CN107553345B - A kind of the aircraft target ship pre stress shot peen tooling and ball blasting method of multiple spot active load - Google Patents
A kind of the aircraft target ship pre stress shot peen tooling and ball blasting method of multiple spot active load Download PDFInfo
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Abstract
The present invention is the aircraft target ship pre stress shot peen tooling and ball blasting method of a kind of multiple spot active load.It is made of rigid frame, stringer and multiple formed punches.Design has linear guide on frame, and stringer is installed in linear guide, and height is equipped on stringer can be by the hold-down mechanism for the formed punch and fixed siding that computer numerical control adjusts.Each formed punch is provided with integrated digital controlled driving decelerating motor, and motor rotate driving lead screw is realized that punch body is adjusted in axial height, and can be locked at an arbitrary position.Compared to traditional pre stress shot peen fixture, numerical control formed punch may be constructed siding part pre-bending of the Prebending type face realization to any curvature, and large number of formed punch makes prestressing force suffered by siding more evenly, and single-point force is effectively avoided to cause local distortion's phenomenon；During contour peening, used height of punch can be adjusted in real time according to the deformation of siding, improve the precision of contour peening；After contour peening, which can be used as the form error for examining pattern detection curvature panel.
Description
Technical field
The invention belongs to machinery manufacturing technology field, specifically a kind of aircraft target ship prestressing force of multiple spot active load
Shot-peening tooling and ball blasting method.
Background technique
In aircraft manufacturing field, as one kind part --- integral panel most important on aircraft, it is that aircraft is pneumatic
Shape wants component part, while being also the main load-carrying member of wing, fuselage etc..But its biggish size and complex curvatures pair
Forming technique proposes test.At present at home and abroad, contour peening is especially large-scale because its unique advantage is as modern aircraft
A kind of best approach of passenger plane Forming of Aircraft Wing Skin Panels.However contour peening has certain forming limit, that is to say, that its
The curvature of forming has a limiting value, and free shot-peening be easy to cause the spherical deformation of plate.Therefore propose pre stress shot peen at
Shape technology first applies prestressing force to wall panel parts that is, before shot-peening, so that part is generated pre-bending, then carries out contour peening again.
Practice have shown that prestress peen forming can increase substantially the forming limit of free shot-peening, while eliminating free shot-peening and generating
Spherical deformation tendency, control deformation direction well.Currently, large-scale compressed air shotblasting machine has pre- angle coupling corresponding with its size
Tool, for realizing different sizes, the siding of different curvature carries out clamping and pre-bending.However fixture commonly used in the prior art is main
There are the deficiencies in terms of following two: one, the force application mechanism of fixture is unsatisfactory for versatility, and a set of force application mechanism is often only limited to one
Kind wall panel parts；Two, the prestressing force point of application is less, be easy to cause local distortion, and prestress distribution is uneven, and pre-bending is ineffective.
Summary of the invention
The present invention provides one kind, and multiple point of applications, for different sizes, the siding of any curvature can be controlled by computer
The aircraft target ship pre stress shot peen tooling and ball blasting method that there is class part the multiple spot of the flexible prestressing of versatility actively to load,
Overcome the above-mentioned deficiency of existing shot-peening tooling and ball blasting method.
Technical solution of the present invention is described with reference to the drawings as follows:
A kind of aircraft target ship pre stress shot peen tooling of multiple spot actively load, the tooling include connector sliding block 3, pressing clip 5,
Multiple spot punch systems 7, rack and pinion drive mechanism, two linear guides 2 of guide rail base 4, two of rigid frame 1, two and more
With stringer 6；Guide rail base 4 described in two is fixed on two rigid frames 1；It is equipped on guide rail base 4 described in two
Two linear guides 2；Mostly connect respectively with connector sliding block 3 with the both ends of the stringer 6, and wherein one end be equipped with it is locked
Mechanism 9, the other end is equipped with rack and pinion drive mechanism；The connector sliding block 3 is slidably matched with linear guide 2；Described
Multiple multiple spot punch systems 7 are fixed with by third nut 24 on stringer 6；Pressure is respectively and fixedly provided with above 6 both ends of stringer
Grip 5.
Guide rail scale 11 is provided on guide rail base 4 described in one, the side of the stringer 6 is provided with stringer scale
10。
The two sides of the stringer 6 are provided with the first T-slot 8 through stringer 6, and centre is provided with the second T-slot 21.
Second T-slot 21 is provided with more set multiple spot punch systems 7；The multiple spot punch systems 7 include shell
25, motor 27, formed punch 28 are applied in control circuit 26, adjustment；The adjustment is using the output end of motor 27 and with internal screw thread
Formed punch 28 be threadedly coupled；The second nut 29 of fixed punch head 28 is provided with outside the shell 25；The adjustment application electricity
Machine 27 is connected with control circuit 26；The control circuit 26 is connected by repeater with computer.
Pressing clip 5 is provided in first T-slot 8 described in two, the pressing clip 5 includes pressing clip rack 16, adjusts
Pole 17 and pressing clip pressure head 18；The both ends of the pressing clip rack 16 are arranged by the first bolt 14 in the first T-slot 8
Interior, the top of first bolt 14 is provided with the first nut 19；It is set between first bolt 14 and the first nut 19
There is gasket 20；The adjusting rod 17 is fixed on one end of pressing clip rack 16, and lower end is fixed with pressing clip pressure head 18；It is described
Pressing clip pressure head 18 and formed punch 28 between place wall panel parts 12.
There is the elastic cushion 13 of polyurethane between the wall panel parts 12 and formed punch 28.
The rack and pinion drive mechanism includes rack gear 22 and gear 23；The gear 23 passes through gear shaft and stringer
6 connections；The rack gear 22 is fixed on two guide rail bases 4 and is meshed with gear 23.
A kind of aircraft target ship pre stress shot peen method that multiple spot actively loads, method includes the following steps:
Step 1: Prebending type face is determined by formula calculating first, Prebending type face is made of formed punch 28 before shot-peening, it is multiple
Formed punch is arranged in " face " and realizes prestressed application to guarantee that prestressing force is uniform；
Step 2: during shot-peening, since practical pre-bending amount and shot-peening parameter are difficult to accurately formulate, because pre-bending amount is bigger than normal or
Stress error caused by less than normal and shot-peening parameter inexactness can be mended by the method for adjusting 28 height of formed punch in real time
It repays, moment of flexure is bigger than normal, reduces by 28 height of formed punch, and moment of flexure is less than normal, increases 28 height of formed punch；
Step 3: formed punch 28 may be constructed part type face as the forming mistake for examining pattern detection curvature panel after shot-peening
Difference.
The invention has the benefit that
The present invention plays " flexibility " feature of fixture with multiple spot punch systems out to out, before shot-peening, is controlled by computer
Formed punch can accurately constitute the Prebending type face of any curvature, therefore can realize to different shape, the siding part of any curvature
Pre-bending.Formed punch large number of simultaneously makes prestressing force suffered by siding more evenly, and single-point force is effectively avoided to cause local distortion
Phenomenon guarantees prestressing force effect；During contour peening, used punching can be adjusted in real time according to the deformation of siding
Grease head highness improves the precision of contour peening；After contour peening, numerical control formed punch may be constructed part type face as inspection pattern detection
The form error of curvature panel.
Detailed description of the invention
Fig. 1 is the aircraft target ship pre stress shot peen tool structure schematic diagram that multiple spot actively loads；
Fig. 2 is the schematic diagram that the aircraft target ship pre stress shot peen tooling that multiple spot actively loads carries out tangential pre-bending；
Fig. 3 is the schematic diagram that the aircraft target ship pre stress shot peen tooling that multiple spot actively loads carries out hyperbolicity pre-bending；
Fig. 4 is the compression clip schematic diagram for the aircraft target ship pre stress shot peen tooling that multiple spot actively loads；
Fig. 5 is a kind of schematic diagram of stringer cross section T-shape slot structure；
Fig. 6 is another schematic diagram of stringer cross section T-shape slot structure；
Fig. 7 is locking mechanism schematic diagram.
In figure: 1, rigid frame；2, linear guide；3, connector sliding block；4, guide rail base；5, pressing clip；6, stringer；7, more
Point punch systems；8, the first T-slot；9, locking mechanism；10, stringer scale；11, guide rail scale；12, wall panel parts；13, elastic
Pad；14, the first bolt；15, hyperbolicity pre-bending part；16, pressing clip rack；17, adjusting rod；18, pressing clip pressure head；19,
One nut；20, gasket；21, the second T-slot；22, rack gear；23, gear；24, third nut；25, shell；26, control circuit；
27, motor is applied in adjustment；28, formed punch；29, the second nut；30, the second bolt；31, baffle；32, handle.
Specific embodiment
Refering to fig. 1, Fig. 2, Fig. 3, a kind of aircraft target ship pre stress shot peen tooling that multiple spot actively loads, which includes connecing
Head slider 3, pressing clip 5, multiple spot punch systems 7, rack and pinion drive mechanism, two rigid frames, 1, two guide rail base 4, two
A linear guide 2 and Duo Gen stringer 6；Guide rail base 4 described in two is fixed on two rigid frames 1；It is led described in two
There are two linear guides 2 for installation on base of the rail seat 4；The both ends of stringer 6 described in more are connect with connector sliding block 3 respectively, and its
Middle one end is equipped with locking mechanism 9, and the other end is equipped with rack and pinion drive mechanism；The connector sliding block 3 and linear guide 2
It is slidably matched, connector sliding block 3 can drive stringer 6 to move back and forth in linear guide 2, and mobile purpose is according to different exhibitions
To the position of the siding of size adjustment stringer 6, while guide rail scale 11 being installed on guide rail base 4, after the completion of positioning, utilizes lock
Crash structure 9 fixes stringer, and the locking mechanism 9 is made of the second bolt 30 and baffle 31, is withstood on and is led using the second bolt 30
It realizes and locks on base of the rail seat 4, as shown in Figure 7.Multiple multiple spot punch systems are fixed with by third nut 24 on the stringer 6
7；Pressing clip 5 is respectively and fixedly provided with above 6 both ends of stringer.
Refering to Fig. 5, Fig. 6, the two sides of the stringer 6 are provided with the first T-slot 8 through stringer 6, and centre is provided with the 2nd T
Type groove 21.
Second T-slot 21 of rail inner is provided with more set multiple spot punch systems 7；The multiple spot punch systems 7 include
Motor 27, formed punch 28 are applied in shell 25, control circuit 26, adjustment；The control circuit 26, adjustment exist using the setting of motor 27
In shell 25；The adjustment is threadedly coupled using the output end of motor 27 with internal thread formed punch 28；The shell
The second nut 29 of fixed punch head 28 is provided with outside 25；The adjustment application motor 27 is connected with control circuit 26；Described
Control circuit is connected by repeater with computer.Arrange that multiple repeaters, repeater control multiple adjustment applications by computer
Motor 27, adjustment drive screw rod rotation using motor 27, so that tool internal thread formed punch 28 be driven to move up and down, realize formed punch
28 axially adjust, and can position at an arbitrary position.Can be the characteristics of axial any position position using formed punch 28, quantity
Numerous formed punches 28 can form the arbitrary Prebending type face of curvature as force application mechanism, realize the pre-bending to siding.Shell 25 can
A whole set of multiple spot punch systems 7 are driven to move freely in the second T-slot 21,25 exterior of shell has to fixed punch after the completion of movement
First 28 the second nut 29, stringer side is equipped with stringer scale 10.
Refering to fig. 1, Fig. 4, pressing clip 5 is provided in the first T-slot 8 described in two, and the pressing clip 5 includes compressing
Press from both sides rack 16, adjusting rod 17 and pressing clip pressure head 18；The both ends of the pressing clip rack 16 are arranged by the first bolt 14
In first T-slot 8, the first bolt 14 can move freely in the first T-slot 8, and 14 top of the first bolt also has the first spiral shell
Mother 19.Formed punch 28 and the position of pressing clip 5 can be adjusted according to the wall panel parts 12 of Bu Tong tangential size；Described
Gasket 20 is equipped between one bolt 14 and the first nut 19；The adjusting rod 17 is fixed on one end of pressing clip rack 16,
Lower end is fixed with pressing clip pressure head 18；Wall panel parts 12 are placed between the pressing clip pressure head 18 and formed punch 28.It is first when mobile
The first nut 19 is first unscrewed, mobile first bolt 14, is positioned with stringer scale 10, reach suitable position in the first T-slot 8
It postpones and screws on the first nut 19, fixing.
Referring to fig. 2, Fig. 2 is moved firstly, being opened up according to siding to size with gear and rack teeth mechanism to the tangential pre-bending of siding
Connector sliding block 3 is moved to adjust the position of stringer 6, and guide rail scale 11 is installed to carry out stringer 6 on linear guide pedestal 2
It positions, with the fixed stringer of locking mechanism 9 after stringer 6 to suitable position.Secondly, utilizing the second T-type according to the tangential size of siding
Slot 21 adjusts the position of multiple spot punch systems 7 and pressing clip 5 on stringer 6.Before multiple spot punch systems 7 are mobile, shell is first unscrewed
The second nut 29 outside 25, then mobile shell 25, to drive a whole set of multiple spot punch systems 7,6 side of stringer is equipped with the use of scale 10
With positioning, after the completion of positioning, the fixed formed punch of the second nut 29 is tightened.Mobile the by mobile first T-slot 8 of pressing clip 5
One bolt 14 is realized, is equally positioned with stringer scale 10, after the completion of positioning, is tightened the first nut 19 and is fixed and clamped folder.So
Operation handle 32 afterwards, handle 32 above push away, and open clip, wall panel parts 12 are placed, then operation handle, according to four-bar mechanism
Automatic dead-locking function compresses siding.Motor 27 is applied by computer control adjustment again, drives lead screw rotation, so that driving has
The formed punch 28 of internal screw thread moves up, and numerous formed punches 28 presses upwards simultaneously, forms pre-bending curved surface.Simultaneously in order to avoid multiple spot
Formed punch small impression caused by siding and stress are concentrated, and it is poly- ammonia that layer of material can be added between multiple spot formed punch 28 and siding
The elastic cushion 13 of ester.During contour peening, because pre-bending amount is difficult to accurately calculate, by pre-bending amount is bigger than normal or less than normal and shot-peening is joined
Error caused by several inexactnesies can be compensated by adjusting 28 height of formed punch in real time.Siding bending moment is bigger than normal, reduces
28 height of formed punch, siding bending moment is less than normal, increases 28 height of formed punch.After shot-peening, 28 constituent part appearance curved surface of formed punch, the work
Dress is alternatively arranged as examining the form error of pattern detection curvature panel.
Referring to the hyperbolicity pre-bending that Fig. 3, Fig. 3 are to siding, the curvature of real aircraft siding is sufficiently complex, and Curvature varying is simultaneously
It is not uniform, and other than most important tangential curvature, there is certain spanwise curvature toward contact, therefore implementing hyperbolicity
It during pre-bending, needs to adjust the length of adjusting rod 17, is just able to achieve with controlling the height of pressing clip pressure head 18 to hyperbolicity wall
The compression of plate 15.Multiple spot punch device has advantage outstanding for the pre-bending of the wall panel parts of curvature complexity, i.e., according to plate
Pre-bending meter calculate the displacement of each formed punch 28, the displacement of each formed punch 28 axially is accurately controlled by computer i.e.
It can.
Because the forming curvature of siding is different, required pre-bending amount and pre-bending curvature are different.Therefore pre stress shot peen fixture
Must have an ability of the pre-bending to different curvature siding, i.e., so-called versatility or " flexibility ".The aircraft that multiple spot actively loads
" flexibility " of siding pre stress shot peen tooling by high degree digital control multiple spot punch systems, can be along the mobile pressing clip of " T " slot and punching
Head system, and realized jointly along the stringer that linear guide moves.Multiple spot punch systems advantage the most outstanding is: shot-peening
Before, the arbitrary Prebending type face of curvature can accurately be constituted by the multiple punch of numerical control, Prebending type face can be calculated by the excessively curved coefficient of siding
It obtains, therefore, the pre-bending realized to arbitrarily complicated curvature siding part, and multiple forces can be automated by this shot-peening tooling
Siding stress discretization is avoided local distortion caused by single-point or 3 points of press-bendings by point, and prestressing force suffered by siding more evenly, guarantees
Prestressing force effect；During shot-peening, as pre-bending amount it is bigger than normal or less than normal caused by stress error can be by adjusting numerical control in real time
Height of punch is compensated, and improves contour peening precision；After shot-peening, numerical control formed punch constituent part appearance curved surface, the tooling may be used also
As the form error for examining pattern detection curvature panel.
A kind of aircraft target ship pre stress shot peen method that multiple spot actively loads, method includes the following steps:
Step 1: Prebending type face is determined by formula calculating first, Prebending type face is constituted by numerical control formed punch 28 before shot-peening,
Multiple formed punches 28 be arranged in " face " realize it is prestressed application to guarantee that prestressing force is uniform, the calculating step in Prebending type face are as follows:
1, datum level and datum mark are determined；Datum level: the chordwise section at 12 both ends of wall panel parts, datum mark (y0,z0): wall
The intersection point of piece a bus and datum level appearance curve of plate；
2, the appearance curve on calculating benchmark face；External Shape curve is divided into many sections, every segmental arc is calculated as follows
Chord length L and slope K:
kn-1=(zn-zn-1)/(yn-yn-1)
Then, then calculate pre-bending curve take up an official post meaning point coordinate value yn' and zn', to constitute pre-bending curve,
yn'=yn-1'+Ln-1×cos(αn-1-γ0-γ1-…-γn-1)
zn'=zn-1'+Ln-1×sin(αn-1-γ0-γ1-…-γn-1)
Wherein, yn、yn-1And zn、zn-1For the tangential and high to coordinate value of the every segmental arc two-end-point of External Shape curve；yn'、
yn-1' and zn'、zn-1' for the coordinate value of arbitrary point on pre-bending appearance curve；αn-1=arctgKn-1, γn-1=(C-1) θn-1, θn-1
=arctg (kn-2-kn-1)/(1+Kn-2×Kn-1), C --- excessively curved coefficient, value is External Shape radius of curvature and pre-bending radius
Ratio.
3, Prebending type face is constructed；After calculating the appearance curve on two datum levels using identical excessively curved coefficient, to two
Corresponding points (on same bus) on appearance curve even straight line, that is, may make up Prebending type face.
Step 2: during shot-peening, since practical pre-bending amount and shot-peening parameter are difficult to accurately formulate, because pre-bending amount is bigger than normal or
Stress error caused by less than normal and shot-peening parameter inexactness can be mended by the method for adjusting 28 height of formed punch in real time
It repays, moment of flexure is bigger than normal, reduces by 28 height of formed punch, and moment of flexure is less than normal, increases 28 height of formed punch.
Step 3: formed punch 28 may be constructed part type face as the forming mistake for examining pattern detection curvature panel after shot-peening
Difference.
Claims (2)
1. the aircraft target ship pre stress shot peen tooling that a kind of multiple spot actively loads, which is characterized in that the tooling includes connector sliding block
(3), pressing clip (5), multiple spot punch systems (7), rack and pinion drive mechanism, two rigid frames (1), two guide rail bases
(4), two linear guide (2) He Duogen stringers (6)；Guide rail base (4) described in two is fixed on two rigid frames (1)
On；There are two linear guide (2) for installation on guide rail base (4) described in two；The both ends of stringer (6) described in more respectively with
Connector sliding block (3) connection, and wherein one end is equipped with locking mechanism (9), and the other end is equipped with rack and pinion drive mechanism；Institute
The connector sliding block (3) stated is slidably matched with linear guide (2)；On the stringer (6) by third nut (24) be fixed with it is more
A multiple spot punch systems (7)；Pressing clip (5) are respectively and fixedly provided with above described stringer (6) both ends；Guide rail base described in one
(4) it is provided on guide rail scale (11), the side of the stringer (6) is provided with stringer scale (10)；The stringer (6)
Two sides are provided with the first T-slot (8) through stringer (6), and centre is provided with the second T-slot (21)；In second T-slot (21)
Equipped with more sets multiple spot punch systems (7)；The multiple spot punch systems (7) include shell (25), control circuit (26), adjust and answer
With motor (27), formed punch (28)；The output end of the adjustment application motor (27) with internal thread formed punch (28) screw thread
Connection；The second nut (29) of fixed punch head (28) is provided with outside the shell (25)；The adjustment application motor (27)
It is connected with control circuit (26)；The control circuit (26) is connected by repeater with computer；First T-type described in two
It is provided with pressing clip (5) in slot (8), the pressing clip (5) includes that pressing clip rack (16), adjusting rod (17) and compression clamp
Head (18)；The both ends of the pressing clip rack (16) are arranged in the first T-slot (8) by the first bolt (14), described
It is provided with above first bolt (14) the first nut (19), is equipped between first bolt (14) and the first nut (19)
Gasket (20)；The adjusting rod (17) is fixed on one end of pressing clip rack (16), and lower end is fixed with pressing clip pressure head
(18)；Wall panel parts (12) are placed between the pressing clip pressure head (18) and formed punch (28)；The wall panel parts (12) and
There is the elastic cushion (13) of polyurethane between formed punch (28)；The rack and pinion drive mechanism includes rack gear (22) and gear
(23)；The gear (23) is connect by gear shaft with stringer (6)；The rack gear (22) is fixed on guide rail base (4)
And it is meshed with gear (23).
2. a kind of aircraft target ship pre stress shot peen method that multiple spot actively loads, which is characterized in that method includes the following steps:
Step 1: determining Prebending type face before shot-peening by formula calculating first, constituting Prebending type face, Duo Gechong by formed punch (28)
Head is arranged in " face " and realizes prestressed application to guarantee that prestressing force is uniform；
Step 2: during shot-peening, since practical pre-bending amount and shot-peening parameter are difficult to accurately formulate, because pre-bending amount is bigger than normal or less than normal
And stress error caused by the inexactness of shot-peening parameter can be compensated by the method for adjusting formed punch (28) height in real time,
Moment of flexure is bigger than normal, reduces formed punch (28) height, and moment of flexure is less than normal, increases formed punch (28) height；
Step 3: formed punch (28) may be constructed part type face as the form error for examining pattern detection curvature panel after shot-peening.
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| CN108838516A (en) * | 2018-07-09 | 2018-11-20 | 吉林大学 | A kind of prestressing force laser peening flexible fixture that multiple spot actively loads |
| CN110110400B (en) * | 2019-04-19 | 2022-05-10 | 成都飞机工业（集团）有限责任公司 | Calculation method for shot blasting deformation of large-size arc-shaped part |
| CN111112395B (en) * | 2020-01-03 | 2022-03-04 | 中国航空制造技术研究院 | Pre-bending tool for obtaining double-curvature wall plate and shot blasting forming process |
| 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 |
| CN114921627B (en) * | 2022-06-01 | 2023-10-31 | 沈阳飞机工业（集团）有限公司 | Aircraft support arm part shot blasting reverse deformation device and deformation control method using same |
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| CN102101363A (en) * | 2010-12-24 | 2011-06-22 | 哈尔滨工业大学（威海） | Multi-point forming device for plate |
| KR101170628B1 (en) * | 2012-02-29 | 2012-08-02 | 이경표 | A prestressed steel plate and the construction method for a steel composite slab bridge using thereof |
| CN103433854A (en) * | 2013-08-29 | 2013-12-11 | 西北工业大学 | Digital shot peen forming method for integral wallboard |
| CN103753454A (en) * | 2014-02-11 | 2014-04-30 | 中航飞机股份有限公司西安飞机分公司 | Pneumatic combined flexible prestress clamp and control system thereof |
| CN104588441A (en) * | 2014-10-15 | 2015-05-06 | 中航飞机股份有限公司西安飞机分公司 | Wallboard pre-stressed shot blasting sizing method and pre-bending fixture |
| CN105690290A (en) * | 2014-11-27 | 2016-06-22 | 西安众智惠泽光电科技有限公司 | Self-locking type rapid compressing clamp |
| CN104646475A (en) * | 2015-03-05 | 2015-05-27 | 吉林大学 | Multi-point forming method for whole aluminum alloy wall plate of aircraft |
| CN106180247A (en) * | 2016-08-04 | 2016-12-07 | 吉林大学 | A kind of high muscle aluminium alloy wallboard manufacture method |
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