CN104722618A - Stretch bending forming method for Z-shaped proximate matters of airplane at a time - Google Patents
Stretch bending forming method for Z-shaped proximate matters of airplane at a time Download PDFInfo
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- CN104722618A CN104722618A CN201510098013.1A CN201510098013A CN104722618A CN 104722618 A CN104722618 A CN 104722618A CN 201510098013 A CN201510098013 A CN 201510098013A CN 104722618 A CN104722618 A CN 104722618A
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- 238000005452 bending Methods 0.000 title claims abstract description 82
- 238000000034 method Methods 0.000 title claims abstract description 55
- 239000000463 material Substances 0.000 claims abstract description 27
- 238000004519 manufacturing process Methods 0.000 claims abstract description 15
- 238000004088 simulation Methods 0.000 claims abstract description 8
- 238000004364 calculation method Methods 0.000 claims abstract description 6
- 238000010438 heat treatment Methods 0.000 claims abstract description 6
- 230000008569 process Effects 0.000 claims description 28
- 230000008901 benefit Effects 0.000 claims description 10
- 238000003462 Bender reaction Methods 0.000 claims description 9
- 238000001125 extrusion Methods 0.000 claims description 5
- 238000007493 shaping process Methods 0.000 claims description 5
- 238000012512 characterization method Methods 0.000 claims description 3
- 229910052751 metal Inorganic materials 0.000 abstract description 3
- 239000002184 metal Substances 0.000 abstract description 3
- 238000010791 quenching Methods 0.000 abstract description 3
- 230000000171 quenching effect Effects 0.000 abstract description 3
- 238000005259 measurement Methods 0.000 abstract 1
- 238000004458 analytical method Methods 0.000 description 8
- 238000009434 installation Methods 0.000 description 5
- 230000007935 neutral effect Effects 0.000 description 5
- 238000006073 displacement reaction Methods 0.000 description 4
- 238000009826 distribution Methods 0.000 description 4
- 229910001250 2024 aluminium alloy Inorganic materials 0.000 description 3
- 230000002153 concerted effect Effects 0.000 description 3
- VEXZGXHMUGYJMC-UHFFFAOYSA-N Hydrochloric acid Chemical compound Cl VEXZGXHMUGYJMC-UHFFFAOYSA-N 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000005489 elastic deformation Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229910001148 Al-Li alloy Inorganic materials 0.000 description 1
- 241001212149 Cathetus Species 0.000 description 1
- 208000034189 Sclerosis Diseases 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- FCVHBUFELUXTLR-UHFFFAOYSA-N [Li].[AlH3] Chemical compound [Li].[AlH3] FCVHBUFELUXTLR-UHFFFAOYSA-N 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 239000004744 fabric Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000001989 lithium alloy Substances 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
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- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D7/00—Bending rods, profiles, or tubes
- B21D7/02—Bending rods, profiles, or tubes over a stationary forming member; by use of a swinging forming member or abutment
- B21D7/022—Bending rods, profiles, or tubes over a stationary forming member; by use of a swinging forming member or abutment over a stationary forming member only
- B21D7/0225—Bending rods, profiles, or tubes over a stationary forming member; by use of a swinging forming member or abutment over a stationary forming member only using pulling members
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D37/00—Tools as parts of machines covered by this subclass
- B21D37/10—Die sets; Pillar guides
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D—WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS OR PROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21D7/00—Bending rods, profiles, or tubes
- B21D7/12—Bending rods, profiles, or tubes with programme control
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Bending Of Plates, Rods, And Pipes (AREA)
Abstract
The invention relates to the field of airplane metal proximate matter stretch bending forming, in particular to a stretch bending forming method for Z-shaped proximate matters of an airplane at a time. The method includes the following steps that 1 Z-shaped section proximate matter stretch bending resilience value is pre-measured by an analytic calculation or a numerical simulation method, stretch bending mould resilience compensation design is conducted according to a pre-measured result, and stretch bending mould making is complete; 2 heat treatment is conducted on the Z-shaped section proximate matter to be formed, when a new quenching state is achieved, a part is taken out to wait to be formed; 3 parameters of a stretch bender are set; 4 stretch bending forming is conducted at a time, prestretching is conducted, stretch bending is conducted, stretching is compensated, and unloading is conducted; 5 accuracy measurement is conducted, after technological parameters are adjusted, the step 4 is repeated until an desired appearance of the part is obtained. By means of the method, the forming quality of the part is improved, the repairing and correcting amount which is conducted by handwork is reduced, the forming time is effectively saved, product manufacturing cycle is shortened, and the cost is lowered. A mould is simple in structure and easy to manufacture, materials are convenient to draw, and the manufacturing cost is low.
Description
Technical field
The present invention relates to aircraft shape stretch wrap forming field, be specifically related to an a kind of stretch wrap forming method for aircraft Z-type material.
Background technology
Stretch bending refers to workpiece in addition tangential pulling force while bending, changes a kind of shape bending technique of the stress state in workpiece interface, has following process characteristic relative to other bending process: can the baroque section bar part of formingspace; The shape bending part that the yield tensile ratio that can be shaped is large; There is the comprehensive shaping characteristic that different process method combines; Bending precision is high, and resilience is little; There is flexible manufacturing feature.
Stretch bending is usually used in be shaped various large-scale, complex section, asymmetric, the three-dimensional section bar part of variable curvature, thus, is widely used in the manufacturing industry such as Aero-Space, automobile, building, bridge, elevator and train.The extrudate that long purlin equidimension is large, relative bending radius is large, the curved material bool of plate of section and engine nacelle before and after edge strip on aircraft, fuselage, the stressed part of this kind of part composition airframe, directly have influence on the aerodynamic shape of aircraft, thus form accuracy requires very high, generally adopts the method for stretch wrap forming to manufacture this kind of part in production.The outer metal decorative strip of vehicle body etc. of the outer metal decorative strip of body of a motor car and sash, flowing water eaves and bumper and medium-to-high grade car all adopts stretch bending process to be shaped.
C919 aircraft architrave class part is shaped by Z-section stretch bending, due to the impact by cross sectional shape, bending radius, material property etc., general secondary stretch wrap forming process medium section cross section distortion, narrowed cross section and seriously thinning, cause forming quality not reach requirement; Part is variable curvature profile, springback control difficulty, and after being shaped, manual school shape amount is large.
Summary of the invention
The object of the invention is to solve the problem, an a kind of stretch wrap forming method for aircraft Z-type material is provided.
In order to realize object of the present invention, the technical solution used in the present invention is:
For a stretch wrap forming method of aircraft Z-type material, its characterization step is as follows:
The first step, adopts analytical Calculation or method for numerical simulation prediction Z-section Stretch Bending of Extrusions amount, carries out the design of stretch bending mold springback compensation, and complete stretch bending mold manufacture according to predicting the outcome;
Second step, the Z-section section bar treating shaping is heat-treated, after reaching new as-quenched, take out part, waits to be formed;
3rd step, setting stretch benders parameter, described stretch benders setting parameter is: swing arm speed is 1.3 degree/second, and stretching cylinder speed is 0.4inch/s; Clinging force is 3 tons, and prestretched amount is 9mm, and benefit amount of tension is 60mm, remains set stretch benders parameter in stretch bending process;
4th step, a stretch wrap forming, prestretched, stretch bending, mends and stretches, unloading, and the part after the heat treatment of second step needs to complete stretch wrap forming in 30min, otherwise it is medium to be formed to need to be positioned over refrigerator;
5th step, precision measure also repeats FOUR EASY STEPS after adjusting process parameter, until obtain desirable External Shape.
A kind of stretch bending mold of said method, comprise overhead gage, pattern, lower baffle plate, pattern is between overhead gage and lower baffle plate, the upper surface of pattern and the lower surface of overhead gage are fitted, the lower surface of pattern and the upper surface of lower baffle plate are fitted, described pattern is similar with lower baffle plate structure, by the connection of multiple fastening bolt, profile piece is compressed between overhead gage and pattern, in addition at overhead gage, also by multiple fastening bolt described overhead gage, pattern and lower baffle plate be connected between pattern and lower baffle plate and tighten up.
Pattern is also respectively equipped with some lightening cores, locating hole, hole for hoist.
Beneficial effect of the present invention is: improve part forming quality comprehensively, significantly reduces manual school of repairing and measures, effectively can save curring time, shorten the product manufacturing cycle, reduce costs, the mould structure in the present invention is simply easy to manufacture, draw materials easy to use, low cost of manufacture.
Accompanying drawing explanation
Fig. 1 is the inventive method stretch bending mold structural upright schematic diagram used,
Fig. 2 is the inventive method stretch bending mold structural front view used,
Fig. 3 is the A-A sectional view of Fig. 2,
Fig. 4 is typical section bar stretch wrap forming principle process schematic,
Fig. 5 is critical cross-section stress distribution,
Fig. 6 is that before and after shape bending resilience, physical dimension compares,
Fig. 7 is stretch wrap forming method flow diagram of the present invention.
Detailed description of the invention
Below in conjunction with drawings and Examples, the present invention is further described:
Embodiment: see Fig. 1 to Fig. 7.
For a stretch wrap forming method of aircraft Z-type material, its characterization step is as follows:
The first step, springback compensation.Extract section bar cross sectional shape, the assembly relation of section bar and mould and relative position relation, External Shape parameter and mould guide curvature of a curve and length characteristic, single tension strain curve data of material parameter and material, or matching Parameters of constitutive model, hardening model parameter, use stretch bending process parameter to comprise the prestretched amount of stretch bending process, benefit amount of tension and molding condition comprise friction condition, as coefficient of friction, forming speed condition, loading environment, load mode, after boundary condition, adopt analytical Calculation or method for numerical simulation prediction Z-section Stretch Bending of Extrusions amount, namely the departure under corresponding stretch wrap forming condition before and after the resilience of part guide line, departure according to predicting the outcome oppositely is revised, iterative computation, realize the design of stretch bending mold springback compensation and namely generate the stretch bending mold profile after springback compensation according to revised guide line, and increase the technology characteristics of conventional stretch bending mold, as block design, servicing unit, obtain stretch bending mould digital-to-analogue, and complete stretch bending mold manufacture.
Second step, section bar heat treatment.The Z-section section bar that provides is 2024 aluminium alloy O state extrudates, the requirement of formation of parts is T state, therefore, need to heat-treat quenching for W state extrudate to 2024 aluminium alloy O state extrudates, i.e. new as-quenched, then stretch wrap forming, timeliness obtains T state extrudate again, 2024 aluminum alloy heat process adopt hydrochloric acid pond carry out being heated to 493 DEG C and be incubated 30 minutes, then within 3 second time, be transferred to rapidly water-cooled pond and obtain W state, the advantage that W state carries out stretch wrap forming is, the material softer of W state, plastic force is little, resilience is little, if arrive T state stretch wrap forming again, resilience is larger, wayward.
3rd step, installation mold also sets stretch benders parameter.Mould is installed to be needed to require correctly to place die location according to lathe handbook, and regulate the reasonable clearance of mould active position, mold height regulates and stretch bending chuck matched, and checks that mould installs reasonability and lathe crystallized ability, ensures device security.Described stretch benders parameter (adopt when parameters and the first step springback Prediction technological parameter consistent) is: swing arm speed is 1.3 degree/second, and stretching cylinder speed is 0.4inch/s; Clinging force is 3 tons, prestretched amount is 9mm, benefit amount of tension is 60mm, and completes the data code collection (coordination for the elongation and pivoted arm amount of spin that automatically complete stretch bending process stretching cylinder) of stretch bending machine, remains set stretch benders parameter.
4th step, a stretch wrap forming.By extrudate after parameters tension quenching, eliminate the distortion that heat treatment causes, prestretched, by parameters stretching section bar, wrinkling for eliminating stretch bending process section bar internal layer, stretch bending, notices that workpiece pastes mould situation, original formation needs suitable amendment beaming limit arranges and ensures that part pastes mould completely, mend and stretch, the axial tension that lathe makes section bar reach enough according to the benefit amount of tension arranged, reach the effect reducing stretch bending resilience, shaping terminates rear unloading stretch bending part, from stretch bending clamp, take out part.In addition, the part after heat treatment needs to complete stretch wrap forming in 30min, otherwise it is medium to be formed to need to be positioned over refrigerator.
5th step, precision measure also carries out FOUR EASY STEPS after adjusting process parameter, until obtain desirable External Shape.Because stretch wrap forming technological parameter is more, springback capacity, by multiple parameter influence, when part does not reach manufacture requirements, suitably can increase the benefit amount of drawing size, even revise the numerical control code of lathe, until forming quality meets the demands.
For a stretch bending mold for said method, comprise overhead gage 2, pattern 1, lower baffle plate 3, described pattern 1 and lower baffle plate 3 semicircular in shape, overhead gage 2 is in circular arc, material is No. 45 steel, and pattern 1 is similar with lower baffle plate 3 structure, and the outer profile size of lower baffle plate 3 is greater than the outer profile size of pattern 1.Along the straight outline of pattern 1 to bias internal 30mm, the shoulder hole 4 of distribution 8 installation fastening bolts 9, for fastening pattern 1 and lower baffle plate 3.Along the straight outline of pattern 1 to bias internal 131mm, distribute 4 large lightening cores 5, for alleviating mold integral weight.Along the straight outline of pattern 1 to bias internal 150mm, distribute 2 locating holes 6, plays the role of positioning when mould is installed.Distribute in the both sides of the symmetrical center line of pattern 1 four holes for hoist 7, for the carrying of mold integral after installation suspension ring, at symmetrical center line punishment cloth lightening core 5 of pattern 1.The shoulder hole 4 of the inside distribution of offsets of the circular-arc-shaped exterior contour along pattern 1 10 installation fastening bolts 9, for the pattern 1 after fastening installation workpiece 8 and overhead gage 2.Other circular holes on pattern 1 are fabrication hole.
Being described as follows of Z-section Stretch Bending of Extrusions amount is predicted about analytical Calculation or method for numerical simulation:
1, analytical Calculation process: stretch bending refers to workpiece in addition tangential pulling force while bending, change a kind of shape bending technique of the stress state in workpiece interface, namely certain axial tension is kept in section bar prestretched to load bending during Materials Yield Limit, the BENDING PROCESS be shaped in the type groove making it press-in die.Its typical process process comprises prestretched, bending and final (benefit is drawn) three phases that stretches, as shown in Figure 4.
Stretch bending and common bending difference are: common bending time neutral line substantially constant, and during stretch bending section bar neutral line in move, move on to the inner side of section bar even or shift out inner surface.
A-7B stretch bending machine adopts stay wire sensor record mold feature profile, and numerical control program determines the strain neutral layer position of stretch bending while producing.Generally, mold feature profile is mould innermost layer guide line, i.e. section bar cross section innermost layer.Assuming that the innermost layer of stretch wrap forming process cathetus section and bending section critical cross-section is neutral line (also can suppose that intermediate cross-section is critical cross-section), in conjunction with aluminium lithium alloy material mechanical performance feature, critical cross-section stress distribution as shown in Figure 5 can be obtained.
Critical cross-section innermost layer radius is Rn, strain stress n
ε
n＝0
The strain stress of critical cross-section optional position can be approximately
R is any position, cross section radius.Substitute into the ture stress-strain relational expression of material, the stress σ size of optional position can be calculated.
σ＝Eε,ε≤ε
s
σ＝Kε
n,ε≥ε
s
The P0 that makes a concerted effort of integral and calculating critical cross-section is
P
0＝∫σ
0dA
A is area of section.The P θ size of making a concerted effort of stretch bending section bar arbitrary section can be calculated
P
θ＝P
0e
-μθ
The neutral line place radius of arbitrary section is R'n, assuming that
R'
n＝R
n+kH
In formula, H is depth of section, and k is transport coefficient (between-1 ~ 1), and integrable arbitrary section makes a concerted effort to be
P
θ ＝∫σ
θdA
Adopt dichotomy, k value size can be solved, thus obtain the ess-strain value in the whole each cross section of stretch bending section bar.
Section bar, in BENDING PROCESS, not only there is plastic deformation in its cross section, but also there is elastic deformation area, in addition, in plastically deforming area material plastic deformation in also contain elastic deformation.After axial tension and moment of flexure unloading, the bending radius of part increases than before unloading, and bent angle reduces, Here it is rebound phenomenon.Before and after shape bending resilience, physical dimension more as shown in Figure 6.
The radius springback capacity of arbitrary section is
In formula, Rnq be the bending radius of innermost layer material before resilience, be increased to Rnh after resilience, σ n is the stress intensity of cross section innermost layer, and σ w is the outermost stress intensity in cross section.
2, numerical simulation:
Geometrical model: whole stretch bending Shell model is made up of section bar and mould, in stretch bending process, section bar is deformable so be defined as deformable body, and mould thinks indeformable so be defined as discrete rigid body, and defines reference point to represent the rigid motion of all frees degree.
Assembling model: each geometrical model is independent under respective local coordinate system foundation, and assembling model is the initial relative position relation in order to define global coordinate system lower sectional material and mould.
Material properties defines: mould is defined as rigid body so need not give material properties, and section bar is that deformable body must give material properties to set up external load or contact response, and material properties passes through definition material elastic modulus E, density p, Poisson's ratio υ etc.Ture stress-strain is necessary, is used for setting up the impact of material strain sclerosis.
Contact definition: after contact conditions is given, contacting with each other between surface must define, and in stretch bending process, can select universal contact type to specify so contact relation, comprises each face and the obverse contact relation of mould.Also can applying " face-face " contact mode, to define each contact right, it is pointed out that interarea should select die face, thus selection type face defines contact.For stretch bending forming process, the definition of friction between section bar and mould often adopts classical static friction pattern.Adopt penalty function method as the touch controls algorithm between section bar and mould.
Constraint and load definition: global coordinate system is as the definition datum of stretch bending shaping institute's Constrained and load.The rigidity of mould moves and adopts reference point to represent, so to impose restriction on mould and load all applies to realize in reference point, meanwhile, needs to set up Rigid Constraints between mould and reference point.Boundary constraint and load are realized by displacement/rotation, symmetry/antisymmetry/fixing and pressure Three models.Adopt pressure pattern to control section bar axial force, forming process is divided into three analysis step to complete, prestretching-bending-mend and draw, prestretching analysis step, axial force rises to the pretension size of applying from 0, and bending analysis step axial force suitably increases, benefit draws analysis step, and axial force adopts idle mode.Simulate clamp by the reference point of the two end section definition that are coupled, adopt displacement/rotary mode to control the application of clamp reference point, axially freely, control termination, bending analysis portion rotates and realizes angle of bend prestretching analysis step, mends and draws analysis step, controls benefit and draws axial displacement.Mould is retrained by symmetry/antisymmetry/fixed mould, and whole forming process, mould is fixed.In addition, for preventing on section bar along turning up, along the one-movement-freedom-degree of line Y-direction on needing restraint.
Stress and strain model: section bar adopts linear reduction integration S4R unit, and this unit can simulate large deformation.Profile unit quantity is 20*333, and die unit quantity is 4950.Section bar thickness direction point is 9 Simpson's points, and section bar median surface is defined and contacts with section bar, and contact method is to the hard contact mode of employing, and this is consistent with physical model.Difference is, adopt housing side load pattern to apply axial force, applying size is that entities stress size is multiplied by section thickness value.The discrete rigidity R3D4 unit of bilinearity rigidity quadrangle selected by mould.
Model calculates: adopt following parameter simulation, and material adopts isotropic hardening, and axial compressive force is prestretching 158MPa, and BENDING PROCESS rises to 158MPa, and angle of bend is consistent with part, and mending the amount of drawing is 0 ~ 1.74%, and coefficient of friction is 0.2.Wherein, mend the amount of drawing 1.74% and calculate equivalent stress and equivalent plastic strain for deforming simulation, show that maximum equivalent is 203MPa.The equivalent plastic strain of whole section bar is not more than 8%, and show that minimum thickness is 1.98mm, minimum Reducing thickness is 2%.
Resilience result: adopt the distortion of ABAQUS/Standard (implict) module analysis Stretch Bending of Extrusions, a step is adopted to analyze resilience, section bar centre position fixed constraint, non-linear closedown, and be configured as resilience benchmark, to observe springback capacity size after selecting distortion.Mend the amount of drawing be 0.87% stretch bending resilience can show that the maximum resilience displacement of termination is 21.07mm, the maximum springback capacity in part active component termination is the right 16.15mm of left 13.93mm.
Embodiments of the invention announce be one of preferred embodiment also; but be not limited thereto; those of ordinary skill in the art; very easily according to above-described embodiment; understand spirit of the present invention; and make different amplifications and change, but only otherwise depart from spirit of the present invention, all in protection scope of the present invention.
Claims (3)
1., for a stretch wrap forming method of aircraft Z-type material, its characterization step is as follows:
The first step, adopts analytical Calculation or method for numerical simulation prediction Z-section Stretch Bending of Extrusions amount, carries out the design of stretch bending mold springback compensation, and complete stretch bending mold manufacture according to predicting the outcome;
Second step, the Z-section section bar treating shaping is heat-treated, after reaching new as-quenched, take out part, waits to be formed;
3rd step, setting stretch benders parameter, described stretch benders setting parameter is: swing arm speed is 1.3 degree/second, and stretching cylinder speed is 0.4 inch/s; Clinging force is 3 tons, and prestretched amount is 9mm, and benefit amount of tension is 60mm, remains set stretch benders parameter in stretch bending process;
4th step, a stretch wrap forming, prestretched, stretch bending, mends and stretches, unloading, and the part after the heat treatment of second step needs to complete stretch wrap forming in 30min, otherwise it is medium to be formed to need to be positioned over refrigerator;
5th step, precision measure also repeats FOUR EASY STEPS after adjusting process parameter, until obtain desirable External Shape.
2. the stretch bending mold for method described in claim 1, it is characterized in that: comprise overhead gage, pattern, lower baffle plate, pattern is between overhead gage and lower baffle plate, the upper surface of pattern and the lower surface of overhead gage are fitted, the lower surface of pattern and the upper surface of lower baffle plate are fitted, described pattern is similar with lower baffle plate structure, by the connection of multiple fastening bolt, profile piece is compressed between overhead gage and pattern, in addition at overhead gage, also by multiple fastening bolt described overhead gage, pattern and lower baffle plate be connected between pattern and lower baffle plate and tighten up.
3. a kind of stretch bending mold according to claim 2, is characterized in that: on pattern, be also respectively equipped with some lightening cores, locating hole, hole for hoist.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107052109A (en) * | 2017-05-03 | 2017-08-18 | 天津航天长征火箭制造有限公司 | A kind of split stretch bending mold and application method for rocket frame of section bar |
| CN110899421A (en) * | 2019-12-27 | 2020-03-24 | 卡斯马汽车系统（重庆）有限公司 | Method for bending metal bumper beam and method for bending aluminum alloy bumper beam |
| CN111822577A (en) * | 2019-04-22 | 2020-10-27 | 东汉新能源汽车技术有限公司 | Sheet metal part stretch forming method |
| CN112756432A (en) * | 2020-12-24 | 2021-05-07 | 中航贵州飞机有限责任公司 | Numerical control stretch bending process method for channel-shaped part |
| CN114192695A (en) * | 2021-11-03 | 2022-03-18 | 哈尔滨飞机工业集团有限责任公司 | Combined stretch bending forming method for complex angle part |
| CN115572809A (en) * | 2022-10-13 | 2023-01-06 | 广东铭利达科技有限公司 | A Control Method of Springback Deformation of Aluminum Alloy Thin-walled Die Casting |
| CN115608826A (en) * | 2022-10-17 | 2023-01-17 | 山东南山铝业股份有限公司 | Bending method of bending section bar for civil aircraft wing lower stringer |
| CN117371296A (en) * | 2023-12-07 | 2024-01-09 | 中铝材料应用研究院有限公司 | Profile stretch bending process method |
| CN119525330A (en) * | 2025-01-07 | 2025-02-28 | 燕山大学 | Metal profile electric-assisted bending forming device and bending method |
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| CN111822577A (en) * | 2019-04-22 | 2020-10-27 | 东汉新能源汽车技术有限公司 | Sheet metal part stretch forming method |
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| CN117371296A (en) * | 2023-12-07 | 2024-01-09 | 中铝材料应用研究院有限公司 | Profile stretch bending process method |
| CN117371296B (en) * | 2023-12-07 | 2024-03-01 | 中铝材料应用研究院有限公司 | Technological method for stretch bending forming of section bar |
| CN119525330A (en) * | 2025-01-07 | 2025-02-28 | 燕山大学 | Metal profile electric-assisted bending forming device and bending method |
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