Note: Descriptions are shown in the official language in which they were submitted.
CA 02844136 2014-02-26
SYSTEM AND METHOD OF MANUFACTURING COMPOSITE CORE
BACKGROUND
Technical Field:
The present disclosure relates to a system and method of manufacturing
composite core.
Description of Related Art:
A composite structure, such as a composite honeycomb core, can conventionally
be
manufactured using a manual process of creating a corrugated pattern in a
plurality of
composite layers by pressing mandrels against the composite layers. For
example, the method
described in U.S. Patent No. 5,567,500, utilizes such a process. The geometry
of adjacent
composite layers to collectively form the cells of the honeycomb core. Such a
process is labor
intensive which can make the honeycomb core product very expensive. Further,
this
manufacturing method can result honeycomb core that is not optimal for various
structural
implementations.
Hence, there is a need for an improved system and method for manufacturing
composite core.
SUMMARY
In one aspect, there is provided a method of wrapping a mandrel with a
composite material, the
method comprising: securing a mandrel with a winding jig; orienting the
composite material at a
wrap angle to the mandrel; securing a first portion of the composite material
toward a first end of
the mandrel; and depositing the composite material around a circumference of
the mandrel
starting from the first end of the mandrel.
In another aspect, there is provided a method of manufacturing a composite
core for use in a
structural assembly, the method comprising: wrapping a mandrel in a mandrel
wrapping process
comprising: securing a mandrel with a winding jig; orienting the composite
material at a wrap
angle to the mandrel; and depositing the composite material around a
circumference of the
mandrel; assembling the wrapped mandrels in a tool; and applying a pressure to
the composite
material during a curing cycle.
Page 1
CA 02844136 2014-02-26
In another aspect, there is provided a system for automation of a
manufacturing a composite
core, the system comprising: a mandrel hopper; a winding jig; and a mechanical
arm for
stacking a plurality of wrapped mandrels in a tool.
In another aspect, there is provided a method of wrapping a mandrel with a
composite material
for the fabrication of a composite core, the method comprising: securing a
mandrel with a
winding jig; orienting a slit of composite material at a wrap angle to the
mandrel, the slit having a
prescribed width that is dependent upon the wrap angle and a circumference of
the mandrel;
and wrapping the slit of composite material around a circumference of the
mandrel starting from
a first end of the mandrel.
In a further aspect, there is provided a method of wrapping a mandrel with a
composite material
for the fabrication of a composite core, the method comprising: calculating a
width of a slit of
composite material based upon a geometry of the mandrel and a desired wrap
angle; orienting
the slit of composite material at the wrap angle to the mandrel; and wrapping
the slit of
composite material around a circumference of the mandrel in a helical path.
DESCRIPTION OF THE DRAWINGS
The novel features believed characteristic of the system and method of the
present disclosure
are set forth in the appended claims. However, the system and method itself,
as well as a
preferred mode of use, and further objectives and advantages thereof, will
best be understood
by reference to the following detailed description when read in conjunction
with the
accompanying drawings, wherein:
Figure 1 is a side view of an rotorcraft, according to one example embodiment;
Figure 2 is a side view of a panel, according to one example embodiment;
Figure 3 is a cross-sectional view of the panel, taken from section lines 3-3
in Figure 2,
according to one example embodiment;
Figure 4 is a perspective view of a composite core, according to one example
embodiment;
Figure 5 is a cross-sectional view of the composite core, taken from section
lines 5-5 in Figure
4, according to one example embodiment;
Page 2
CA 02844136 2014-02-26
Figure 6 is a schematic view of a method of manufacturing a composite core,
according to one
example embodiment;
Figure 7 is a partially stylized view of a system for wrapping and assembling
mandrels,
according to example embodiment;
Figure 8 is an exploded view of a mandrel winding jig, according to example
embodiment;
Figure 9A is a top view of a winding jig, according to example embodiment;
Figure 9B is a top view of a winding jig, according to example embodiment;
Figure 10 is a top view of a winding jig, according to example embodiment;
Figure 11 is a top view of a winding jig, according to example embodiment;
Figure 12 is a stylized, plan view of a mandrel being wrapped with uncured
composite material,
according to one particular embodiment;
Figure 13 is a stylized, plan view of a mandrel being wrapped with uncured
composite material,
according to one particular embodiment;
Figure 14 is a top view of a winding jig, according to example embodiment;
Figure 15 is a detail view taken from Figure 14, according to one example
embodiment;
Figure 16 is a detail view taken from Figure 14, according to one example
embodiment;
Figure 17 is a perspective view of a cutting tool, according to one example
embodiment;
Figure 18 is a is an end view of a plurality of composite-wrapped mandrels
stacked on a partial
tool, according to one example embodiment;
Figure 19 is an end view of a plurality of composite-wrapped mandrels
assembled in a tool,
according to one example embodiment;
Figure 20 is a plan view of a plurality of composite-wrapped mandrels
assembled in a tool,
according to one example embodiment; and
Page 3
CA 02844136 2014-02-26
Figure 21 is a cross-section view of a mandrel taken from Figure 8, according
to one example
embodiment.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Illustrative embodiments of the system and method of the present disclosure
are described
below. In the interest of clarity, all features of an actual implementation
may not be described in
this specification. It will of course be appreciated that in the development
of any such actual
embodiment, numerous implementation-specific decisions must be made to achieve
the
developer's specific goals, such as compliance with system-related and
business-related
constraints, which will vary from one implementation to another. Moreover, it
will be appreciated
that such a development effort might be complex and time-consuming but would
nevertheless
be a routine undertaking for those of ordinary skill in the art having the
benefit of this disclosure.
In the specification, reference may be made to the spatial relationships
between various
components and to the spatial orientation of various aspects of components as
the devices are
depicted in the attached drawings. However, as will be recognized by those
skilled in the art
after a complete reading of the present disclosure, the devices, members,
apparatuses, etc.
described herein may be positioned in any desired orientation. Thus, the use
of terms such as
"above," "below," "upper," "lower," or other like terms to describe a spatial
relationship between
various components or to describe the spatial orientation of aspects of such
components should
be understood to describe a relative relationship between the components or a
spatial
orientation of aspects of such components, respectively, as the device
described herein may be
oriented in any desired direction.
Referring now to Figure 1 in the drawings, a rotorcraft 101 is illustrated.
Rotorcraft 101 has a
rotor system 103 with a plurality of rotor blades 105. The pitch of each rotor
blade 105 can be
managed in order to selectively control direction, thrust, and lift of
rotorcraft 101. Rotorcraft 101
can further include a fuselage 107, anti-torque system 109, and an empennage
111.
Rotorcraft 101 is merely illustrative of the wide variety of aircraft,
vehicles, and other objects that
are particularly well suited to take advantage of the method and system of the
present
disclosure. It should be appreciated that other aircraft can also utilize the
method and system of
the present disclosure.
Further, other vehicles and objects can utilize composite core
manufactured by the system and method of the present disclosure. Illustrative
embodiments
can include wind turbine blades, sea based vehicles, radomes, enclosures,
shelters, bridge
Page 4
CA 02844136 2014-02-26
decks, building facades, ground vehicles, rail vehicles, air vehicles, space
vehicles, and manned
or un-manned vehicles, to name a few.
Referring now also to Figures 2 and 3, a panel 113 on rotorcraft 101 is
illustrative of a wide
variety of structures that can include a core member configured as a
lightweight means of
generating strength and stiffness in the structure. Panel 113 is a composite
assembly that can
include an upper skin 301, a lower skin 303, and a composite core 305.
Composite core 305
can be adhesively bonded to upper skin 301 and lower skin 303. It should be
appreciated that
panel 113 can take on a wide variety of contours and configurations.
Referring now also to Figures 4 and 5, composite core 401 is illustrated in a
raw stock
configuration. Composite core 305 (shown in Figure 3), having implementation
specific
geometry, can be carved from composite core 401, for example. In another
embodiment,
composite core 401 is manufactured in a net shape such that a subsequent
carving procedure
is not required. Composite core 401 can be of a wide variety of materials and
cell sizes. For
example, in one embodiment composite core 401 is made from a carbon fiber and
resin
composite system. Composite core 401 includes a plurality of tubes 403 (only
one tube labeled
for clarity) arranged in a two-dimensional array. However, in one embodiment
the tubes 403
can be selectively positioned such that the end portions are not in the same
plane. Each tube
403 defines a passageway or "cell" 405 extending therethrough. Composite core
401 can
comprise any suitable number, size, cross-sectional shape, and construction of
tubes 403.
Each tube 403 of composite core 401 can include a plurality of reinforcement
fibers disposed in
a polymeric matrix. For example, tubes 403 may comprise fibers comprising one
or more of
carbon, graphite, glass, an aromatic polyamide (i.e., "aramid") material, a
variant of an aromatic
polyamide material (e.g., a polyparaphenylene terephthalamide material, such
as Kevlar by E.
I. du Pont de Nemours and Company of Richmond, Virginia), or the like. The
scope of the
present disclosure, however, encompasses fibers comprising any suitable
material or
combination of materials. The polymeric matrix may comprise any suitable resin
system, such
as a thermoplastic or thermosetting resin for example. Exemplary resins
include epoxy,
polyimide, polyamide, bismaleimide, polyester, vinyl ester, phenolic,
polyetheretherketone
(PEEK), polyetherketone (PEK), polyphenylene sulfide (PPS), and the like.
The fibers of tubes 403 may be oriented in one or more directions and may be
woven or
unwoven. It should be appreciated that tube 307 may alternatively only include
fibers arranged
Page 5
CA 02844136 2014-02-26
in a single direction, such as a uniaxial or helical fiber configurations.
In yet another
embodiment, a first ply comprises fibers and a second ply comprises fibers,
such that the
second ply is laid-up over the first ply.
Referring now also to Figure 6, a method 601 of manufacturing a composite
core, such as
composite core 401, is schematically illustrated. Method 601 can include a
step 603 of
configuring a plurality of mandrels. A step 605 can include wrapping a
composite material
around each mandrel. A step 607 can include assembling the wrapped mandrels. A
step 609
can include curing the composite material to form a cured core member. A step
611 can include
cooling the mandrels and removing the mandrels from the cured core member.
Each step of
method 601 is described in further detail herein.
Referring to Figure 21, a cross-sectional view through a mandrel 701 is
illustrated. Step 603
includes configuring a plurality of mandrels. In the illustrated embodiment,
mandrel 701 is a
metallic mandrel, such an aluminum material. Mandrel 701 is configured having
a material with
a relatively low coefficient of thermal expansion (CTE). In the illustrated
embodiment, mandrel
701 is preferably cured in a tool that utilizes a bladder or other device to
apply pressure from the
exterior. However, it should be appreciated that method 701 can also be
configured with a
material having a desired amount of CTE so that curing pressure is derived
from a thermal
expansion of the mandrels within a confining tool.
Mandrel 701 may be configured with a hollow portion 703 extending through the
centerline
length of mandrel 701, forming a body portion 705 between hollow portion 701
and outer
surface 707. Mandrel 701 is configured so that during the curing process of
the composite core
401, the temperature of each mandrel 701 is increased such that body portion
705
volumetrically expands uniformly both in an inward direction and an outward
direction, until
outer surface 707 is bounded by its nearest neighbor mandrel, at which point
the pressure
exerted by mandrel 701 on its nearest neighbor mandrel remains relatively
constant, and the
thermal expansion of body portion 705 continues primarily in inward direction.
The degree of
thermal expansion each mandrel 701 is dependent upon the CTE of the material
of each
mandrel 701. The geometry of mandrel 701 can be selected to tailor the
physical properties of
mandrel 701 and the resultant composite core 401. Further, the geometry of
mandrel 701 can
be selected to tailor the strength/stiffness of the mandrel 701. Further, the
wall thickness of
body portion 705, as well as the geometry of hollow portion 703, can be
selectively controlled to
produce a desired thermal expansion profile. For example, a mandrel having a
smaller hollow
Page 6
CA 02844136 2014-02-26
portion 703 would provide a higher external pressure than mandrel 701. In the
illustrated
embodiment, hollow portion 703 is of a cylindrical shape; however, it should
be appreciated that
other embodiments may have non-cylindrical shapes.
Each mandrel 701 is configured with a hollow portion 703 which allows hot air
to be ducted
therethrough during the cure cycle, as discussed further herein. However, it
should be
appreciated that an alternative embodiment of mandrel 701 does not include a
hollow portion
703. It should be appreciated that mandrel 701 is merely illustrative of a
wide variety of mandrel
configurations contemplated. Even though the exterior shape of the mandrels
are illustrated as
hexagonal, the present disclosure includes mandrels having other exterior
shapes, such as
square, rectangular, triangular, to name a few examples. Further, it should be
appreciated that
the hollow portion within the mandrels can be any variety of shape, or shapes.
The exact shape
of the hollow portion is implementation specific.
In one example embodiment, a Teflone material, or other bond resistant
material or coating, can
be used to prevent the composite material from bonding to the exterior surface
of mandrel 701
during the cure cycle. As such, each mandrel 701 can include a layer 709 of
the bond resistant
material adjacent to the outer surface 707 of each mandrel 701.
Referring again to Figure 6, step 605 includes wrapping composite material
around each
mandrel, such as mandrel 701. The exact method of wrapping or otherwise
depositing the
uncured composite material on the exterior surface of each mandrel is
implementation specific.
In the preferred embodiment, one or more steps of method 601 are performed by
an automated
system; however, it should be appreciated that any of the steps can be
performed manually.
Referring also to Figure 7, a system 801 for at least partially performing one
or more steps of
method 601 is illustrated. Further, system 801 is particularly well suited for
performed steps 605
and 607. Step 605 includes wrapping composite material around each mandrel.
Step 607
includes assembling the wrapped mandrels. Each of steps 605 and 607, as well
as system 801,
are further described herein.
System 801 can include a hopper 803 configured to house a plurality of
mandrels 701. Each
mandrel 701 can be selectively deployed and captured by a winding jig 805. For
example, each
mandrel 701 can be released onto a conveyor 807 and picked up by the arms of
winding jig
805.
Page 7
CA 02844136 2014-02-26
Referring also to Figure 8, an embodiment of winding jig 805 is illustrated.
Winding jig 805 is
configured to position and retain mandrel 701 for the depositing of composite
material thereon.
It should be appreciated that winding jig 805 can take on a variety of
implementation specific
configurations. In one embodiment, winding jig 805 can include a driver 809
and a support
member 811. Adapters 813a and 813b are operably associated with driver 809 and
support
member 811, respectively. A coupling 815a is positioned between driver 809 and
a first end
portion of mandrel 701. Similarly, a coupling 815b is positioned between
support member 811
and a second end portion of mandrel 701.
Winding jig 805 is configured to operably secure mandrel 701 between couplings
815a and
815b. Couplings 815a and 815b have similar geometry to that of mandrel 701.
Further, winding
jig 805 is configured such that the geometry of couplings 815a and 815b are
aligned with
mandrel 701 during the composite material winding process. In the illustrated
embodiment,
driver 809 is configured to drive the rotation of adapters 813a and 813b,
couplings 815a and
815b, and mandrel, while support member 811 is configured to provide
freewheeling support. In
an alternative embodiment, mandrel 701 and couplings 815a and 815b are held
stationary while
a device operates to place the composite material about the mandrel and
couplings 815a and
815b, as discussed further herein. It should be appreciated that winding jig
805 is merely
illustrative of a fixture that can be used to facilitate the depositing of
composite material onto
mandrel 701 in step 605 of method 601.
Referring also to Figure 9A, one non-limiting example embodiment of winding
jig 805 for
performing at least step 605 of method 601 is illustrated. Winding jig 805 is
mounted to a
plafform 817 that can be translated along a prescribed path. A first end
portion of slit 819 can
be secured to a mount 821 that is secured to platform 817. Slit 819 is
positioned through an
opening 823 in coupling 815b. A second end portion of slit 819 can remain part
of a roll 827 of
composite material. In one embodiment, a plurality of cutting members cut roll
827 of composite
material into a plurality of slits 819 at prescribed widths, each slit 819
being fed to different
winding jigs 805. Platform 817 is biased in direction 825 by a constant
tension member such
that slit 819 is held in tension. Mount 821 and roll 817 are positioned so
that slit 819 is oriented
at a desired angle relative to mandrel 701. In the illustrated embodiment, the
desired angle of
slit 819 is 45 degrees; however, slit 819 can be oriented at any desired
angle.
Referring also to Figure 9B, the operation of winding jig 805 is illustrated.
Driver 809 is
operated so as to cause mandrel 701 to rotate, which causes slit 819 to wrap
around mandrel
Page 8
CA 02844136 2014-02-26
701. As slit 819 wraps around mandrel 701, platform 817 is pulled toward roll
817 in direction
829 while the wrap angle is maintained.
Referring also to Figure 10, another example embodiment of a winding jig 1005
for wrapping
composite material on each mandrel 701 in step 605 is illustrated. Winding jig
1005 is
substantially similar to winding jig 805; however, winding jig 1005 is
configured so that mandrel
701 is held stationary while a material placement head 1001 moves around
mandrel 701, as
well as translates along an axis of mandrel 701, such as in directions 1007
and 1009,
respectively. Material placement head 1001 is configured to feed composite
material while
moving in a prescribed path. In such an embodiment, slit 819 can be secured at
a stationary
mount 1003 so that slit 819 can be placed in tension by material placement
head 1001 as slit
819 is wrapped around mandrel 701.
Referring also to Figure 11, another example embodiment of a winding jig 1105
for wrapping
composite material on each mandrel 701 in step 605 is illustrated. Winding jig
1105 is
substantially similar to winding jig 1005; however, winding jig 1105 is
configured so that mandrel
701 is rotated in a direction 1107 while material placement head 1001
translates along an axis
of mandrel 701 corresponding with direction 1009. In such an embodiment, slit
819 can be
secured to coupling 815a, for example, so that tension can be formed in slit
819 as material
placement head 1001 translates and mandrel 701 rotates.
In another example embodiment, the winding jig is configured to translate
along a direction
corresponding with the axis of mandrel 701 while material placement head 1001
rotates but
does not translate.
It should be appreciated that the winding jig can be configured in any
combination of the
configurations described herein. For example, mandrel 701 can rotate in a
first rotational
direction while material placement head 1001 rotates around mandrel 701 in an
opposite
direction to that of the first rotational direction. Further, either mandrel
701 can translate along
its axis or the material placement head can translate in a direction
corresponding to the mandrel
axis, or any combination thereof.
It should be appreciated that the exact system and method for depositing raw
composite
material on mandrel 701 can be dependent at least upon the material form of
the raw composite
material.
Page 9
CA 02844136 2014-02-26
Referring also to Figure 12, one technique of wrapping uncured composite
material around
mandrel 701 utilizes a filament winding process. A continuous, resin-
impregnated fiber 1401,
extending from a filament winding machine 1403, is wound about mandrel 701.
The resin can
be either a thermosetting or thermoplastic resin and becomes the polymeric
matrix of tube 403
upon curing. The material placement process may be conducted in a variety of
processes; for
example, mandrel 701 can move axially while a spool of fiber 1401 rotates
around the mandrel
701, as indicated by an arrow 1407. Alternatively, a spool or a plurality of
spools of material
could rotate around mandrel 701. Relative motion of the material dispensing
mechanism to
mandrel 701 is inferred. As fiber 1401 is wound onto mandrel 701 by filament
winding machine
1403, a helical shaped pattern is formed. One or more plies 1409 of fiber
1401, in desired
orientations with respect to mandrel 701, are wound onto mandrel 701 to form
the basic
geometry of tube 403. The angle of which fiber 1401 is wound about mandrel 701
may vary
along the length of the mandrel 701 in order to customize the strength of core
401. For
example, the angle of the fiber 1401 may be dynamically changed during the
material
placement process in order to customize a compressive strength of the core.
Note that, in the
illustrated embodiment, mandrel 701 exhibits a size and shape corresponding to
cell 405 (see
Figure 4 or 5). It should be further noted; however, that the present
disclosure is not limited to
the particular illustrated configurations of filament winding machine 1403 or
mandrel 701.
Mandrel 701 and the one or more plies 1409 that have been filament wound onto
mandrel 701
are subsequently assembled with other mandrels and plies, as will be discussed
in greater
detail herein, to form core 401 (shown in Figure 4). It should further be
appreciated that upon
cutting of plies 1409 and the mandrel 701, the material may have a tendency to
un-wind. A
band of material, potentially adhesive or fibrous, may be used to keep fiber
1401 from
unraveling upon cutting of the plies 1409 and the mandrel 701. An adhesive
material with
unidirectional fibers could be used to band the fiber 1401 on mandrel 701.
Further, the band
can be selectively located and used to provide extra support for a subsequent
post processing
procedure of the core, such as a machining process.
In yet another example technique of performing step 605 of method 601, shown
in Figure 13,
wrapping uncured composite material around mandrel 701 is performed using a
fiber placement
process.
A continuous, resin-impregnated tow 1301 (only one labeled for clarity) of
approximately, but not limited to, 1000 fibers is applied to a mandrel 701 by
a fiber placement
machine 1305. It should be appreciated that tow 1301 may also be portions of a
full tow; for
example, tow 1301 may be a half tow of 500 fibers. In lieu of a tow 1301, a
tape of fibers, cut to
Page 10
CA 02844136 2014-02-26
a prescribed width, may be used. A pre-cut tape of fibers may be referred to
as a "slit-tape." A
slit-tape allows the user to more closely control the width dimension, as
compared to a tow of
fibers. Exemplary prescribed widths of slit-tape include 1/8" and 1/4", to
name a few. The resin
can be a thermosetting or thermoplastic resin, to name two examples, and
becomes the
polymeric matrix of tube 403 upon curing. During the fiber placement process,
mandrel 701 can
move axially while tow 1301 rotates around the mandrel 701, as indicated by an
arrow 1307. As
tow 1301 is applied to mandrel 701 by fiber placement machine 1305, a helical
shaped pattern
is formed. One or more plies 1309 of tow 1301, in desired orientations with
respect to mandrel
701, are wound onto mandrel 701. In one embodiment, one or more non-helical
plies layers
may be assembled on mandrel 701 to customize mechanical properties in certain
directions. It
should be appreciated that more than one tow 1301 or slit-tape of different
materials may be
used. Note that, in the illustrated embodiment, mandrel 1303 exhibits a size
and shape
corresponding to cell 405 (see Figure 4 or 5). It should be further noted,
however, that the
present disclosure is not limited to the particular illustrated configurations
of fiber placement
machine 1305 or mandrel 701. Mandrel 701 and the one or more plies 1309 that
have been
fiber placed onto mandrel 701 are subsequently assembled with other mandrels
and plies, as
will be discussed in greater detail below, to form core 401 (shown in Figure
4).
Referring now also to Figures 14-16, one example embodiment of step 605
includes wrapping
mandrel 701 with a broadgood form of slit 819 in such a procedure that results
in solid
passageway or "closed cell" geometry. Namely, the broadgood form of slit 819
has a width W1
that is selected to prevent a gap or space in the slit 819 after slit 819 is
wrapped around
mandrel 701. Further, as slit 819 is wrapped around mandrel 701, a continuous
seam 831 is
formed; however, seam 831 is not a gap or space in the material, rather seam
831 represents
an abutment of helically wrapped material, such as slit 819, which is an
example of a
customized width broadgood composite material. In contrast, the wrapping of a
mandrel with
composite material that produces a gap or space in the material, or an "open
cell" geometry, as
described with regard to Figures 12 and 13, can have undesirable attributes in
certain
implementations. For example, the "open cell" embodiment may be limited by the
widths of the
tows or slits having to be consistent, resulting in having only a fixed whole
number of tows for a
given spacing and angle, and the gaps having to be a uniform width. The result
is only having a
fixed whole number of materials for a given spacing and angle. The angle with
which the tow or
slit is wrapped cannot be varied infinitely and still retain a specific tow or
slit width and spacing.
Furthermore, an "open cell" geometry core can be undesirable in some panel
implementations
Page 11
CA 02844136 2014-02-26
because of insufficient bond surface at the core/skin interface. Further, for
a given mandrel
geometry there are a limited number of tow or slit width and gap combinations
that will satisfy
construction of the core tube for a given wrap angle.
Referring in particular to Figures 15 and 16, the orientation fibers 1501 of
slit 819 is
implementation specific.
In the embodiment illustrated in Figure 15, fibers 1501 are
unidirectional such that all the fibers extend in a direction corresponding
with the length of the
slit 819. In the embodiment illustrated in Figure 16, fibers 1501 are
multidirectional so as to
form a fabric configuration.
Still referring to Figures 14-16, a nominal width W1 of slit 819 can be
calculated by multiplying
the circumference of the exterior surface of mandrel 701 by the cosine of the
wrap angle Al.
One major advantage of using slit 819 to wrap mandrel 701 without material
gaps is that the
angle Al can be customized for the core implementation while simply adjusting
for the width W1
of slit 819. Furthermore, the slit 819 can be cut off from a much wider roll
of bulk raw material,
such that the customization of width W1 can be simply a matter of adjusting
the cutting tool to
provide the implementation specific width. Customizing the angle Al allows a
user to tailor the
physical properties of the core by orienting the fibers 1501 in a direction to
produce said
physical properties. Referring briefly to Figure 17, an example cutting tool
1701 is illustrated.
Cutting tool 1701 can have a plurality of cutting members 1703, such as
blades, that can be
oriented to cut slits 819 at prescribed widths from a raw material roll 1705.
Each slit 819 can be
communicated to a winding jig 805, as discussed further herein. Cutting tool
1701 is especially
well suited for cutting slits 819 having unidirectional fibers such that
cutting members 1703 cut
the raw material along between adjacent fibers. In contrast, a cutting tool
having a male/female
press cutting members may be better suited for cutting slits 819 having
multidirectional fibers.
Still referring to Figures 14-16, the "closed cell" geometry core produced by
wrapping
broadgood composite material in step 605 of method 601 enables the use of much
thinner and
lighter composite material, thereby producing a core with very low density.
Further, the "closed
cell" geometry core can have significantly higher stiffness and strength than
is achievable with
"open cell" geometry core. Furthermore, "closed cell" geometry core is fully
tailorable.
In another embodiment of step 605 of method 601, mandrel 701 is wrapped
multiple times to
produce multiple layers of composite material layers. In such an embodiment,
the fiber
Page 12
CA 02844136 2014-02-26
orientation, wrap angle, and/or wrapping direction can be varied to produce
tailored mechanical
and physical properties.
In some situations it may be desirable to provide ventilation and/or drainage
in the composite
core, such as in a wing member of an aircraft that also functions as a fuel
tank. In such an
embodiment, step 605 of method 601 can also include creating perforations in
the raw material
or slit 819. The perforations can be created by any variety of methods; one
method can be
running the raw material or slit 819 over a spiked wheel or spiked roller
support, for example.
Referring again to Figures 6 and 7, step 607 of method 601 includes assembling
the wrapped
mandrels. Step 607 can further include assembling and inserting the wrapped
mandrels in a
tool or other fixture. The exact configuration of the tool is implementation
specific. Referring
now also to Figures 18-20, an example of a tool 1201 is illustrated. Tool 1201
is configured to
produce a hexagonal shaped core member; however, tool 1201 can be configured
to provide
any desirable shape. For example, alternative shapes of tool 1201 can be
configured to
produce circular, square, rectangular, or even part customized core shapes. In
the illustrated
embodiment, the plurality of mandrels 701 having wrapped composite material
are assembled
onto partial tool members 1203a-1203f in a pyramid shape. In one embodiment,
system 801 is
configured to automate the assembly and stacking of wrapped mandrels, as shown
in Figure 7.
In another embodiment, the assembly and stacking of wrapped mandrels can be
performed
manually. Each partial tool member 1203a-1203f can include apertures 1205 to
control and
tailor any thermal expansion of the partial tool member 1203a-1203f during the
cure process. In
one embodiment, each partial tool member 1203a-1203f is stacked with seven
levels of
wrapped mandrels. Upon assembling each partial tool member 1203a-1203f and
their wrapped
mandrels, one additional wrapped mandrel 1205 is located in the center.
However, it should be
appreciated that each partial tool member 1203a-1203f may be stacked with
wrapped mandrels
and assembled in a variety of ways.
In one example embodiment, tool 1201 includes a bladder 1207 that is
configured to inflate to
provide a prescribed inward pressure upon the assembly of wrapped mandrels
701. However, it
should be appreciated that the present disclosure contemplates other methods
of providing
pressure to the composite material wrapped around each mandrel 701 during the
curing
process, such as mechanical pressure generating devices.
Page 13
CA 02844136 2014-02-26
In another embodiment, curing pressure can be generated by the thermal
expansion of the
mandrels 701. In such an embodiment, tool 1201 can include a rigid
constraining structure in
lieu of bladder 1207. The heating of the mandrels 701 causes thermal
expansion, which
generates pressure at the composite material between mandrels 701.
Tool 1201 can include a blower 1209 for generating an airflow 1211 and evenly
distributing the
airflow through the interiors of the plurality of mandrels 701. In an
alternative embodiment, a
fluid, such as an oil, is circulated through the interiors of the plurality of
mandrels 701. Step 609
can include heating the wrapped mandrels within tool 1201 for a prescribed
duration in
accordance with the cure requirement of the composite system. An oven can be
used to
generate that requisite heat, for example. Airflow 1211 can improve the
heating rate and heat
distribution to the composite material wrapped around each mandrel 701, as
such; it is
particularly desirable to have an interior opening through each mandrel 701
that is sized to
accommodate a prescribed amount of airflow. Bladder 1207 can be controlled by
a controller
1213 so as to tailor the amount and timing of pressure exerted at the cell
walls of composite
material between mandrels 701 within tool 1201.
Referring again to Figure 6, step 609 of method 601 includes curing the
composite material
wrapped around the mandrels 701 to form the cured composite core 401. As
discussed further
above, the uncured composite material around each mandrel 701 is cured by
subjecting the
assembly to the requisite temperature and pressure. As discussed above, the
temperature and
rate of temperature change of the composite material can be controlled in part
by blowing hot air
through the interior of mandrels 701. During the curing process of step 609,
the temperature
and pressure exerted upon the composite material is implementation specific.
Bladder 1207
can be controlled by controller 1213 so as to tailor the amount and timing of
pressure exerted at
the cell walls of composite material between mandrels 701 within tool 1201.
For example,
bladder 1207 can be controlled by controller 1213 to change the amount of
pressure during a
viscosity change of the resin in the composite material.
After the cure cycle is complete, a composite core 401 is achieved as the
uncured composite
material around each mandrel 701 becomes rigidly bonded to each adjacent tube
403. It should
be noted that composite core 401 that is formed by wrapping mandrels 701 with
unidirectional
fiber slits 819 at a prescribed angle produces composite core 401 that has
cross-linked fibers at
the cell walls. For example, multiple mandrels 701 wrapped at a wrap angle of
+45 degrees
with slits 819 having unidirectional fibers will produce cured composite core
401 with cell walls
Page 14
CA 02844136 2014-02-26
having two plies of fibers at 90 degrees to each other. This unique result of
the method and
system of the present disclosure produces a very lightweight and strong
composite core 401.
Still referring to Figure 6, step 611 of method 601 includes cooling mandrels
701 and removing
mandrels 701 from the composite core 401.
The systems and methods disclosed herein include one or more of the following
advantages.
The method of the present disclosure allows for the efficient production of
composite core,
which can reduce the cost of the composite core. Further, wrapping mandrels
with
unidirectional slits provides tailorability of the composite core. Further,
the method of curing
composite core results in a high quality composite core.
The particular embodiments disclosed herein are illustrative only, as the
system and method
may be modified and practiced in different but equivalent manners apparent to
those skilled in
the art having the benefit of the teachings herein. Modifications, additions,
or omissions may be
made to the system described herein without departing from the scope of the
invention. The
components of the system may be integrated or separated. Moreover, the
operations of the
system may be performed by more, fewer, or other components.
Furthermore, no limitations are intended to the details of construction or
design herein shown,
other than as described in the claims below. It is therefore evident that the
particular
embodiments disclosed above may be altered or modified and all such variations
are
considered within the scope of the disclosure. Accordingly, the protection
sought herein is as
set forth in the claims below.
Page 15
