NL2007603C2 - Fiber metal laminate. - Google Patents

Fiber metal laminate. Download PDF

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Publication number
NL2007603C2
NL2007603C2 NL2007603A NL2007603A NL2007603C2 NL 2007603 C2 NL2007603 C2 NL 2007603C2 NL 2007603 A NL2007603 A NL 2007603A NL 2007603 A NL2007603 A NL 2007603A NL 2007603 C2 NL2007603 C2 NL 2007603C2
Authority
NL
Netherlands
Prior art keywords
magnesium
fiber
layers
layer
metal laminate
Prior art date
Application number
NL2007603A
Other languages
Dutch (nl)
Inventor
Reyndert Christiaan Alderliesten
Maryn Conen
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 NL2007603A priority Critical patent/NL2007603C2/en
Application granted granted Critical
Publication of NL2007603C2 publication Critical patent/NL2007603C2/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
    • 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
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • 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
    • B32B27/00—Layered products comprising a layer of synthetic resin
    • B32B27/04—Layered products comprising a layer of synthetic resin as impregnant, bonding, or embedding substance
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/02—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by structural features of a fibrous or filamentary layer
    • 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/02—Synthetic macromolecular fibres
    • B32B2262/0261—Polyamide fibres
    • B32B2262/0269—Aromatic polyamide fibres
    • 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/101—Glass fibres
    • 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
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/10—Inorganic fibres
    • B32B2262/106—Carbon fibres, e.g. graphite fibres
    • 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
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

Description

Fiber metal laminate
The invention relates to a fiber metal laminate comprising at least one magnesium layer and at least one fiber 5 reinforced plastic layer.
Such a fiber metal laminate is known from the article 'The fracture properties of a fiber metal laminate based on magnesium alloy' by P. Cortés and WJ Cantwell, Composites: part B. 37 (2006) 163 - 170. The fiber metal laminate accord-10 ing to this article has either a woven carbon fiber reinforced epoxy or a unidirectional glass fiber reinforced polypropylene sandwiched between two magnesium layers. The article reports that tension-tension fatigue tests on center notched fiber metal laminates have indicated that the fatigue life of the 15 glass fiber/polypropylene fiber metal laminate is up to an order of magnitude greater than that of a plain magnesium alloy.
The article 'The applicability of magnesium-based fiber metal laminates in aerospace structures' by René Alderli-esten, Calvin Rans and Rinze Benedictus, Composites Science 20 and Technology 68 (2008), 2983 - 2993 provides criticism on the known fiber metal laminate incorporating magnesium layers and glass fiber reinforced plastic layers. Aspects that need to be investigated are the fatigue aspects related to the application of magnesium in fiber reinforced metal layers; al-25 though in the article by Cortés and Cantwell an increase of fatigue crack propagation life in magnesium-based fiber metal reinforced layers over monolithic magnesium is reported, the latter article mentions that the reported fatigue lives are lower than those of monolithic aluminum and are thus unaccept-30 able for current structural applications.
Nevertheless Alderliesten et al acknowledge that a potential application for magnesium-based fiber metal laminates might be in aircraft structural parts that are heavily determined by compression buckling criteria. The compression 35 properties of a fiber metal laminate skin are determined among other properties by the thickness of the skin. Increasing the skin thickness by using magnesium-based fiber metal laminates without adding weight as compared to an aluminum-based fiber 2 metal laminate, might therefore increase the compression properties of the skin.
Both articles express different opinions on the corrosion-problem of the magnesium layer, which is an impediment 5 for applying a fiber metal laminate with a magnesium layer in practice .
Another problem is that the person skilled in the art will not readily consider the application of magnesium in aerospace structures due to the flammability properties and low 10 fire/burn resistance of magnesium. Magnesium is therefore not considered for primary structural applications.
It is an object of the invention to provide such a fiber metal laminate with a magnesium layer, which answers to the requirements of practical applications in that it does not 15 suffer from the just mentioned corrosion problem and poor flammability properties, and that it has a fatigue life which equals or surpasses that of a fiber metal laminate based on aluminum whilst providing improved resistance to buckling.
According to the invention a fiber metal laminate is 20 therefore proposed in accordance with one or more of the appended claims.
In a first aspect of the invention the at least one magnesium layer is sandwiched between two fiber reinforced plastic layers, wherein each of said plastic layers is pro-25 vided with an outer metal layer on its side that faces away from the magnesium layer. This means that each of said plastic layers is provided with an outer metal layer distant from the side of the plastic layer that faces towards the magnesium layer. By sandwiching the magnesium layer and thereby covering 30 it by the fiber reinforced plastic layers on both sides, the magnesium layer is protected against corrosion and exposure to fire. Meanwhile the thickness of the magnesium layer can be selected at a value to provide the laminate with the required buckling resistance.
35 Preferably the outer metal layers are aluminum lay ers. These outer aluminum layers can be dimensioned with a view at the desired impact resistance.
Another aspect of the invention is that the fiber reinforced plastic layer preferably comprises glass fibers.
3
The invention will hereinafter be further elucidated with reference to the drawing and the following example.
In the drawing: -figure 1 illustrates a first sample of a fiber metal 5 laminate in accordance with the invention; -figure 2 illustrates a second sample of a fiber metal laminate in accordance with the invention; and -figure 3 shows measurement results of an example magnesium-based fiber metal laminate according to the inven-10 tion in comparison with a conventional aluminum-based fiber metal laminate.
With reference first to figure 1 the fiber metal laminate 1 of the invention is shown to comprise at least one magnesium layer 4 and at least one fiber reinforced plastic 15 layer 3, 3'. Figure 1 shows an embodiment in which on each side of the magnesium layer 4 there are two fiber reinforced plastic layers 3, 3' wherein for strength considerations the fibers of the immediately adjacent layers 3 and 3' can have perpendicular orientation with respect to each other.
20 In the variation of the fiber metal laminate 1 of the invention as shown in figure 2, there are plural magnesium layers 4.
Both figure 1 and figure 2 clearly show that the magnesium layer 4 (figure 1) is, or magnesium layers (figure 2) 25 are sandwiched between two fiber reinforced plastic layers 3, 3', and further that each of said plastic layers 3, 3' is provided with an outer metal layer 2 distant from the side of the plastic layer 3, 3' that faces towards the magnesium layer 4. Clearly the outer metal layer 2 need not be provided immedi-30 ately adjacent and against the plastic layer 3, 3' that is lying immediately against a magnesium layer 4, but there can be intermediate layers in between, that separate such plastic layers 3, 3' from the metal outer layers 2. Preferably the outer metal layers 2 are aluminum layers. The thickness of the 35 aluminum layers 2 can range from 0.2 to 1.0 mm, whereas the thickness of the magnesium layer(s) 4 can be suitably selected between 0.4 and 2.0 mm. The thickness of the aluminum layers 2 and the magnesium layer(s) 4 are preferably selected in a ratio that causes that any crack initiation develops first in 4 the outer aluminum layers 2, which is beneficial for inspection .
The at least one fiber reinforced plastic layer 3, 3' can be from any suitable material, such as for instance car-5 bon, aramid or PBO fibers. Preferably the fiber reinforced plastic layer or layers comprise however glass fibers.
As an example in the table below the magnesium-based fiber metal laminate of the invention is compared with an aluminum-based fiber metal laminate known under the trade name 10 Glare2-3/2-0.3 having three layers of 0.3 mm aluminium each and in-between two aluminium layers two glass fiber layers oriented in the same direction. The magnesium-based fiber metal laminate according to the invention is indicated with the formula AlMgFML2-2/l/2-0.3/1.0, implying a similar laminate as 15 Glare2-3/2-0.3 except that the core layer consists of a 1.0 mm magnesium layer.
Static stiffness parameters__
Stiffness i ijiareZ-3/2-0.3 AIMqFML2-2/l/2-0.3/1.0 _^ 0° I 90° 0° ....90° ........
Axial stiffness [MPa-m]__91__69__114__93
Bending stiffness [Pa m3] 17__15__51__42
Shear stiffness [MPa-m]__27__36_ 20
Further a comparison is made between fatigue initiation and crack propagation behavior of these two different types of fiber metal laminate, assuming an equal applied load (20 kN equivalent to a laminate stress of 155 MPa for Glare2A 25 and 104 MPa for AlMgFML). For further comparison purposes additionally a Glare2A-3/2-0.3/0.666/0.3 with a core layer of 0.666 mm aluminium has been added, which has a weight equal to the weight of the AlMg fiber metal laminate of the invention. The results are shown in the attached figure 3.
30 The higher measured crack growth rate of AlMgFML is attributed to a lower delamination resistance of this laminate observed during the test. Because in this test the pretreatment of the Mg sheets for obtaining an equal delamination resistance as standard Glare2A was not yet applied, the de-35 lamination growth is faster. Analytical evaluation reveals that solving the pre-treatment and therefore delamination re- 5 sistance, will imply similar crack growth curves as standard Glare2A.
The figure further illustrates that crack initiation is 1.5 to 2 times later than Glare counterparts, and that si-5 milar low crack growth rates can be achieved. In addition it was observed that the selected ratio of magnesium thickness to aluminium thickness causes fatigue initiation to occur in the outer aluminum layers first, and only then in the magnesium layers. This is beneficial for inspection purposes; cracks 10 should be noticeable in the outside layers first. The fiber metal laminate of the invention is very suitable to tailor to this desired behavior.

Claims (3)

1. Vezelmetaal-laminaat (1) omvattende tenminste één magnesiumlaag (4) en tenminste één vezelversterkte kunststof-laag (3, 3'), met het kenmerk, dat de tenminste ene magnesiumlaag (4) opgenomen is tussen twee vezelversterkte kunst- 5 stoflagen (3, 3') waarbij ieder van genoemde kunststoflagen (3, 3') voorzien is van een buitengelegen metaallaag (2) op haar zijde die weggericht is van de magnesiumlaag (4).Fiber-metal laminate (1) comprising at least one magnesium layer (4) and at least one fiber-reinforced plastic layer (3, 3 '), characterized in that the at least one magnesium layer (4) is included between two fiber-reinforced plastic layers (3, 3 ') wherein each of said plastic layers (3, 3') is provided with an outer metal layer (2) on its side facing away from the magnesium layer (4). 2. Vezelmetaal-laminaat (1) volgens conclusie 1, met het kenmerk, dat de buitengelegen metaallagen (2) aluminium 10 lagen zijn.Fiber-metal laminate (1) according to claim 1, characterized in that the outer metal layers (2) are aluminum layers. 3. Vezelmetaal-laminaat (1) volgens conclusie 1 of 2, met het kenmerk, dat de tenminste ene vezelversterkte kunst-stoflaag (3, 3') vezels omvat die geselecteer zijn uit de groep omvattende aramide, koolstof, PHO vezels, glas vezels. 2007603Fiber metal laminate (1) according to claim 1 or 2, characterized in that the at least one fiber-reinforced plastic layer (3, 3 ') comprises fibers selected from the group consisting of aramid, carbon, PHO fibers, glass fibers . 2007603
NL2007603A 2011-10-14 2011-10-14 Fiber metal laminate. NL2007603C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
NL2007603A NL2007603C2 (en) 2011-10-14 2011-10-14 Fiber metal laminate.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NL2007603A NL2007603C2 (en) 2011-10-14 2011-10-14 Fiber metal laminate.
NL2007603 2011-10-14

Publications (1)

Publication Number Publication Date
NL2007603C2 true NL2007603C2 (en) 2013-04-16

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994001277A1 (en) * 1992-07-09 1994-01-20 Structural Laminates Company Spliced laminate for aircraft fuselage
US5547735A (en) * 1994-10-26 1996-08-20 Structural Laminates Company Impact resistant laminate
WO1998053989A1 (en) * 1997-05-28 1998-12-03 Akzo Nobel N.V. Method for making a laminate and laminate obtainable by said method
WO2002094565A1 (en) * 2001-05-21 2002-11-28 Fokker Aerostructures B.V. Method for producing a shaped laminate
WO2005002845A2 (en) * 2003-07-03 2005-01-13 Stork Fokker Aesp B.V. Laminate with local reinforcement

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994001277A1 (en) * 1992-07-09 1994-01-20 Structural Laminates Company Spliced laminate for aircraft fuselage
US5547735A (en) * 1994-10-26 1996-08-20 Structural Laminates Company Impact resistant laminate
WO1998053989A1 (en) * 1997-05-28 1998-12-03 Akzo Nobel N.V. Method for making a laminate and laminate obtainable by said method
WO2002094565A1 (en) * 2001-05-21 2002-11-28 Fokker Aerostructures B.V. Method for producing a shaped laminate
WO2005002845A2 (en) * 2003-07-03 2005-01-13 Stork Fokker Aesp B.V. Laminate with local reinforcement

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Effective date: 20150501