CN106626715B - A kind of super hybrid composite manner laminate shot peen forming of fiber metal and intensifying method - Google Patents
A kind of super hybrid composite manner laminate shot peen forming of fiber metal and intensifying method Download PDFInfo
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- CN106626715B CN106626715B CN201710048763.7A CN201710048763A CN106626715B CN 106626715 B CN106626715 B CN 106626715B CN 201710048763 A CN201710048763 A CN 201710048763A CN 106626715 B CN106626715 B CN 106626715B
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- 239000000835 fiber Substances 0.000 title claims abstract description 43
- 238000005480 shot peening Methods 0.000 claims abstract description 33
- 238000003801 milling Methods 0.000 claims abstract description 9
- 238000004458 analytical method Methods 0.000 claims abstract description 3
- 239000011324 bead Substances 0.000 claims abstract 2
- 229910000838 Al alloy Inorganic materials 0.000 claims description 15
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/0012—Mechanical treatment, e.g. roughening, deforming, stretching
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/0004—Cutting, tearing or severing, e.g. bursting; Cutter details
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B41/00—Arrangements for controlling or monitoring lamination processes; Safety arrangements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B41/00—Arrangements for controlling or monitoring lamination processes; Safety arrangements
- B32B2041/04—Detecting wrong registration, misalignment, deviation, failure
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a kind of super hybrid composite manner laminate shot peen forming of fiber metal and intensifying methods, it is cut by milling method, after laminate fixation being carried out by adhering fixed mode, the contour peening under 60%-100% coverage rates is carried out to composite material surface using shot-blast process of the shot peening strength less than 0.25A, its bead blasted surfaces is controlled and obtains the compression for being less than 200MPa；It is swept by ultrasonic wave C and carries out damage and curvature measuring analysis, final school shape with cubing；This method is the unique flexible mouldless shaping method proposed at present for fiber metal superhybrid composite, it is at low cost, flexibility ratio is high, effective solution method is provided for the forming of such composite material hyperbolicity, multi-curvature component, significantly improves the static strength and fatigue behaviour of material；This method can meet active demand of the Aeronautics and Astronautics industry to such composite material large scale complex component；Preferable thinking is provided for the Plastic Forming of other laminar composites.
Description
Technical field
The invention belongs to the forming technique field of advanced composite material more particularly to a kind of super hybrid composite manners of fiber metal
Laminate shot peen forming and intensifying method.
Background technology
Fiber metal superhybrid composite is after one kind replacing laying by sheet metal and fibrous composite, one
Interply hybrid composites made of curing under fixed temperature and pressure.It combines traditional fibre composite material and metal material
The characteristics of, there is high specific strength and specific stiffness, excellent fatigue behaviour and high damage tolerance, these advantages make such
Material has been widely used in aerospace industry, and has very in rail traffic, automobile and other industrial circles
Big application potential quality.
There are two thinkings for the forming of fiber metal superhybrid composite component generally tool, i.e., before hot-press solidifying or solid
While change, target shape is shaped；Or for Glare tablets prepared by autoclave, carry out its post forming.
According to the first thinking, Univ Delft Tech proposes so-called from forming technique (Self-forming
Technique), and it is widely used in the forming of airframe, wing wallboard superhybrid composite component.From forming
Technology be by fiber metal superhybrid composite in the mold with target shape size paving, solidification of hot-press tank, with
The shape for having curvature is obtained while material preparation.However, it is only capable of the smaller single-curvature component of manufacture curvature from forming, it can not
Shape more complicated hyperbolicity or multi-curvature component；Meanwhile the technique need to be formed while material solidification of hot-press tank,
The flexibility of forming is small, and die cost is high.Moreover, notable from the rebound problem of forming technology, it need to carry out empirical
Repair a die repeatedly, increase die manufacturing cost.Chinese patent CN201410056071.3 discloses a kind of entitled " Glare structures
Part prepares manufacturing process " patent of invention, but the patent can not be prepared in autoclave, and the fiber metal obtained is super
Hybrid composite can have notable defect, be unable to reach the manufacture requirement of aerospace component.
In addition to from forming technique, more research also focuses on fiber metal superhybrid composite in the autoclave system of completion
Post forming method after standby；But since the failure strain of fiber is small, the forming limit of material is caused to be much smaller than corresponding metal
Material, and be easy to generate interlaminar failure, forming difficulty is big.For single-curvature component, roll forming is generally used；And for hyperbolic
Rate component mainly uses stretch forming at present.But due to the failure strain very little of fiber metal superhybrid composite, roll bending
Small with process window when stretch forming, Components Shape is very limited.
Shot-peening is to hit metal component surface using the bullet stream of high speed injection, so that it is deformed, surface peening and table
The technology of face cleaning, is a kind of cold-treating process of multiple surface impacts form.According to the purpose of shot-peening, shot-peening can be divided mainly into
Two kinds of forming and shot peening strengthening.Wherein, contour peening is made by spray table during bullet high-speed impact metal sheet surface
Face is plastically deformed, and forms residual stress, and component is gradually made to reach the manufacturing process that its target curvature requires.It is as one
Kind of non-mold forming technique, have the preparatory period is short, at low cost, processing length is not limited by specification of equipment, stable technical process and
The advantages that reproducibility is good, workpiece anti-fatigue life is long and anti-stress corrosion performance.
Chinese patent CN 201520006846 discloses a kind of a kind of entitled " contour peening dress of composite bimetal pipe
Set " patent of invention, which is mainly made of high-speed screw wheel abrator and mobile device.The patent shaping form is single, can not
The complex parts of multilayered structure are prepared, purposes limitation is big, it is often more important that, it is only applicable to the contour peening of simple metals laminate,
It is not particularly suited for the forming of fiber metal superhybrid composite, and engineering application is also not implemented.
Current contour peening and reinforcement technique is confined to metal material, does not there is the case history for composite material；
Meanwhile there are significant differences with traditional metal materials for the contour peening of fiber metal superhybrid composite.First, shot-peening
The mechanism of forming be using High-velocity Projectiles stream hit sheet metal surface, make the skin-material being impacted generate plastic deformation and it is residual
Residue stress causes inner layer material to deform.Fiber metal superhybrid composite was curing as laminar composite
Journey has formed complicated stress field, and after contour peening, there are rebalancing processes for stress, and with shear stress be present in fibrous layer/
Metal bed boundary is easy to that layering is caused to be failed.Secondly, the metal layer and fibrous layer of fiber metal superhybrid composite are only
0.2mm-0.5mm can directly lead to fibre damage and interfacial failure using the ball blasting method and technique of existing metal material, can not
Meet its forming requirements.In addition, the presence of fibrous layer on the one hand can be when bullet strikes composite material surface, by changing metal
The partial mold deformational behavior of layer influences the generation feature of stress, while can also be in composite material overall deformation, to material
Cooperative transformation rule impacts, and how by the control of ball blasting method and technique, realizes fiber metal superhybrid composite
The manufacture of component has great difficulty.
Invention content
In view of the above problems, the present invention is intended to provide a kind of super hybrid composite manner laminate mechanic shot peening of fiber metal
Forming and intensifying method, this method are the unique flexible mouldless shapings proposed at present for fiber metal superhybrid composite
Method, advantage at low cost, flexibility ratio is high provide effectively for the forming of such composite material hyperbolicity, multi-curvature component
Solution can meet active demand of the Aeronautics and Astronautics industry to such composite material large scale complex component；Also it is other layers
The Plastic Forming of shape composite material provides preferable thinking.
To achieve the goals above, the technical solution adopted in the present invention is as follows：
A kind of super hybrid composite manner laminate shot peen forming of fiber metal and intensifying method, include the following steps：
1）It cuts：Fiber metal superhybrid composite is cut to target size；More than rotating speed 10000r/min,
Milling under the conditions of cutter diameter 2mm, and composite layered plate is fixed on by workbench using adhering fixed mode；
2）Shot-peening is fixed：Using above-mentioned adhering fixed mode, which is fixed on support device surface；
3）Contour peening and reinforcing：Select rational bullet and shot-blast process, to fiber metal superhybrid composite into
Row forming and reinforcing；
Diameter is selected to be less than the ceramic shot-peening of 0.425mm, the shot-blast process using shot peening strength less than 0.25A is to composite wood
Expect that surface carries out the contour peening under 60%-100% coverage rates, the residual compressive stress on control shot-peening surface layer is less than 200MPa；
4）Failure and curvature measuring：It is swept respectively by ultrasonic wave C and damage and curvature is carried out to component formed thereby with cubing
Detection and analysis；
5）School shape：The component that miss the mark size requires carries out manual shot-peening school shape.
Preferably, the super hybrid composite manner laminate of fiber metal is cured after fibrous material replaces laying with metal
The composite material of layer structure.
Preferably, layered mechanism characteristics are 2/1 structure, 3/2 structure, 4/3 structure, 5/4 structure.
Preferably, the step（1）Method of cutting out be rotating speed 10000r/min or more, cutter diameter 2mm is below
Milling, and composite layered plate is fixed on by workbench using adhering fixed mode, to ensure processing quality and prevent composite layered plate
Layering failure.
The beneficial effects of the invention are as follows：It is compared with prior art, of the invention to the improvement is that,
1, the present invention provides a kind of flexible mouldless shaping methods being directed to fiber metal superhybrid composite, show
Write the production cost for reducing other Plastic Forming on mold is processed, repaired a die repeatedly etc.；Its process flexibility is strong, component
Size is not limited by specification of equipment, efficiently solves the large-size components such as large aircraft wing（20 meters of length or more）Forming it is difficult
Topic.
2, the present invention is based on the balanced action shapes of the intrinsic residual stress of fiber metal superhybrid composite and shot-peening stress
At deformation, the shortcomings that being only capable of forming single-curvature component from forming technique, roll forming technology is overcome, is mixed for fibre metal is super
The complicated double-curvature of composite material, the figuration manufacture of multi-curvature component provide effective solution method.
3, binding fiber of the present invention-metal superhybrid composite is in the side such as mechanical processing, failure behaviour and damage check
The proprietary feature in face, it is proposed that a set of method suitable for the cutting of such material, fixation, detection, context of detection, common metal material
It is not have to non-destructive testing, but this material is composite material after material shot-peening, damage is not macroscopic, it is necessary to plus damage
Detection.Binding fiber of the present invention-metal superhybrid composite is in mechanical processing, failure behaviour and damage check etc.
Proprietary feature, compared with traditional metal materials, the contour peening the step of in, it is proposed that be suitable for the proprietary cutting of such composite material,
Fixed and shot-blast process, and non-destructive testing is increased, it forms a set of suitable for the cutting of such material, fixation, forming, detection side
Method provides important guiding to other forming of such material.
4, the present invention rationally controls the stress state after contour peening by the design of shot-blast process, is lost avoiding layering
While effect, the metal layer tensile stress state caused by material thermal expansion coefficient difference is changed into compressive stress state, causes to split
The generation of line closed effect；The notable processing hardening in conjunction with caused by such material during shot-peening, it is common to realize that material is quiet strong
Degree and fatigue behaviour significantly improve.
5, exploitativeness of the present invention is strong, and forming accuracy is high, no rebound phenomenon, has important engineering application value.
Description of the drawings
Fig. 1 is the contour peening process route chart of the present invention.
Fig. 2 is that the present invention is used for the fixed support device of shot-peening.
Fig. 3 is 3/2 structure, 0 °/90 ° laying laminate schematic diagrames of the present invention.
In Fig. 2,1- supporting surfaces gap, 2- aluminium alloys supporting surface, the abutting edges 3-；
In Fig. 3,4- metal layers, 5-0 ° of fibrous layer, 6-90 ° of fibrous layer.
Specific implementation mode
In order to make those skilled in the art be better understood on technical scheme of the present invention, below in conjunction with the accompanying drawings and
Embodiment is further described technical scheme of the present invention.
Embodiment 1：With reference to a kind of super hybrid composite manner laminate shot peen forming of attached fiber metal shown in FIG. 1 and reinforcing
Method includes the following steps：
The first step chooses 3/2 structure that thickness is 1.5mm, as shown in figure 3, the glass that fiber laying direction is 0 °/90 °
Fiber-aluminium alloy superhybrid composite, wherein the top is metal layer 4, centre is 0 ° of fibrous layer 5, bottom is 90 ° of fibrous layers
6, specific material component is S4 high-strength glass fibres, epoxy resin, 2024 aluminium alloys；
Second step, by digital control milling processing method, by the material cutting to 6000mm × 1000mm, specific milling technology
Parameter is：Rotating speed 14000r/min, feed speed 2m/min, back engagement of the cutting edge 0.1mm, cutter diameter 1mm, oil cooling；
Third walks, and using adhering fixed mode, glass fibre-aluminium alloy superhybrid composite is fixed on support device
Surface；Support device includes aluminium alloy supporting surface 2 and abutting edge 3, and several supports are additionally provided on the aluminium alloy supporting surface 2
Face gap 1；As shown in Fig. 2, the support device is generally aluminium alloy structure, for saving material cost and conducive to part after shot-peening
Unsticking can be equipped with gap in support device, but deformation of composite layered plate during shot-peening, interval area are answered small in order to prevent
In bearing area；
Traditional metal materials are generally formed with diameter more than 0.6mm or more cast steel balls, and the intensity of forming is also very high；And
The super hybrid composite manner laminate of the fiber metal is only capable of using ceramic bullet, and the diameter and intensity of bullet have the stringent upper limit, to keep away
Exempt from the failure and damage of material；
Contour peening and reinforcing are to be carried out at the same time in the present invention, are designed, are shaping to shot-peening parameter before shot-peening
While formed surface be less than 200MPa compression, to reach enhancement purpose；
4th step selects AZB425 ceramics bullets, and single side contour peening is carried out to material under the shot peening strength of 0.155A,
Material is set to obtain 60% shot-peening coverage rate.Specific process parameter is：Pressure 0.2MPa, flow 5Kg/min, distance 500mm,
45 ° of spray angle, machine velocity 368.3mm/min.It is final to obtain glass fibre-aluminium alloy superhybrid composite hyperbolicity structure
Part；
5th step is swept by ultrasonic wave C and carries out failure feelings to the glass fibre after shot-peening-aluminium alloy superhybrid composite
Condition inspection, and using the curvature of three-coordinates measuring machine test member；Component is corrected shape using manual shot-peening.
Embodiment 2
The first step chooses 5/4 structure that thickness is 2.6mm, and carbon fiber-titanium alloy that fiber laying direction is 0 °/0 ° is super
Hybrid composite, specific material component are T700 carbon fibers, polyimide resin, TC4 aluminium alloys；
Second step, by digital control milling processing method, by the material cutting to 600mm × 600mm.Specific process parameter
For：Rotating speed 10000r/min, feed speed 1m/min, back engagement of the cutting edge 0.1mm, cutter diameter 2mm, water cooling；
Third walks, and using adhering fixed mode, carbon fiber-titanium alloy superhybrid composite is fixed on support device table
Face；
4th step selects AZB600 ceramics bullets, and single side contour peening is carried out to material under the shot peening strength of 0.25A,
Material is set to obtain 80% shot-peening coverage rate.Specific process parameter is：Pressure 0.22MPa, flow 10Kg/min, distance
600mm, 90 ° of spray angle, machine velocity 505.5mm/min.It is final to obtain glass fibre-aluminium alloy superhybrid composite ball
Surface member；
5th step is swept by ultrasonic wave C and carries out failure feelings to the glass fibre after shot-peening-aluminium alloy superhybrid composite
Condition inspection, and using the curvature of three-coordinates measuring machine test member；Processing need not generally be corrected shape.
Embodiment 3
The first step, chooses 2/1 structure that thickness is 1.0mm, and the carbon fiber that fiber laying direction is 0 °/90 °/0 °-aluminium closes
Golden hybrid composite, specific material component are T300 carbon fibers, acrylic resin, 7075 aluminium alloys；
Second step, by digital control milling processing method, by the material cutting to 3000mm × 900mm, specific milling technology
Parameter is：Rotating speed 16000r/min, feed speed 2m/min, back engagement of the cutting edge 0.05mm, cutter diameter 05mm, oil cooling；
Third walks, and using adhering fixed mode, carbon fiber-titanium alloy superhybrid composite is fixed on support device table
Face；
4th step selects AZB210 ceramics bullets, and two-sided contour peening is carried out to material under the shot peening strength of 0.105A
And strengthen, so that material is obtained 100% shot-peening coverage rate.Specific process parameter is：Pressure 0.35MPa, flow 6Kg/min, away from
From 500mm, 45 ° of spray angle, machine velocity 1471mm/min.It is final to obtain glass fibre-aluminium alloy superhybrid composite
Single-curvature component；
5th step is swept by ultrasonic wave C and carries out failure feelings to the glass fibre after shot-peening-aluminium alloy superhybrid composite
Condition inspection, and using the curvature of three-coordinates measuring machine test member；Processing need not generally be corrected shape.
Table 1：Table is compareed for performance before and after fiber metal superhybrid composite shot-peening of the present invention
The basic principles, main features and advantages of the present invention have been shown and described above.The technology of the industry
Personnel are it should be appreciated that the present invention is not limited to the above embodiments, and the above embodiments and description only describe this
The principle of invention, without departing from the spirit and scope of the present invention, various changes and improvements may be made to the invention, these changes
Change and improvement all fall within the protetion scope of the claimed invention.The claimed scope of the invention by appended claims and its
Equivalent thereof.
Context of detection is not have to non-destructive testing, but this material is composite material after common metal material shot-peening, damage
It is not macroscopic, it is necessary to plus the detection of damage.It can supplement in this way：The super hybrid composite manner material of binding fiber-metal of the present invention
The proprietary feature in mechanical processing, failure behaviour and damage check etc. is expected, compared with traditional metal materials, in the step of contour peening
In rapid, it is proposed that be suitable for such composite material proprietary cutting, fixation and shot-blast process, and increase non-destructive testing, form
It is a set of suitable for the cutting of such material, fixation, forming, detection method, other forming of such material are provided important
Guidance.
Claims (5)
1. a kind of super hybrid composite manner laminate shot peen forming of fiber metal and intensifying method, which is characterized in that including following step
Suddenly：
1）It cuts：Fiber metal is surpassed into hybrid composite manner laminate and is cut to target size, the method for cutting out is, in rotating speed
Milling under conditions of 10000r/min or more, cutter diameter 2mm；
2）Shot-peening is fixed：Using adhering fixed mode, which is fixed on support device surface；
3）Contour peening and reinforcing：It selects diameter to be less than the bullet of 0.425mm, the shot-peening work of 0.25A is less than using shot peening strength
Skill carries out the contour peening under 60%-100% coverage rates and reinforcing to composite layered plate surface, controls the residual compressive stress of bead blasted surfaces
Less than 200MPa；
4）Failure and curvature measuring：It is swept respectively by ultrasonic wave C and failure and curvature is carried out to composite layered plate formed thereby with cubing
Detection and analysis；
5）School shape：Manual shot-peening school shape is carried out to the composite layered plate that miss the mark curvature requires.
2. a kind of super hybrid composite manner laminate shot peen forming of fiber metal according to claim 1 and intensifying method,
It is characterized in that：The super hybrid composite manner laminate of fiber metal is cured layer structure after fibrous material replaces laying with metal
Composite material.
3. a kind of super hybrid composite manner laminate shot peen forming of fiber metal according to claim 2 and intensifying method,
It is characterized in that：Layered structure is 2/1 structure, 3/2 structure, 4/3 structure or 5/4 structure.
4. a kind of super hybrid composite manner laminate shot peen forming of fiber metal according to claim 1 and intensifying method,
It is characterized in that：The step（2）In support device include aluminium alloy supporting surface and abutting edge, in the aluminium alloy supporting surface
On be additionally provided with several supporting surface gaps.
5. a kind of super hybrid composite manner laminate shot peen forming of fiber metal according to claim 1 and intensifying method,
It is characterized in that：The step（3）In bullet use ceramic pellet.
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| CN107310242A (en) * | 2017-07-19 | 2017-11-03 | 南京航空航天大学 | A kind of flexible roll forming apparatus and method of the super hybrid composite manner laminate of fibre metal |
| US11597057B2 (en) * | 2019-02-01 | 2023-03-07 | Trelleborg Sealing Solutions Germany Gmbh | Impact forming of thermoplastic composites |
| CN113696509B (en) * | 2021-08-06 | 2022-10-04 | 南京航空航天大学 | Integrated forming method of super-hybrid panel/three-dimensional woven hollow interlayer composite material |
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| CN102505068A (en) * | 2011-09-30 | 2012-06-20 | 上海交通大学 | Method for improving surface performance of titanium-based composite material by pre-stress shot blasting |
| CN103895315A (en) * | 2014-02-19 | 2014-07-02 | 南京航空航天大学 | Preparation molding method of Glare component |
| CN105382707A (en) * | 2014-08-28 | 2016-03-09 | 富士重工业株式会社 | Blast treatment device and blast treatment method |
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2017
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