CN103691793B - A kind of based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method - Google Patents
A kind of based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method Download PDFInfo
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- CN103691793B CN103691793B CN201310711973.1A CN201310711973A CN103691793B CN 103691793 B CN103691793 B CN 103691793B CN 201310711973 A CN201310711973 A CN 201310711973A CN 103691793 B CN103691793 B CN 103691793B
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Abstract
The invention discloses a kind of based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method, first aluminum alloy slab is fixed on shaping dies, after vacuum sealing, puts into autoclave; There is provided in autoclave inside that aluminium alloy timeliness is temperature required pastes pressure needed for mould with component, make deep camber part material reach yield limit and keep pasting mould state after there is plastic deformation and enter the creep ageing stage.The present invention can eliminate because of the performance problem of non-uniform that internal stress difference causes in creep ageing process by the distribution of local plastic deformation adjustment internal stress, adopts flow to be combined with creep and reduces production cycle and resilience, can reduce mold height.This process can be not less than 10Bar at maximum working pressure, and serviceability temperature scope can meet 100 DEG C ~ 200 DEG C, and has the interior enforcement of the autoclave of enough capacity.And easy and simple to handle, frock is simple, only needs a set of die to realize, cost-saving, has actual industrial production using value.
Description
Technical field
The present invention relates to nonferrous materials processing engineering technology field, particularly a kind of be applicable to manufacture the variable curvature shape face with deep camber profile or complexity can ageing strengthening aluminium alloy wallboard class A of geometric unitA based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method.
Background technology
Overall structure wallboard is widely used in the manufacturing such as Aero-Space and communications and transportation because of its weight reduction, the reduction advantage such as production cost and assembly work amount.Creep age forming is exactly a kind of manufacture method grown up for this large-scale integral wallboard, it combines metal creep and aluminium alloy ageing strengthening characteristic, utilize aging temp to carry out the deformation of creep, there is security and repeatable and can realize the one-shot forming of wall panel parts.Creep age forming is because shaping stress low (elastic range), and thus residual stress level is low, can reduce crackle and produce probability, improves endurance and stress corrosion resistant ability.But this lower shaping stress also limit the crystallized ability of this method simultaneously, under the institution of prescription that aluminium alloy is conventional, its creep compliance is generally lower than 1%.And the Aero-Space integral panel component of reality, as often having complicated variable curvature shape face or deep camber profile in the integral panel such as wing wallboard, aircraft door component, the very difficult creep ageing of these components realizes one-shot forming, weakens creep ageing technology in production cost and the advantage in the cycle.In addition, existing many bibliographical informations are pointed out at present, and different creep stresses or mould shape face can affect the material property of creep age forming part.It is uneven that this component causing Curvature varying larger there will be performance after creep age forming, affects the service life of component.Visible, above-mentioned creep ageing one-shot forming needs improvement badly in the shortcoming of component shape face and aspect of performance, otherwise is difficult to the development bottleneck breaking through the manufacture of integral panel creep forming.
Summary of the invention
The object of the present invention is to provide a kind of can be used for having the variable curvature shape face of deep camber profile or complexity can the one-step moulding method of ageing strengthening aluminium alloy integral panel class A of geometric unitA, while guarantee is shaped, obtain uniform material property, and the residual stress effectively controlling drip molding is within 50MPa.
Object of the present invention realizes by the following method: a kind of based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method, comprise the following steps: first aluminum alloy slab is fixed on shaping dies, then vacuum sealing insert in autoclave, the shape face of mould comprises deep camber scope shape face, at least two kinds in small curve scope shape face and intermediate curvature scope shape face, slab is after inserting autoclave, pressure needed for mould is pasted with component to slab applying aluminium alloy timeliness is temperature required, after slab generation plastic deformation, keep temperature-resistant, reduce pressure needed for pressure to creep ageing then to keep until completion of prescription.
Described method, slab gross thickness is 1 ~ 50mm, and slab type is without muscle structure or band muscle structure.
Described method, the curvature range in the shape face of shaping dies is determined by the ratio R/t of the radius R of mould shape face curvature same area and the sheet metal thickness t of relevant position, 0<R/t<kE
t/ σ
stfor deep camber scope, R/t>kE
p/ σ
spfor small curve scope, kE
t/ σ
st<R/t<kE
p/ σ
spfor intermediate curvature scope, wherein, k is the constant relevant to material and slab gross thickness, and scope is 0.3 ~ 0.8, and the little exemplar forming test by equal thickness is determined; E
tfor tensile modulus of elasticity, E
pfor modulus of elasticity in comperssion, σ
stfor material solid solution state tensile yield strength, σ
spfor material solid solution state compression yield strength.
Described method, the component position within the scope of described deep camber, material forming is plastic deformation, and mold radius scope is 0.8R
*~ R
*, wherein R
*for radius of target.
Described method, the component position within the scope of described small curve, material forming is creep forming, and mold radius scope is 0.2R
*~ 0.5R
*, wherein R
*for radius of target.
Described method, the component position within the scope of described small curve, material forming is creep and plastic deformation acting in conjunction, and mold radius scope is 0.5R
*~ 0.8R
*, wherein R
*for radius of target.
Described method, the aging temp provided in autoclave is 100 ~ 200 DEG C.
Described method, it is 5 ~ 20Bar that described component pastes pressure needed for mould, and temperature retention time is 0.5 ~ 2h.
Described method, pressure needed for described creep ageing is 1 ~ 5Bar, and temperature retention time is 5 ~ 30h.
The present invention has following consideration in structural design: for the variable curvature shape surface member of complexity, first at deep camber position, plastic deformation occurs, thus releases the internal stress at this position.For the second step creep forming stage provides more uniform interior state, form the approximate creep compliance that waits and be shaped, the performance difference that internal stress causes can be eliminated, improve member integrated performance uniformity.For simple deep camber shape surface member, adopt the mode that this flow and creep are carried out simultaneously, obviously can reduce springback capacity, improve forming accuracy.
The invention has the advantages that: 1. first for the local plastic deformation at deep camber position, release the internal stress that component partial is larger, can eliminate in creep ageing process because of component performance problem of non-uniform that internal stress difference causes; 2. the once-forming method adopting plastic deformation to be combined with creep age forming, not only reduces the production cycle, also can obviously reduce final springback capacity, and this is significant for reduction large mold height, reduction production cost; 3. the residual stress of this process Forming Workpiece shapes workpiece much smaller than traditional plastic, and easy and simple to handle, and frock is simple, only needs a set of die to realize, cost-saving, has actual industrial production using value.
Indication aluminium alloy of the present invention can adopt diverse ways to prepare material requested and (or) parts.Creep ageing mould adopts Chinese patent 2011110209737.0: a kind of metal creep forming die.Embodiment of the present invention uses ATOS raster scanner to detect wallboard outer rim curved surface.Tensile tests at room makes standard tensile specimen according to GB GB/T228-2002, and stretching experiment carries out on CSS-44100 universal material mechanical stretch machine, and draw speed is 2mm/min.Residual stress test adopts borehole strain method for releasing, according to the residual stress of CB3395-1992 sheet material measurement.
Below in conjunction with accompanying drawing, the invention will be further described.
Accompanying drawing explanation
Fig. 1 is for being present invention process step schematic diagram;
Fig. 2 is fixture for forming schematic diagram of the present invention.
Detailed description of the invention
Be intended to further illustrate the present invention below in conjunction with embodiment, and unrestricted the present invention.
Be divided into 5 sections along shaping wallboard bending direction is equidistant in each embodiment, extract sample at every section and carry out Mechanics Performance Testing and residual stress test.The definition bibliography " HoKC; LinJ; DeanTA.Modellingofspringbackincreepformingthickaluminums heets.InternationalJournalofPlasticity, 2004,20 (4 – 5): 733-751. " of resilience in the present invention.Be calculated as follows: η=(d
max/ d
0) × 100%, d in formula
maxfor after drip molding resilience with the maximum normal distance of mould, be d
0mould relevant position is apart from the distance of slab initial plane.Tensile test at room temperature standard adopts GB/T228-2002, and residual stress test adopts borehole strain method for releasing, and standard adopts CB3395-1992.
Embodiment 1
Wallboard material is 7050 aluminium alloys, and slab length is 850mm, and width is 240mm, and thickness is 10mm.Target shape face is 1000mm ~ 15000mm continuous distributed along described wallboard length direction bending radius, in streamlined, adopts T6 institution of prescription.After 470 DEG C of solid solution 120min and shrend, slab is fixed on shaping dies, has covered after vacuum diaphragm forms the fixture for forming of vacuum sealing and put into autoclave.Wherein mould shape face comprises deep camber scope: R/t=600/10 ~ 0.51 × (70.3 × 10
3/ 360)/10, small curve scope: R/t=0.51 × (73.8 × 10
3/ 320)/10 ~ 15000/10, intermediate curvature scope: R/t=0.51 × (70.3 × 10
3/ 360)/10 ~ 0.51 × (73.8 × 10
3/ 320)/10.There is provided 120 DEG C of temperature and 4Bar pressure at autoclave, slab and mould are fitted, now reaches yield limit at deep camber part material and plastic deformation occurs.After keeping 1h, in tank, Pressure Drop is to 2Bar.After this in autoclave, temperature continues maintenance 120 DEG C of constant temperature 23h and carries out creep ageing.Finally, the air pressure in removal autoclave also reduces temperature, obtains required complicated variable curvature integral panel after slab resilience.
Embodiment 2
Wallboard material is 2124 aluminium alloys, and slab length is 1800mm, and width is 900mm, and thickness is 8mm.Target shape face is the ellipse that length semiaxis is respectively 378mm, 126mm along described wallboard length direction, wide bending to straight nothing, adopts T6 institution of prescription.After 490 DEG C of solid solution 120min and shrend, slab is fixed on shaping dies, has covered after vacuum diaphragm forms the fixture for forming of vacuum sealing and put into autoclave.Wherein mould shape face comprises deep camber scope: R/t=400/8 ~ 0.43 × (72 × 10
3/ 330)/8, small curve scope: R/t=0.43 × (74 × 10
3/ 300)/8 ~ 1200/8, intermediate curvature scope: R/t=0.43 × (72 × 10
3/ 330)/8 ~ 0.43 × (74 × 10
3/ 300)/8.There is provided 190 DEG C of temperature and 8Bar pressure at autoclave, slab and mould are fitted, now reaches yield limit at the deep camber part material at ellipsoid two ends and plastic deformation occurs.After keeping 1h, in tank, Pressure Drop is to 2Bar.After this in autoclave, temperature continues maintenance 190 DEG C of constant temperature 11h and carries out creep ageing.Finally, the air pressure in removal autoclave also reduces temperature, obtains required ellipsoid integral panel after slab resilience.
Embodiment 3
Wallboard material is 7475 aluminium alloys, and slab length is 1200mm, and width is 600mm.Web thickness is 2mm, and web side is provided with the rib of high 18mm, thick 3mm.Rib is square-section and the distribution in grid, and totally 16 single lattice, each single lattice size is 300mm × 150mm.Target shape face is single-curvature bending radius 750mm along described wallboard width, adopts T76 institution of prescription.After 470 DEG C of solid solution 90min and shrend, slab is fixed on shaping dies, has covered after vacuum diaphragm forms the fixture for forming of vacuum sealing and put into autoclave.Wherein mold radius is 650mm, belongs to intermediate curvature scope: R/t=0.15 × (70 × 10
3/ 380)/20 ~ 0.15 × (73 × 10
3/ 310)/20.There is provided 120 DEG C of temperature and 5Bar pressure at autoclave, slab and mould are fitted, now in the plastic deformation of slab generating portion.After keeping 1h, by Pressure Drop in tank to 3Bar.After this in autoclave, temperature continues maintenance 120 DEG C of temperature 5h and carries out creep ageing, is then warming up to 175 DEG C and keeps 8h.Finally, the air pressure in removal autoclave also reduces temperature, obtains required deep camber band muscle integral panel after slab resilience.
The room-temperature mechanical property of material, springback capacity and residual stress after table 1 embodiment of the present invention wallboard is shaped
Claims (8)
1. one kind based on autoclave can ageing strengthening aluminium alloy integral panel one-step moulding method, comprise the following steps: first aluminum alloy slab is fixed on shaping dies, then vacuum sealing insert in autoclave, it is characterized in that, the shape face of mould comprises deep camber scope shape face, at least two kinds in small curve scope shape face and intermediate curvature scope shape face, slab is after inserting autoclave, pressure needed for mould is pasted with component to slab applying aluminium alloy timeliness is temperature required, after slab generation plastic deformation, keep temperature-resistant, then reduce pressure needed for pressure to creep ageing keeps until completion of prescription, the curvature range in the shape face of shaping dies is determined by the ratio R/t of the radius R of mould shape face curvature same area and the sheet metal thickness t of relevant position, 0<R/t<kE
t/ σ
stfor deep camber scope, R/t>kE
p/ σ
spfor small curve scope, kE
t/ σ
st<R/t<kE
p/ σ
spfor intermediate curvature scope, wherein, k is the constant relevant to material and slab gross thickness, and scope is 0.3 ~ 0.8, E
tfor tensile modulus of elasticity, E
pfor modulus of elasticity in comperssion, σ
stfor material extending yield strength, σ
spfor Material compression yield strength.
2. method according to claim 1, is characterized in that, slab gross thickness is 1 ~ 50mm, and slab type is without muscle structure or band muscle structure.
3. method according to claim 1, is characterized in that, the component position within the scope of described deep camber, and material forming is plastic deformation, and mold radius scope is 0.8R
*~ R
*, wherein R
*for radius of target.
4. method according to claim 1, is characterized in that, the component position within the scope of described small curve, and material forming is creep forming, and mold radius scope is 0.2R
*~ 0.5R
*, wherein R
*for radius of target.
5. method according to claim 1, is characterized in that, the component position within the scope of described small curve, and material forming is creep and plastic deformation acting in conjunction, and mold radius scope is 0.5R
*~ 0.8R
*, wherein R
*for radius of target.
6. method according to claim 1, is characterized in that, the aging temp provided in autoclave is 100 ~ 200 DEG C.
7. method according to claim 1, is characterized in that, it is 5 ~ 20Bar that described component pastes pressure needed for mould, and temperature retention time is 0.5 ~ 2h.
8. method according to claim 1, is characterized in that, pressure needed for described creep ageing is 1 ~ 5Bar, and temperature retention time is 5 ~ 30h.
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| CN103691793B true CN103691793B (en) | 2015-12-30 |
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|---|---|---|---|---|
| CN104190777B (en) * | 2014-09-26 | 2016-06-29 | 中南大学 | A kind of once-forming method of the integral panel of aluminium alloy without ageing strengthening based on autoclave |
| CN104438481B (en) * | 2014-11-28 | 2016-04-06 | 中南大学 | A kind of preparation method of deep camber aluminium alloy integral panel component |
| CN105779748A (en) * | 2014-12-24 | 2016-07-20 | 北京有色金属研究总院 | Aging strengthened alloy ring creep aging shape correcting method |
| CN104561848B (en) * | 2014-12-26 | 2016-09-07 | 中国航空工业集团公司北京航空制造工程研究所 | A kind of creep age forming process |
| CN106978578B (en) * | 2017-05-18 | 2019-01-25 | 中南大学 | A kind of aluminium alloy plate creep age forming method |
| CN107988569A (en) * | 2017-10-18 | 2018-05-04 | 中国航发北京航空材料研究院 | A kind of age forming method of aluminium lithium alloy with muscle integral panel |
| CN108637081B (en) * | 2018-04-28 | 2020-06-30 | 中南大学 | Method for vacuum creep age forming of aluminum alloy component with complex curvature |
| CN108380736B (en) * | 2018-04-28 | 2020-01-31 | 中南大学 | device for vacuum creep age forming of aluminum alloy member with complex curvature |
| US20200222967A1 (en) * | 2019-01-11 | 2020-07-16 | Embraer S.A. | Methods for producing creep age formed aircraft components |
| CN110026478B (en) * | 2019-04-30 | 2024-05-03 | 中国民用航空飞行学院 | Method and device for vibration creep composite aging incremental forming based on pneumatic loading |
| CN110252881B (en) * | 2019-06-28 | 2020-09-01 | 中南大学 | Creep age forming regulation and control method |
| CN111122315B (en) * | 2019-12-13 | 2022-06-28 | 中国航空工业集团公司西安飞机设计研究所 | Aging performance assessment method for eliminating residual stress of aviation metal part |
| CN111122316B (en) * | 2019-12-13 | 2022-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Device for eliminating residual stress of aviation metal part and examining aging performance |
| CN111218633A (en) * | 2020-02-18 | 2020-06-02 | 南昌航空大学 | Method and device for press aging forming of plate |
| CN112570537B (en) * | 2020-10-27 | 2022-11-11 | 航天材料及工艺研究所 | Creep aging precision forming method for aluminum alloy thin-wall component assisted by rubber padding |
| CN113976707B (en) * | 2021-11-03 | 2023-09-01 | 西北工业大学 | Composite forming method for aluminum alloy large-curvature complex wallboard member |
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