NL2005028C2 - Laminate and airplane provided with such a laminate. - Google Patents

Laminate and airplane provided with such a laminate. Download PDF

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Publication number
NL2005028C2
NL2005028C2 NL2005028A NL2005028A NL2005028C2 NL 2005028 C2 NL2005028 C2 NL 2005028C2 NL 2005028 A NL2005028 A NL 2005028A NL 2005028 A NL2005028 A NL 2005028A NL 2005028 C2 NL2005028 C2 NL 2005028C2
Authority
NL
Netherlands
Prior art keywords
laminate
type
fiber
fibers
area
Prior art date
Application number
NL2005028A
Other languages
Dutch (nl)
Inventor
Rinze Benedictus
Reyndert Christiaan Alderliesten
Calvin David Rans
Msc Ricardo Rodi
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 NL2005028A priority Critical patent/NL2005028C2/en
Application granted granted Critical
Publication of NL2005028C2 publication Critical patent/NL2005028C2/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
    • 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
    • B32B5/22—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 the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—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 the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • B32B5/26—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 the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
    • 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
    • B29C70/06—Fibrous reinforcements only
    • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
    • B29C70/088—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers and with one or more layers of non-plastics material or non-specified material, e.g. supports
    • 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
    • B32B15/14—Layered products comprising a layer of metal next to 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
    • 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
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
    • B32B3/18—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by an internal layer formed of separate pieces of material which are juxtaposed side-by-side
    • 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
    • B32B5/08—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 the fibres or filaments of a layer being of different substances, e.g. conjugate fibres, mixture of different fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Description

Laminate and airplane provided with such a laminate
The invention relates to a laminate and to an airplane provided with such a laminate.
A laminate according to the preamble of claim 1 is known from WO 03/068494. This document discloses a laminate com-5 prising at least one series of metal layers and fiber reinforced plastic layers which are attached to one another, whereby at least two different series are provided which series include a transition and that at the location of the transition at least one of the internal layers is discontinuous and all the other 10 layers are continuous. The interruption of the internal layer is provided to suit the application of one or more additional layers in order to have a gradual transition between the various regions in the panel which is desirable to avoid stress concentrations. It also results in a gradual transition of the thick-15 ness of the panel which is beneficial for the avoidance of undesirable aerodynamic effects.
Generally speaking the known laminate which is used as skin material for an aircraft fuselage may for instance be composed of thin aluminium sheets with the thickness of 0.3-0.5 20 millimeters having in between unidirectional or cross ply preimpregnated glass fiber/epoxy resin layers. Such a laminate with unidirectional glass fibers has a modulus of elasticity in the order of 60-70 GPa, whereas such a laminate with cross ply glass fibers may exhibit a modulus of elasticity of 50-65 GPa. A mono-25 lithic aluminium skin sheet has however a modulus of elasticity-which is in the range of 70-75 GPa.
The lower stiffness of the laminate imposes on the engineer wishing to apply both laminates and monolithic aluminium sheets for the skin material of the fuselage of the airplane 30 several design issues, which in part also relate to the design of the airplane back up structure. This has to do with the fact that a backup structure which is completely made out of aluminium exhibits a higher stiffness then laminate skin material, which therefore results in that the backup structure attracts 35 more load than the skin. The resistance properties on fatigue crack growth of the laminate skin can therefore not be fully utilized, because the backup structure of the airplane would severely suffer from fatigue crack growth. To resolve this problem 2 it is known to also apply a backup structure (stringers and the like) of the same material as the laminate at the expense of higher manufacturing costs. Another proposed solution is the application of fibers with a higher stiffness, however at the ex-5 pense of reduced impact performance and reduced residual strength of the laminate caused by the lower strain to failure of this type of fibers.
It is a first objective of the invention to improve the known laminate and to provide an alternative for the laminate of 10 known construction.
It is a second objective of the invention to provide a laminate having increased damage resistance and tolerance compared to the known laminate.
It is a third objective of the invention to improve on 15 fatigue initiation life, fatigue crack growth and residual strength.
The laminate and the airplane of the invention are to that end embodied with the features of one or more of the appended claims .
20 Essentially the laminate of the invention comprises sheet metal layers and plastic layers reinforced with fiber straps of a first type that are provided between said sheet metal layers, and has at least one transitional area in which at least one fiber reinforced plastic layer with fibers of the 25 first type is interrupted such that in the at least one transitional area fiber straps of a second type are comprised whereby the fiber straps of the second type exhibit a higher modulus of elasticity then the fiber straps of the first type.
The airplane of the invention comprising a fuselage 30 with a backup structure of frames and/or stringers, wherein said backup structure supports the said laminate is preferably construed such that the at least one transitional area in the laminate is provided at the location where the backup structure connects to and supports the laminate.
35 The invention is based on the insight that at the tran sitional area the higher modulus of elasticity of the fiber straps of the second type minimizes the stiffness difference with a backup structure of the airplane made out entirely of aluminium, thus reducing the fatigue criticality of the backup 40 structure which can therefore be designed less costly.
3
Furthermore the so-called pillowing effect causes that the strains in the laminate are reduced at the location where the laminate is supported by the backup structure in comparison with the parts of the laminate that are not supported by the 5 backup structure. This pillowing effect thus limits the strain on the fibers of the second type which exhibit a higher modulus of elasticity then the fiber straps of the first type, and which higher modulus of elasticity would normally result in reduced impact performance or residual strength.
10 The application of the fiber straps of the second type in the said transitional area where the laminate will be supported by the airplane's backup structure balances the load distribution between the laminate and said backup structure, improving the fatigue life of the backup structure, while at the 15 same time the backup structure limits the strains in the fibers of the second type, which prevents premature fiber failure. At the same time the laminate exhibits the properties that are characteristic for a laminate that is provided with fibers of the first type.
20 Another beneficial aspect of the laminate and airplane of the invention is that the at least one transitional area and the area that immediately borders to said at least one transitional area exhibit the same thickness. This is beneficial for the avoidance of design complexity.
25 It is proven preferable that the fiber straps of the first type are glass fibers and the fiber straps of the second type are selected from the group comprising carbon fibers, boron fibers .
The invention will hereinafter be further elucidated 30 with reference to a drawing of typical examples of a laminate and an airplane part construed in accordance with the principles of the invention.
In the drawing: -figure 1A shows a first embodiment of a laminate ac-35 cording to the invention; -figure IB shows a second embodiment of a laminate according to the invention; and -figure 2 shows a part of a fuselage of an airplane according to the invention.
40 Wherever in the figures the same reference numerals are 4 applied, these numerals refer to the same parts.
Referring first to figure 1A a laminate according to a first embodiment is shown, wherein this laminate 1 comprises sheet metal layers 2, 3 and plastic layers 4, 5 reinforced with 5 fiber straps of a first type that are provided between said sheet metal layers 2, 3.
This laminate 1 of the invention has at least one transitional area 6 in which the fiber reinforced plastic layer or layers 4, 5 with fibers of the first type is/are interrupted, 10 and wherein in this transitional area 6 fiber straps of a second type are comprised whereby the fiber straps of the second type exhibit a higher modulus of elasticity then the fiber straps of the first type.
In the first embodiment of the laminate 1 of the inven-15 tion the fiber straps of the second type are all arranged in the same direction. The second embodiment of the laminate 1 of the invention as shown in figure IB differentiates from the first embodiment in that the fiber straps of the second type are arranged in a first direction of the transitional area 6' as well 20 as in a second direction of the transitional area 6'' which is orthogonal to the first direction of the transitional area 6'.
Both figure 1A and figure IB show that the at least one transitional area 6', 6' ' and the area that immediately borders to said at least one transitional area exhibit the same thick-25 ness.
It is preferred that the fiber straps of the first type are glass fibers and that the fiber straps of the second type are carbon fibers or boron fibers or another suitable type of fibers having a higher stiffness than glass fibers.
30 Turning now to figure 2 a part of an airplane is· shown comprising a fuselage 7 with a backup structure of frames and/or stringers 8, wherein said backup structure supports a laminate 1 according to the first embodiment or the second embodiment. It is clearly shown that the at least one transitional area 6 in 35 the laminate 1 is provided at the location where the backup structure, in the shown case the stringers 8, connect to and support the laminate 1.
5
Example
Comparing the laminate of the invention with a laminate according to the prior art, such as defined by the type Glare 5 mentioned in WO 03/068494, provides the following results, whereby the known laminate is each time referenced at 100%.
fatigue initiation life : 120 % fatigue crack growth life : 190 % 10 the crack growth rate at transitional area : 24 % residual strength : 122 %
It is specifically pointed out that the offered elucidation with reference to the drawing is merely intended to elu-15 cidate the claims and that the claims should not be considered limited to what is shown in the drawing and explained with reference thereto. Accordingly the scope of the invention and the protection afforded by the appended claims should be understood in the broadest possible sense as is warranted by the contribu-20 tion of the invention in comparison with the prior art as defined by the wording of the appended claims.

Claims (8)

1. Laminaat (1) omvattende metaallagen (2, 3) en kunst-stoflagen (4, 5) versterkt met vezelbanden van een eerste type die voorzien zijn tussen genoemde metaallagen (4, 5), waarbij er ten minste één overgangsgebied (6, 6', 6'') is in welke ten min- 5 ste één vezelversterkte kunststoflaag met vezels van het eerste type onderbroken zijn, met het kenmerk, dat in het ten minste ene overgangsgebied (6, 6', 6'') vezelbanden van een tweede type opgenomen zijn waarbij de vezelbanden van het tweede type een hogere elasticiteitsmodulus bezitten dan de vezelbanden van het 10 eerste type.A laminate (1) comprising metal layers (2, 3) and plastic layers (4, 5) reinforced with fiber tapes of a first type provided between said metal layers (4, 5), wherein there are at least one transition region (6, 6 ', 6' ') in which at least one fiber-reinforced plastic layer with fibers of the first type are interrupted, characterized in that in the at least one transition region (6, 6', 6 '') fiber bands of a second type are included wherein the fiber tapes of the second type have a higher elastic modulus than the fiber tapes of the first type. 2. Laminaat volgens conclusie 1, met het kenmerk, dat het ten minste ene overgangsgebied (6, 6', 6'') en het gebied dat onmiddellijk grenst aan genoemd ten minste ene overgangsgebied (6, 6', 6'') dezelfde dikte bezitten.Laminate according to claim 1, characterized in that the at least one transition area (6, 6 ', 6' ') and the area immediately adjacent to said at least one transition area (6, 6', 6 '') are the same thickness. 3. Laminaat volgens conclusie 1 of 2, met het kenmerk, dat de vezelbanden van het eerste type glasvezels zijn en de vezelbanden van het tweede type geselecteerd zijn uit de groep omvattende koolstofvezels, boronvezels.A laminate according to claim 1 or 2, characterized in that the fiber bands are of the first type of glass fibers and the fiber bands of the second type are selected from the group comprising carbon fibers, boron fibers. 4. Laminaat volgens één der voorgaande conclusies, met 20 het kenmerk, dat het ten minste ene overgangsgebied (6, 6', 6'') geselecteerd is op een locatie welke beoogd is om te worden verbonden met en ondersteund door een ondersteuningsconstructie (8) van een romp (7) van een vliegtuig.4. Laminate according to any one of the preceding claims, characterized in that the at least one transition area (6, 6 ', 6' ') is selected at a location which is intended to be connected to and supported by a support structure (8). ) of a fuselage (7) of an aircraft. 5. Vliegtuig omvattende een romp (7) met een ondersteu-25 ningsconstructie (8) van frames en/of steunbalken, waarin genoemde ondersteuningsconstructie een laminaat (1) steunt welke metaallagen (2, 3) en kunststoflagen (4, 5) versterkt met vezelbanden van een eerste type omvat, welke voorzien zijn tussen genoemde metaallagen (2, 3), waarbij er ten minste één overgangs- 30 gebied (6, 6', 6'') is in welke ten minste één vezelversterkte kunststoflaag met vezels van het eerste type onderbroken is, met het kenmerk, dat het ten minste ene overgangsgebied (6, 6' , 6'') vezelbanden van een tweede type omvat waarbij de vezelbanden van het tweede type een hogere elasticiteitsmodulus bezitten dan de 35 vezelbanden van het eerste type.5. Aircraft comprising a fuselage (7) with a support structure (8) of frames and / or support beams, wherein said support structure supports a laminate (1) which reinforces metal layers (2, 3) and plastic layers (4, 5) with comprises fiber tapes of a first type provided between said metal layers (2, 3), wherein there is at least one transition region (6, 6 ', 6' ') in which at least one fiber-reinforced plastic layer with fibers of the the first type is interrupted, characterized in that the at least one transition region (6, 6 ', 6' ') comprises fiber bands of a second type wherein the fiber bands of the second type have a higher elastic modulus than the fiber bands of the first type . 6. Vliegtuig volgens conclusie 5, met het kenmerk, dat het ten minste ene overgangsgebied (6, 6', 6'') en het gebied - 7 - dat onmiddellijk grenst aan genoemd ten minste ene overgangsgebied (6, 6', 6'') dezelfde dikte bezitten.Aircraft according to claim 5, characterized in that the at least one transition area (6, 6 ', 6' ') and the area - 7 - immediately adjacent to said at least one transition area (6, 6', 6 ' ') have the same thickness. 7. Vliegtuig volgens conclusie 5 of 6, met het kenmerk, dat de vezelbanden van het eerste type glasvezels zijn en de ve- 5 zelbanden van het tweede type geselecteerd zijn uit de groep omvattende koolstofvezels, boronvezels.7. Aircraft according to claim 5 or 6, characterized in that the fiber bands are of the first type of glass fibers and the fiber bands of the second type are selected from the group comprising carbon fibers, boron fibers. 8. Vliegtuig volgens één der conclusies 5-7, met het kenmerk, dat het ten minste ene overgangsgebied (6, 6', 6'') in het laminaat (1) voorzien is op een locatie waar de ondersteu- 10 ningsconstructie (8) verbonden is met het laminaat (1) en dit ondersteunt.8. Aircraft as claimed in any of the claims 5-7, characterized in that the at least one transition area (6, 6 ', 6' ') is provided in the laminate (1) at a location where the support structure (8) ) is connected to the laminate (1) and supports this.
NL2005028A 2010-07-05 2010-07-05 Laminate and airplane provided with such a laminate. NL2005028C2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
NL2005028A NL2005028C2 (en) 2010-07-05 2010-07-05 Laminate and airplane provided with such a laminate.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NL2005028A NL2005028C2 (en) 2010-07-05 2010-07-05 Laminate and airplane provided with such a laminate.
NL2005028 2010-07-05

Publications (1)

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NL2005028C2 true NL2005028C2 (en) 2012-01-09

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NL1019957C2 (en) * 2002-02-13 2003-10-03 Stork Fokker Aesp Bv Laminated panel with discontinuous inner layer.
EP1614531A2 (en) * 1996-01-11 2006-01-11 The Boeing Company Titanium-polymer hybrid laminates
DE102004058014A1 (en) * 2004-12-01 2006-06-08 Airbus Deutschland Gmbh Structural component for aircraft shells has reinforcement element, which is partly coated with cladding element, embedded in the carrier element
NL1029088C2 (en) * 2005-05-20 2006-11-21 Netherlands Inst For Metals Re Fiber-metal laminates and constructions with these.

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1614531A2 (en) * 1996-01-11 2006-01-11 The Boeing Company Titanium-polymer hybrid laminates
NL1019957C2 (en) * 2002-02-13 2003-10-03 Stork Fokker Aesp Bv Laminated panel with discontinuous inner layer.
DE102004058014A1 (en) * 2004-12-01 2006-06-08 Airbus Deutschland Gmbh Structural component for aircraft shells has reinforcement element, which is partly coated with cladding element, embedded in the carrier element
NL1029088C2 (en) * 2005-05-20 2006-11-21 Netherlands Inst For Metals Re Fiber-metal laminates and constructions with these.

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