CN104778305A - Part bend springback compensation method - Google Patents
Part bend springback compensation method Download PDFInfo
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- CN104778305A CN104778305A CN201510104111.1A CN201510104111A CN104778305A CN 104778305 A CN104778305 A CN 104778305A CN 201510104111 A CN201510104111 A CN 201510104111A CN 104778305 A CN104778305 A CN 104778305A
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- crimp
- reference face
- design
- springback
- compensation method
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Abstract
The invention relates to a part bend springback compensation method. The part bend springback compensation method is characterized in that by taking springback compensation into consideration, a bend is reconstructed on the basis of a bend design reference surface, a die design reference surface is created, the part bend springback compensation problem is studied on the basis of the geometric method, and a compensated part bend reference surface is rapidly created by the method of dispersing shape intersection lines, compensating a bend section line and shifting a compensating surface. A compensation result can effectively meet practical engineering applications, and moreover, the compensation process is rapid and simple.
Description
Technical field
The invention belongs to manufacturing technology field, be specifically related to a kind of part crimp springback compensation method.
Background technology
Resilience is common after part forming but masty problem.In sheet metal forming process, resilience is a kind of common phenomenon, more obvious U-shaped middle resilience especially.The net shape of stamping parts depends on the springback capacity after shaping, therefore the existence of rebound phenomenon is to shape, the dimensional accuracy important of part, brings difficulty also to follow-up assembly work, not only reduces production efficiency, and increase production cost.In composite material solidification forming process, due to the distribution of material gradient factor that cure shrinkage effect and the technological process of matrix cause, inside configuration inevitably will produce unrelieved stress, and then cause composite material structural member to produce resilience after demoulding, make the design shape of component free shape at room temperature and expection there is certain difference, result adds manufacturing cost and assembly difficulty.Trace it to its cause, rebound phenomenon is actually after external applied load is removed, part generation elasticity is recovered and is produced, the elasticity of unloading is recovered to be one and is sought internal stress from the process balanced each other, the elasticity produced is recovered to cause part geometry shape generation resilience, when part reaches internal stress in time balancing each other, elasticity rejuvenation terminates.
Resilience is a kind of prevailing quality defect existed in part forming process, and springback compensation is the main path addressed this problem, present stage effective springback compensation method have a variety of.In periodical literature, the people such as Yang Yimei propose a kind of part crimp springback compensation method, and by carrying out discrete to part crimp line, working knowledge storehouse compensates and prediction springback capacity, finally set up part process model, but compensation process is more.Carbon fiber and glass fibre, for broad-band radar absorbers RAS, mix by the people such as Woo-Kyun Jung, study the resilience problem of component after this kind of part curing molding, by prediction member springs back amount, and react in part tooling, reach the object of compensation.The people such as Woo-Kyun Jung method by experiment obtains the springback capacity after forming parts, and compensates part tooling.The factors such as the people such as G.Fernlund technique study solidification temperature by experiment, cooling rate, solidifying pressure, laying quantity, mold materials are on the impact of part resilience.Chen Xiao waits people quietly and studies the thermo parameters method of composite element in autoclave molding process, by the finite element prediction be out of shape composite element, proposes the profile backoff algorithm based on column joints deformation.The people such as Jia Lijie start with the subscale test part of typical C shape structure, adopt laser tracker to detect distortion, simultaneously by analogue simulation means, predict that it is out of shape, and release the fitting formula of C shape construction rebound distortion according to test figure and analog result.The people such as Yang Xining, on the basis of traditional moulds method for designing, utilize the thermal expansion deformation amount of finite element software analog computation mould, compensate at the heat distortion amount of die design stage to mould.The people such as Xu Jing are by Finite Element Method, and the distortion of prediction composite element, proposes die face backoff algorithm.Above-mentioned research is substantially all the prediction carrying out springback capacity based on experiment or finite element analysis software, then revises mould, reaches the object of compensation, but springback angle is predicted and crimp compensation process is consuming time longer.
Summary of the invention
The technical matters solved
In order to avoid the deficiencies in the prior art part, the present invention proposes a kind of part crimp springback compensation method, improves springback compensation efficiency.
Technical scheme
A kind of part crimp springback compensation method, is characterized in that step is as follows:
Step 1: calculate part crimp design reference face
with part web inside surface S
wintersecting lens, using intersecting lens as crimp profile cross spider
i is the number in part crimp design reference face;
Step 2: along segmentation crimp design reference face, Bending edge height direction
obtain crimp segmentation reference surface
crimp is split reference surface
direction, distalmost end boundary line extension obtains crimp extended reference face vertically
step is as follows:
Step a: get web inside surface S
wplace plane F
w, by plane F
walong Bending edge height direction translation h, obtain translated plane F
wD; Translated plane F
wDwith crimp design reference face
intersect, obtain intersection
with intersection
with profile intersection
segmentation crimp design reference face
part between two intersections is crimp segmentation reference surface
Step b: crimp segmentation reference surface
axial distalmost end boundary line is respectively
with
crimp is split reference surface
along boundary line
be extended down to boundary line outward
obtain crimp extended reference face
expansion profile cross spider is
Step 3: to expansion profile cross spider
carry out equidistantly discrete, expansion profile cross spider
arc length is l
i, form discrete point
j=1,2 ..., J; Wherein:
Step 4: cross discrete point
make expansion profile cross spider
normal plane
normal plane
with crimp extended reference face
intersect, obtain crimp section line
by crimp section line
around expansion profile cross spider
to crimp bending direction
rotate a springback angle φ, the crimp section line after being compensated
Step 5: the crimp section line after multi-section surface fitting compensates
obtain mold reference face
mold reference face
along spares bend direction
skew l, obtains mould deflection reference face
Step 6: mould deflection reference face
with part web inside surface S
wcorners, radius of corner R
0equal with Element Design model radius of corner R, obtain Design of Dies reference surface
according to this Design of Dies reference surface
design elements mould.
The maximum Bending edge height of the translation distance h=+20mm of described step a.
The extension distance d=10mm of described step b.
The discrete spacing of described step 3 is d
i=1mm ~ 3mm.
The springback angle φ of described step 4 adopts Finite Element Method calculating to determine.
The skew of described step 5
α
0=φ+α, R
0=R; Wherein: α is Element Design model crimp angle, α
0for die face oblique angle, R is Element Design model radius of corner, R
0for superplastic.
Beneficial effect
A kind of part crimp springback compensation method that the present invention proposes, based on the technique study part crimp springback compensation problem of geometry, by discrete profile cross spider, compensates crimp section line, and the method in migration face is set up part fast and compensated rear crimp reference surface.Compensation result well can not only meet practical implementation, and compensation process is fast and convenient.
Accompanying drawing explanation
Fig. 1 is example part.
Fig. 2 is example part crimp design reference face.
Fig. 3 is the intersection of web inside surface and Element Design reference surface.
Fig. 4 is that intersection intercepting design reference face obtains crimp segmentation reference surface.
Fig. 5 is that crimp segmentation reference surface extension obtains crimp extended reference face.
Fig. 6 is expansion profile cross spider discrete results
Fig. 7 is crimp extended reference face discrete results
Fig. 8 is the crimp section line after compensating
Fig. 9 is the section line Local map after compensating
Figure 10 is mold reference face
Figure 11 is Design of Dies reference surface
Figure 12 is Design of Dies reference surface section line Local map
Embodiment
Now in conjunction with the embodiments, the invention will be further described for accompanying drawing:
For Fig. 1 example part, this part is made up of planar webs and two crimps.By reference to the accompanying drawings, the specific implementation process of this example part crimp springback compensation method is described.
1. example part has 2 crimp design reference faces
with
crimp design reference face
with part web inside surface S
wintersection is
i.e. crimp profile cross spider, as shown in Figure 3; By the plane F at web inside surface place
walong Bending edge height direction translation h=27mm (Bending edge height)+20mm=47mm, obtain translated plane F
wD, translated plane F
wDwith crimp design reference face
intersection is
intersection
with
intercept crimp design reference face
obtain crimp segmentation reference surface
as shown in Figure 4; Crimp is split reference surface
along boundary line
be extended down to boundary line outward
extension distance d=10mm, obtains crimp extended reference face
expansion profile cross spider is
as shown in Figure 5.
2. pair expansion profile cross spider
carry out equidistantly discrete, expansion profile cross spider
arc length is 282.612mm, and discrete spacing is 1mm, forms discrete point
discrete results as shown in Figure 6; Cross discrete point
make expansion profile cross spider
normal plane
normal plane
with crimp extended reference face
intersect, obtain crimp section line
as shown in Figure 7; By crimp section line
around expansion profile cross spider
to crimp bending direction
rotate springback angle φ=5 °, the crimp section line after being compensated
as shown in Fig. 8 Fig. 9.
3. the crimp section line after matching compensation
obtain mold reference face
as shown in Figure 10; Mold reference face
along spares bend direction
skew
wherein R
0=5.5mm, α=87 °, obtain mould deflection reference face
mould deflection reference face
with part web inside surface S
wcorners, obtains Design of Dies reference surface
as shown in Figure 11 Figure 12.
Claims (6)
1. a part crimp springback compensation method, is characterized in that step is as follows:
Step 1: calculate part crimp design reference face
i=1,2 ..., I and part web inside surface S
wintersecting lens, using intersecting lens as crimp profile cross spider
i is the number in part crimp design reference face;
Step 2: along segmentation crimp design reference face, Bending edge height direction
obtain crimp segmentation reference surface
crimp is split reference surface
direction, distalmost end boundary line extension obtains crimp extended reference face vertically
step is as follows:
Step a: get web inside surface S
wplace plane F
w, by plane F
walong Bending edge height direction translation h, obtain translated plane F
wD; Translated plane F
wDwith crimp design reference face
intersect, obtain intersection
with intersection
with profile intersection
segmentation crimp design reference face
part between two intersections is crimp segmentation reference surface
Step b: crimp segmentation reference surface
axial distalmost end boundary line is respectively
with
crimp is split reference surface
along boundary line
be extended down to boundary line outward
obtain crimp extended reference face
expansion profile cross spider is
Step 3: to expansion profile cross spider
carry out equidistantly discrete, expansion profile cross spider
arc length is l
i, form discrete point
j=1,2 ..., J; Wherein:
Step 4: cross discrete point
make expansion profile cross spider
normal plane
normal plane
with crimp extended reference face
intersect, obtain crimp section line
by crimp section line
around expansion profile cross spider
to crimp bending direction
rotate a springback angle φ, the crimp section line after being compensated
Step 5: the crimp section line after multi-section surface fitting compensates
obtain mold reference face
mold reference face
along spares bend direction
skew l, obtains mould deflection reference face
Step 6: mould deflection reference face
with part web inside surface S
wcorners, radius of corner R
0equal with Element Design model radius of corner R, obtain Design of Dies reference surface
according to this Design of Dies reference surface
design elements mould.
2. part crimp springback compensation method according to claim 1, is characterized in that: the maximum Bending edge height of the translation distance h=+20mm of described step a.
3. part crimp springback compensation method according to claim 1, is characterized in that: the extension distance d=10mm of described step b.
4. part crimp springback compensation method according to claim 1, is characterized in that: the discrete spacing of described step 3 is d
i=1mm ~ 3mm.
5. part crimp springback compensation method according to claim 1, is characterized in that: the springback angle φ of described step 4 adopts Finite Element Method to calculate to determine.
6. part crimp springback compensation method according to claim 1, is characterized in that: the skew of described step 5
α
0=φ+α, R
0=R; Wherein: α is Element Design model crimp angle, α
0for die face oblique angle, R is Element Design model radius of corner, R
0for superplastic.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510104111.1A CN104778305A (en) | 2015-03-10 | 2015-03-10 | Part bend springback compensation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510104111.1A CN104778305A (en) | 2015-03-10 | 2015-03-10 | Part bend springback compensation method |
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| Publication Number | Publication Date |
|---|---|
| CN104778305A true CN104778305A (en) | 2015-07-15 |
Family
ID=53619766
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510104111.1A Pending CN104778305A (en) | 2015-03-10 | 2015-03-10 | Part bend springback compensation method |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105183970A (en) * | 2015-08-31 | 2015-12-23 | 西北工业大学 | Springback compensation method for recess-free continuous bending edge in frame and rib part |
| CN113127969A (en) * | 2021-03-24 | 2021-07-16 | 东风柳州汽车有限公司 | Automobile damping plate simulation modeling method, device, equipment and storage medium |
| CN113221398A (en) * | 2021-03-31 | 2021-08-06 | 成都飞机工业（集团）有限责任公司 | Method for predicting L-shaped composite material part curing deformation rebound angle |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7117065B1 (en) * | 2006-03-31 | 2006-10-03 | Ford Global Technologies, Llc | Method for modifying a stamping die to compensate for springback |
| CN101546349A (en) * | 2009-05-06 | 2009-09-30 | 湖南大学 | A method to generate a springback compensation surface based on mesh mapping of the edge lines or section lines of curved surfaces |
| CN102982200A (en) * | 2012-11-06 | 2013-03-20 | 西北工业大学 | Design method of airplane frame and rib type sheet metal part processing model |
| CN104392052A (en) * | 2014-11-29 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | S-section sag-free aircraft frame and rib sheet metal part springback compensation calculation method |
-
2015
- 2015-03-10 CN CN201510104111.1A patent/CN104778305A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7117065B1 (en) * | 2006-03-31 | 2006-10-03 | Ford Global Technologies, Llc | Method for modifying a stamping die to compensate for springback |
| CN101546349A (en) * | 2009-05-06 | 2009-09-30 | 湖南大学 | A method to generate a springback compensation surface based on mesh mapping of the edge lines or section lines of curved surfaces |
| CN102982200A (en) * | 2012-11-06 | 2013-03-20 | 西北工业大学 | Design method of airplane frame and rib type sheet metal part processing model |
| CN104392052A (en) * | 2014-11-29 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | S-section sag-free aircraft frame and rib sheet metal part springback compensation calculation method |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105183970A (en) * | 2015-08-31 | 2015-12-23 | 西北工业大学 | Springback compensation method for recess-free continuous bending edge in frame and rib part |
| CN105183970B (en) * | 2015-08-31 | 2018-06-29 | 西北工业大学 | A kind of springback compensation method without the continuous crimp that sink in frame rib part |
| CN113127969A (en) * | 2021-03-24 | 2021-07-16 | 东风柳州汽车有限公司 | Automobile damping plate simulation modeling method, device, equipment and storage medium |
| CN113221398A (en) * | 2021-03-31 | 2021-08-06 | 成都飞机工业（集团）有限责任公司 | Method for predicting L-shaped composite material part curing deformation rebound angle |
| CN113221398B (en) * | 2021-03-31 | 2022-08-12 | 成都飞机工业（集团）有限责任公司 | Method for predicting L-shaped composite material part curing deformation rebound angle |
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Application publication date: 20150715 |