CN106626715A - Mechanical shot peening forming and strengthening method of fiber-metal super-hybrid composite laminated sheet - Google Patents
Mechanical shot peening forming and strengthening method of fiber-metal super-hybrid composite laminated sheet Download PDFInfo
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- CN106626715A CN106626715A CN201710048763.7A CN201710048763A CN106626715A CN 106626715 A CN106626715 A CN 106626715A CN 201710048763 A CN201710048763 A CN 201710048763A CN 106626715 A CN106626715 A CN 106626715A
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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
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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
- B32B38/0004—Cutting, tearing or severing, e.g. bursting; Cutter details
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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
- B32B41/00—Arrangements for controlling or monitoring lamination processes; Safety arrangements
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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
- B32B41/00—Arrangements for controlling or monitoring lamination processes; Safety arrangements
- B32B2041/04—Detecting wrong registration, misalignment, deviation, failure
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Abstract
The invention discloses a mechanical shot peening forming and strengthening method of a fiber-metal super-hybrid composite laminated sheet. The mechanical shot peening forming and strengthening method comprises the following steps: cutting the fiber-metal super-hybrid composite laminated sheet out with a milling and cutting method; after the cut laminated sheet is fixed in a bonding fixing manner, performing shot peening forming at the coverage rate being 60-100% on a composite material surface by using a shot peening technology of which the shot peening strength is lower than 0.25A; controlling the shot peening surface of the composite material surface to obtain compressive stress lower than 200MPa; performing damage detection and analysis and curvature detection and analysis by ultrasonic wave C scanning and a test device; and finally performing profiling. The mechanical shot peening forming and strengthening method disclosed by the invention is the only flexible non-mold forming method provided in accordance with a fiber-metal super-hybrid composite material at present, and is low in cost and high in flexibility; an effective solution is provided for the forming of double-curvature members and multi-curvature members of the type of the composite material, and the static strength and the fatigue performance of the material are obviously improved; and urgent requirements for large-sized complex members of the type of the composite materials in aerospace industry can be met by the mechanical shot peening forming and strengthening method, and a good thought for the plasticity forming of other lamellar composite materials is provided.
Description
Technical field
The invention belongs to the forming technique field of advanced composite material, more particularly to a kind of super hybrid composite manner of fiber metal
Laminate shot peen forming and intensifying method.
Background technology
Fiber metal superhybrid composite is that one kind is replaced after laying, one by sheet metal and fibrous composite
The interply hybrid composites solidified under fixed temperature and pressure.It combines traditional fibre composite and metal material
The characteristics of, with high specific strength and specific stiffness, excellent fatigue behaviour and high damage tolerance, these advantages cause such
Material is obtained a wide range of applications in aerospace industry, and is had very in track traffic, automobile and other industrial circles
Big application potential quality.
The shaping of fiber metal superhybrid composite component typically has two thinkings, i.e., before hot-press solidifying or solid
While change, target shape is shaped；Or for Glare flat boards 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 airframe, the shaping of wing wallboard superhybrid composite component.From shaping
Technology be by fiber metal superhybrid composite in the mould with target shape size paving, solidification of hot-press tank, with
Material obtains the shape of curvature while preparation.However, being only capable of manufacturing the less single-curvature component of curvature from shaping, it is impossible to
The more complicated hyperbolicity of shaping or multi-curvature component；Meanwhile, the technique need to be formed while material solidification of hot-press tank, its
The flexibility of forming is little, and die cost is high.Moreover, the resilience problem from forming technology is notable, 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 cannot be prepared in autoclave, and the fiber metal that obtained surpasses
Can there is notable defect in hybrid composite, it is impossible to reach the manufacture requirements of Aero-Space component.
Except from forming technique, more research also focuses on fiber metal superhybrid composite in the autoclave system of completing
Post forming method after standby；But because the failure strain of fiber is little, the forming limit for causing material is much smaller than corresponding metal
Material, and be easy to produce interlaminar failure, shaping difficulty is big.For single-curvature component, typically using roll forming；And for hyperbolic
Rate component, mainly adopts at present stretch forming.But due to the failure strain very little of fiber metal superhybrid composite, roll bending
Little with process window during stretch forming, Components Shape is very limited.
Shot-peening is to clash into metal component surface using the bullet stream of at a high speed injection so as to be 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 is can be divided mainly into
Two kinds of shaping and shot peening strengthening.Wherein, contour peening is during bullet high-speed impact metal sheet surface, to make by spray table
Face is plastically deformed, and forms residual stress, and progressively makes component reach the manufacturing process that its target curvature is required.It is used as one
Kind of non-mold forming technique, with the preparatory period is short, low cost, processing length are not limited by specification of equipment, stable technical process and
Repeatability is good, workpiece anti-fatigue life length and the advantages of anti-stress corrosion performance.
Chinese patent CN 201520006846 discloses a kind of a kind of entitled " contour peening dress of composite bimetal pipe
Put " patent of invention, the patent is mainly made up of high-speed screw wheel abrator and mobile device.The patent shaping form is single, it is impossible to
The complex parts of sandwich construction are prepared, purposes limitation is big, it is often more important that, the contour peening of simple metals laminate is only applicable to,
The shaping of fiber metal superhybrid composite is not particularly suited for, 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；
Meanwhile, there is significant difference in contour peening and the traditional metal materials of fiber metal superhybrid composite.First, shot-peening
The mechanism of shaping is to clash into sheet metal surface using High-velocity Projectiles stream, produces the skin-material being impacted and is plastically deformed and residual
Residue stress, causes inner layer material to deform.Fiber metal superhybrid composite was solidifying as laminar composite
Journey has formed the stress field of complexity, and after contour peening, its stress has a releveling process, and with shear stress be present in fibrage/
Metal bed boundary, it is easy to cause layering failure.Secondly, the metal level and fibrage of fiber metal superhybrid composite are only
0.2mm-0.5mm, using the ball blasting method and technique of existing metal material fibre damage and interfacial failure can be directly caused, it is impossible to
Meet its forming requirements.Additionally, the presence of fibrage on the one hand can be when bullet impacts composite material surface, by changing metal
The partial mold deformational behavior of layer affects the generation feature of stress, while can also be in composite bulk deformation, to material
Cooperative transformation rule is impacted, and how by the control of ball blasting method and technique, realizes fiber metal superhybrid composite
The manufacture of component has great difficulty.
The content of the invention
For above-mentioned problem, the present invention is intended to provide a kind of super hybrid composite manner laminate mechanic shot peening of fiber metal
Shaping and intensifying method, the method is the unique flexible mouldless shaping proposed currently for fiber metal superhybrid composite
Method, the high advantage of its low cost, flexibility ratio is provided effectively for the shaping of such composite hyperbolicity, multi-curvature component
Solution, can meet active demand of the Aeronautics and Astronautics industry to such composite large scale complex component；Also it is other layers
The Plastic Forming of shape composite provides preferable thinking.
To achieve these goals, 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, comprise the following steps：
1）Cutting：Fiber metal superhybrid composite is cut into target size；In more than rotating speed 10000r/min, cutter
Milling under the conditions of 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, the composite is fixed on into support meanss surface；
3）Contour peening and reinforcing：Rational bullet and shot-blast process are selected, fiber metal superhybrid composite is carried out into
Shape and reinforcing；
Ceramic shot-peening of the diameter less than 0.425mm is selected, using shot-blast process of the shot peening strength less than 0.25A to composite table
Face carries out the contour peening under 60%-100% coverage rates, and the residual compressive stress for controlling shot-peening top layer is less than 200MPa；
4）Failure and curvature measuring：Swept by ultrasonic wave C respectively and component formed thereby is damaged and curvature measuring with cubing
Analysis；
5）School shape：The component of miss the mark dimensional requirement carries out manual shot-peening school shape.
Preferably, the super hybrid composite manner laminate of the fiber metal is that fibrous material replaces laying solidify afterwards with metal
The composite of layer structure.
Preferably, layered mechanism characteristicses are 2/1 structure, 3/2 structure, 4/3 structure, 5/4 structure.
Preferably, the step（1）Method of cutting out be more than rotating speed 10000r/min, tool diameter below 2mm
Milling, and composite layered plate is fixed on by workbench using adhering fixed mode, to ensure crudy and prevent composite layered plate
Layering failure.
The invention has the beneficial effects as follows：It is compared with prior art, of the invention to the improvement is that,
1st, the invention provides a kind of flexible mouldless shaping method for being directed to fiber metal superhybrid composite, significantly drop
Low other Plastic Forming are in mould processing, the production cost of the first-class aspect that repairs a die repeatedly；Its process flexibility is strong, scantling
Do not limited by specification of equipment, efficiently solved the large-size components such as large aircraft wing（More than 20 meters of length）A shaping difficult problem.
2nd, the present invention is based on the intrinsic residual stress of fiber metal superhybrid composite and the balanced action shape of shot-peening stress
Into deformation, overcome from forming technique, roll forming technology and be only capable of shaping the shortcoming of single-curvature component, being that fibre metal is super mixes
The complicated double-curvature of composite, the figuration manufacture of multi-curvature component provide effective solution.
3rd, binding fiber of the present invention-metal superhybrid composite is in the side such as machining, failure behaviour and damage check
The proprietary feature in face, it is proposed that a set of cutting for being suitable to such material, fixation, the method for detection, context of detection, common metal material
It is that, without Non-Destructive Testing, but this material is composite 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 at aspects such as machining, failure behaviour and damage checks
Proprietary feature, compared with traditional metal materials, the step of contour peening in, it is proposed that be suitable to the proprietary cutting of such composite,
Fixed and shot-blast process, and Non-Destructive Testing is increased, define a set of cutting for being suitable to such material, fixation, shaping, detection side
Other forming of such material are provided important guiding by method.
4th, by the design of shot-blast process, rationally the stress state after control contour peening, loses the present invention layering is avoided
While effect, will because caused by material thermal expansion coefficient difference metal level tensile stress state change into compressive stress state, cause to split
The generation of line closed effect；The notable processing caused during shot-peening with reference to such material is hardened, and realizes that material is quiet strong jointly
Degree and fatigue behaviour are significantly improved.
5th, exploitativeness of the present invention is strong, and forming accuracy is high, without rebound phenomenon, with important engineering application value.
Description of the drawings
Fig. 1 is the contour peening process route chart of the present invention.
Fig. 2 is the support meanss that the present invention is fixed for shot-peening.
Fig. 3 is 3/2 structure of the present invention, 0 °/90 ° laying laminate schematic diagrames.
In Fig. 2,1- supporting surfaces gap, 2- aluminium alloy supporting surfaces, 3- abutting edges；
In Fig. 3,4- metal levels, 5-0 ° of fibrage, 6-90 ° of fibrage.
Specific embodiment
In order that one of ordinary skill in the art is better understood on technical scheme, below in conjunction with the accompanying drawings and
Embodiment is further described to technical scheme.
Embodiment 1：The super hybrid composite manner laminate shot peen forming of a kind of fiber metal shown in 1 and reinforcing referring to the drawings
Method, comprises the following steps：
The first step, choose thickness for 1.5mm 3/2 structure, as shown in figure 3, fiber laying direction be 0 °/90 ° glass fibre-
Aluminium alloy superhybrid composite, wherein be topmost metal level 4, it is middle be 0 ° of fibrage 5, bottom is 90 ° of fibrages 6, tool
Body material component is S4 high-strength glass fibres, epoxy resin, 2024 aluminium alloys；
Second step, by digital control milling processing mode, by the material cutting to 6000mm × 1000mm, concrete milling technology parameter
For：Rotating speed 14000r/min, feed speed 2m/min, back engagement of the cutting edge 0.1mm, tool diameter 1mm, oil cooling；
3rd step, using adhering fixed mode, by glass fibre-aluminium alloy superhybrid composite support meanss table is fixed on
Face；Support meanss include aluminium alloy supporting surface 2 and abutting edge 3, and on the aluminium alloy supporting surface 2 some supporting surfaces are additionally provided with
Gap 1；It is to save material cost and take off beneficial to part after shot-peening as shown in Fig. 2 the support meanss are generally aluminium alloy structure
It is viscous, gap can be provided with support meanss, but in order to prevent deformation of the composite layered plate during shot-peening, interval area should be less than
Area of bearing；
Traditional metal materials with diameter greater than more than 0.6mm cast steel balls typically with forming, and the intensity of shaping is also very high；And the fibre
The super hybrid composite manner laminate of dimension-metal is only capable of using ceramic bullet, and the diameter and intensity of bullet have the strict upper limit, to avoid material
The failure and damage of material；
Contour peening and reinforcing in the present invention is while carry out, shot-peening parameter to be designed before shot-peening, in the same of shaping
When formed surface less than 200MPa compression, to reach enhancement purpose；
4th step, selects AZB425 ceramics bullets, and one side contour peening is carried out to material under the shot peening strength of 0.155A, makes material
Material obtains 60% shot-peening coverage rate.Specific process parameter is：Pressure 0.2MPa, flow 5Kg/min, apart from 500mm, injection
45 ° of angle, machine velocity 368.3mm/min.It is final to obtain glass fibre-aluminium alloy superhybrid composite hyperbolicity component；
5th step, swept by ultrasonic wave C carries out failure conditions inspection to the glass fibre after shot-peening-aluminium alloy superhybrid composite
Look into, 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 of the thickness for 2.6mm, and fiber laying direction is that 0 °/0 ° of carbon fiber-titanium alloy is super to be mixed
Composite, concrete material component is T700 carbon fibers, polyimide resin, TC4 aluminium alloys；
Second step, by digital control milling processing mode, by the material cutting to 600mm × 600mm.Specific process parameter is：Turn
Fast 10000r/min, feed speed 1m/min, back engagement of the cutting edge 0.1mm, tool diameter 2mm, water-cooled；
3rd step, using adhering fixed mode, by carbon fiber-titanium alloy superhybrid composite support meanss surface is fixed on；
4th step, selects AZB600 ceramics bullets, and one side contour peening is carried out to material under the shot peening strength of 0.25A, makes material
Material obtains 80% shot-peening coverage rate.Specific process parameter is：Pressure 0.22MPa, flow 10Kg/min, apart from 600mm, spray
90 ° of firing angle degree, machine velocity 505.5mm/min.It is final to obtain glass fibre-aluminium alloy superhybrid composite sphere component；
5th step, swept by ultrasonic wave C carries out failure conditions inspection to the glass fibre after shot-peening-aluminium alloy superhybrid composite
Look into, and using the curvature of three-coordinates measuring machine test member；Process need not typically be corrected shape.
Embodiment 3
The first step, chooses 2/1 structure of the thickness for 1.0mm, and fiber laying direction is that 0 °/90 °/0 ° of carbon fiber-aluminium alloy is mixed
Miscellaneous composite, concrete material component is T300 carbon fibers, acrylic resin, 7075 aluminium alloys；
Second step, by digital control milling processing mode, by the material cutting to 3000mm × 900mm, concrete milling technology parameter
For：Rotating speed 16000r/min, feed speed 2m/min, back engagement of the cutting edge 0.05mm, tool diameter 05mm, oil cooling；
3rd step, using adhering fixed mode, by carbon fiber-titanium alloy superhybrid composite support meanss surface is fixed on；
4th step, selects AZB210 ceramics bullets, and two-sided contour peening and strong is carried out to material under the shot peening strength of 0.105A
Change, make material obtain 100% shot-peening coverage rate.Specific process parameter is：Pressure 0.35MPa, flow 6Kg/min, distance
500mm, 45 ° of spray angle, machine velocity 1471mm/min.It is final to obtain glass fibre-aluminium alloy superhybrid composite list
Curvature component；
5th step, swept by ultrasonic wave C carries out failure conditions inspection to the glass fibre after shot-peening-aluminium alloy superhybrid composite
Look into, and using the curvature of three-coordinates measuring machine test member；Process need not typically be corrected shape.
Form 1：For performance control form before and after fiber metal superhybrid composite shot-peening of the present invention
General principle, principal character and the advantages of the present invention of the present invention has been shown and described above.The technical staff of the industry
It should be appreciated that the present invention is not restricted to the described embodiments, described in above-described embodiment and specification the present invention is simply illustrated
Principle, without departing from the spirit and scope of the present invention, the present invention also have various changes and modifications, these change and
Improvement is both fallen within scope of the claimed invention.The claimed scope of the invention is by appending claims and its equivalent
Thing is defined.
Context of detection, is that, without Non-Destructive Testing, but this material is composite after common metal material shot-peening, is damaged
It is not macroscopic, it is necessary to plus the detection for damaging.Can so supplement：The super hybrid composite manner material of binding fiber-metal of the present invention
The proprietary feature at aspects such as machining, failure behaviour and damage checks is expected, compared with traditional metal materials, in the step of contour peening
In rapid, it is proposed that be suitable to the proprietary cutting of such composite, fixation and shot-blast process, and increased Non-Destructive Testing, define
A set of cutting for being suitable to such material, fixation, shaping, detection method, to such material other forming provide it is important
Instruct.
Claims (6)
1. a kind of super hybrid composite manner laminate shot peen forming of fiber metal and intensifying method, it is characterised in that including following step
Suddenly：
1）Cutting：Fiber metal superhybrid composite is cut into target size；
2）Shot-peening is fixed：Using adhering fixed mode, the composite is fixed on into support meanss surface；
3）Contour peening and reinforcing：Rational bullet and shot-blast process are selected, fiber metal superhybrid composite is carried out into
Shape and reinforcing；
Shot-peening of the diameter less than 0.425mm is selected, composite material surface is entered using shot-blast process of the shot peening strength less than 0.25A
Contour peening under row 60%-100% coverage rates, the residual compressive stress for controlling shot-peening top layer is less than 200MPa；
4）Failure and curvature measuring：Swept by ultrasonic wave C respectively and component formed thereby is damaged and curvature measuring with cubing
Analysis；
5）School shape：The component of miss the mark dimensional requirement carries out manual shot-peening school shape.
2. a kind of super hybrid composite manner laminate shot peen forming of fiber metal according to claim 1 and intensifying method, its
It is characterised by：The super hybrid composite manner laminate of the fiber metal is the layer structure that fibrous material replaces laying solidify afterwards with metal
Composite.
3. a kind of super hybrid composite manner laminate shot peen forming of fiber metal according to claim 2 and intensifying method, its
It is characterised by：Layered mechanism characteristicses are 2/1 structure, 3/2 structure, 4/3 structure, 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, its
It is characterised by：The step（1）Method of cutting out refer in more than rotating speed 10000r/min for milling, tool diameter 2mm conditions
Under milling.
5. a kind of super hybrid composite manner laminate shot peen forming of fiber metal according to claim 1 and intensifying method, its
It is characterised by：The step（2）In support meanss include aluminium alloy supporting surface and abutting edge, in the aluminium alloy supporting surface
On be additionally provided with some supporting surface gaps.
6. a kind of super hybrid composite manner laminate shot peen forming of fiber metal according to claim 1 and intensifying method, its
It is characterised by：The step（3）In shot-peening adopt 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 |
| WO2020160386A1 (en) * | 2019-02-01 | 2020-08-06 | Trelleborg Sealing Solutions Us, Inc. | Impact forming of thermoplastic composites |
| CN113696509A (en) * | 2021-08-06 | 2021-11-26 | 南京航空航天大学 | Integrated forming method for super-hybrid panel/three-dimensional woven hollow interlayer composite material |
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| CN113696509A (en) * | 2021-08-06 | 2021-11-26 | 南京航空航天大学 | Integrated forming method for super-hybrid panel/three-dimensional woven hollow interlayer composite material |
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| CN106626715B (en) | 2018-10-30 |
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