CN109204873A - A kind of aircraft center wing box numeric terminal positioning system and localization method - Google Patents
A kind of aircraft center wing box numeric terminal positioning system and localization method Download PDFInfo
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- CN109204873A CN109204873A CN201711033496.2A CN201711033496A CN109204873A CN 109204873 A CN109204873 A CN 109204873A CN 201711033496 A CN201711033496 A CN 201711033496A CN 109204873 A CN109204873 A CN 109204873A
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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
Abstract
The present invention relates to a kind of aircraft center wing box numeric terminal positioning system and localization method, the digitlization flexibility positioning tool being related to is divided into lathe bed main unit, front-axle beam positioning unit, back rest positioning unit, the conformal unit of left wing's rib, the conformal unit of right flank rib, upper tool locating compressing unit and lower tool locating compressing unit according to functional module.It is used carries out automation localization method on the basis of skeleton, the skeleton parts such as the front-axle beam, the back rest and rib of larger central wing box are accurately positioned first, later on the basis of skeleton, the components such as wainscot, lower wall panels and stringer are positioned, until completing the entire position fixing process to central wing box.The numeric terminal positioning system and localization method can refine positioning, automation control, multifunctional unit, flexibility design larger central wing box.
Description
Technical field
The present invention relates to a kind of aircraft center wing box numeric terminal positioning system and localization methods, belong to aircraft manufacturing skill
Art field.
Background technique
Central wing box is as aircraft critical component, and there is aerodynamic configuration to require, and stringent, change in design is frequent, product configuration is many
More, part material and it is different, internal structure is complicated, spaces compact, sorts of systems arrangement are intensive and spare part quantity is big
The features such as, assembly difficulty is big, and assembling quality requirement is high.From the nineties in last century, the external big rule of primary means air developed country
Mould carries out the research of aircraft digital mounting technology, and has developed digitizer of a batch for aircraft assembly.Due to technology
The reasons such as block, the application of Domestic Aircraft numeric terminal is also in the exploration practice stage, except small part main engine plants introduce number
Locator is used as basic unit, and most of assembly mode substantially also follows traditions of the past manual mode, using big
The complicated type frame of amount carries out positioning and clamping, and the assembly period of aircraft and quality are difficult to ensure.
In recent years, the external research for aircraft central wing capsule location technology has been achieved for certain achievement.Through
The literature search discovery to the prior art is crossed, Boeing Co. uses vertical during 787 type aircraft central wing capsule
Formula Digital location assembling scheme, and carried out application verification.EI company cooperates with Air Passenger company, has developed a set of wing jointly
Automation positioning assembly tooling system, the wing for A340-600 type aircraft are automatically positioned assembly.
Domestic correlative study is still in infancy, and key technology is not yet broken through completely, be only confined to fuselage, wing etc. at
In the big component docking operation of product, to the simple application of digital positioners, and complex large-sized components this for central wing box are filled
It is less with application.Therefore, currently, domestic main engine plants still use traditional vertical craft substantially during central wing capsule
Type frame assembly technology, rigid type frame are equipped with snap-gauge and positioning pin carry out product component positioning, manually as fixing tool main body
Compactor is compressed.This localization method causes the Operational preparation period long, and position fixing process is complicated, and tooling takes up a large area, work
People's labor intensity is high, and tooling is not restructural, the consistency and poor reliability of Product Assembly.And Digital location method is using number
Change flexible frock to position product component, high degree of automation, positioning accuracy is quasi-, has restructural type, is suitable for more
The assembly of a different model product needs, and greatly improves production efficiency and product quality.
But existing central wing assembly method has different degrees of problem both at home and abroad.Firstly, being directed to central wing at present
The Digital location method of box is mainly vertical positioning.Although using Digital location technology in external assembling process,
Aircraft Product Assembly posture and actual use posture there are larger difference, cause to deform after product undercarriage it is larger and unpredictable,
Influence product quality.For the central wing box of aircraft, components volume is big, from great, rigidity is small, and product becomes
Shape problem is even more serious.Wing box numeric terminal method in aircraft center according to the present invention is horizontal assembling method, product orientation
Posture is consistent with product actual use posture, and deflection is smaller compared to vertical assembly, and can further control in assembling process
The generation of deflection processed.Meanwhile horizontal undercarriage on product, worker are assemblied in the cognition degree of product, the opening character of tool structure
Etc. compared to it is vertical assembly all have more advantage.Secondly, positioning tool has a single function in current assembly method, it is especially traditional
Type frame positioning tool needs worker to carry out a large amount of manual operationss, and need to be directed to each part assembly positioning tool customized, expends people
Power material resources, positioning accuracy is low, and the production cycle is long, and labor intensity is high, and economic serviceability is poor.
Summary of the invention
For problems of the prior art, high-precision, the high efficiency numeric terminal of aircraft center wing box are realized, this
Invention provides a kind of aircraft center wing box numeric terminal positioning system and localization method, the digitlization flexibility positioning being related to
Tooling according to functional module be divided into lathe bed main unit, front-axle beam positioning unit, back rest positioning unit, the conformal unit of left wing's rib,
The conformal unit of right flank rib, upper tool locating compressing unit and lower tool locating compressing unit.It is used is carried out on the basis of skeleton
Localization method is automated, the skeleton parts such as the front-axle beam, the back rest and rib of larger central wing box are accurately positioned first, it
Afterwards on the basis of skeleton, the components such as wainscot, lower wall panels and stringer are positioned, until completing to the entire of central wing box
Position fixing process.The numeric terminal positioning system and localization method can refine positioning, automation control, multifunctional unit,
Flexibility designs larger central wing box.
In order to realize the present invention, which employs following technical solutions:
A kind of aircraft center wing box numeric terminal positioning system, it is characterised in that: be divided into lathe bed main body according to functional module
The conformal unit 4 of unit 1, front-axle beam positioning unit 2, back rest positioning unit 3, left wing's rib, the conformal unit 5 of right flank rib, upper tool locating
Compressing unit 6 and lower tool locating compressing unit 7, specific structure are as follows:
Lathe bed main unit 1 be numeric terminal positioning system structure main body, be front-axle beam positioning unit 2, back rest positioning unit 3,
The peace of the conformal unit 4 of left wing's rib, the conformal unit 5 of right flank rib, upper tool locating compressing unit 6 and lower tool locating compressing unit 7
Dress basis, is made of, top lathe bed 9 former and later two column groups 8, former and later two top lathe beds 9 and former and later two lower part lathe beds 10
It is fixed on 8 top of column group, lathe bed 9 upper surface in top is equipped with guide rail, and column group 8 is fixed on foundation surface, lower part lathe bed 10
It is directly fixed on foundation surface, lathe bed 10 upper surface in lower part is equipped with guide rail, and multiple TB measurement points are disposed in column group 8；
Front-axle beam positioning unit 2 is positioned by front-axle beam fixed frame 11, front-axle beam mobile framework 12, front-axle beam driving assembly 13, preceding beam splice
Part 14, front-axle beam positioning card board group and front stringer locating piece 18 form, and front-axle beam fixed frame 11 is fixedly mounted in column group 8,
Front-axle beam driving assembly 13 is fixedly mounted on front-axle beam fixed frame 11, before front-axle beam mobile framework 12 is mounted on by guide rail and sliding block
On beam fixed frame 11, multiple ERS measurement points are disposed in front-axle beam mobile framework 12, front-axle beam mobile framework 12 is in front-axle beam driving group
It can move under the action of part 13 and along course, preceding beam splice locating piece 14, front-axle beam locating clamp plate are housed in front-axle beam mobile framework 12
Group and front stringer locating piece 18, and be disposed with OTP measurement point and have pressing device；Front-axle beam positioning unit 2 is to aircraft center
Preceding beam splice, the front-axle beam of wing box play main positioning action, play auxiliary positioning and pressuring action to the stringer of aircraft center wing box；
Back rest positioning unit 3 is positioned by back rest fixed frame 19, back rest mobile framework 20, back rest driving assembly 21, rear beam splice
Part 22, back rest positioning card board group and rear portion stringer locating piece 26 form；Back rest fixed frame 19 is fixedly mounted in column group 8,
Back rest driving assembly 21 is fixedly mounted on back rest fixed frame 19, after back rest mobile framework 20 is mounted on by guide rail and sliding block
On beam fixed frame 19, multiple ERS measurement points are disposed in back rest mobile framework 20, back rest mobile framework 20 is in back rest driving group
It can move under the action of part 21 and along course, rear beam splice locating piece 22, back rest locating clamp plate are housed in back rest mobile framework 19
Group and rear portion stringer locating piece 26, and be disposed with OTP measurement point and have pressing device；Back rest positioning unit 3 is to aircraft center
Rear beam splice, the back rest of wing box play main positioning action, play auxiliary positioning and pressuring action to stringer；
The structure of the conformal unit 4 of left wing's rib and the structure of the conformal unit 5 of right flank rib are along aircraft plane of symmetry mirror symmetry, by conformal
Crossbeam 27, Mobile Slide 28, beam splice locating piece 29, interior conformal snap-gauge group 30, siding locating piece 31, course driving assembly 32,
It opens up and is formed to driving assembly 33；Mobile Slide 28 is connect with column group 8, and Mobile Slide 28 can navigate along the horizontal plane in column group 8
Mobile to direction, conformal crossbeam 27 is connect with Mobile Slide, and conformal crossbeam 27 can move on Mobile Slide 28 along spanwise direction,
It is disposed with multiple ERS measurement points on conformal crossbeam 27 and rolling guide is housed, beam splice locating piece 29 can navigate along rolling guide
To displacement, interior conformal snap-gauge group 30 and siding locating piece 31 are connected firmly by landing nipple with conformal crossbeam 27, interior conformal snap-gauge group
30 and siding locating piece 31 on be respectively arranged multiple OTP measurement points, inside in conformal snap-gauge group 30 have quick-changing mechanism；Left wing's rib
Conformal unit 4 and the conformal unit 5 of right flank rib are to conformal support is played on the inside of aircraft central wing box wall plate end face, to upper and lower wall
Plate plays main positioning action and plays auxiliary positioning to beam splice；
Upper 6 main body of tool locating compressing unit is trabeation, is installed on top lathe bed 9, including upper beam component 34, upper cross
The vertical locator 35 of beam, upper machine frame 36 and upper shape snap-gauge group 37, upper beam component 34 pass through across two top lathe bed of front and back
Guide rail slide block guiding on its both ends, cooperates, upper beam component 34 can be in lathe bed main body list with the guide rail of 9 upper surface of top lathe bed
It extends in member 1 to movement；34 both ends of upper beam component are passed through using the synchronous driving of servo motor, bilateral gear rack-driving
Precise synchronization displacement of the upper beam component 34 in spanwise direction is realized in grating scale Real-time Feedback upper beam component 34 position in two sides
Control；The vertical locator 35 of upper beam is arranged on upper beam component 34, and upper machine frame 36 is arranged in the vertical locator of upper beam
35 ends are equipped with shape snap-gauge group 37 below upper machine frame 36, are disposed with OTP measurement point in upper shape snap-gauge group 37, and
With quick-changing mechanism；The vertical locator 35 of upper beam can move on course and vertical direction, and pass through grating scale position feedback,
The end of the vertical locator 35 of crossbeam is equipped with force snesor；Upper tool locating compressing unit 6 plays the rib of aircraft center wing box
Main positioning action plays pressuring action to aircraft center wing box wainscot, to the stringer of aircraft center wing box rise auxiliary positioning and
Pressuring action；
Lower 7 main body of tool locating compressing unit is trabeation, is installed on lower part lathe bed 10, including lower beam component 38, under
The vertical locator 39 of crossbeam, lower machine frame 40 and lower shape snap-gauge group 41, structure type and upper 6 structure of tool locating compressing unit
Form is similar, but structure size etc. is not fully consistent；Lower tool locating compressing unit 7 plays the rib of aircraft center wing box
Main positioning action plays pressuring action to the lower wall panels of aircraft center wing box；
Preferably, the front-axle beam positioning card board group include front-axle beam course locating piece 15, front-axle beam open up it is vertical to locating piece 16 and front-axle beam
Locating piece 17；
Preferably, the back rest positioning card board group include back rest course locating piece 23, the back rest open up it is vertical to locating piece 24 and the back rest
Positioning 25；
Preferably, respectively by ball-screw-transmission, lead screw installs shape for the front-axle beam mobile framework 12 and back rest mobile framework 20
For formula to be fixed-free, fixing end drives umbrella tooth gear to drive lead screw by handwheel, and free end feed screw nut passes through nut seat with before
Beam mobile framework 12 and back rest mobile framework 20 connect firmly；
Preferably, the vertical locator 35 of the upper beam is telescoping structure, and outer sleeve can be by guide rail slide block guiding, servo motor
Lead screw transmission, bilateral gear rack-driving are driven, the course guide rail on upper beam component 34 carries out course and moves, and inner sleeve can
It moves along the vertical direction；
Preferably, the Mobile Slide 28 of following structure type can be used, Mobile Slide 28 is by the two fixed base stations 42 in left and right, left and right
Two course slide plates 43 are opened up to slide plate 44, open up to slide unit 45, Mobile Slide course transmission component 46 and Mobile Slide and open up to transmission
Component 47 forms, and driving form is lead screw transmission, using fixation-fixed installation form, exhibition can be made to extend to slide unit 45 to, boat
It is mobile to two directions；Mobile Slide 28 passes through fixed base station 42 and is fixedly mounted in column group 8, and the two course slide plates 43 in left and right can
It is slided along the guide rail on fixed base station 42 along course, opens up to the both ends of slide plate 44 one respectively with the two course slide plates 43 in left and right
End is connected, and the guide rail on slide plate 44 can be extended to slide unit 45 by, which opening up, extends to sliding, and conformal crossbeam 27 is connected with opening up to slide unit 45,
To realize conformal crossbeam 27 in course driving assembly 32, open up under the driving of driving assembly 33 can course, Zhan Xiang along the horizontal plane
It is mobile to do twocouese；
Preferably, the main body of cross-beam of upper beam component is beam structure part 48, and unilateral driving structure includes anticollision block 49, prevents
Hit detection switch 50, gear reduction unit 51, servo motor 52, guide rail 53, rack gear 54 and grating scale 55,52 selective gear of servo motor
Speed reducer 51 drives, and using rack pinion, guide rail 53 is oriented to, and cooperation grating scale carries out crossbeam position feedback, realizes tooling
The accurate movement and positioning of positioning compression unit；
Preferably, the upper shape snap-gauge group 37 is by the one or three axis angle-adjusting mechanism 56, upper shape snap-gauge 57 and hold-down mechanism
58 compositions, the one or three axis angle-adjusting mechanism 56 are connect with upper machine frame 36, and upper shape snap-gauge 57 is mounted on the one or three shaft angle degree
The lower section of adjustment mechanism 56, hold-down mechanism 58 are fixedly mounted on shape snap-gauge 57；
Preferably, the lower shape snap-gauge group 41 is opened up from lower shape snap-gauge 59, rib to locating piece 60, rib course locating piece 61
It is formed with the two or three axis angle-adjusting mechanism 62, the two or three axis angle-adjusting mechanism 62 is connect with lower machine frame 40, lower shape card
Plate 59 is mounted on the top of the two or three axis angle-adjusting mechanism 56, and rib is opened up fixed to locating piece 60 and rib course locating piece 61
It is mounted on lower shape snap-gauge 59.
The present invention also provides carry out numeric terminal positioning to aircraft center wing box using above-mentioned assembly positioning system
Method, it is characterised in that: steps are as follows:
1), first based on the TB point being arranged in column group 8, front-axle beam mobile framework 11, back rest mobile framework 19, conformal crossbeam
ERS measurement point on 27 is auxiliary, carries out the acquisition of point position in space coordinate to above-mentioned measurement point using laser tracker, fits winged
Machine center wing box coordinate system, the benchmark as aircraft center wing box numeric terminal；Internal conformal snap-gauge group 30, upper shape snap-gauge
57, lower shape snap-gauge 59 and rib are opened up measures to the OTP point of locating piece 60, rib course locating piece 61, to measured value with
The snap-gauge and locating piece that theoretical value is not inconsistent are re-scaled；
2) preceding beam splice locating piece 14, rear beam splice locating piece 22, beam splice locating piece 29 to theoretical position, are adjusted, using work
Skill hole matching thread locking pin positioning and locking；Upper tool locating compressing unit 6 moves to frame outskirt, and lifting front-axle beam is vertical fixed to front-axle beam
It is bonded above the part 17 of position, using fast compressing device, web patch and front-axle beam course locating piece 15 before making, before the fitting of web stud
Beam is opened up to locating piece 16, and the fastener pre-connection of front-axle beam and preceding beam splice is completed；It lifts on the back rest to the vertical locating piece 25 of the back rest
Side's fitting makes rear web patch and back rest course locating piece 23 using fast compressing device, and the web stud fitting back rest is opened up to fixed
Position part 24, completes the fastener pre-connection of the back rest and rear beam splice；
3), front-axle beam mobile framework 12, back rest mobile framework 20 back out slot milling along course, upper tool locating compressing unit 6, under
Tool locating compressing unit 7 is moved to assembly theoretical position, successively lifts central wing box rib, keeps the fitting of rib lower end surface lower outer
Shape snap-gauge 59, rib web fitting rib are opened up to locating piece 60, and web stud is bonded rib course locating piece 61, pressing device pressure
Tightly, until all ribs complete positioning；Front-axle beam mobile framework 12, back rest mobile framework 20 move back to theoretical position, make forward and backward beam
Web is bonded with the left and right end face of rib, completes the fastener pre-connection of rib and front and rear beam, and it is fixed so far to complete central wing box skeleton
Position and fastener pre-connection, at this time entire central wing box skeleton by include preceding beam splice locating piece 14, rear beam splice locating piece 22,
The connector locating piece of beam splice locating piece 29 carries out positioning support；
4), lower tool locating compressing unit 7 moves to frame outskirt, and lifting lower wall panels paste siding external surface and lower shape snap-gauge group 41
It closes, makes lower wall panels edge respectively and on the siding locating piece 31 and beam positioning unit on the conformal unit of rib using a device is threaded into
Front-axle beam course locating piece 15, back rest course locating piece 23 be bonded, lower tool locating compressing unit 7 move to assembly theoretical position under
Side, the vertical locator 39 of lower beam slowly rises while detecting pressure change, until lower wall panels are correctly pasted with central wing box skeleton
It closes, completes the fastener pre-connection of lower wall panels and skeleton；
5), upper tool locating compressing unit 6 moves to frame outskirt, and lifting wainscot is bonded shape face in siding with skeleton, utilizes spiral shell
Screwing in position device makes wainscot edge navigate respectively with the front-axle beam on the siding locating piece 31 and beam positioning unit on the conformal unit of rib
It is bonded to locating piece 15, back rest course locating piece 23；Upper tool locating compressing unit 6 moves to above assembly theoretical position, upper cross
The vertical locator 35 of beam slowly declines while detecting pressure change, until wainscot is correctly bonded with central wing box skeleton, completes
The fastener pre-connection of wainscot and skeleton so far completes the positioning and pre-connection of central wing box wall plate；
6), upper tool locating compressing unit 6 moves to frame outskirt, successively lifts above stringer to wainscot, fixed using front stringer
Position part 18, rear portion stringer locating piece 26 position stringer, compress stringer with wainscot using hold-down mechanism 58 and are bonded simultaneously
Complete the fastener pre-connection of stringer and wainscot；
So far, the assembly positioning of entire central wing box components is completed.
Technical effect of the invention is as follows:
First, it is different from traditional vertical assemble flow, proposes the horizontal assembly technique of aircraft center wing box, is guaranteeing to produce
Under the conditions of product assembly posture and flight attitude are consistent, the accurate positioning to a variety of components of central wing box is realized, belong to domestic head
Secondary application；
Second, using large span planer-type Digital location device, locating clamp plate quick-changing mechanism and laser measuring technique, complete pair
The accurate positioning of the central multiple and different type parts of wing box (including rib, stringer) and the compression of siding, realize the more of equipment
Functionality reduces cost of goods manufactured；
Third, positioning tool are designed using flexibility, and reconfigurability is strong, when existing product remodeling or aerodynamic configuration change
When, new product can be rapidly adapted to, production latent period is shortened by replacing the corresponding function module.
4th, the Digital location method of use, positioning tool is mobile to be driven using servo motor, and grating scale closed-loop is anti-
Feedback, landing nipple and locating clamp plate are with multifunctional quick mechanism and have power monitoring function, achievable to connect to central wing box beam
The quick positioning of a variety of components such as head, spar, rib, siding, stringer and compression, positioning accuracy is high, easy to operate.
5th, wing box numeric terminal method in aircraft center according to the present invention is horizontal assembling method, product orientation appearance
State is consistent with product actual use posture, and deflection is smaller compared to vertical assembly, and can further control in assembling process
The generation of deflection.Meanwhile horizontal undercarriage on product, worker are assemblied in the cognition degree of product, opening character of tool structure etc.
Aspect all has more advantage compared to vertical assembly.
Detailed description of the invention
Fig. 1 aircraft center wing box numeric terminal positioning system general illustration；
Fig. 2 lathe bed main unit structure chart；
Fig. 3 front-axle beam positioning unit structure chart；
Fig. 4 back rest positioning unit structure chart；
The conformal cellular construction figure of Fig. 5 rib；
Tool locating compressing unit structure chart on Fig. 6；
Tool locating compressing unit structure chart under Fig. 7；
The structural schematic diagram of Fig. 8 Mobile Slide；
The unilateral driving schematic diagram of the upper beam component of tool locating compressing unit on Fig. 9；
The vertical locator unit appearance diagram of Figure 10 upper beam；
Shape snap-gauge group structure chart on Figure 11；
Shape snap-gauge group structure chart under Figure 12；
In figure: 1- lathe bed main unit, 2- front-axle beam positioning unit, 3- back rest positioning unit, the conformal unit of 4- left wing rib, 5- right flank
The conformal unit of rib, the upper tool locating compressing unit of 6-, tool locating compressing unit under 7-, 8- column group, the top 9- lathe bed, 10-
Lower part lathe bed, 11- front-axle beam fixed frame, 12- front-axle beam mobile framework, 13- front-axle beam driving assembly, beam splice locating piece before 14-,
15- front-axle beam course locating piece, 16- front-axle beam are opened up to locating piece, the vertical locating piece of 17- front-axle beam, the front 18- stringer locating piece, after 19-
Beam fixed frame, 20- back rest mobile framework, 21- back rest driving assembly, beam splice locating piece, the positioning of 23- back rest course after 22-
Part, the 24- back rest are opened up to locating piece, the vertical locating piece of the 25- back rest, the rear portion 26- stringer locating piece, the conformal crossbeam of 27-, and 28- is mobile
Slide unit, 29- beam splice locating piece, conformal snap-gauge group in 30-, 31- siding locating piece, the course 32- driving assembly, 33- are opened up to drive
Dynamic component, 34- upper beam component, the vertical locator of 35- upper beam, the upper machine frame of 36-, the upper shape snap-gauge group of 37-, cross under 38-
Beam assembly, the vertical locator of 39- lower beam, machine frame under 40-, shape snap-gauge group under 41-, the fixed base station of 42-, the course 43- are sliding
Plate, 44- are opened up to slide plate, and 45- is opened up to slide unit, 46- Mobile Slide course transmission component, and 47- Mobile Slide is opened up to transmission component,
48- beam structure part, 49- anticollision block, 50- anticollision detection switch, 51- gear reduction unit, 52- servo motor, 53- guide rail,
54- rack gear, 55- grating scale, the one or three axis angle-adjusting mechanism of 56-, the upper shape snap-gauge of 57-, 58- hold-down mechanism, shape under 59-
Snap-gauge, 60- rib are opened up to locating piece, 61- rib course locating piece, the two or three axis angle-adjusting mechanism of 62-.
Specific embodiment
It is fixed to a kind of aircraft center wing box numeric terminal of the invention with Figure of description combined with specific embodiments below
Position system and localization method are further elaborated, but protection content of the invention is not limited to following embodiment.
It is as shown in Figure 1 aircraft center wing box numeric terminal positioning system general illustration, aircraft center wing box number
Makeup with positioning system include lathe bed main unit 1, front-axle beam positioning unit 2, back rest positioning unit 3, the conformal unit 4 of left wing's rib,
The conformal unit 5 of right flank rib, upper tool locating compressing unit 6 and lower tool locating compressing unit 7.Lathe bed main unit 1 is number
Positioning system structure main body is matched in makeup, is front-axle beam positioning unit 2, back rest positioning unit 3, the conformal unit 4 of left wing's rib, right flank rib guarantor
The installation foundation of shape unit 5, upper tool locating compressing unit 6 and lower tool locating compressing unit 7.
It is illustrated in figure 2 lathe bed main unit structure chart, lathe bed main unit 1 is by by former and later two column groups 8, front and back two
A top lathe bed 9 and former and later two lower part lathe beds 10 composition, top lathe bed 9 are fixed on 8 top of column group, table on top lathe bed 9
Face is equipped with guide rail, and column group 8 is fixed on foundation surface, and lower part lathe bed 10 is directly fixed on foundation surface, on lower part lathe bed 10
Surface is equipped with guide rail, and multiple TB measurement points are disposed in column group 8, and (also known as fiducial tool ball point (Tooling Ball) is used
In the control point for establishing tooling type frame coordinate system, TB point be mainly used in aircraft digital assembly in laser tracker in work
It is applied in dress type frame assembly, belongs to aircraft digital assembly field basic conception.).The guide rail of lathe bed main unit is extended to cloth
It sets.
It is illustrated in figure 3 front-axle beam positioning unit structure chart, front-axle beam positioning unit 2 is installed on column group 8, by front-axle beam fixed frame
Frame 11, front-axle beam mobile framework 12, front-axle beam driving assembly 13, preceding beam splice locating piece 14, front-axle beam course locating piece 15, front-axle beam open up to
The vertical locating piece 17 of locating piece 16, front-axle beam, front stringer locating piece 18 form.Front-axle beam fixed frame 11 is fixedly mounted on column group
On 8, front-axle beam driving assembly 13 is fixedly mounted on front-axle beam fixed frame 11, and front-axle beam mobile framework 12 is installed by guide rail and sliding block
On front-axle beam fixed frame 11, multiple ERS measurement points (also known as enhancing coordinate mooring points is disposed in front-axle beam mobile framework 12
(Enhance Reference System), be tooling manufacture installation process in, from existing coordinate system convert or for calculate
Machine auxiliary measurement system specially generates, and for the permanent coordinate system standard point that the entire tooling service life establishes, ERS point is mainly answered
It is applied in the assembly of tooling type frame for laser tracker in aircraft digital assembly, it is basic to belong to aircraft digital assembly field
Concept.), front-axle beam mobile framework 12 (front-axle beam mobile framework upper rail arranges that the direction in course is directed toward front-axle beam by the back rest along course)
Can move under the action of front-axle beam driving assembly 13 and along course, in front-axle beam mobile framework 12 equipped with preceding beam splice locating piece 14,
Front-axle beam positioning card board group and front stringer locating piece 18, and it is disposed with OTP measurement point (also known as optical tooling ball point (Optical
Tooling Points), it is given in Fixture Design, for determining the control point of assembly tooling locating piece spatial position, OTP
Point is mainly used in laser tracker in aircraft digital assembly and applies in the assembly of tooling type frame, belongs to airplane digital makeup
With field basic conception.) and have pressing device, pressing device is arranged on front stringer locating piece 18, is hand power screw
Compactor form compresses stringer and siding and forward and backward beam framework, interlayer spacings is eliminated, to meet drilling condition；Front-axle beam is mobile
Frame 12 and back rest mobile framework 20 are respectively by ball-screw-transmission, and to be fixed-free, fixing end passes through lead screw installation form
Handwheel drives umbrella tooth gear to drive lead screw, and free end feed screw nut passes through nut seat and front-axle beam mobile framework 12 and back rest movable frame
Frame 20 connects firmly.Front-axle beam positioning unit 2 plays main positioning action to preceding beam splice, the front-axle beam of aircraft center wing box, to aircraft center
The stringer of wing box plays auxiliary positioning and pressuring action.The stringer of aircraft center wing box is long band plate structure, is located on siding, with
Rib is in same plane inside wing box, extends to rear beam-ends by preceding beam-ends.Front stringer locating piece 18 and rear portion stringer position
Part 26 respectively positions the both ends of stringer, guarantees that it is in correct spatial position.
It is illustrated in figure 4 back rest positioning unit structure chart, back rest positioning unit 3 is installed on column group 8, by back rest fixed frame
Frame 19, back rest mobile framework 20, back rest driving assembly 21, rear beam splice locating piece 22, back rest course locating piece 23, the back rest open up to
The vertical positioning 25 of locating piece 24, the back rest, rear portion stringer locating piece 26 form.Back rest fixed frame 19 is fixedly mounted on column group 8
On, back rest driving assembly 21 is fixedly mounted on back rest fixed frame 19, and back rest mobile framework 20 is installed by guide rail and sliding block
On back rest fixed frame 19, multiple ERS measurement points are disposed in back rest mobile framework 20, back rest mobile framework 20 is driven in the back rest
It can move under the action of dynamic component 21 and along course, be positioned in back rest mobile framework 19 equipped with rear beam splice locating piece 22, the back rest
Snap-gauge group and rear portion stringer locating piece 26, and be disposed with OTP measurement point and have pressing device, pressing device is arranged in rear portion
On stringer locating piece 26, it is hand power screw compactor form, stringer and siding and forward and backward beam framework is compressed, eliminate interlayer
Gap, to meet drilling condition；Back rest positioning unit 3 plays main positioning action to rear beam splice, the back rest of aircraft center wing box,
Auxiliary positioning and pressuring action are risen to stringer.
It is illustrated in figure 5 the conformal cellular construction figure of rib, the left and right conformal unit 4,5 of rib is installed on column group 8, by protecting
Shape crossbeam 27, Mobile Slide 28, beam splice locating piece 29, interior conformal snap-gauge group 30, siding locating piece 31, course driving assembly
32, it opens up and is formed to driving assembly 33.Mobile Slide 28 is connect with column group 8, and Mobile Slide 28 can be in column group 8 along the horizontal plane
Course direction is mobile, and conformal crossbeam 27 is connect with Mobile Slide, and conformal crossbeam 27 can move on Mobile Slide 28 along spanwise direction
It is dynamic, it is disposed with multiple ERS measurement points on conformal crossbeam 27 and rolling guide is housed, beam splice locating piece 29 can be done along rolling guide
Course displacement, interior conformal snap-gauge group 30 and siding locating piece 31 are connected firmly by landing nipple with conformal crossbeam 27, interior conformal snap-gauge
Multiple OTP measurement points are respectively arranged on group 30 and siding locating piece 31, has quick-changing mechanism in conformal snap-gauge group 30 inside, works as product
When shape face is changed, using original locating piece, conformal snap-gauge is replaced to adapt to new product shape face；The conformal unit 4 of left wing's rib and right flank
The conformal unit 5 of rib plays main positioning action to upper and lower siding to conformal support is played on the inside of aircraft central wing box wall plate end face
And auxiliary positioning is played to beam splice；
The specific constructive form of Mobile Slide 28 are as follows: from the two fixed base stations 42 in left and right, the two course slide plates 43 in left and right, open up to cunning
Plate 44 is opened up and is opened up to slide unit 45, Mobile Slide course transmission component 46 and Mobile Slide to the composition of transmission component 47, and driving form is equal
For lead screw transmission, using fixation-fixed installation form, exhibition can be made to extend to slide unit 45 mobile to, two direction of course；Mobile Slide
28 are fixedly mounted in column group 8 by fixed base station 42, and the course slide plate 43 of left and right two can be along leading on fixed base station 42
Rail is slided along course, is opened up one end to the both ends of slide plate 44 respectively with the two course slide plates 43 in left and right and is connected, opening up can to slide unit 45
It extends the guide rail on slide plate 44 to extend to sliding, conformal crossbeam 27 is connected with opening up to slide unit 45, to realize conformal crossbeam 27
Course driving assembly 32, open up under the driving of driving assembly 33 can along the horizontal plane course, open up to mobile, such as Fig. 8 that does twocouese
It is shown.
It is illustrated in figure 6 tool locating compressing unit structure chart, upper tool locating compressing unit 6 is installed on top lathe bed
9, it is made of upper beam component 34, the vertical locator 35 of upper beam, upper machine frame 36, upper shape snap-gauge group 37.Main body is crossbeam
Formula structure, upper beam component 34 are oriented to, with top lathe bed 9 across two top lathe bed of front and back by the guide rail slide block on its both ends
The guide rail of upper surface cooperates, and upper beam component 34 can be extended in lathe bed main unit 1 to movement；It adopts at 34 both ends of upper beam component
It is driven with servo motor is synchronous, bilateral gear rack-driving, and passes through 34 position of two sides grating scale Real-time Feedback upper beam component,
Realize precise synchronization Bit andits control of the upper beam component 34 in spanwise direction；The vertical locator 35 of upper beam is arranged in upper beam
On component 34, upper machine frame 36 is arranged in vertical 35 end of locator of upper beam, is equipped with shape snap-gauge on upper machine frame 36
37 and locating piece are organized, OTP measurement point is disposed in upper shape snap-gauge group 37, and have quick-changing mechanism；The vertical locator of upper beam
35 can move on course and vertical direction, and by grating scale position feedback, the end of the vertical locator 35 of crossbeam is equipped with power
Sensor；The vertical locator 35 of upper beam is telescoping structure, and outer sleeve can be oriented to by guide rail slide block, servo motor drives lead screw
Transmission, bilateral gear rack-driving, the course guide rail on upper beam component 34 carry out course and move, and inner sleeve can be along vertical side
To movement.Upper tool locating compressing unit 6 plays main positioning action to the rib of aircraft center wing box, in the wing box of aircraft center
Siding plays pressuring action, plays auxiliary positioning and pressuring action to the stringer of aircraft center wing box；
The main body of cross-beam of upper beam component is beam structure part 48, and unilateral driving structure includes anticollision block 49, anticollision detection
Switch 50, gear reduction unit 51, servo motor 52, guide rail 53, rack gear 54 and grating scale 55,52 selective gear speed reducer of servo motor
51 drivings, using rack pinion, guide rail 53 is oriented to, and cooperation grating scale carries out crossbeam position feedback, realizes tool locating pressure
The accurate movement and positioning of tight unit, as shown in Figure 9；
The vertical locator 35 of upper beam is telescoping structure, and outer sleeve can be oriented to by guide rail slide block, servo motor driving lead screw passes
Dynamic, bilateral gear rack-driving, the course guide rail on upper beam component 34 carries out course and moves, and inner sleeve can be along the vertical direction
It is mobile, the vertical locator unit installation diagram of upper beam as shown in Figure 10；
The structure type of upper shape snap-gauge group 37 are as follows: by three axis angle-adjusting mechanisms 56, upper shape snap-gauge 57,58 groups of hold-down mechanism
At three axis angle-adjusting mechanisms 56 are connect with upper machine frame 36, and upper shape snap-gauge 57 is mounted on three axis angle-adjusting mechanisms 56
Lower section, hold-down mechanism 58 are fixedly mounted on shape snap-gauge 57.Upper shape snap-gauge assembly assumption diagram as shown in figure 11.
It is illustrated in figure 7 lower tool locating compressing unit structure chart, lower tool locating compressing unit 7 is installed on lower part lathe bed
10, it is made of lower beam component 38, the vertical locator 39 of lower beam, lower machine frame 40, lower shape snap-gauge group 41.Structure type with
Upper 6 structure type of tool locating compressing unit is similar, but structure size etc. is not fully consistent；Lower tool locating compressing unit 7
Main positioning action is risen to the rib of aircraft center wing box, pressuring action is risen to the lower wall panels of aircraft center wing box；
The structure type of lower shape snap-gauge group 41 are as follows: opened up from lower shape snap-gauge 59, rib to locating piece 60, rib course locating piece
61 and the 2nd 3 axis angle-adjusting mechanism 62 composition, the two or three axis angle-adjusting mechanism 62 are connect with lower machine frame 40, lower shape
Snap-gauge 59 is mounted on the top of three axis angle-adjusting mechanisms 56, and rib is opened up to locating piece 60 and the fixed peace of rib course locating piece 61
On lower shape snap-gauge 59.Lower shape snap-gauge assembly assumption diagram as shown in figure 12.
In the present embodiment, the position fixing process of central wing capsule are as follows:
First based on the TB point being arranged in column group 8, front-axle beam fixed frame 11, back rest fixed frame 19, conformal crossbeam 27
On ERS measurement point be auxiliary, using laser tracker to above-mentioned measurement point carry out the acquisition of point position in space coordinate, fit center
Wing box aircraft product coordinate system, the benchmark as the assembly of central wing box Products Digital；Internal conformal snap-gauge group 30, upper shape card
Plate 57, lower shape snap-gauge 59 and rib are opened up to the OTP point of locating piece 60, rib course locating piece 61 and measure (aircraft product
Pre-installation need to only measure the OTP point of the locating piece closely related with product orientation, snap-gauge, guarantee itself and digital-to-analogue theory
Position consistency), the snap-gauge and locating piece not being inconsistent with theoretical value measured value re-scale.
Preceding beam splice locating piece 14, rear beam splice locating piece 22, beam splice locating piece 29 to theoretical position are adjusted, using work
Skill hole matching thread locking pin positioning and locking；Upper tool locating compressing unit 6 moves to frame outskirt, and lifting front-axle beam is vertical fixed to front-axle beam
It is bonded above the part 17 of position, using fast compressing device, web patch and front-axle beam course locating piece 15 before making, before the fitting of web stud
Beam is opened up to locating piece 16, and the fastener pre-connection of front-axle beam and preceding beam splice is completed；It lifts on the back rest to the vertical locating piece 25 of the back rest
Side's fitting makes rear web patch and back rest course locating piece 23 using fast compressing device, and the web stud fitting back rest is opened up to fixed
Position part 24, completes the fastener pre-connection of the back rest and rear beam splice.
Front-axle beam mobile framework 12, back rest mobile framework 20 back out slot milling along course, upper tool locating compressing unit 6,
Lower tool locating compressing unit 7 is moved to assembly theoretical position, central wing box rib is successively lifted, under being bonded rib lower end surface
Shape snap-gauge 59, rib web fitting rib are opened up to locating piece 60, and web stud is bonded rib course locating piece 61, pressing device pressure
Tightly, until all ribs complete positioning.Front-axle beam mobile framework 12, back rest mobile framework 20 move back to theoretical position, make forward and backward beam
Web is bonded with the left and right end face of rib, completes the fastener pre-connection of rib and front and rear beam, and it is fixed so far to complete central wing box skeleton
Position and fastener pre-connection.Central wing box skeleton entire at this time is connect by preceding beam splice locating piece 14, rear beam splice locating piece 22, beam
The connectors locating pieces such as head locating piece 29 carry out positioning support.
Lower tool locating compressing unit 7 moves to frame outskirt, and lifting lower wall panels make siding external surface and lower shape snap-gauge group 41
Fitting, using be threaded into a device make lower wall panels edge respectively with the siding locating piece 31 and beam positioning unit on the conformal unit of rib
On front-axle beam course locating piece 15, back rest course locating piece 23 be bonded.Lower tool locating compressing unit 7 moves to assembly theoretical position
Lower section, the vertical locator 39 of lower beam slowly rises while detecting pressure change, until lower wall panels and central wing box skeleton are correct
The fastener pre-connection of lower wall panels and skeleton is completed in fitting.
Upper tool locating compressing unit 6 moves to frame outskirt, and lifting wainscot is bonded siding inner mold face with skeleton, utilizes spiral shell
Screwing in position device makes wainscot edge navigate respectively with the front-axle beam on the siding locating piece 31 and beam positioning unit on the conformal unit of rib
It is bonded to locating piece 15, back rest course locating piece 23.Upper tool locating compressing unit 6 moves to above assembly theoretical position, upper cross
The vertical locator 35 of beam slowly declines while detecting pressure change, until wainscot is correctly bonded with central wing box skeleton, completes
The fastener pre-connection of wainscot and skeleton so far completes the positioning and pre-connection of central wing box wall plate.
Upper tool locating compressing unit 6 moves to frame outskirt, successively lifts above stringer to wainscot, fixed using front stringer
Position part 18, rear portion stringer locating piece 26 position stringer, compress stringer with wainscot using hold-down mechanism 58 and are bonded simultaneously
Complete the fastener pre-connection of stringer and wainscot.
So far, the positioning of entire central wing box components is completed.
Claims (10)
1. a kind of aircraft center wing box numeric terminal positioning system, it is characterised in that: be divided into lathe bed master according to functional module
Body unit (1), front-axle beam positioning unit (2), back rest positioning unit (3), the conformal unit of left wing's rib (4), the conformal unit of right flank rib
(5), upper tool locating compressing unit (6) and lower tool locating compressing unit (7), specific structure are as follows:
Lathe bed main unit (1) is numeric terminal positioning system structure main body, is front-axle beam positioning unit (2), back rest positioning list
First (3), the conformal unit of left wing's rib (4), the conformal unit of right flank rib (5), upper tool locating compressing unit (6) and lower tool locating pressure
The installation foundation of tight unit (7), by former and later two column groups (8), former and later two top lathe beds (9) and former and later two lower part lathe beds
(10) it forms, top lathe bed (9) is fixed at the top of column group (8), and top lathe bed (9) upper surface is equipped with guide rail, column group (8)
It is fixed on foundation surface, lower part lathe bed (10) is directly fixed on foundation surface, and lower part lathe bed (10) upper surface is equipped with guide rail, stands
Multiple TB measurement points are disposed in column group (8)；
Front-axle beam positioning unit (2) is by front-axle beam fixed frame (11), front-axle beam mobile framework (12), front-axle beam driving assembly (13), front-axle beam
Connector locating piece (14), front-axle beam positioning card board group and front stringer locating piece (18) composition, the fixed peace of front-axle beam fixed frame (11)
On column group (8), front-axle beam driving assembly (13) is fixedly mounted on front-axle beam fixed frame (11), front-axle beam mobile framework (12)
It is mounted on front-axle beam fixed frame (11) by guide rail and sliding block, multiple ERS measurement points is disposed in front-axle beam mobile framework (12),
Front-axle beam mobile framework (12) is under the action of front-axle beam driving assembly (13) and can move along course, and front-axle beam mobile framework fills on (12)
There are preceding beam splice locating piece (14), front-axle beam positioning card board group and front stringer locating piece (18), and is disposed with OTP measurement point and band
There is pressing device；Front-axle beam positioning unit (2) plays main positioning action to preceding beam splice, the front-axle beam of aircraft center wing box, to aircraft
The stringer of central wing box plays auxiliary positioning and pressuring action；
Back rest positioning unit (3) is by back rest fixed frame (19), back rest mobile framework (20), back rest driving assembly (21), the back rest
Connector locating piece (22), back rest positioning card board group and rear portion stringer locating piece (26) composition；The fixed peace of back rest fixed frame (19)
On column group (8), back rest driving assembly (21) is fixedly mounted on back rest fixed frame (19), back rest mobile framework (20)
It is mounted on back rest fixed frame (19) by guide rail and sliding block, multiple ERS measurement points is disposed in back rest mobile framework (20),
Back rest mobile framework (20) is under the action of back rest driving assembly (21) and can move along course, and back rest mobile framework fills on (19)
There are rear beam splice locating piece (22), back rest positioning card board group and rear portion stringer locating piece (26), and is disposed with OTP measurement point and band
There is pressing device；Back rest positioning unit (3) plays main positioning action to rear beam splice, the back rest of aircraft center wing box, to stringer
Play auxiliary positioning and pressuring action；
The structure of the conformal unit of left wing's rib (4) and the structure of the conformal unit of right flank rib (5) along aircraft plane of symmetry mirror symmetry, by
Conformal crossbeam (27), Mobile Slide (28), beam splice locating piece (29), interior conformal snap-gauge group (30), siding locating piece (31), boat
To driving assembly (32), open up to driving assembly (33) composition；Mobile Slide (28) is connect with column group (8), Mobile Slide (28)
Can course direction is mobile along the horizontal plane on column group (8), conformal crossbeam (27) connect with Mobile Slide, and conformal crossbeam (27) can
It moves on Mobile Slide (28) along spanwise direction, multiple ERS measurement points are disposed on conformal crossbeam (27) and are led equipped with rolling
Rail, beam splice locating piece (29) can do course displacement along rolling guide, and interior conformal snap-gauge group (30) and siding locating piece (31) are logical
It crosses landing nipple to connect firmly with conformal crossbeam (27), be respectively arranged on interior conformal snap-gauge group (30) and siding locating piece (31) multiple
OTP measurement point has quick-changing mechanism on interior conformal snap-gauge group (30)；The conformal unit of left wing's rib (4) and the conformal unit of right flank rib (5)
To conformal support is played on the inside of aircraft central wing box wall plate end face, main positioning action is played to upper and lower siding and to beam splice
Play auxiliary positioning；
Upper tool locating compressing unit (6) main body is trabeation, is installed on top lathe bed (9), including upper beam component
(34), the vertical locator of upper beam (35), upper machine frame (36) and upper shape snap-gauge group (37), upper beam component (34) is across preceding
Two top lathe bed afterwards is oriented to by the guide rail slide block on its both ends, is cooperated with the guide rail of top lathe bed (9) upper surface, upper beam
Component (34) can extend on lathe bed main unit (1) to movement；It is driven using servo motor is synchronous at upper beam component (34) both ends
It is dynamic, bilateral gear rack-driving, and by two sides grating scale Real-time Feedback upper beam component (34) position, realize upper beam component
(34) the precise synchronization Bit andits control in spanwise direction；The vertical locator of upper beam (35) is arranged in upper beam component (34)
On, upper machine frame (36) is arranged in the vertical locator of upper beam (35) end, is equipped with shape card below upper machine frame (36)
Board group (37) is disposed with OTP measurement point on upper shape snap-gauge group (37), and has quick-changing mechanism；The vertical locator of upper beam
(35) it can be moved on course and vertical direction, and by grating scale position feedback, the end of the vertical locator of crossbeam (35) is filled
Force sensor；Upper tool locating compressing unit (6) plays main positioning action to the rib of aircraft center wing box, to aircraft center
Wing box wainscot plays pressuring action, plays auxiliary positioning and pressuring action to the stringer of aircraft center wing box；
Lower tool locating compressing unit (7) main body is trabeation, is installed on lower part lathe bed (10), including lower beam component
(38), the vertical locator of lower beam (39), lower machine frame (40) and lower shape snap-gauge group (41), structure type and upper tool locating
Compressing unit (6) structure type is similar, but size is different, rib of the lower tool locating compressing unit (7) to aircraft center wing box
Main positioning action is played, pressuring action is risen to the lower wall panels of aircraft center wing box.
2. a kind of aircraft center wing box numeric terminal positioning system according to claim 1, which is characterized in that before described
Beam positioning card board group includes that front-axle beam course locating piece (15), front-axle beam are opened up to locating piece (16) and the vertical locating piece of front-axle beam (17).
3. a kind of aircraft center wing box numeric terminal positioning system according to claim 2, which is characterized in that after described
Beam positioning card board group includes that back rest course locating piece (23), the back rest are opened up to locating piece (24) and the vertical positioning of the back rest (25).
4. a kind of aircraft center wing box numeric terminal positioning system according to claim 3, which is characterized in that before described
Respectively by ball-screw-transmission, lead screw installation form is that fixation-is free for beam mobile framework (12) and back rest mobile framework (20),
Fixing end drives umbrella tooth gear to drive lead screw by handwheel, and free end feed screw nut passes through nut seat and front-axle beam mobile framework (12)
It is connected firmly with back rest mobile framework (20).
5. a kind of aircraft center wing box numeric terminal positioning system according to claim 4, which is characterized in that on described
The vertical locator of crossbeam (35) is telescoping structure, and outer sleeve can be oriented to by guide rail slide block, servo motor drives lead screw transmission, double
Side gear rack-driving, the course guide rail on upper beam component (34) carry out course movement, and inner sleeve can move along the vertical direction
It is dynamic.
6. a kind of aircraft center wing box numeric terminal positioning system according to claim 5, which is characterized in that the shifting
Dynamic slide unit (28) from the two fixed base stations (42) in left and right, control two course slide plates (43), open up to slide plate (44), open up to slide unit
(45), Mobile Slide course transmission component (46) and Mobile Slide are opened up forms to transmission component (47), and driving form is lead screw
Transmission can be such that exhibition extends to slide unit (45) mobile to, two direction of course using fixation-fixed installation form；Mobile Slide (28)
It is fixedly mounted on column group (8) by fixed base station (42), the course slide plate (43) of left and right two can be along fixed base station (42)
On guide rail along course slide, open up to the both ends of slide plate (44) respectively with left and right two course slide plates (43) one end be connected, exhibition
The guide rail on slide plate (44) can be extended to slide unit (45) to extend to sliding, conformal crossbeam (27) and open up to slide unit (45) be connected,
To realize conformal crossbeam (27) in course driving assembly (32), open up and can navigate along the horizontal plane under the driving of driving assembly (33)
To, open up it is mobile to twocouese is done.
7. a kind of aircraft center wing box numeric terminal positioning system according to claim 6, which is characterized in that upper beam
The main body of cross-beam of component is beam structure part (48), and unilateral driving structure includes anticollision block (49), anticollision detection switch
(50), gear reduction unit (51), servo motor (52), guide rail (53), rack gear (54) and grating scale (55), servo motor (52) are matched
Gear reduction unit (51) driving, using rack pinion, guide rail (53) guiding, cooperation grating scale carries out crossbeam position feedback,
Realize the accurate movement and positioning of tool locating compressing unit.
8. a kind of aircraft center wing box numeric terminal positioning system according to claim 7, which is characterized in that on described
Shape snap-gauge group (37) is made of the one or three axis angle-adjusting mechanism (56), upper shape snap-gauge (57) and hold-down mechanism (58), the
One or three axis angle-adjusting mechanisms (56) are connect with upper machine frame (36), and upper shape snap-gauge (57) is mounted on the adjustment of the one or three shaft angle degree
The lower section of mechanism (56), hold-down mechanism (58) are fixedly mounted on shape snap-gauge (57).
9. a kind of aircraft center wing box numeric terminal positioning system according to claim 8, which is characterized in that under described
Shape snap-gauge group (41) is opened up from lower shape snap-gauge (59), rib to locating piece (60), rib course locating piece (61) and the two or three
Axis angle-adjusting mechanism (62) composition, the two or three axis angle-adjusting mechanism (62) are connect with lower machine frame (40), lower shape snap-gauge
(59) it is mounted on the top of the two or three axis angle-adjusting mechanism (56), rib is opened up to locating piece (60) and rib course locating piece
(61) it is fixedly mounted on lower shape snap-gauge (59).
10. the method that numeric terminal positioning is carried out to aircraft center wing box using assembly positioning system as claimed in claim 9,
It is characterized by: steps are as follows:
(1) first based on the TB point being arranged on column group (8), front-axle beam mobile framework (11), is protected at back rest mobile framework (19)
ERS measurement point on shape crossbeam (27) is auxiliary, carries out the acquisition of point position in space coordinate to above-mentioned measurement point using laser tracker,
Fit aircraft center wing box coordinate system, the benchmark as aircraft center wing box numeric terminal；Internal conformal snap-gauge group (30),
Upper shape snap-gauge (57), lower shape snap-gauge (59) and rib open up to locating piece (60), rib course locating piece (61) OTP point into
Row measurement, the snap-gauge and locating piece not being inconsistent with theoretical value measured value re-scale；
(2) preceding beam splice locating piece (14), rear beam splice locating piece (22), beam splice locating piece (29) to theoretical position are adjusted,
Using fabrication hole matching thread locking pin positioning and locking；Upper tool locating compressing unit (6) moves to frame outskirt, and lifting front-axle beam is to preceding
Fitting above the vertical locating piece of beam (17), using fast compressing device, web patch and front-axle beam course locating piece (15), abdomen before making
Plate stud fitting front-axle beam is opened up to locating piece (16), and the fastener pre-connection of front-axle beam and preceding beam splice is completed；The back rest is lifted to the back rest
Fitting above vertical locating piece (25) makes rear web patch and back rest course locating piece (23), web using fast compressing device
The stud fitting back rest is opened up to locating piece (24), and the fastener pre-connection of the back rest and rear beam splice is completed；
(3) front-axle beam mobile framework (12), back rest mobile framework (20) back out slot milling, upper tool locating compressing unit along course
(6), lower tool locating compressing unit (7) is moved to assembly theoretical position, successively lifts central wing box rib, makes rib lower end surface
It is bonded lower shape snap-gauge (59), rib web fitting rib is opened up to locating piece (60), and web stud is bonded rib course locating piece
(61), pressing device compresses, until all ribs complete positioning；Front-axle beam mobile framework (12), back rest mobile framework (20) are mobile
Theoretical position is returned, is bonded forward and backward web with the left and right end face of rib, completes the fastener pre-connection of rib and front and rear beam, until
This completes central wing box framework location and fastener pre-connection, and central wing box skeleton entire at this time is by including preceding beam splice locating piece
(14), rear beam splice locating piece (22), beam splice locating piece (29) connector locating piece carry out positioning support；
(4) tool locating compressing unit (7) moves to frame outskirt under, and lifting lower wall panels make siding external surface and lower shape snap-gauge group
(41) be bonded, using be threaded into a device make lower wall panels edge respectively with siding locating piece (31) He Liangding on the conformal unit of rib
Front-axle beam course locating piece (15), back rest course locating piece (23) fitting on bit location, lower tool locating compressing unit (7) move to
It assembles below theoretical position, the vertical locator of lower beam (39) slowly rises while detecting pressure change, until lower wall panels are in
Centre wing box skeleton is correctly bonded, and completes the fastener pre-connection of lower wall panels and skeleton；
(5) tool locating compressing unit (6) moves to frame outskirt on, and lifting wainscot is bonded shape face in siding with skeleton, utilizes
Be threaded into a device make wainscot edge respectively on the siding locating piece (31) and beam positioning unit on the conformal unit of rib before
Beam course locating piece (15), back rest course locating piece (23) fitting；Upper tool locating compressing unit (6) moves to assembly theoretical position
Top, the vertical locator of upper beam (35) slowly decline while detecting pressure change, until wainscot and central wing box skeleton are just
The fastener pre-connection of wainscot and skeleton is completed in really fitting, so far completes the positioning and pre-connection of central wing box wall plate；
(6) tool locating compressing unit (6) moves to frame outskirt on, successively lifts above stringer to wainscot, utilizes front stringer
Locating piece (18), rear portion stringer locating piece (26) position stringer, make stringer and wainscot pressure using hold-down mechanism (58)
It is close to merge the fastener pre-connection for completing stringer and wainscot；So far, the assembly positioning of entire central wing box components is completed.
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| CN201711033496.2A CN109204873B (en) | 2017-10-30 | 2017-10-30 | Digital assembly positioning system and positioning method for central wing box of airplane |
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| CN201711033496.2A CN109204873B (en) | 2017-10-30 | 2017-10-30 | Digital assembly positioning system and positioning method for central wing box of airplane |
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| CN116423188A (en) * | 2023-06-15 | 2023-07-14 | 西安泽达航空制造有限责任公司 | A stringer frock for aircraft is made |
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| CN110525683A (en) * | 2019-10-08 | 2019-12-03 | 江西洪都航空工业集团有限责任公司 | A kind of conformal tooling of numeric terminal, implementation and application method |
| CN110756994B (en) * | 2019-10-09 | 2021-09-21 | 中国船舶重工集团公司第七一六研究所 | Flexible clamping system and clamping method for robot welding of large-scale component |
| CN110756994A (en) * | 2019-10-09 | 2020-02-07 | 中国船舶重工集团公司第七一六研究所 | Flexible clamping system and clamping method for robot welding of large-scale component |
| CN111731504A (en) * | 2020-06-12 | 2020-10-02 | 陕西飞机工业（集团）有限公司 | Positioning method of cockpit glass framework |
| CN111746819A (en) * | 2020-07-10 | 2020-10-09 | 中国航空制造技术研究院 | Automatic assembly equipment for helicopter hub |
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| CN113353242A (en) * | 2021-05-17 | 2021-09-07 | 南京航空航天大学 | Temporary fastener layout optimization method for composite wing box pre-connection stage |
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| CN114148541A (en) * | 2021-08-12 | 2022-03-08 | 中航西安飞机工业集团股份有限公司 | Flexible shape-keeping device and method for horizontal assembly of wing ribs of wing box |
| CN113772116A (en) * | 2021-09-18 | 2021-12-10 | 中航西安飞机工业集团股份有限公司 | Modular reconfigurable aircraft movable wing surface assembly tool and assembly method |
| CN114013680B (en) * | 2021-11-19 | 2023-04-18 | 航天特种材料及工艺技术研究所 | Assembly fixture for wing end ribs and assembly method for wing butt joint mounting seat |
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| CN114872924A (en) * | 2022-06-15 | 2022-08-09 | 中国民用航空飞行学院 | Aircraft structure repair fixture |
| CN114872924B (en) * | 2022-06-15 | 2023-07-07 | 中国民用航空飞行学院 | Repair type frame for aircraft structure |
| CN116423188A (en) * | 2023-06-15 | 2023-07-14 | 西安泽达航空制造有限责任公司 | A stringer frock for aircraft is made |
| CN116423188B (en) * | 2023-06-15 | 2023-08-22 | 西安泽达航空制造有限责任公司 | A stringer frock for aircraft is made |
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