation roller axle ring internal ring and the decussation roller axle ring connection end of support frame fixing.
Support inspection assembly to be made up of installing plate, Y-direction servo deceleration gear, active servo electric cylinder, support bulb, passive installing plate, passive servo electric jar, vacuum cup, adaptor, pull pressure sensor, length gauge (or laser range sensor) etc..Installing plate passes through guideway with the Y-direction guide rail supported on verification unit, boundary element along sliding connection；Y-direction servo deceleration gear is arranged on the support arm of installing plate；Active servo electric cylinder is installed on a mounting board；Support bulb and be arranged on the end of active servo electric cylinder extension bar by screw thread locating pin structure；Passive installing plate upper end is pressed on active servo electric cylinder extension bar upper end by supporting bulb, and bottom is connected with its extension bar shaft hole matching；Passive servo electric jar is parallel to active servo electric cylinder and is screwed onto on passive installing plate, and extension bar end is spirally connected pull pressure sensor lower end；Adaptor lower end and pull pressure sensor upper end are by Stud connection, and upper end is spirally connected by the Kong Weiyu vacuum cup on flat board；Length gauge (or laser range sensor) and passive servo electric jar are installed in parallel on adaptor.Each inspection is propped up support component and is all connected with the measurement head of a Y-direction bull grating scale, engages formation rack-and-pinion motion by Y-direction servo deceleration gear on each assembly with the Y-direction tooth bar on support verification unit, boundary element.
It is that the side parallel with support frame length direction adds edge locating part on the passive installing plate supporting inspection assembly that X props up support component to border；It is that the side vertical with support frame length direction adds edge locating part on the passive installing plate supporting inspection assembly that support component is propped up on Y-direction border；Edge locating part is by F body, tension-compression sensor, semicircle cambered surface locating part.
Many groups support verification units, boundary element connected with the X direction guiding rail on matrix 1 by the connecting plate in steering mechanism, base plate after at the U-type groove mouth upper surface of matrix along X to moving, single group or many groups support after verification unit is connected with the X direction guiding rail on matrix by the connecting plate in steering mechanism, base plate at upper surface at the bottom of the U-type groove of matrix along X to moving；Driven the decussation roller Zhou Huan center deflection supporting verification unit, boundary element in steering mechanism to the speed difference of servo deceleration gear by two groups of X；Supporting the support inspection assembly of the Y-direction servo deceleration gear driven in verification unit to move along Y-direction, the Y-direction servo deceleration gear driven boundary element in edge cells moves along Y-direction；Support inspection assembly, X prop up support component to border, Y-direction border is propped up on support component active servo electric cylinder to drive and support bulb and put aircraft wing shot-peening wall panel skin is formed support along Z-direction arrival specific bit of moving, and formed just position curved profile according to supporting the simulation of dot matrix position coordinates；Supporting the inspection passive servo electric jar that assembly, X prop up support component to border, Y-direction border is propped up on support component drives vacuum cup to move arrival aircraft wing shot-peening wall panel skin surface to apply pressure controllable to wall panel skin shape along Z-direction；Y-direction servo deceleration gear 32 drives X to prop up support component to border, Y-direction border is propped up support component and arrived aircraft wing shot-peening wall panel skin boundary position and by the tension-compression sensor perception wall panel skin terminal pressure on edge locating part, and prop up support component by the automatic modified chi of terminal pressure size to border, Y-direction border props up that the support component physical location simulation formation on wall panel skin border is first positions cover edges；By supporting inspection length gauge (or laser range sensor) the survey aircraft wing shot-peening wall panel skin shape that assembly, X prop up support component to border, Y-direction border is propped up on support component, by measured value and theoretical value comparison, to reach aircraft wing shot-peening wall panel skin shape and the most qualified purpose of boundary condition.
Control system is made up of distribution box, control machine room, wiring drag chain and pipe network etc. containing integrated management and server, and control system sends position command and controls to support verification unit, boundary element and move along X, Y, Z respectively and reach predetermined examined aircraft wing shot-peening wall panel skin theoretical position.
Laser system comprises the compositions such as laser tracker, target point, target point installing rack, laser tracker installing rack.The advantage of the application is to achieve the wing stringer automatic flexible inspection of different aircraft model, achieve the orthopedic external force of applying automatically to wing cover, edge can be automatically positioned, fixture have automatically inspection, without auxiliary mould, advantage easy and simple to handle, the inspection of wing class eyelid covering or less curvature smooth contour flat-type infrastructure product is had and has general applicability.
Below in conjunction with drawings and Examples, the application is described in further detail.
Accompanying drawing explanation
Fig. 1 one aircraft wing shot-peening wall panel skin flexible testing fixture overall structure schematic diagram；
Fig. 2 support unit, boundary element and the layering space layout of verification unit；
Fig. 3 support unit, boundary element and verification unit X are to arrangement schematic diagram；
Fig. 4 supports verification unit structure chart；
Fig. 5 boundary element structure chart；
Fig. 6 supports verification unit, boundary element cut-away view；
Fig. 7 supports inspection assembly assumption diagram；
Fig. 8 Y-direction border supports assembly assumption diagram；
Fig. 9 X supports assembly assumption diagram to border；
Figure 10 steering mechanism structure chart；
Figure 11 supports inspection skeleton；
In Fig. 1～Figure 11: 1, matrix；2, verification unit is supported；3, boundary element；4, control system；5, laser system；6, main body framework；7, X direction guiding rail；8, X is to tooth bar；9, X is to bull grating scale；10, support frame；11, inspection assembly is supported；12, support component is propped up on Y-direction border；13, X is to servo deceleration gear；14, Y-direction guide rail；15, Y-direction tooth bar；16, steering mechanism；17, Y-direction bull grating scale；18, sub-control box；19, X props up support component to border；20, skeleton；21, decussation roller axle ring connection end；22, guide rails assembling face；23, grating scale mounting groove；24, groove is passed through；25, tooth bar installed surface；26, connecting plate；27, base plate；28, guide rail is turned to；29, intermediate plate；30, decussation roller axle ring；31, installing plate；32, Y-direction servo deceleration gear；33, active servo electric cylinder；34, bulb is supported；35, passive installing plate；36, passive servo electric jar；37, vacuum cup；38, adaptor；39, pull pressure sensor；40, length gauge (or laser range sensor)；41, edge locating part；42, F body；43, tension-compression sensor；44, semicircle cambered surface locating part；45, aircraft wing shot-peening wall panel skin；46, distribution box；47, the control machine room containing integrated management and server；48, wiring drag chain and pipe network；49, laser tracker；50, target point；51, target point installing rack；52, laser tracker installing rack.
Detailed description of the invention
See Fig. 1～Figure 11, in a particular application, a kind of aircraft wing shot-peening wall panel skin flexible testing fixture, support 2, two groups of boundary elements 3 of verification unit, control system 4 and laser system 5 including matrix 1, many groups；Described matrix 1 comprises main body framework 6, X direction guiding rail 7, X to tooth bar 8 and X to bull grating scale 9, main body framework 6 is the U-shaped trough body structure on parallel ground, and two groups of X direction guiding rails 7 (2) parallel to each other, X are laid on main body framework 6U type bottom land and notch upper surface to tooth bar 8 (2) and X respectively to bull grating scale 9 (1).
Support verification unit 2 and include that support frame 10, many groups support inspection 11,2 groups of Y-direction borders of assembly and prop up support component 12, X to servo deceleration gear 13, Y-direction guide rail 14, Y-direction tooth bar 15, steering mechanism 16, Y-direction bull grating scale 17, sub-control box 18.
Boundary element 3 includes that support frame 10, many group X prop up 19,2 groups of Y-direction borders of support component and prop up support component 12, X to servo deceleration gear 13, Y-direction guide rail 14, Y-direction tooth bar 15, steering mechanism 16, Y-direction bull grating scale 17, sub-control box 18 to border.
Support frame 10 comprise skeleton 20, decussation roller axle ring connection end 21, guide rails assembling face 22, grating scale mounting groove 23, by groove 24, tooth bar installed surface 25.Skeleton 20 generally trench structure, two ends lower surface is steering mechanism's connection end 21, upper surface is guide rails assembling face 22, side is grating scale mounting groove 23, centre arrange support inspection assembly 2 and border prop up support component 3 by groove 24, tooth bar installed surface 25 is set by groove 24 side, guide rails assembling face 22, grating scale mounting groove 23, is parallel to each other by groove 24, tooth bar installed surface 25.
Steering mechanism 16 by connecting plate 26, base plate 27, turn to guide rail 28, intermediate plate 29, decussation roller axle ring 30 etc. to form.Connecting plate 26, base plate 27 are by guideway and X direction guiding rail 7 sliding connection；Be arranged parallel to Y-direction on base plate 27 turns to guide rail 28, turn to the guideway sliding connection intermediate plate 29 on guide rail 28, it is spirally connected fixing with decussation roller axle ring 30 outer shroud on the upside of connecting plate 26, intermediate plate 29, is spirally connected on the downside of decussation roller axle ring 30 internal ring and the decussation roller axle ring connection end 21 of support frame 10 fixing.
Support inspection assembly 11 to be made up of installing plate 31, Y-direction servo deceleration gear 32, active servo electric cylinder 33, support bulb 34, passive installing plate 35, passive servo electric jar 36, vacuum cup 37, adaptor 38, pull pressure sensor 39, length gauge (or laser range sensor) 40 etc..Installing plate 31 passes through guideway with the Y-direction guide rail 13 supported on verification unit 2, boundary element 3 along sliding connection；Y-direction servo deceleration gear 32 is arranged on the support arm of installing plate 31；Active servo electric cylinder 33 is arranged on installing plate 31；Support bulb 34 and be arranged on the end of active servo electric cylinder 33 extension bar by screw thread locating pin structure；Passive installing plate 35 upper end is pressed on active servo electric cylinder 33 extension bar upper end by supporting bulb 34, and bottom is connected with its extension bar shaft hole matching；Passive servo electric jar 36 is parallel to active servo electric cylinder 33 and is screwed onto on passive installing plate 35, and extension bar end is spirally connected pull pressure sensor 39 lower end；Adaptor 38 lower end is spirally connected by the Kong Weiyu vacuum cup 37 on flat board by Stud connection, upper end with pull pressure sensor 39 upper end；Length gauge (or laser range sensor) 40 and passive servo electric jar 36 are installed in parallel on adaptor 38.Each inspection is propped up support component 11 and is all connected with the measurement head of a Y-direction bull grating scale 17, engages formation rack-and-pinion motion by Y-direction servo deceleration gear 32 on each assembly with the Y-direction tooth bar 13 on support verification unit 2, boundary element 3.
It is that the side parallel with support frame 10 length direction adds edge locating part 41 on the passive installing plate 35 supporting inspection assembly 11 that X props up support component 19 to border；It is that the side vertical with support frame 10 length direction adds edge locating part 41 on the passive installing plate 35 supporting inspection assembly 11 that support component 12 is propped up on described Y-direction border；Edge spacing 41 by F body 42, tension-compression sensor 43, semicircle cambered surface locating part 44.
Many groups support verification units 2, boundary element 3 connected with the X direction guiding rail 7 on matrix 1 by the connecting plate 26 in steering mechanism 16, base plate 27 after at the U-type groove mouth upper surface of matrix 1 along X to moving, single group or many groups support after verification unit 2 is connected with the X direction guiding rail 7 on matrix 1 by the connecting plate 26 in steering mechanism 16, base plate 27 at upper surface at the bottom of the U-type groove of matrix 1 along X to moving；Driven the decussation roller Zhou Huan 30 center deflection supporting verification unit 2, boundary element 3 in steering mechanism 16 to the speed difference of servo deceleration gear 13 by two groups of X；Supporting the Y-direction servo deceleration gear 32 in verification unit 2 drives support inspection assembly 2 to move along Y-direction, and the Y-direction servo deceleration gear 32 in edge cells 3 drives boundary element 3 to move along Y-direction；Support inspection assembly 11, X props up support component 19 to border, Y-direction border is propped up on support component 12 active servo electric cylinder 33 drives and supports bulb 34 and put to form aircraft wing shot-peening wall panel skin 45 support along Z-direction arrival specific bit of moving, and is formed just position curved profile according to supporting the simulation of dot matrix position coordinates；Support inspection assembly 11, the passive servo electric jar 36 that X props up support component 19 to border, Y-direction border is propped up on support component 12 drive vacuum cup 37 to move arrival aircraft wing shot-peening wall panel skin 45 surface to apply pressure controllable to wall panel skin shape along Z-direction；Y-direction servo deceleration gear 32 drives X to prop up support component 19 to border, Y-direction border is propped up support component 12 and arrived aircraft wing shot-peening wall panel skin 45 boundary position and by the tension-compression sensor 43 perception wall panel skin terminal pressure on edge locating part 41, and prop up support component 19 by the automatic modified chi of terminal pressure size to border, Y-direction border is propped up at the beginning of the support component 12 physical location simulation on wall panel skin border is formed and is positioned cover edges；By length gauge (or laser range sensor) 40 survey aircraft wing shot-peening wall panel skin 45 profile supporting inspection assembly 11, X props up support component 19 to border, Y-direction border is propped up on support component 12, by measured value and theoretical value comparison, to reach aircraft wing shot-peening wall panel skin 45 profile and the most qualified purpose of boundary condition.
Control system 4 is made up of distribution box 46, control machine room 47, wiring drag chain and pipe network 48 etc. containing integrated management and server, and control system 4 sends position command and controls to support verification unit 2, boundary element 3 and move along X, Y, Z respectively and reach predetermined examined aircraft wing shot-peening wall panel skin 45 theoretical position.
Laser system 5 comprises the compositions such as laser tracker 49, target point 50, target point installing rack 51, laser tracker installing rack 52.
Claims (3)
1. an aircraft wing shot-peening wall panel skin flexible testing fixture, supports verification unit (2), two groups of boundary elements (3), control system (4) and laser measurement system (5) including matrix (1), many groups；Described matrix (1) comprises main body framework (6), X direction guiding rail (7), X to tooth bar (8) and X to bull grating scale (9), main body framework (6) is the U-shaped trough body structure on parallel ground, two groups often organize each 2 X direction guiding rails (7) parallel to each other, 2 X are laid at the bottom of main body framework (6) U-type groove to bull grating scale (9) and notch upper surface to tooth bar (8) and 1 X respectively；Support verification unit (2) and include that support component (12), X are propped up to servo deceleration gear (13), Y-direction guide rail (14), Y-direction tooth bar (15), steering mechanism (16), Y-direction bull grating scale (17), sub-control box (18) in support frame (10), many groups support inspection assembly (11), 2 groups of Y-direction borders；Boundary element (3) includes support frame (10), X props up support component (19) to many groups to border, support component (12), X are propped up to servo deceleration gear (13), Y-direction guide rail (14), Y-direction tooth bar (15), steering mechanism (16), Y-direction bull grating scale (17), sub-control box (18) in 2 groups of Y-direction borders；Described support frame (10) comprises skeleton (20), decussation roller axle ring connection end (21), guide rails assembling face (22), grating scale mounting groove (23), by groove (24), tooth bar installed surface (25), skeleton (20) generally trench structure, two ends lower surface is steering mechanism's connection end (21), upper surface is guide rails assembling face (22), side is grating scale mounting groove (23), centre arrange support inspection assembly (2) and border prop up support component (3) by groove (24), by groove (24) side, tooth bar installed surface (25) is set, guide rails assembling face (22), grating scale mounting groove (23), by groove (24), tooth bar installed surface (25) is parallel to each other；Described steering mechanism (16) by connecting plate (26), base plate (27), turn to guide rail (28), intermediate plate (29), decussation roller axle ring (30) etc. to form；Connecting plate (26), base plate (27) are by guideway and X direction guiding rail (7) sliding connection；Be arranged parallel to Y-direction on base plate (27) turns to guide rail (28), turn to guideway sliding connection intermediate plate (29) on guide rail (28), connecting plate (26), intermediate plate (29) upside is spirally connected fixing with decussation roller axle ring (30) outer shroud, and decussation roller axle ring (30) internal ring is spirally connected fixing with decussation roller axle ring connection end (21) of support frame (10) downside；Described support inspection assembly (11) is made up of installing plate (31), Y-direction servo deceleration gear (32), active servo electric cylinder (33), support bulb (34), passive installing plate (35), passive servo electric jar (36), vacuum cup (37), adaptor (38), pull pressure sensor (39), length gauge (40) etc.；Installing plate (31) passes through guideway with the Y-direction guide rail (13) supported on verification unit (2), boundary element (3) along sliding connection；Y-direction servo deceleration gear (32) is arranged on the support arm of installing plate (31)；Active servo electric cylinder (33) is arranged on installing plate (31)；Support bulb (34) and be arranged on the end of active servo electric cylinder (33) extension bar by screw thread locating pin structure；Passive installing plate (35) upper end is pressed on active servo electric cylinder (33) extension bar upper end by supporting bulb (34), and bottom is connected with its extension bar shaft hole matching；Passive servo electric jar (36) is parallel to active servo electric cylinder (33) and is screwed onto on passive installing plate (35), and extension bar end is spirally connected pull pressure sensor (39) lower end；Adaptor (38) lower end is spirally connected by the Kong Weiyu vacuum cup (37) on flat board by Stud connection, upper end with pull pressure sensor (39) upper end；Length gauge (40) and passive servo electric jar (36) are installed in parallel on adaptor (38)；Each inspection is propped up support component (11) and is all connected with the measurement head of Y-direction bull grating scale (17), by Y-direction servo deceleration gear (32) on each assembly with support verification unit (2), Y-direction tooth bar (13) on boundary element (3) engage and forms rack-and-pinion motion；It is to add edge locating part (41) in the upper side parallel with support frame (10) length direction of the passive installing plate (35) supporting inspection assembly (11) that described X props up support component (19) to border；It is to add edge locating part (41) in the upper side vertical with support frame (10) length direction of the passive installing plate (35) supporting inspection assembly (11) that support component (12) is propped up on described Y-direction border；Edge spacing (41) part is by F body (42), tension-compression sensor (43), semicircle cambered surface locating part (44)；Many groups support verification unit (2), boundary element (3) connected by the connecting plate (26) in steering mechanism (16), X direction guiding rail (7) on base plate (27) same to matrix (1) after at the U-type groove mouth upper surface of matrix (1) along X to moving, single group or many groups support after verification unit (2) is connected by the connecting plate (26) in steering mechanism (16), X direction guiding rail (7) on base plate (27) same to matrix (1) at upper surface at the bottom of the U-type groove of matrix (1) along X to moving；Driven decussation roller axle ring (30) the center deflection supporting verification unit (2), boundary element (3) in steering mechanism (16) to the speed difference of servo deceleration gear (13) by two groups of X；Supporting verification unit (2) inner Y-direction servo deceleration gear (32) to drive and support inspection assembly (2) and move along Y-direction, inner Y-direction servo deceleration gear (32) of edge cells (3) drives boundary element (3) to move along Y-direction；Support inspection assembly (11), X props up support component (19) to border, Y-direction border is propped up on support component (12) active servo electric cylinder (33) drives and supports bulb (34) and put to form aircraft wing shot-peening wall panel skin (45) support along Z-direction arrival specific bit of moving, and is formed just position curved profile according to supporting the simulation of dot matrix position coordinates；Support inspection assembly (11), the passive servo electric jar (36) that X props up support component (19) to border, Y-direction border is propped up on support component (12) drive vacuum cup (37) to move arrival aircraft wing shot-peening wall panel skin (45) surface to apply pressure controllable to wall panel skin shape along Z-direction；Y-direction servo deceleration gear (32) drives X to prop up support component (19) to border, Y-direction border is propped up support component (12) and arrived aircraft wing shot-peening wall panel skin (45) boundary position and by tension-compression sensor (43) the perception wall panel skin terminal pressure on edge locating part (41), and prop up support component (19) by the automatic modified chi of terminal pressure size to border, Y-direction border props up that the support component (12) the physical location simulation formation on wall panel skin border is first positions cover edges；By length gauge (40) survey aircraft wing shot-peening wall panel skin (45) profile supporting inspection assembly (11), X props up support component (19) to border, Y-direction border is propped up on support component (12), by measured value and theoretical value comparison, to reach aircraft wing shot-peening wall panel skin (45) profile and the most qualified purpose of boundary condition.
A kind of aircraft wing shot-peening wall panel skin flexible testing fixture the most according to claim 1, it is characterized in that described control system (4) includes distribution box (46), control machine room (47), wiring drag chain and pipe network (48) containing integrated management and server, control system (4) sends that position command controls to support verification unit (2), boundary element (3) moves along X, Y, Z respectively and reaches predetermined examined aircraft wing shot-peening wall panel skin (45) theoretical position.
A kind of aircraft wing shot-peening wall panel skin flexible testing fixture the most according to claim 1, it is characterised in that described laser measurement system (5) comprises laser tracker (49), target point (50), target point installing rack (51), laser tracker installing rack (52).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520785084.4U CN205426649U (en) | 2015-10-10 | 2015-10-10 | Flexible inspection jig of aircraft wing peening wallboard covering |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520785084.4U CN205426649U (en) | 2015-10-10 | 2015-10-10 | Flexible inspection jig of aircraft wing peening wallboard covering |
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| CN205426649U true CN205426649U (en) | 2016-08-03 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105372121A (en) * | 2015-10-10 | 2016-03-02 | 中航飞机股份有限公司西安飞机分公司 | Flexibility inspection clamp of aircraft wing shot blasting wallplate skin |
| CN114043389A (en) * | 2021-11-08 | 2022-02-15 | 陕西飞机工业有限责任公司 | Horizontal shot blasting clamp for double-curvature skin of airplane |
| CN115540791A (en) * | 2022-12-01 | 2022-12-30 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
-
2015
- 2015-10-10 CN CN201520785084.4U patent/CN205426649U/en not_active Withdrawn - After Issue
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105372121A (en) * | 2015-10-10 | 2016-03-02 | 中航飞机股份有限公司西安飞机分公司 | Flexibility inspection clamp of aircraft wing shot blasting wallplate skin |
| CN105372121B (en) * | 2015-10-10 | 2018-04-03 | 中航飞机股份有限公司西安飞机分公司 | A kind of aircraft wing shot-peening wall panel skin flexible testing fixture |
| CN114043389A (en) * | 2021-11-08 | 2022-02-15 | 陕西飞机工业有限责任公司 | Horizontal shot blasting clamp for double-curvature skin of airplane |
| CN115540791A (en) * | 2022-12-01 | 2022-12-30 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
| CN115540791B (en) * | 2022-12-01 | 2023-03-14 | 成都市鸿侠科技有限责任公司 | Aircraft skin appearance precision detection device |
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