WO2000009315A1 - A method of constructing skin for a member of a body such as an aircraft - Google Patents

A method of constructing skin for a member of a body such as an aircraft Download PDF

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Publication number
WO2000009315A1
WO2000009315A1 PCT/GB1999/002668 GB9902668W WO0009315A1 WO 2000009315 A1 WO2000009315 A1 WO 2000009315A1 GB 9902668 W GB9902668 W GB 9902668W WO 0009315 A1 WO0009315 A1 WO 0009315A1
Authority
WO
WIPO (PCT)
Prior art keywords
skin
pieces
fabric
piece
shape
Prior art date
Legal status (The legal status 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 status listed.)
Ceased
Application number
PCT/GB1999/002668
Other languages
French (fr)
Inventor
Andrew Paul Godbehere
Stephen Williams
Robert David Spear
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
BAE Systems PLC
Original Assignee
British Aerospace PLC
BAE Systems PLC
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 British Aerospace PLC, BAE Systems PLC filed Critical British Aerospace PLC
Priority to AT99940317T priority Critical patent/ATE239607T1/en
Priority to BRPI9913038-6A priority patent/BR9913038B1/en
Priority to AU54314/99A priority patent/AU5431499A/en
Priority to EP99940317A priority patent/EP1105281B1/en
Priority to DE69907691T priority patent/DE69907691T2/en
Priority to CA002340691A priority patent/CA2340691C/en
Priority to JP56283599A priority patent/JP3319604B2/en
Priority to US09/490,954 priority patent/US6669806B1/en
Publication of WO2000009315A1 publication Critical patent/WO2000009315A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/304—In-plane lamination by juxtaposing or interleaving of plies, e.g. scarf joining
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
    • Y10T156/1062—Prior to assembly
    • Y10T156/1075—Prior to assembly of plural laminae from single stock and assembling to each other or to additional lamina
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
    • Y10T156/10—Methods of surface bonding and/or assembly therefor
    • Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
    • Y10T156/1062—Prior to assembly
    • Y10T156/1075—Prior to assembly of plural laminae from single stock and assembling to each other or to additional lamina
    • Y10T156/1077—Applying plural cut laminae to single face of additional lamina

Definitions

  • the invention relates to a method of constructing a skin for a member of a body, for
  • example the skin of an aircraft wing.
  • the tape is laid up in a multi-axial manner by a tape laying machine which
  • Multi-axial means that alternate
  • wing skin manufacture directions for wing skin manufacture are 0° (spanwise for the wing) ⁇ 45°, -45° and
  • lay-up from face to face could be as follows:
  • a skin for a member of a body such as an aircraft comprising providing
  • a skin substantially double the thickness of each of the separate pieces
  • the method may include, forming third and fourth pieces from multi axial fabric
  • the method may further include forming the pieces from areas of the fabric which lie
  • the areas of the fabric are preferably elongate and preferably extend substantially in a
  • the method may include forming the
  • multi-axial fabric with a layer of 0° fibres extending in the longitudinal direction of
  • the method includes forming the multi-axial fabric by joining together
  • the method may include producing at least one of the first and second pieces in such a way that
  • said piece is formed partly from one of said plurality of fabrics and partly from the
  • the joint between the two fabrics preferably runs in the one of
  • the axial directions of the multi-axial fabric for example in the 0° direction.
  • the member is an aerofoil such as a wing on the body and
  • the method include shaping the first and second pieces to correspond respectively to
  • a skin for a member of a body such as an aircraft the skin being constructed in accordance with the
  • Figure 1 is a plan view of a multi-axial fabric having thereon wing-skin
  • Figure 2 is a perspective view partly broken away showing the way in which
  • Figure 3 shows to a larger scale a cross-section through a wing-skin shown in
  • Figure 4 is a diagrammatic front view of an aircraft having wing skins made by
  • length of fabric has a 0° layer 14. a -45° layer 16 and a +45° layer 18. Such a fabric is
  • the two lengths of fabric 10,12 are joined together along a joint line 20. Again, the two lengths of fabric 10,12 are joined together along a joint line 20.
  • An elongate wing-skin pattern is applied to the joined fabrics 10,12 so as to form four
  • the areas A, Al are substantially mirror images of
  • each other and the areas B, B l are likewise substantially mirror images of each other.
  • the patterns A, Al correspond substantially to wing skin plan view shapes for right
  • wing skin plan view shapes for the respective left and right hand wings. The areas are then cut out to produce four pieces. In the embodiment illustrated it
  • the cut out piece A corresponding to the shape of the right hand wing 30 can be
  • shape of the right hand wing 30 can be inverted about its outer edge 26 and placed on
  • the cut out piece B 1 corresponding to the shape of the left hand wing or can be
  • the wing skin can be
  • the wing-skin may. however,
  • wings 30.32 extending from a fuselage 33 of an aircraft as shown in Figure 4.
  • the pieces A. B can be made from a first piece of fabric 34 and the pieces
  • A, B from a separate second piece of fabric 35 rather than from a continuous piece
  • Al, B, B l can be made from single fabric lengths

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Lining Or Joining Of Plastics Or The Like (AREA)
  • Laminated Bodies (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Blow-Moulding Or Thermoforming Of Plastics Or The Like (AREA)
  • Application Of Or Painting With Fluid Materials (AREA)

Abstract

The method of constructing a skin for a member (30) of a body such as an aircraft comprises providing from a multi-axial fabric first and second pieces (A, A1) shaped to correspond respectively to the shape of the member (30) to be covered by the skin and to the shape of a similar member (32) on the opposite side of the body, and inverting one of the pieces and placing it on the other. The method may include providing third and fourth pieces (B, B1) from multi-axial fabric shaped to correspond respectively to the shape of the member (30) to be covered by the skin and to the shape of the similar member (32) on the opposite side of the body and inverting one of the third and fourth pieces (B, B1) and placing it on the other to form a skin for the similar member. In order to minimise wastage the method preferably includes forming the first piece (A) and third piece (B) from areas of the fabric which lie alongside each other and/or forming the second piece (A1) and the fourth (B1) piece from areas of the fabric which lie alongside each other.

Description

A METHOD OF CONSTRUCTING SKIN FOR A MEMBER OF A BODY
SUCH AS AN AIRCRAFT
The invention relates to a method of constructing a skin for a member of a body, for
example the skin of an aircraft wing.
It is known to produce wing skins from composite laminae. Such laminae are
produced by a process known in the art as "laying up" using, for example, carbon
fibre tape. The tape is laid up in a multi-axial manner by a tape laying machine which
provides a high degree of accuracy. The term "Multi-axial" means that alternate
layers of tape will be laid by the machine in several different directions to produce a
skin fabric having optimum strength in required directions. Commonly used
directions for wing skin manufacture are 0° (spanwise for the wing) ±45°, -45° and
90° (substantially chordwise).
In order for the skin to exhibit the correct characteristics when in position on, say, the
completed wing, it is desirable that the laminae forming the skins be balanced. For
example taking the case of a multi-axial skin having eight layers or plies a balanced
lay-up from face to face could be as follows:
+45° .450. 90°. 0°. 0°. 90°. -45°. +45° The laying up process is slow and a object of the present invention is to enable a
balanced laminae arrangement to be constructed more quickly and easily than known
hitherto.
According to a first aspect of the invention there is provided a method of constructing
a skin for a member of a body such as an aircraft, the method comprising providing
from a multi-axial fabric first and second pieces shaped to correspond respectively to
shape of the member to be covered by the skin and to that of a similar member on the
opposite side of the body, and inverting one of the pieces and placing it against the
other to provide the skin.
By using the method in accordance with the invention, the placing of one of the
pieces against the other produces the balanced laminae arrangement as described
above. Also, a skin substantially double the thickness of each of the separate pieces
can be made without having to produce the skin by a single laying up process, thus
reducing production time.
The method may include, forming third and fourth pieces from multi axial fabric
shaped to correspond respectively to the shape of the member to be covered by the
skin and to the shape of the similar member on the opposite side of the body and
inverting one of the third and fourth pieces and placing it on the other to form a skin
for the similar member. The method may further include forming the pieces from areas of the fabric which lie
alongside each other. In that way. fabric wastage is minimised.
The areas of the fabric are preferably elongate and preferably extend substantially in a
common longitudinal direction. In such a case, the method may include forming the
multi-axial fabric with a layer of 0° fibres extending in the longitudinal direction of
said areas thereof.
Preferably, the method includes forming the multi-axial fabric by joining together
edges of a plurality a fabrics made by a laying up process. In such a case, the method
may include producing at least one of the first and second pieces in such a way that
said piece is formed partly from one of said plurality of fabrics and partly from the
other joined thereto. The joint between the two fabrics preferably runs in the one of
the axial directions of the multi-axial fabric, for example in the 0° direction.
In a preferred embodiment, the member is an aerofoil such as a wing on the body and
the method include shaping the first and second pieces to correspond respectively to
the plan view shape of the aerofoil and to that of a similar aerofoil on the opposite
side of the body, inverting one of the pieces and placing it against the other to provide
a skin for one of the aerofoils.
According to a second aspect of the invention there is provided a skin for a member of a body such as an aircraft, the skin being constructed in accordance with the
method of the first aspect of the invention or any of the consistory clauses relating
thereto.
According to a third aspect of the invention there is provided an aircraft aerofoil
having a skin made in accordance with the method of the first aspect of the invention
or any of the consistory clauses relating thereto.
A method in accordance with the invention will now be described by way of example
with reference to the accompanying drawings, in which:
Figure 1 is a plan view of a multi-axial fabric having thereon wing-skin
patterns for wings on both sides of an aircraft and shown partly broken away;
Figure 2 is a perspective view partly broken away showing the way in which
two pieces cut from the fabric have been inverted and placed on each other to
form a wing-skin;
Figure 3 shows to a larger scale a cross-section through a wing-skin shown in
Figure 2 on the line III III in Figure 2; and
Figure 4 is a diagrammatic front view of an aircraft having wing skins made by
the method of the present invention. Looking at Figure 1 , two lengths 10, 12 of multi-axial fabric are provided. Each
length of fabric has a 0° layer 14. a -45° layer 16 and a +45° layer 18. Such a fabric is
also disclosed in our UK Patent Application No. 9817777.7 filed 15 August 1998 and
in our co-pending International Patent Application No. PCT/GB99/
(Ref. MA/BO 14PCT) claiming priority therefrom, entitled "Composite Material
Construction" and filed simultaneously with this application.
The two lengths of fabric 10,12 are joined together along a joint line 20. Again, the
joint line is disclosed in the aforesaid co-pending application and the reader is
directed to the specification thereof for full details of the joint. The joint will not be
described in detail in the present application.
The two lengths of material 10,12 are joined together so that their 0° layers 14 form
the upper surface of the fabric as viewed in Figure 1, and the +45° layers form the
lower surface of the fabric.
An elongate wing-skin pattern is applied to the joined fabrics 10,12 so as to form four
discrete areas B, Bl and A, Al . The areas A, Al are substantially mirror images of
each other and the areas B, B l are likewise substantially mirror images of each other.
The patterns A, Al correspond substantially to wing skin plan view shapes for right
and left hand wings 30, 32 respectively and the patterns B, B l similarly correspond to
wing skin plan view shapes for the respective left and right hand wings. The areas are then cut out to produce four pieces. In the embodiment illustrated it
will be noted that the joint line 20 runs through each piece. The 0° layer runs
longitudinally of the four areas preferably parallel with the joint line 20.
The cut out piece A corresponding to the shape of the right hand wing 30 can be
inverted about its inner edge 22 and laid on cut out piece cut out piece Al
corresponding to the shape of the left hand wing 32 or can be inverted about its
leading edge 24 and placed on B 1. Similarly, the cut out piece B corresponding to the
shape of the right hand wing 30 can be inverted about its outer edge 26 and placed on
the cut out piece B 1 corresponding to the shape of the left hand wing or can be
inverted about its leading edge 28 and placed on Al . The latter arrangement is shown
in Figure 2. By following the inversion process the wing-skin cross-section will take
the form shown in Figure 3 showing a balanced arrangement of laminae as follows:
laminae 18 16 14 14 16 18 axes +45° -45° 0° 0° -45° +45°
Several fabric cross-sections as shown in Figure 3 can be produced and laid one upon
the other to form an even thicker wing-skin and. if desired, the wing skin can be
gradually tapered from the wing root end towards the wing tip end by reducing the
numbers of laminae towards the wing tip. Where tape is used to produce the fabric, it
is normally pre-impregnated with epoxy resin which is in an uncured stated in the
laying up process and when cut to produce the pieces A. Al. B. B l . Once the desired
skin thickness has been built up. the wing-skins are then placed in an autoclave under heat and pressure to compress the fabric layers, create a bond between them and
effect curing of the epoxy resin to complete the skin. The wing-skin may. however,
be formed from layers of fabric to which a suitable bonding matrix is applied as
described in our aforesaid co-pending application.
By making up four wing skins as shown in Figure 2 and indicated at SK. the skins,
when cured, can be orientated and used to form upper and lower surfaces on the
wings 30.32 extending from a fuselage 33 of an aircraft as shown in Figure 4.
If desired, the pieces A. B can be made from a first piece of fabric 34 and the pieces
A, B from a separate second piece of fabric 35 rather than from a continuous piece
By arranging the areas A, B and Al. Bl alongside each other in the manner shown in
Figure 1. maximum use is made of the fabric with minimum wastage. Also, as the
skin thickness can be effectively doubled by laying one piece upon another, it is
necessary only to lay up the basic fabric 10, 12 instead of having to lay-up fabrics of
double thickness thereby saving lay-up time.
If desired smaller discrete pieces A. Al, B, B l can be made from single fabric lengths
not joined at 20 and can be arranged in a similar manner to minimise wastage.
However, using joined fabrics 10.12 is particularly advantageous as the wing skin
construction time is reduced bv doine so.

Claims

1. According to the invention there is provided a method of constructing a skin
for a member of a body such as an aircraft, the method being characterised by
providing from a multi-axial fabric (10, 12) first and second pieces (A, Al) shaped to
correspond respectively to the shape of the member (30) to be covered by the skin and
to the shape of a similar member (32) on the opposite side of the body (33), and
inverting one of the pieces (A) and placing it on the other (Al), to form a skin (SK)
for the member (30).
2. A method according to claim 1 characterised by providing third and fourth
pieces (B, B l) from multi-axial fabric (10, 12), the pieces being shaped to correspond
respectively to the shape of the member (30) to be covered by the skin and to the
shape of the similar member (32) on the opposite side of the body (33) and inverting
one of the third and fourth pieces (B) and placing it on the other (B l) to form a skin
(SK) for the similar member (32).
3. A method according to claim 2 characterised by forming the first piece (A) and
third piece (B) from areas of the fabric which lie alongside each other.
4. A method according to claim 2 or 3 characterised by forming the second piece
(B) and the fourth piece (B l ) from areas of the fabric (10. 12) which lie alongside
each other.
5. A method according to claim 3 or 4 in which the pieces are of elongate form
and the areas of the fabric are elongate and extend substantially in a common
longitudinal direction.
6. A method according to claim 4 or 5. characterised by forming the multi-axial
fabric (10, 12) with a layer of 0° fibres extending in the longitudinal direction of said
areas thereof.
7. A method according to any preceding claim characterised by forming the
multi-axial fabric by joining together edges of a plurality a fabrics for example by a
laying up process.
8. A method according to claim 7 characterised by producing at least one of the
first and second pieces (A. Al) in such a way that said piece (A) is formed partly
from one of said plurality of fabrics (10, 12) and partly of another joined thereto.
9. A method according to claim 7 or 8 in which a joint (20) between the two
fabrics (10. 12) runs in the one of the axial directions of the multi-axial fabric.
10. A method according to claim 9 in which the joint (20) between the two fabrics
(10, 12) runs in the 0° direction.
11. A method according to any preceding claim characterised in that the member is
an aerofoil on the body and in that the method includes shaping the first and second
pieces (A. Al) to correspond respectively to the plan view shape of the aerofoil (30)
and to that of a similar aerofoil on the opposite side of the body (33). inverting one of
the pieces (A) and placing it on the other (Al) to provide a skin for one of the
aerofoils (30).
12. A method according to any preceding claim characterised by bonding the
pieces (A. Al ; B, B l) together after placing them one upon the other.
13. An aircraft aerofoil such as a wing having a skin made in accordance with the
method of anv of claims 1 to 1 1.
14. An aircraft having a skin made in accordance with the method of any of claims
l to l l .
PCT/GB1999/002668 1998-08-15 1999-08-12 A method of constructing skin for a member of a body such as an aircraft Ceased WO2000009315A1 (en)

Priority Applications (8)

Application Number Priority Date Filing Date Title
AT99940317T ATE239607T1 (en) 1998-08-15 1999-08-12 METHOD FOR PRODUCING A SKIN FOR A PART OF A BODY SUCH AS AN AIRPLANE
BRPI9913038-6A BR9913038B1 (en) 1998-08-15 1999-08-12 process for constructing a liner for an element of an aircraft body.
AU54314/99A AU5431499A (en) 1998-08-15 1999-08-12 A method of constructing skin for a member of a body such as an aircraft
EP99940317A EP1105281B1 (en) 1998-08-15 1999-08-12 A method of constructing skin for a member of a body such as an aircraft
DE69907691T DE69907691T2 (en) 1998-08-15 1999-08-12 METHOD FOR PRODUCING A SKIN FOR A PART OF A BODY LIKE A PLANE
CA002340691A CA2340691C (en) 1998-08-15 1999-08-12 A method of construction skin for a member of a body such as an aircraft
JP56283599A JP3319604B2 (en) 1998-08-15 1999-08-12 Construction method of skins to be used as members of bodies like aircraft
US09/490,954 US6669806B1 (en) 1998-08-15 2000-01-24 Method of constructing skin for a member of a body such as an aircraft

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB9817778.5 1998-08-15
GBGB9817778.5A GB9817778D0 (en) 1998-08-15 1998-08-15 A method of constructing skin for a member of a body such as an aircraft

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US09/490,954 Continuation US6669806B1 (en) 1998-08-15 2000-01-24 Method of constructing skin for a member of a body such as an aircraft

Publications (1)

Publication Number Publication Date
WO2000009315A1 true WO2000009315A1 (en) 2000-02-24

Family

ID=10837298

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB1999/002668 Ceased WO2000009315A1 (en) 1998-08-15 1999-08-12 A method of constructing skin for a member of a body such as an aircraft

Country Status (11)

Country Link
US (1) US6669806B1 (en)
EP (1) EP1105281B1 (en)
JP (1) JP3319604B2 (en)
AT (1) ATE239607T1 (en)
AU (1) AU5431499A (en)
BR (1) BR9913038B1 (en)
CA (1) CA2340691C (en)
DE (1) DE69907691T2 (en)
ES (1) ES2199590T3 (en)
GB (1) GB9817778D0 (en)
WO (1) WO2000009315A1 (en)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110089591A1 (en) * 2009-10-16 2011-04-21 Gerber Scientific International, Inc. Methods and Systems for Manufacturing Composite Parts

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2202809A1 (en) * 1972-10-17 1974-05-10 Aerospatiale Light aircraft sandwich structure - coated with resin impregnated reinforcing fabric
DE2905701A1 (en) * 1979-02-15 1980-08-28 Arthur Wybiral Moulding model aeroplane parts in split moulds - by placing into first split mould in succession glass fibre blank, foamed polystyrene core and glass fibre blank
US4741943A (en) * 1985-12-30 1988-05-03 The Boeing Company Aerodynamic structures of composite construction
WO2000009321A1 (en) 1998-08-15 2000-02-24 Bae Systems Plc Composite material construction

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3617613A (en) * 1968-10-17 1971-11-02 Spaulding Fibre Co Punchable printed circuit board base
US4571355A (en) * 1984-11-28 1986-02-18 The Boeing Company Fiber reinforced resin composites formed of basic ply blankets
US5209804A (en) 1991-04-30 1993-05-11 United Technologies Corporation Integrated, automted composite material manufacturing system for pre-cure processing of preimpregnated composite materials
US5809805A (en) * 1996-09-03 1998-09-22 Mcdonnell Douglas Corporation Warp/knit reinforced structural fabric

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2202809A1 (en) * 1972-10-17 1974-05-10 Aerospatiale Light aircraft sandwich structure - coated with resin impregnated reinforcing fabric
DE2905701A1 (en) * 1979-02-15 1980-08-28 Arthur Wybiral Moulding model aeroplane parts in split moulds - by placing into first split mould in succession glass fibre blank, foamed polystyrene core and glass fibre blank
US4741943A (en) * 1985-12-30 1988-05-03 The Boeing Company Aerodynamic structures of composite construction
WO2000009321A1 (en) 1998-08-15 2000-02-24 Bae Systems Plc Composite material construction

Also Published As

Publication number Publication date
CA2340691C (en) 2006-01-03
JP3319604B2 (en) 2002-09-03
EP1105281A1 (en) 2001-06-13
ES2199590T3 (en) 2004-02-16
AU5431499A (en) 2000-03-06
US6669806B1 (en) 2003-12-30
BR9913038B1 (en) 2009-05-05
ATE239607T1 (en) 2003-05-15
GB9817778D0 (en) 1998-10-14
CA2340691A1 (en) 2000-02-24
DE69907691T2 (en) 2003-11-06
JP2001506201A (en) 2001-05-15
DE69907691D1 (en) 2003-06-12
BR9913038A (en) 2001-05-08
EP1105281B1 (en) 2003-05-07

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