NL2005667C2 - Method for fabrication of a fiber metal laminate. - Google Patents

Method for fabrication of a fiber metal laminate. Download PDF

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Publication number
NL2005667C2
NL2005667C2 NL2005667A NL2005667A NL2005667C2 NL 2005667 C2 NL2005667 C2 NL 2005667C2 NL 2005667 A NL2005667 A NL 2005667A NL 2005667 A NL2005667 A NL 2005667A NL 2005667 C2 NL2005667 C2 NL 2005667C2
Authority
NL
Netherlands
Prior art keywords
laminate
fiber metal
bag
metal laminate
vacuum
Prior art date
Application number
NL2005667A
Other languages
Dutch (nl)
Inventor
Reyndert Christiaan Alderliesten
Bernardus Alphonsus Grashof
Original Assignee
Univ Delft Tech
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Univ Delft Tech filed Critical Univ Delft Tech
Priority to NL2005667A priority Critical patent/NL2005667C2/en
Application granted granted Critical
Publication of NL2005667C2 publication Critical patent/NL2005667C2/en

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Classifications

    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
    • B32B37/1018—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using only vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • 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
    • B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
    • B32B37/0007—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding involving treatment or provisions in order to avoid deformation or air inclusion, e.g. to improve surface quality
    • B32B37/003—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding involving treatment or provisions in order to avoid deformation or air inclusion, e.g. to improve surface quality to avoid air inclusion
    • 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
    • B32B2305/00—Condition, form or state of the layers or laminate
    • B32B2305/07—Parts immersed or impregnated in a matrix
    • 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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/54—Yield strength; Tensile strength
    • 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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/542—Shear strength
    • 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
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/50—Properties of the layers or laminate having particular mechanical properties
    • B32B2307/552—Fatigue strength
    • 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
    • B32B2309/00—Parameters for the laminating or treatment process; Apparatus details
    • B32B2309/02—Temperature
    • 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
    • B32B2309/00—Parameters for the laminating or treatment process; Apparatus details
    • B32B2309/12—Pressure
    • 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
    • B32B2311/00—Metals, their alloys or their compounds

Description

Method for fabrication of a fiber metal laminate
The invention relates to a method for fabrication of a fiber metal laminate that comprises metal layers and in between said metal layers fiber reinforced resin layers, comprising placement of the fiber metal laminate in a first bag or cover 5 for vacuuming the fiber metal laminate, followed by a curing treatment of the fiber metal laminate at elevated pressure.
Such a method is commonly used for the production of aircraft fuselage skin material, being assembled of thin aluminum sheets with in-between cross ply pre-impregnated glass fi-10 ber/epoxy resin layers. It is known to manufacture such material by laying up the individual layers and plies on or in a mould. Once the total stack has been assembled, the panel is vacuum bagged for curing. In this known method the curing process is performed in an autoclave, because of the temperature (120°C-15 175°C depending on the epoxy resin) and pressure (6-11 bars) re quired to obtain sufficient quality.
The necessity to use in the prior art an autoclave implies not only significant costs, but also a limitation in the maximum dimensions of the panels that can be manufactured ac-20 cording to this known method. The high pressure during the autoclave cure cycle according to this known manufacturing method is necessary to push the air bubbles (voids) out of the panel, or to make the voids collapse inside the panel during the curing cycle. This may necessitate that for certain fiber metal lami- 25 nate panels the applied pressure may be as high as 11 bars.
It is an objective of the invention to provide a method for manufacturing a fiber metal laminate having less restrictions and disadvantages then the known method as discussed herein above.
30 It is a further objective of the invention to obviate the need of using an autoclave for the curing process and thus provide the possibility to increase the dimensions of the fiber metal laminate that is being manufactured.
The method for fabrication of a fiber metal laminate in 35 accordance with the invention has to this end the features of one or more of the appended claims.
2
The invention is essentially characterized in that the pressure treatment comprises the steps of -placing the first bag with the fiber metal laminate under a second bag or cover, and 5 -drawing a vacuum in said second bag or cover, and that the pressure treatment and the curing treatment of the fiber metal laminate are executed separate from each other.
It is remarked that W02005/113213 teaches a double vacuum bag process for resin matrix composite manufacturing, 10 wherein a first vacuum bag (inner bag) is sealed to a tool plate with a vacuum port built into the tool plate inside the inner bag connected to a vacuum pump to draw a vacuum within the inner bag. A second bag designated as an outer bag is similarly situated external to the inner bag with a perforated tool disposed 15 intermediate to the outer bag and the inner bag. Further, a second vacuum port provided intermediate to the outer bag and inner bag allows for the creation of a second vacuum atmosphere or environment .
In operating this known method according to 20 W02005/113213 a low-temperature ramp-and-hold period is applied to the processed laminate by introducing a vacuum into the outer bag at a higher vacuum than the vacuum introduced in the inner bag. This pulls the inner bag towards the outer bag, and does not compress the laminate. Since the laminate is not compacted 25 by vacuum pressure, it remains loose and volatiles are free to escape by the vacuum suction from the inner bag vacuum pump during this stage. At the end of the low-temperature ramp-and-hold period the outer bag is purged to atmospheric pressure, while the vacuum within the inner bag is increased. This causes the 30 inner bag to collapse to consolidate the laminate during the high temperature ramp-and-hold period of the two-step cycle that follows the low-temperature ramp-and-hold. In this known method the laminate, which does not comprise metal layers, can be placed in any heating chamber, such as an oven, a vacuum oven, a 35 vacuum press, or an autoclave to apply the necessary heat for the cure cycle stages.
According to the invention it has been proven possible to apply a pressure treatment on a fiber metal laminate by placing the first bag with the fiber metal laminate under a second 40 bag or cover, arid by drawing a vacuum in said second bag or 3 cover, wherein the pressure treatment and the curing treatment of the fiber metal laminate are executed separate from each other. This avoids using a two-step temperature ramp-and-hold cycle for curing as is taught by W02005/113213, according to 5 which teaching this curing cycle requires to maintain an elevated pressure on the laminate by applying a vacuum in the second bag or cover during the low-temperature ramp-and-hold period. Contrary to the known prior art, according to the invention it is possible that the pressure treatment is executed 10 separate and preferably prior to the curing treatment of the fiber metal laminate.
In the method of the invention it is further proven sufficient and preferable that during the curing treatment of the fiber metal laminate the vacuum of the fiber metal laminate 15 in the first bag is maintained. This secures that during curing the elements of the laminate are maintained in position and that the return of pressed out air is prevented.
Summarized it can be said that in the method of the invention, all air that resides in the laminate is enabled to be 20 permanently removed during the pressure treatment prior to the curing treatment. Once the removal of the air bubbles from the laminate is complete it suffices to maintain the vacuum of the fiber metal laminate in the first bag and to carry out then the curing treatment of the fiber metal laminate. During curing it 25 is not necessary to apply any external pressure. It suffices that the laminate is cured while it is under vacuum. In this way, the laminate can be cured with only the atmospheric pressure applied to the vacuum bag in which the laminate is contained .
30 Since no additional pressure is necessary to be applied during curing on the laminate, the laminate can be cured in either an oven, or using heat blankets or heating devices above or inside a mould. This brings about the advantage that both the vacuum cycle and the cure cycle can be performed at the same lo-35 cation where the laminate has been assembled, without necessity to physically move the laminate to another location or to an autoclave. This makes it easier to manufacture also very large laminates.
The invention will now further be explained with reference to 40 the drawing, showing in: 4 -figure 1 a setup of a fiber metal laminate placed on a mould; -figure 2 the fiber metal laminate of figure 1 placed in a vacuum bag and under a second cover; 5 -figures 3-6 four different curing methods to be ap plied while the fiber metal laminate is in a vacuum bag; -figure 7 a comparison of the tensile stress strain behavior of a conventionally manufactured (cross ply and unidirectional) laminate and a (cross ply and unidirectional) laminate 10 manufactured according to the invention; -figure 8 a comparison of the compressive stress strain behavior of a conventionally manufactured (cross ply and unidirectional) laminate and a (cross ply and unidirectional) laminate manufactured according to the invention; 15 -figure 9 a comparison of the interlaminar shear prop erties of a conventionally manufactured (cross ply and unidirectional) laminate and a (cross ply and unidirectional) laminate manufactured according to the invention; -figure 10 a comparison of the fatigue properties of a 20 conventionally manufactured (cross ply and unidirectional) laminate and a (cross ply and unidirectional) laminate manufactured according to the invention.
With reference to figure 1 a very schematic setup is shown of a laminate 1, which is assembled on top of a mould 2 25 prior to it being subjected to the processing steps of the method of the invention.
In figure 2 it is shown that the laminate 1 is placed in a first bag or cover 3 for vacuuming the fiber metal laminate 1, such that it can subsequently be subjected to a pressure 30 treatment comprising the steps of placing the first bag 3 with the fiber metal laminate 1 under a second bag or cover 4, and drawing a vacuum in said second bag or cover 4 for executing a pressure treatment on the laminate 1. During this pressure treatment all air that resides in the laminate 1 is enabled to 35 be removed prior to the curing treatment that can be executed thereafter. Once the removal of the air bubbles from the laminate 1 is complete it suffices to maintain the vacuum of the fiber metal laminate 1 in the first bag 3 and to carry out then the curing treatment of the fiber metal laminate 1.
5
Possible embodiments of curing treatments are respectively shown in the figures 3-6.
Figure 3 shows a curing treatment using an oven 5.
Figure 4 shows a curing treatment using the mould 2 as 5 a heating device .
Figure 5 shows a curing treatment with a separate meeting device 6 above the mold 2.
Figure 6 shows a curing treatment with the application of a heating blanket 7.
10
Tensile properties
With reference to figure 7 it is shown that the laminate of the invention 7.3, 7.4 exhibits comparable tensile stress strain behavior in comparison with a conventionally manu-15 factured laminate 7.1, 7.2. The laminates of this figure 7 are laminates having unidirectionally 7.1, 7.3 and cross ply 7.2, 7.4 oriented fibers. The conventionally manufactured laminate was subjected to a standard cure cycle at 120°C and 6 bars in an autoclave .
20
Compression properties
With reference to figure 8 it is shown that the laminate of the invention 8.3, 8.4 exhibits comparable compressive stress strain behavior in comparison with a conventionally manu-25 factured laminate 8.1, 8.2. The laminates of this figure 8 are laminates having unidirectionally 8.1, 8.3 and cross ply 8.2, 8.4 oriented fibers. The conventionally manufactured laminate was subjected to a standard cure cycle at 120°C and 6 bars in an autoclave.
30
Interlaminar shear properties
With reference to figure 9 it is shown that the laminate of the invention 9.3, 9.4 exhibits comparable interlaminar shear behavior in comparison with a conventionally manufactured 35 laminate 9.1, 9.2. The laminates of this figure 9 are laminates having unidirectionally 9.1, 9.3 and cross ply 9.2, 9.4 oriented fibers. The conventionally manufactured laminate was subjected to a standard cure cycle at 120°C and 6 bars in an autoclave.
6
Fatigue properties
With reference to figure 10 it is shown that the laminate of the invention 10.3, 10.4 exhibits comparable fatigue crack growth behavior in comparison with a conventionally manu-5 factured laminate 10.1, 10.2. The laminates of this figure 10 are laminates having unidirectionally 10.1, 10.3 and cross ply 10.2, 10.4 oriented fibers. The conventionally manufactured laminate was subjected to a standard cure cycle at 120°C and 6 bars in an autoclave.

Claims (3)

1. Werkwijze voor het vervaardigen van een vezelmetaal laminaat (1) welke metaallagen en tussen genoemde metaallagen vezelversterkte harslagen omvat, omvattende het plaatsen van het vezelmetaal laminaat (1) in een eerste zak of afdekking (3) voor 5 het vacumeren van het vezelmetaal laminaat (1), gevolgd door een drukbehandeling en een uithardbehandeling van het vezelmetaal laminaat, met het kenmerk, dat de drukbehandeling de stappen omvat van het - plaatsen van de eerste zak (3) met het vezelmetaal 10 laminaat (1) onder een tweede zak of afdekking (4), en - het trekken van een vacuüm in genoemde tweede zak of afdekking (4), en dat - de drukbehandeling en de uithardbehandeling van het vezelmetaal laminaat (1) gescheiden van elkaar worden uitge- 15 voerd.Method for manufacturing a fiber metal laminate (1) comprising metal layers and fiber-reinforced resin layers between said metal layers, comprising placing the fiber metal laminate (1) in a first bag or cover (3) for vacuuming the fiber metal laminate (1), followed by a pressure treatment and a curing treatment of the fiber metal laminate, characterized in that the pressure treatment comprises the steps of - placing the first bag (3) with the fiber metal laminate (1) under a second bag or cover (4), and - drawing a vacuum in said second bag or cover (4), and - the pressure treatment and the curing treatment of the fiber metal laminate (1) are carried out separately from each other. 2. Werkwijze voor het vervaardigen van een vezelmetaal laminaat volgens conclusie 1, met het kenmerk, dat - de drukbehandeling uitgevoerd wordt gescheiden en voorafgaand aan de uithardbehandeling van het vezelmetaal lami- 20 naat (1).2. A method for manufacturing a fiber metal laminate according to claim 1, characterized in that - the pressure treatment is carried out separately and laminate (1) prior to the curing treatment of the fiber metal. 3. Werkwijze voor het vervaardigen van een vezelmetaal laminaat volgens conclusie 1 of 2, met het kenmerk, dat gedurende de uithardbehandeling van het vezelmetaal laminaat (1) het vacuüm van het vezelmetaal laminaat in de eerste zak (3) gehand- 25 haafd wordt.3. Method for manufacturing a fiber metal laminate according to claim 1 or 2, characterized in that the vacuum of the fiber metal laminate in the first bag (3) is maintained during the curing treatment of the fiber metal laminate (1).
NL2005667A 2010-11-11 2010-11-11 Method for fabrication of a fiber metal laminate. NL2005667C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
NL2005667A NL2005667C2 (en) 2010-11-11 2010-11-11 Method for fabrication of a fiber metal laminate.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NL2005667 2010-11-11
NL2005667A NL2005667C2 (en) 2010-11-11 2010-11-11 Method for fabrication of a fiber metal laminate.

Publications (1)

Publication Number Publication Date
NL2005667C2 true NL2005667C2 (en) 2012-05-14

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NL2005667A NL2005667C2 (en) 2010-11-11 2010-11-11 Method for fabrication of a fiber metal laminate.

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0186787A2 (en) * 1984-12-04 1986-07-09 Asahi Glass Company Ltd. Process for producing a laminated glass
EP1336469A1 (en) * 2002-02-19 2003-08-20 Alenia Aeronautica S.P.A. Methods of manufacturing a stiffening element for an aircraft skin panel and a skin panel provided with the stiffening element
US20030183331A1 (en) * 2002-03-26 2003-10-02 Ciambrone David F. System and method for vacuum bag fabrication

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0186787A2 (en) * 1984-12-04 1986-07-09 Asahi Glass Company Ltd. Process for producing a laminated glass
EP1336469A1 (en) * 2002-02-19 2003-08-20 Alenia Aeronautica S.P.A. Methods of manufacturing a stiffening element for an aircraft skin panel and a skin panel provided with the stiffening element
US20030183331A1 (en) * 2002-03-26 2003-10-02 Ciambrone David F. System and method for vacuum bag fabrication

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Effective date: 20140601