KR102335596B1 - Dual-matrix composite member having shape restoring force and reconfigurable deployabel tube including the same - Google Patents

Abstract

A double resin composite member having a shape restoring force and a variable development type tube including the same are disclosed, and the double resin composite member having a shape restoring force according to an embodiment of the present application, an inner carbon fiber layer made of a material containing carbon fibers, the A hinge portion provided on the outer surface of the inner carbon fiber layer and a rigid portion provided in a portion where the hinge portion is not provided on the outer surface of the inner carbon fiber layer, wherein the hinge portion is provided with a material having elastic restoring force against bending, the The double resin composite member may be formed to correspond to the folded area.

Description

DUAL-MATRIX COMPOSITE MEMBER HAVING SHAPE RESTORING FORCE AND RECONFIGURABLE DEPLOYABEL TUBE INCLUDING THE SAME}

The present application relates to a double resin composite member having a shape restoring force and a variable development type tube including the same.

Recently, as the weather environment is rapidly changing around the world, development of high-performance artificial satellites is being attempted for accurate and rapid global weather prediction. Specifically, research on super-large space structures for the advancement of satellite missions and maximization of performance is being conducted mainly in advanced space development countries such as the United States, Europe, and Japan.

In particular, structure technology that develops on its own in space orbit can be said to be a core technology required for all space structures such as communication/image aperture antennas and solar panels.

In the case of a space launch vehicle on which satellites, etc. are mounted, there is a limit to the internal space of the fairing and the payload, so the volume or weight of the payload mounted inside is strictly limited.

However, since most of the conventional deployable space structures follow the mechanical deployment method, the weight of the deployment device occupies a relatively large proportion, and the deployment mechanism parts sometimes account for more than 90% of the weight of the entire structure.

According to this conventional mechanical deployment method, excessive weight problems, storage space securing problems, etc. always existed, and enormous R&D costs were inevitably invested to solve these problems.

On the other hand, the existing composite material skin structure that can be used for large-scale deployment structures (eg, Antenna, Reflector, Solar array, etc.) mounted on space launch vehicles, etc. Since it has a disadvantage in that the bending properties are lowered in terms of the surface, it is necessary to implement a skin structure in which rigidity is constant and free shape deformation is possible.

The technology that is the background of the present application is disclosed in Korean Patent Publication No. 10-1868768.

An object of the present application is to provide a double resin composite member having a shape restoring force capable of freely deforming a shape while maintaining rigidity and a variable deployment type tube including the same in order to solve the problems of the prior art.

However, the technical problems to be achieved by the embodiments of the present application are not limited to the technical problems described above, and other technical problems may exist.

As a technical means for achieving the above technical problem, the double resin composite member having shape restoring force according to an embodiment of the present application is provided on the outer surface of the inner carbon fiber layer and the inner carbon fiber layer made of a material containing carbon fibers It may include a hinge portion and a rigid portion provided in a portion not provided with the hinge portion on the outer surface of the inner carbon fiber layer.

In addition, the hinge part may be made of a material having an elastic restoring force against bending, and may be formed to correspond to an area in which the double resin composite member is folded.

In addition, the rigid portion may include a plurality of rigid members having a closed cross-sectional shape based on a cross-section orthogonal to the inner and outer directions, and disposed on the outer surface of the inner carbon fiber layer at a distance from each other.

In addition, the hinge part may be provided in a gap region between the plurality of rigid members.

In addition, the hinge part may be made of a material including at least one of a shape memory polymer (SMP) resin and a silicone resin.

In addition, the hinge part is deformable in a first state that is low temperature based on a preset temperature, and is restored to an initial shape in a second state that is a high temperature based on the preset temperature. It contains a shape memory polymer (SMP) resin. It may be made of a material that

In addition, the rigid part may be made of a material including an epoxy resin.

In addition, the inner carbon fiber layer may be made of a material including WF (Woven Fabric) carbon fibers.

In addition, the rigid part may include an epoxy resin in the form of a film to prevent at least a portion of the hinge part from being impregnated in the inner carbon fiber layer.

In addition, in the double resin composite member having shape restoring force according to an embodiment of the present application, the rigid part including the epoxy resin in the film form is disposed on the outer surface of the inner carbon fiber layer, and the hinge of the outer surface of the inner carbon fiber layer It may be formed by applying a shape restoration material made of a material including at least one of a shape memory polymer (SMP) resin and a silicone resin to an area corresponding to the branch, and then curing the hinge part and the rigid part.

In addition, the curing is a temperature at which the shape restoration material corresponding to the hinge part is cured at a preset first curing temperature or a temperature below the first curing temperature, and then the epoxy resin in the form of a film can be cured. At a second curing temperature, the epoxy resin in the film form corresponding to the rigid portion may be cured.

In addition, the double resin composite member having a shape restoring force according to an embodiment of the present application is provided on the outer surfaces of the hinge part and the rigid part, and may include an outer carbon fiber layer made of a material including carbon fibers.

On the other hand, the variable deployment type tube including a double resin composite member having a shape restoring force according to an embodiment of the present application is in the form of a tube having a hollow inside, but the tube body and the tube including a double resin composite member having the shape restoring force It may include a spar arranged to extend in the longitudinal direction on the inside of the body.

In addition, in the variable deployment type tube including a double resin composite member having shape restoring force according to an embodiment of the present application, the hinge portion of the tube body is made of a material containing a shape memory polymer (SMP) resin or the spar has a shape It may be made of a shape memory material having a restoring force.

In addition, the spar may have a shape restoring force to be restored to the initial shape in a high temperature state based on a preset temperature with a shape extending along the longitudinal direction of the tube body as an initial shape.

In addition, the tube body may include a plurality of hinge portions disposed on the outer surface of the inner carbon fiber layer to be spaced apart from each other at a predetermined longitudinal distance along the longitudinal direction of the tube body.

In addition, the tube body is deployed to extend along the longitudinal direction of the tube body or along the longitudinal direction in a form in which one longitudinal end of the tube body is disposed on the inside and the other longitudinal end of the tube body is disposed on the outside It can be folded.

In addition, in the tube body, the longitudinal distance between the plurality of hinge parts disposed close to one end in the longitudinal direction may be greater than or equal to the longitudinal distance between the plurality of hinge parts disposed close to the other end in the longitudinal direction. .

In addition, when each of the plurality of hinge parts is folded at a preset angle, the tube body is bent along the longitudinal direction to form a preset polygonal receiving pattern and received in the longitudinal direction between the plurality of hinge parts The interval can be determined. have.

In addition, the tube body is folded so as to form a plurality of layers of a polygonal shape according to the polygonal accommodation pattern and to be wound on top of each other, and the plurality of hinges are arranged to correspond to the outer layer of the plurality of layers. It may be provided to increase the longitudinal distance between the hinge parts.

In addition, the plurality of hinge parts may be arranged to be spaced apart from each other at a predetermined circumferential distance from the outer surface of the inner carbon fiber layer along the circumferential direction of the inner carbon fiber layer.

In addition, the polygonal accommodation pattern may be provided such that, compared to the tube accommodated by the circular accommodation pattern, the formation of wrinkles when the variable development type tube is accommodated is reduced, and the storage volume of the variable development type tube is reduced.

The above-described problem solving means are merely exemplary, and should not be construed as limiting the present application. In addition to the exemplary embodiments described above, additional embodiments may exist in the drawings and detailed description.

According to the problem solving means of the present application described above, it is possible to provide a double resin composite member having a shape restoring force capable of freely deforming a shape while maintaining rigidity, and a variable development type tube including the same.

According to the above-described problem solving means of the present application, by using a member having a shape restoring force without a separate driving (deployment) device or connection device for shape deformation of the structure, shape deformation of the structure can be controlled through temperature control. It is possible to reduce the overall weight of the structure.

According to the above-described problem solving means of the present application, the development speed and shape can be adjusted as necessary by designing variously the region pattern of the hinge part of the variable deployment type tube including the double resin composite member having shape restoring force.

According to the above-mentioned means for solving the problems of the present application, it is applied to the development of extra-large/ultra-light space structures, and compared to the existing space structures, the weight reduction (weight reduction) effect, the stowage efficiency improvement effect, and the consequent reduction of the launch cost are applied to the space structure. Development cost can be reduced.

According to the above-described problem solving means of the present application, a double resin composite member having a shape restoring force can be utilized in tents and ground antennas that are easy to carry and deploy.

However, the effects obtainable herein are not limited to the above-described effects, and other effects may exist.

1 is a schematic cross-sectional view of a double resin composite member having a shape restoring force according to an embodiment of the present application.
2 is a conceptual diagram for explaining a process of forming a double resin composite member having a shape restoring force through application and curing of a shape restoring material according to an embodiment of the present application.
3 is a schematic perspective view of a variable deployment type tube including a double resin composite member having a shape restoring force according to an embodiment of the present application.
4 is a schematic perspective view of a variable deployment type tube including a double resin composite member having a shape restoring force according to an embodiment of the present application including a plurality of stiffeners inside the tube body.
5 is a conceptual diagram for explaining the setting of a longitudinal interval between a plurality of hinge parts disposed along the longitudinal direction on the outer surface of the inner carbon fiber layer.
6 is a conceptual diagram for explaining the shape deformation of a variable deployment type tube including a double resin composite member having a shape restoring force according to an embodiment of the present application.
7 is a conceptual diagram for explaining a polygonal accommodation pattern for a variable deployment type tube including a double resin composite member having a shape restoring force according to an embodiment of the present application.
8 is a conceptual diagram for explaining the setting of a longitudinal interval of a hinge portion between a layer and a next layer according to a polygonal accommodation pattern.
9 is a conceptual diagram for explaining that wrinkle formation during storage is reduced by a polygonal accommodation pattern for a variable-deployable tube including a double resin composite member having a shape restoring force according to an embodiment of the present application.
10 is a graph showing the results of simulating the wrinkle reduction effect by the polygonal accommodation pattern as an experimental example in connection with a variable deployment type tube including a double resin composite member having shape restoring force according to an embodiment of the present application. .
11 is an experimental example in connection with a variable-deployable tube including a double resin composite member having a shape restoring force according to an embodiment of the present application. .

Hereinafter, embodiments of the present application will be described in detail with reference to the accompanying drawings so that those of ordinary skill in the art can easily implement them. However, the present application may be implemented in several different forms and is not limited to the embodiments described herein. And in order to clearly explain the present application in the drawings, parts irrelevant to the description are omitted, and similar reference numerals are attached to similar parts throughout the specification.

Throughout this specification, when a part is "connected" with another part, it is not only "directly connected" but also "electrically connected" or "indirectly connected" with another element interposed therebetween. "Including cases where

Throughout this specification, when a member is positioned “on”, “on”, “on”, “on”, “under”, “under”, or “under” another member, this means that a member is positioned on the other member. It includes not only the case where they are in contact, but also the case where another member exists between two members.

Throughout this specification, when a part "includes" a certain component, it means that other components may be further included, rather than excluding other components, unless otherwise stated.

For reference, the terms (length direction, circumferential direction, etc.) related to the direction or position in the description of the embodiment of the present application are described based on the arrangement state of each component shown in the drawings. For example, when viewed in FIG. 3 , the longitudinal direction may be from 2 o'clock to 8 o'clock. However, this direction setting may vary depending on the arrangement state of the apparatus of the present application. For example, if necessary, the device of the present application may be disposed so that the longitudinal direction of FIG. 3 faces a vertical direction (up and down direction), and in another example, the device of the present application may be disposed such that the longitudinal direction of FIG. 3 faces an oblique inclination direction. can

The present application relates to a double resin composite member having a shape restoring force and a variable development type tube including the same.

First, with reference to FIGS. 1 and 2 , the structure and manufacture (formation) of a double resin composite member 1 having a shape restoring force according to an embodiment of the present application (hereinafter referred to as 'composite member 1'). The method will be described in detail, and the variable deployment type tube 100 including the double resin composite member having shape restoring force according to an embodiment of the present application including the composite member 1 will be described.

1 is a schematic cross-sectional view of a double resin composite member having a shape restoring force according to an embodiment of the present application.

Referring to FIG. 1 , the composite member 1 may include an inner carbon fiber layer 11 , a hinge portion 12 , a rigid portion 13 , and an outer carbon fiber layer 14 .

The inner carbon fiber layer 11 may be made of a material including carbon fibers. According to an embodiment of the present application, the inner carbon fiber layer 11 may be made of a material including WF (Woven Fabric) carbon fibers.

The hinge part 12 is provided on the outer surface of the inner carbon fiber layer 11 and may be made of a material having elastic restoring force against bending. For example, the hinge part 12 may be made of a material including at least one of a shape memory polymer (SMP) resin and a silicone resin to have elastic restoring force against bending.

In addition, the hinge part 12 may be formed to correspond to the area in which the composite member 1 is folded. In the description of the embodiment of the present application, when the composite member 1 is folded, the composite member 1 is wound in a predetermined direction (eg, the longitudinal direction of the composite member 1, etc.) or folded ( It is desirable to be broadly understood as a concept that includes all of the bending).

According to an embodiment of the present application, the hinge part 12 is deformable in a first state that is low temperature based on a preset temperature, and is restored to an initial shape in a second state that is high based on a preset temperature. SMP) may be made of a material containing resin.

In summary, the hinge part 120 may include a shape restoring material having a shape restoring force. In other words, according to an embodiment of the present application, the shape restoration material corresponding to the hinge part 120 may be made of a material including at least one of a shape memory polymer (SMP) resin and a silicone resin.

Specifically, when the hinge part 120 is made of a material containing a shape memory polymer (SMP) resin, the shape memory polymer (SMP) memorizes the initial shape and deforms when the glass transition temperature (Tg) or higher It is a polymer that returns to its original form from its original form. The mechanism to recover the deformation can be understood as a change in entropy from the elasticity of the shape memory polymer. Chains and reversible molecules are complex. Molecular chains, once hardened, are irreversible and play a role in preventing free movement.

On the other hand, the reversible phase occupies a large proportion in shape memory polymers and plays an elastic role in deformation and recovery. When a predetermined temperature (eg, the glass transition temperature described above) or higher is reached, the reversible phase becomes in the form of a fluid and the flowability is improved. When an external force is applied above the glass transition temperature, the molecular chains of the shape memory polymer are aligned, which leads to a decrease in entropy. At this time, if the temperature is rapidly lowered below the glass transition temperature, the unstable reversible phase becomes stable again and maintains its deformed shape.

In addition, if the temperature is raised above the glass transition temperature by applying heat again, the molecular chain moves through the stored strain energy and returns to its original shape.

These shape memory polymers have the advantages of large extensibility, high elastic deformation (stress of 200% or more), low cost, low density, a wide range of temperature control, and easy processing. Fibers, trans-isoprene, styrene-butadiene copolymers, and some polyurethanes may be used.

The rigid portion 13 may be provided in a portion where the hinge portion 12 is not provided on the outer surface of the inner carbon fiber layer 11 . According to an embodiment of the present application, the rigid portion 13 may be made of a material including an epoxy resin.

In addition, according to an embodiment of the present application, the rigid portion 13 may include an epoxy resin in the form of a film to prevent at least a portion of the hinge portion 12 from being impregnated in the inner carbon fiber layer 11 .

The outer carbon fiber layer 14 is provided on the outer surfaces of the hinge part 12 and the rigid part 13, and may be made of a material including carbon fibers. According to an embodiment of the present application, the outer carbon fiber layer 14 may be made of a material (eg, WF (Woven Fabric) carbon fiber, etc.) corresponding to the inner carbon fiber layer 11, but is limited thereto. it is not

That is, in the composite member 1, the rigid part 13, which is a structural part having rigidity in the inner carbon fiber layer 11 including carbon fibers, is formed of an epoxy resin and is provided to serve as a hinge between the rigid parts 13. The hinge part 12 may be a dual-matrix composite skin formed of a shape memory polymer (SMP) or a silicone resin. In addition, the composite member 1 may be in the form of a hollow boom having a cross section of a closed shape (eg, circular) shape.

In summary, the composite member 1 has a rigid structure (rigid part 13) formed of epoxy resin, etc. and a hinge (SMPs or silicon) part (hinge part 12) having a predetermined ductility. - It may be a skin member to which a composite matrix) is applied. In other words, the composite member 1 applies an epoxy resin (resin) to the fixed part on the carbon fiber and a resin having shape restoring force to the deformable part serving as a hinge, thereby maintaining the rigidity of the structure high and maintaining the correct structural shape. It is possible to allow free shape transformation while allowing

In other words, the composite member 1 maintains the rigidity of the composite member 1 (skin structure) by providing the rigid portion 13 and the hinge portion 12 according to a predetermined pattern, while maintaining a low temperature based on a preset temperature. In the first state, the hinge part 12 is deformable, and in the second state, which is a high temperature based on a preset temperature, the hinge part 12 can be restored to its initial shape, thereby restoring the shape of the hinge part 12 . It may be possible to develop the composite member (1) through.

2 is a conceptual diagram for explaining a process of forming a double resin composite member having a shape restoring force through application and curing of a shape restoring material according to an embodiment of the present application.

Referring to FIG. 2 , the rigid portion 13 may have a closed cross-sectional shape (eg, a rectangular cross-sectional shape with reference to FIG. 2 ) based on a cross-section orthogonal to the inner and outer directions of the composite member 1 . In addition, the rigid portion 13 may include a plurality of rigid members disposed on the outer surface of the inner carbon fiber layer 11 at a distance from each other. In this regard, the hinge part 12 may be provided in the spaced region between the plurality of rigid members. Specifically, referring to FIG. 2 , the hinge part 12 may be provided in a cross shape in the spaced region between the four rigid members disposed to be spaced apart from each other, but is not limited thereto.

In addition, in the composite member 1, a rigid portion 13 containing an epoxy resin in the form of a film is disposed on the outer surface of the inner carbon fiber layer 11, and corresponding to the hinge portion 12 of the outer surface of the inner carbon fiber layer 11 After the shape restoration material is applied to the region, it may be formed by hardening the hinge portion 12 and the rigid portion 13 .

In this regard, when a liquid type epoxy resin is used for the rigid part 13, as the viscosity of the liquid type epoxy resin decreases during the curing process of the composite member 1, a portion of the epoxy resin serves as a hinge. Since there is a problem that it can flow into the hinge part 12, which is a part, the method using the liquid type epoxy resin makes it difficult to reach the preset rigidity level as well as the pattern of the hinge part 12 provided on the outer surface of the carbon fiber There is a limitation in that it is difficult to implement as originally designed. In addition, there is a disadvantage in that it is difficult to uniformly maintain the thickness and rigidity of the cured composite member 1 because the epoxy resin is non-uniformly distributed.

On the other hand, according to an embodiment of the present application, when an epoxy resin in the form of a film is used for the rigid portion 13, the epoxy resin in the form of a film has flexible characteristics in an uncured state, so it is not limited to a flat plate form, but a boom shape and There is an advantage in that it is easy to apply to a three-dimensional structure having a curvature. In addition, since the epoxy resin in the form of a film is in the form of a multi-layered sheet each having a predetermined thickness, between the carbon fiber layers (for example, the inner carbon fiber layer 11 and the outer carbon fiber side 14) Between) by controlling the number of sheets laminated on the composite member (1) has the advantage of being able to adjust the overall rigidity of the applied structure.

In addition, if the above-mentioned film-type epoxy resin is used for the rigid part 13, the pattern shape of the rigid part 13 can be implemented in various ways, and the original pattern can be maintained while curing (between the curing process), and the film Since the thickness is relatively constant, the entire thickness of the cured composite member 1 can be maintained uniformly. In addition, the epoxy resin in the form of a film is positioned and adhered between the layers of carbon fibers (for example, between the inner carbon fiber layer 11 and the outer carbon fiber side 14) to form the hinge portion 12, which is a flexible structural region. It is possible to prevent the shape restoration material (in other words, silicone or shape memory polymer resin) used for this from being impregnated into the carbon fiber layer on the side of the rigid portion 13 .

In addition, the hinge part 12 made of a material containing at least one of silicone or shape memory polymer resin and the rigid part 13 including the epoxy resin in the form of a film have different curing temperatures. Specifically, since the silicone or shape memory polymer resin of the hinge part 12 can be cured at a relatively low temperature compared to the temperature at which the epoxy resin of the rigid part 13 is cured in a relatively short time, the hinge part 12 and the rigid part It may be possible to manufacture the composite member (1) of the present application based on continuous curing through adjustment of the curing cycle in consideration of the relative difference in curing temperature in (13).

The manufacturing process of the composite member 1 according to an embodiment of the present application described above will be described in order as follows. First, an epoxy resin in the form of a film is positioned according to the pattern of the rigid portion 13 set in advance on the inner carbon fiber layer 11 made of a material containing WF (Woven Fabric) carbon fiber. After that, another WF (Woven Fabric) carbon fiber corresponding to the outer carbon fiber layer 14 is placed on (upper side) of the disposed film-type epoxy resin to form a WF (Woven Fabric) carbon fiber, an epoxy resin, and a WF (Woven) carbon fiber. Fabric) The carbon fibers are stacked in an alternating repeating order. After WF (Woven Fabric) carbon fiber and epoxy resin are alternately laminated in a sandwich form, silicone or shape memory polymer resin, which is a shape restoration material, along the region corresponding to the hinge part 12 located between the rigid part 13 patterns. to spread

After that, silicone or shape memory polymer resin, which is a shape restoration material of the hinge part 12, is first cured at room temperature or a preset temperature (eg, glass transition temperature, Tg), and then the epoxy resin in the form of a film of the rigid part 13 The epoxy resin can be subsequently cured by applying heat to the temperature at which it begins to cure. In other words, the curing process applied after laminating and applying each material in the manufacturing process of the composite member 1 of the present application is a preset first curing temperature (eg, glass transition temperature, Tg) or first curing After curing the shape restoration material corresponding to the hinge part 12 at a temperature below the temperature (for example, room temperature), at the second curing temperature, which is a temperature at which the epoxy resin in the form of a film of the rigid part 13 can be cured It may include a step-by-step process of curing the epoxy resin in the form of a film corresponding to the rigid portion 13 . Here, the second curing temperature, which is a temperature at which the film-type epoxy resin can be cured, may be higher than the first curing temperature for curing the shape restoration material.

In addition, referring to FIG. 2 , the composite member 1 includes a hinge part 12 extending in the longitudinal direction (from 3 o'clock to 9 o'clock with reference to FIG. 2 ) and a direction orthogonal to the longitudinal direction (refer to FIG. 2 ). It may include a flexible structure formed in a two-dimensional array including the hinge portion 12 extending in the 12 o'clock to 6 o'clock direction). As will be described later, in the process of rolling (in other words, folding) the variable-deployable tube 100 including the composite member 1 for storage, the hinge part 120 is folded in the longitudinal direction and the longitudinal direction It may be related to reducing the storage volume of the variable-deployable tube 100 through the hinge part 120 provided to be partially bent even along the circumferential direction of the variable-deployable tube 100 orthogonal to it. In addition, through the flexible structure formed in the above-described two-dimensional arrangement, both directions in the longitudinal direction and the direction orthogonal to the longitudinal direction when the variable deployment type tube 100 including the composite member (1) or the composite member (1) is deployed There is an effect that the deployment can be made easily without a separate external force or deployment device.

In other words, the hinge part 12 may be provided in consideration of at least one of a boundary line in which the composite member 1 is folded and a bending direction in which the composite member 1 is bent when it is wound (folded). In this regard, when the composite member 1 forms a tube like the variable deployment type tube 100 to be described later, the hinge portion 12 extends along the circumferential direction of the tube in response to the tube being wound in the longitudinal direction. A configuration (for example, the form of a plurality of hinge parts 120 spaced apart from each other along the longitudinal direction of the tube body 10) and the length corresponding to the tube being folded flat when the tube is wound in the longitudinal direction It may include a configuration extending along the direction (eg, in the form of a plurality of hinge parts 120 disposed at a distance from each other along the circumferential direction of the tube body 10).

Hereinafter, a variable-deployable tube 100 (hereinafter referred to as 'variable-deployable tube 100') comprising a double resin composite member having a shape restoring force according to an embodiment of the present application including the above-described composite member 1 The structure and function of ) will be described in detail.

3 is a schematic perspective view of a variable deployment type tube including a double resin composite member having a shape restoring force according to an embodiment of the present application.

Referring to FIG. 3 , the variable deployment type tube 100 may include a tube body 10 and a spar 20 .

The tube body 10 may be provided including a double resin composite member 1 having a shape restoring force described above in the form of a tube having a hollow inside. The tube body 10 may include an inner carbon fiber layer (not shown) and a hinge portion 120 and a rigid portion 130 provided on the outer surface of the inner carbon fiber layer. Here, the hinge part 120 and the rigid part 130 of the tube body 10 respectively correspond to the hinge part 12 and the rigid part 13 of the composite member 1 described above. The description of the hinge part 12 and the rigid part 13 of the member 1 may be equally applied to the description of the hinge part 120 and the rigid part 130 of the tube body 10 .

According to an embodiment of the present application, the tube body 10 may include an outer carbon fiber layer (not shown) provided on the outer surface of the hinge portion 120 and the rigid portion 130 . For reference, in FIGS. 3 and 4 , the illustration of the outer carbon fiber layer of the tube body 10 may be omitted in order to easily explain the pattern in which the hinge part 120 and the rigid part 130 are formed.

The spar 20 may be disposed to extend in the longitudinal direction inside the tube body.

According to one embodiment of the present application, the spar 20 may be a material including a shape memory polymer composite material (SMPC: Shape Memory Polymer Composite) including a WF (Woven Fabric) carbon fiber and a shape memory polymer resin. In addition, the spar 20 may be provided to be deformable in shape by controlling the temperature applied to the spar 20 .

In other words, in the variable deployment type tube 100, the hinge part 120 of the tube body 10 is made of a material containing a shape memory polymer (SMP) resin, or the spar 20 is a shape memory material having a shape restoring force. It can be designed to be deployed as needed by the shape (memory) restoring force of the spar 20 and/or the shape restoring force of the hinge part 120 of the tube body 10 by being made.

In addition, according to an embodiment of the present application, the spar 20 has a shape extending along the longitudinal direction of the tube body 10 as an initial shape, and a shape to be restored to an initial shape in a high temperature state based on a preset temperature. can have resilience.

In addition, according to an embodiment of the present application, the spar 20 may be formed in an I-shape in cross section, but is not limited thereto.

More specifically, the spar 20 is disposed in contact with the inner periphery of the tube body 10, the upper and lower flanges (upper flange and lower flange) disposed to face each other and spaced apart from each other by a predetermined distance, and a web interconnecting the upper and lower flanges. can do.

At this time, the upper and lower flanges and the web may be disposed to form a right angle to each other. In addition, the web may interconnect the middle (refer to FIG. 3, the center) of the upper and lower flanges.

In addition, the upper and lower flanges may have a thickness and a protrusion length in which the tube body 10 has a thickness less than a preset thickness and can be folded (or wound). Here, the thickness of the upper and lower flanges means the thickness in the vertical direction based on FIG. 3 , and the protruding length of the upper and lower flanges means the length protruding in the left and right directions with respect to the web. In addition, the upper and lower flanges may be provided to have a thickness and a protrusion length to ensure preset bending rigidity. That is, the upper and lower flanges preferably have a thin thickness or a short protrusion length in terms of being compactly folded (or wound), but preferably have a thick thickness and a long protrusion length in terms of securing predetermined bending rigidity. Accordingly, the upper and lower flanges can be designed to have an appropriate thickness and protrusion length in consideration of both sides.

In addition, the spar 20 may be a material including a shape memory polymer composite material (SMPC: Shape Memory Polymer Composite) mixed with WF (Woven Fabric) carbon fiber and SMP resin.

In addition, the spar 20 may have an initial shape extending along the longitudinal direction of the tube body 10 . In addition, the spar 20 may have a stiffness less than a stiffness at a temperature below a preset temperature so that it can be easily deformed by an external force applied at a temperature higher than a preset temperature. That is, the spar 20 is easily deformed in response to an external force applied due to its low rigidity at a temperature below a preset temperature and can withstand high strain without damage to the material, and when the external force is removed, it returns to its initial shape. It may have an elastic restoring force of superelasticity to be restored.

In addition, the spar 20, at a temperature less than a preset temperature, the elastic restoring force may be lost.

That is, the spar 20 is easily deformed at a temperature greater than or equal to a preset temperature, and when the temperature is lowered, the deformed shape can be maintained without being restored to the initial shape. The spar 20 may return to a shape (initial shape) before deformation when the temperature is raised to a temperature higher than a preset temperature.

In addition, the spar 20, at a temperature above a preset temperature, has a low rigidity that can be easily folded when an external force is applied, and can be automatically deployed to an initial shape before deformation if there is no external force added.

4 is a schematic perspective view of a variable deployment type tube including a double resin composite member having a shape restoring force according to an embodiment of the present application including a plurality of stiffeners inside the tube body.

Referring to FIG. 4 , the variable deployment type tube 100 may include a plurality of stiffeners 30 .

The plurality of stiffeners 30 may have a rod shape extending in the longitudinal direction of the tube body 10 . In addition, the plurality of stiffeners 30 may be arranged at intervals along the circumference of the tube body 10 . In this way, by disposing the stiffener 30 around the tube body 10, reinforcement is made at a position spaced apart from the center of the tube body 10 as much as possible, so that a high cross-sectional secondary moment can be secured, and thus a high A structure having bending rigidity can be constructed. Illustratively, the plurality of stiffeners 30 may be disposed along the inner periphery of the tube body 10 .

In addition, it may be preferable that the plurality of stiffeners 30 are disposed in an area of the tube body 10 where the upper and lower flanges of the spar 20 are not disposed.

In addition, the plurality of stiffeners 30 may have a pair disposed symmetrically to each other when viewed in a cross-section. Exemplarily referring to the cross-sectional view shown at the lower side of FIG. 4 , the plurality of stiffeners 30 may be symmetrically disposed in pairs of four stiffeners 30 .

According to an embodiment of the present application, the plurality of stiffeners 30 may be wires having a superelastic material. Superelasticity may refer to a property of returning to an original initial shape by exerting an elastic restoring force even after a very large deformation.

The tube body 10 may include a plurality of hinge portions 120 arranged to be spaced apart from each other at a predetermined longitudinal distance along the longitudinal direction of the tube body 10 on the outer surface of the inner carbon fiber layer.

In addition, the plurality of hinge parts 120 may be disposed to be spaced apart from each other at a predetermined circumferential distance from the outer surface of the inner carbon fiber layer along the circumferential direction of the inner carbon fiber layer.

In other words, the plurality of hinge parts 120 of the tube body 10 are arranged at a predetermined longitudinal distance along the longitudinal direction of the tube body 10, and a predetermined circumference along the circumferential direction of the tube body 10 It may include a two-dimensional hinge arrangement that is spaced apart in a direction. With respect to the hinge part 120 disposed along the circumferential direction, each of the plurality of hinge parts 120 of the tube body 10 is a tube in the process of folding the variable-deployable tube 100 along the longitudinal direction. It is possible to fold (bend) in two directions that is partially bent even in the circumferential direction of the tube body 10 orthogonal to the longitudinal direction of the body 10, so the polygonal receiving pattern or the circular receiving pattern of the layer and the separation distance between the layers to decrease, further reducing the total storage volume of the variable deployment type tube 100 . Therefore, in consideration of such bending in the circumferential direction, in order to adjust the separation distance between adjacent layers in the polygonal receiving pattern or the circular receiving pattern, or to adjust the storage volume of the variable deployment type tube 100 as needed, the multiple hinges The circumferential spacing between the branches 120 may be adjusted.

According to an embodiment of the present application, the longitudinal distance and the circumferential distance between the plurality of hinge parts 120 may be independently determined.

In addition, according to an embodiment of the present application, each of the plurality of hinge units 120 may be provided in a rectangular shape with reference to the drawings, but is not limited thereto. As another example, each of the plurality of hinge units 120 may have a predetermined polygonal shape, such as a triangle or a hexagon, or may be provided in a shape having a curvature in some area, such as a circular shape or an oval shape.

5 is a conceptual diagram for explaining the setting of a longitudinal interval between a plurality of hinge parts disposed along the longitudinal direction on the outer surface of the inner carbon fiber layer.

5, the tube body 10 of the variable deployment type tube 100 according to an embodiment of the present application is deployed to extend along the longitudinal direction of the tube body 10, or one end in the longitudinal direction of the tube body 10 It is disposed on the inside and the other longitudinal end of the tube body 10 may be folded along the longitudinal direction in a form disposed on the outside. Referring to FIG. 6 (a) to be described later, one longitudinal end of the tube body 10 that is folded to be disposed on the inside is indicated by a1, and the other end in the longitudinal direction of the tube body 10 that is folded to be disposed on the outside is denoted by a2. can be displayed.

In addition, according to an embodiment of the present application, in the tube body 10 , the longitudinal spacing between the plurality of hinge parts 120 disposed close to one end of the tube body 10 in the longitudinal direction is the length of the tube body 10 . It may be provided with more than a longitudinal distance between the plurality of hinge parts 120 disposed close to the other end in the direction. In other words, the longitudinal spacing between the plurality of hinge parts 120 (specifically, the spaced distance between a pair of longitudinally adjacent hinge parts 120 on the outer surface of the inner carbon fiber layer of the tube body 10) Considering the direction in which the silver tube body 10 is folded (winding, wound), the longitudinal direction between the hinges 120 disposed inward when the variable deployment type tube 100 is folded (winding, wound) for storage. The spacing may be determined to be less than or equal to the longitudinal spacing between the hinge parts 120 disposed relatively outwardly.

Referring to FIG. 5 for better understanding, when the tube body 10 is folded so that the longitudinal end of the tube body 10 positioned at 9 o'clock in FIG. The longitudinal distance ( d1 ) between the pair of hinges 120 disposed close to is disposed relatively closer to the other longitudinal end of the tube body 10 (in other words, from the longitudinal end of the tube body 10) It may be provided to be smaller than the longitudinal distance ( d2 ) between the pair of hinge parts 120 ( d2 > d1 ).

6 is a conceptual diagram for explaining the shape deformation of a variable deployment type tube including a double resin composite member having a shape restoring force according to an embodiment of the present application.

Referring to FIG. 6 , (a) of FIG. 6 shows the deployment state of the variable deployment type tube 100, and as it goes from the state of FIG. 6(a) to the state of FIG. 6(d), the variable deployment type tube (100) may represent a rolled state for storage.

Referring to FIG. 6 , in the variable deployment type tube 100 , the hinge part 120 , which is a flexible part serving as a hinge, may be structurally deformed according to a change in temperature, so by controlling the temperature applied to the hinge part 120 . It can be rolled up (in other words, wound or folded) or unfolded. Specifically, the variable-deployable tube 100 of the present application may be rolled in the above-described first state (a low-temperature state based on a preset temperature), and conversely, a second state (a high-temperature state based on a preset temperature) can be developed in Accordingly, for example, the variable deployment type tube 100 may have a rolled state for storage in the first state, and may have a deployed state for use in the second state.

7 is a conceptual diagram for explaining a polygonal accommodation pattern for a variable development type tube including a double resin composite member having shape restoring force according to an embodiment of the present application, and FIG. 8 is between a layer according to the polygonal accommodation pattern and the next layer It is a conceptual diagram for explaining the longitudinal spacing setting of the hinge part.

7 and 8, in the variable deployment type tube 100, when each of the plurality of hinge parts 120 is folded at a preset angle, the tube body 10 is bent along the longitudinal direction, and a preset polygon A distance in the longitudinal direction between the plurality of hinge units 120 may be determined so as to be accommodated in a receiving pattern.

Specifically, according to an embodiment of the present application, the tube body 10 may be folded to form a plurality of layers of a polygonal shape according to a polygonal receiving pattern and to be wound layer by layer. Also, as the plurality of hinge portions 120 are disposed to correspond to the outer layer among the plurality of layers, the lengthwise distance between the plurality of hinge portions 120 may be increased. Illustratively, referring to FIG. 7 , the polygonal accommodation pattern may be in a form in which regular dodecagonal layers are wound a plurality of times, but is not limited thereto. Further, FIG. 7, when la i-th layer (Layer _i) any layer of the polygon stored patterns, the i-th layer, the (i + 1) th layer, then the layer adjacent to the outer side with respect to the (Layer _i) ( When comparing Layer _i+1 ), when folding according to the polygonal accommodation pattern, the i+1th layer is greater than the _{lengthwise interval (L i} ) between the pair of hinge units 120 disposed with respect to the _{i-th layer (Layer i). A longitudinal distance (L i+1} ) between the pair of hinge parts 120 disposed with respect to (Layer _i+1 ) may be large.

_{Specifically, the longitudinal distance (L i+1} ) between the pair of hinge units 120 disposed with respect to the i+1-th layer (Layer _i+1 ) is the previous layer, i-th layer (Layer _i ). It may be determined by the following Equation 1-1 from the _{longitudinal distance (L i} ) between the pair of hinges 120 to be disposed.

[Equation 1-1]

Here, t is the thickness of the tube body 10, L _D is the separation distance between the i-th layer (Layer _i ) and the i+1-th layer (Layer _i+1 ), and θ is the polygon associated with the polygon receiving pattern. It can be determined as 360°/n (deg) when it is n-gonal.

In addition, in connection with Equation 1 above, the _{longitudinal distance (L i} ) between the pair of hinge parts 120 of _{the i-th layer (Layer i} ) in the longitudinal direction between the pair of hinge parts 120 of the first layer When calculated from the interval (L ₁ ), it is expressed in Equation 1-2 below.

[Equation 1-2]

According to an embodiment of the present application, the total length (L _{i,total ) of the i-th layer (Layer i} ) may be calculated by Equation 1-3 below.

[Equation 1-3]

는 도 7 및 도 8을 참조하면, 본원에서의 다각형 수납 패턴에 의할 때, i번째 레이어(Layer_i)와 i+1번째 레이어(Layer_i+1)를 연결하는 한 쌍의 힌지부(120) 사이의 길이방향 간격을 의미하는 것일 수 있다. 구체적으로, i번째 레이어(Layer_i)와 i+1번째 레이어(Layer_i+1)를 연결하는 한 쌍의 힌지부(120)란 도 7을 참조하면, i번째 레이어(Layer_i)의 반시계 방향 기준 마지막 힌지부(120)와 i+1번째 레이어(Layer_i+1)의 반시계 방향 기준 첫 번째 힌지부(120) 사이의 길이방향 간격을 의미하는 것일 수 있다.here,

7 and 8 , according to the polygonal accommodation pattern herein, a pair of hinge units 120 connecting the _{i-th layer (Layer i} ) and the i+1-th layer (Layer _i+1) ) may mean a longitudinal spacing between Specifically, referring to FIG. 7 , the pair of hinge units 120 connecting the i-th layer (Layer _i ) and the i+1-th layer (Layer _i+1 ) are counterclockwise of the _{i-th layer (Layer i).} It may mean a longitudinal distance between the last hinge part 120 based on the direction and the first hinge part 120 based on the counterclockwise direction of the i+1-th layer (Layer _i+1).

According to an exemplary embodiment of the present application, the interval between the adjacent hinge units 120 disposed on the same layer is determined to be equal in the corresponding layer, and the region transitioned to the next layer disposed outside the corresponding layer (refer to FIG. 7 ) So, for example, the distance between the neighboring hinge parts 120 in the 'D' region) is the longitudinal distance between the pair of hinge parts 120 in the _{previous layer (L i} ) and the previous layer (Layer _i ) and the separation distance L _D of the next layer (Layer _i+1 ) may be determined through Equation 1-3 above. Accordingly, the separation distance between the layers is maintained equally between the plurality of layers, and the variable-deployable tube 100 is accommodated so that each layer has a preset polygonal shape, so that the wrinkle formation during storage is reduced as will be described later. And the total storage volume of the variable deployment type tube 100 can be reduced.

In addition, with respect to Equation 1-3, the total length (L _total ) of the variable-deployable tube 100 may be calculated by Equation 4 below.

[Equation 1-4]

Here, N may be the total number of layers according to the polygonal accommodation pattern.

In addition, according to an embodiment of the present application, as the hinge part 120 of the tube body 10 is disposed to correspond to the outer layer among the plurality of layers, the longitudinal length of the hinge part 120 may be increased. . In other words, as the variable deployment type tube 100 of the present application is disposed in an outer layer when receiving through a polygonal accommodation pattern including a plurality of layers of a polygonal shape, the interval between the hinge parts 120 is widened (in other words, Even when the length or area of the rigid part 130 interposed between the hinge parts 120 increases), the bent region (folding region) when stored at a predetermined angle by the hinge part 120 is stably supported. The length of the hinge unit 120 may be increased as it is disposed to correspond to the outer layer among the layers of .

According to an embodiment of the present application, the above-described polygonal accommodation pattern reduces the formation of wrinkles when the variable development type tube 100 is accommodated, compared to the tube accommodated by the circular accommodation pattern, and accommodates the variable development type tube 100 . It may be provided so that the volume is reduced.

In other words, by the above-described polygonal receiving pattern applied to the variable deployment type tube 100, a predetermined flexible member is accommodated by any tube or circular receiving pattern having a structure that extends singly along the longitudinal direction. Compared to the tube being used, the wrinkle formation during storage of the variable deployment type tube 100 of the present application can be reduced. In addition, by the above-described polygonal accommodation pattern, the storage volume of the variable deployment type tube 100 is accommodated by any tube or circular storage pattern having a structure in which a predetermined flexible member extends singly along the longitudinal direction. It can be reduced compared to the tube being used.

9 is a conceptual diagram for explaining that wrinkle formation during storage is reduced by a polygonal accommodation pattern for a variable-deployable tube including a double resin composite member having a shape restoring force according to an embodiment of the present application.

Referring to Figure 9, specifically, Figure 9 (a) is a conceptual diagram for calculating the degree of wrinkle formation when the tube is accommodated by a circular (circular) receiving pattern, Figure 9 (b) is the tube of the present application It is a conceptual diagram for calculating the degree of wrinkle formation in the case of being accommodated by a polygonal accommodation pattern.

According to an embodiment of the present application, the length of the wrinkle generated when the variable deployment type tube 100 is accommodated is the inner length of the tube body 10 and the outer length of the tube body 10 that are generated by the thickness of the tube body 10 . can be estimated from the difference in In other words, as the value obtained by subtracting the inner length from the outer length of the folded tube body 10 for storage increases, it may be determined that the tube body 10 is accommodated in a state in which many wrinkles are formed.

_c)는 하기 식 2-1에 의해 계산될 수 있다.Specifically, referring to FIG. 9 (a), the difference in length between the inside and outside of the tube accommodated by a circular receiving pattern

_c ) can be calculated by the following Equation 2-1.

[Equation 2-1]

Here, t is the thickness of the tube body 10, L is the total length of the tube body 10, n is the number of polygons of the polygonal accommodation pattern of FIG. a storage pattern including a plurality of layers of

_r)는 하기 식 2-2에 의해 계산될 수 있다.In contrast, with reference to FIG. 9 (b), the difference in length between the inside and outside of the tube accommodated by the polygonal accommodation method of the present application (

_r ) can be calculated by the following Equation 2-2.

[Equation 2-2]

Here, t is the thickness of the tube body 10, L is the total length of the tube body 10, and n is the number of polygons of the polygonal accommodation pattern (in other words, a reception pattern comprising a plurality of layers of n-shaped polygons) ) can be

10 is a graph showing the results of simulating the wrinkle reduction effect by the polygonal accommodation pattern as an experimental example in connection with a variable deployment type tube including a double resin composite member having shape restoring force according to an embodiment of the present application. .

Referring to FIG. 10 , the tube according to the inner and outer length difference and the circular accommodation pattern of the variable-deployable tube 100 of the present application to which a polygonal accommodation pattern is applied using a simulation tool such as MATLAB. According to the number of polygons of the inner and outer length difference of each, the diagram is shown with a solid line and a dotted line, and referring to the graph of FIG. It can be seen that the wrinkle formation during storage of the variable-deployable tube 100 of the present application is reduced compared to any tube having a structure that is extended in a single manner.

In the above description, the reduction in the wrinkle formation of the variable development type tube 100 by the polygonal accommodation pattern means that a relatively small shape restoration force and shape change rate are required when the variable development type tube 100 is deployed. It can be, and it can be advantageous in material selection for the manufacture of the expandable tube by this wrinkle reduction characteristic.

_{Also, referring to FIG. 9A , V c} associated with the accommodation volume of the tube by the circular accommodation pattern may be calculated by Equation 3-1 below.

[Equation 3-1]

_{In addition, referring to FIG. 9B , V r} associated with the storage volume of the tube according to the polygonal accommodation method of the present application may be calculated by the following Equation 3-2.

[Equation 3-2]

11 is an experimental example in connection with a variable-deployable tube including a double resin composite member having a shape restoring force according to an embodiment of the present application. .

Referring to FIG. 11 , using a simulation tool such as MATLAB, the storage volume of the tube of the variable-deployable tube 100 of the present application to which a polygonal accommodation pattern is applied and the tube according to the circular accommodation pattern The storage volume is plotted with solid and dotted lines according to the number of polygons, respectively. Referring to the graph of FIG. 11 , the storage volume of the variable-deployable tube 100 due to the polygonal storage pattern is determined by a predetermined flexible member in the longitudinal direction. It can be confirmed that the reduction compared to any tube or tube accommodated by a circular accommodation pattern having a structure that is extended in a single way.

The description of the double resin composite member 1 having the above-described shape restoring force and the variable deployment type tube 100 including the same is, according to the embodiment of the present application, a shape memory double resin having a shape pattern to be described below. It can be understood through the description of the composite material and the variable deployment type tube using the same. Therefore, hereinafter, even if omitted, the content described for the above-described double resin composite member 1 and the variable deployment type tube 100 including the same is a shape memory double resin composite material having the following shape pattern and using the same The same can be applied to the variable deployment type tube. For reference, the composite material 1 to be described below may correspond to the composite member 1 described above, and redundant descriptions in this regard will be omitted.

First, a variable deployment type tube comprising a shape memory double resin composite material having a shape memory double resin composite material having a shape memory double resin composite material having a shape memory double resin composite material according to an embodiment of the present application including a shape memory double resin composite material having a shape pattern according to an embodiment of the present application to be described later (hereinafter 'Bone tube') will be described.

This tube contains a composite material (1). In this tube, the composite material 1 is in the form of a hollow tube.

The composite material 1 includes an inner carbon fiber layer 11 made of a material containing WF (Woven Fabric) carbon fibers.

In addition, the composite material 1 is provided with a predetermined pattern on the outer surface of the inner carbon fiber layer 11, and a hinge portion 12 made of a material including at least one of a shape memory polymer (SMP) resin and a silicone resin. include The hinge part 12 is deformable in a first state that is low temperature based on a preset temperature, and is restored to an initial shape in a second state that is high temperature based on a preset temperature.

In addition, the composite material 1 is provided in a portion where the hinge portion 12 is not provided on the outer surface of the inner carbon fiber layer 11, and includes a rigid portion 13 made of a material containing an epoxy resin.

In addition, the composite material 1 is provided on the outer surfaces of the hinge portion and the rigid portion 13, and may include an outer carbon fiber layer made of a material including carbon fibers.

That is, in the composite material 1, a structural part having rigidity in the inner carbon fiber layer 11 containing WF carbon fiber is formed of an epoxy resin, and a part serving as a hinge is formed of a shape memory polymer (SMP) or a silicone resin. -matrix may be a composite skin, this composite material (1) may be in the form of a hollow boom having a cross section of a closed shape (eg, circular) form.

In summary, this tube can be a circular boom shape in which a dual-composite matrix composed of a rigid structure (rigid part 13) to which epoxy is applied and a flexible hinge (SMPs or silicon) part (hinge part 12) is applied to the skin. have.

By including the rigid part 13 and the hinge part 12 formed in a predetermined pattern, this tube may be freely deformable by the hinge part 12 while maintaining overall rigidity through the rigid part 13 . In other words, the tube can maintain the rigidity of the composite material 1 (skin structure) constant by applying the rigid portion 13 and the hinge portion 12 in a predetermined pattern.

In addition, according to this tube, since the hinge part 12 is deformable in a first state that is low temperature based on a preset temperature, and can be restored to an initial shape in a second state that is high temperature based on a preset temperature, The development of the composite material 1 may be possible through the shape restoring force of the hinge part 12 .

Accordingly, this tube can be controlled to easily deform the structure by temperature by applying SMP to the flexible part (hinge part 12) serving as a hinge, and restore the deformed shape using the shape memory effect of SMP. can be controlled For example, the tube may be rolled up in a first state and deployed in a second state. Accordingly, for example, the tube may have a rolled state for storage in the first state, and may have a usable state in the second state.

In addition, the tube may include a spar that is formed in an I-shape in cross section and is disposed to extend in the longitudinal direction in the interior of the composite material (1).

The spar may be a material including a shape memory polymer composite (SMPC) including a WF (Woven Fabric) carbon fiber and a shape memory polymer resin. Also, the spa is temperature adjustable.

By including such a spar, this tube controls the temperature of the spar, and can be developed by the shape memory restoration force of the spar and the shape restoration force of the hinge part 12 .

In addition, the present tube may have an arbitrary shape, and may be formed to be compact in a accommodated form (rolled form) so that it can be carried and moved freely, and may be light in weight.

In summary, the present application provides a general epoxy resin (rigid part 13) to the structural part having rigidity in WF (Woven Fabrics) carbon fiber (inner carbon fiber layer 11), and also a part serving as a hinge (hinge part 12) )), by using SMP (Shape Memory Polymer) or silicone resin, it is possible to provide this tube including the composite material 1, which can be called SMPC or WFS (Woven Fabric Silicon) skin.

SMP becomes very flexible above a specific temperature (Tg) and has the characteristic of memorizing the shape before deformation. In addition, WFS can be structurally deformed without damage to the material and can recover its initial shape by elastic restoring force.

Accordingly, the present tube can be developed by the shape restoration force of SMP or silicone resin applied to the hinge portion.

The present application applies a different dual-matrix to each of a rigid structure (rigid part 13) and a flexible hinge (hinge part 12), and is stored in a small volume, This tube can provide a self-deployable, self-deploying composite circular cross-section boom without additional machinery.

In addition, the composite material 1 is a dual-matrix composite, and a flexible hinge region (hinge portion 12) is inserted (equipped) in a predetermined pattern shape between rigid structures (rigid portion 13) to maintain rigidity while maintaining freedom. Shape transformation is possible.

Hereinafter, a shape memory double resin composite material (hereinafter referred to as 'this composite material') having a shape pattern according to an embodiment of the present application applicable to the present tube described above will be described. However, in relation to the description of this composite material, the same reference numerals are used for the same or similar configurations as those described in the previous salpin bone tube, and the overlapping description will be simplified or omitted.

The composite material includes an inner carbon fiber layer made of a material including WF (Woven Fabric) carbon fiber.

In addition, the present composite material is provided with a predetermined pattern on the outer surface of the inner carbon fiber layer, and includes a hinge portion made of a material including at least one of a shape memory polymer (SMP) resin and a silicone resin.

In addition, the present composite material is provided in a portion not provided with the hinge portion on the outer surface of the inner carbon fiber layer, and includes a rigid portion made of a material containing an epoxy resin.

The hinge unit is deformable in a first state that is low temperature based on a preset temperature, and is restored to an initial shape in a second state that is high temperature based on a preset temperature.

In addition, the present composite material is provided on the outer surface of the hinge portion and the rigid portion, and may include an outer carbon fiber layer made of a material including carbon fibers.

As described above, this composite material (Dual-matrix composite) uses different double resins to achieve very large structural deformation (180 degree folding) without damage due to micro-buckling of carbon fibers by using the shape restoring force of the flexible structure. possible. In addition, this composite material is capable of producing a three-dimensional structure capable of freely deforming a shape while maintaining overall rigidity through a rigid region (rigid portion 13) and a hinge region (hinge portion 12) of a predetermined pattern.

Existing circular cross-section ultra-thin composite skins are manufactured using TWF (Triaxially Woven Fabric) carbon fiber and silicone resin. However, this skin structure has a disadvantage in that the entire cross-section is a flexible structure, so that the bending properties are lowered in the plane perpendicular to the spar surface.

On the other hand, this composite material has a skin structure using dual-matrix composites with a hinge region added between the rigid structures, so that the rigidity is kept constant at all positions of the skin structure and the unfolding speed and shape are varied by varying the hinge region pattern. can be controlled.

As described above, the torsional rigidity of the main tube can be improved by applying the dual-matrix composite containing epoxy as the skin of the main tube, and the pattern of the rigid portion 13 and the hinge portion 12 is Since it can be applied in various ways, shape accuracy can be improved.

In addition, the present application may provide a shape memory double resin composite material manufacturing method (hereinafter referred to as 'the present manufacturing method') having a shape pattern according to an embodiment of the present application applicable to manufacturing the present composite material described above. Hereinafter, the present manufacturing method will be described. However, in connection with the description of the present manufacturing method, the same reference numerals are used for the same or similar components as those described above, and overlapping descriptions will be simplified or omitted.

In this manufacturing method, an epoxy resin in the form of a film is positioned corresponding to the rigid region pattern (region where the rigid portion 13 is to be formed) set on the outer surface of the WF carbon fiber, and a hinge structure region (hinge portion) positioned between the rigid region patterns. (12) in correspondence with the region to be formed), a silicone resin or a shape memory polymer resin is applied, and the WF carbon fiber is placed on the outside of the epoxy resin and the applied silicone resin (or shape memory polymer resin), thereby WF carbon fiber - epoxy Resin, silicone resin, or shape memory polymer resin - WF carbon fiber, etc. can be stacked in order.

In addition, in this manufacturing method, the silicone resin (or shape memory polymer resin) and the WF carbon fiber coated with the epoxy resin are treated at room temperature or a specific temperature (Tg) to cure the silicone resin (or shape memory polymer resin first, After that, the epoxy resin can be cured by applying heat to the temperature at which the film epoxy resin starts to cure.

As the viscosity of liquid epoxy resin decreases during the curing process, the resin may flow into the flexible structural part that acts as a hinge. have. In addition, since the resin is non-uniformly distributed, there may be a disadvantage in that it is difficult to constantly maintain the thickness and rigidity of the cured composite material.

However, according to the present manufacturing method, since the epoxy resin in the film form has flexible properties in an uncured state, it is easy to apply not only a flat plate shape but also a three-dimensional structure having a curvature such as a boom shape. In addition, since the epoxy resin in the film form is in the form of a sheet having a predetermined thickness, it is possible to secure the advantage of controlling the rigidity of the structure by controlling the number of layers laminated between the carbon fiber layers.

In addition, the film-type epoxy resin has the advantage of being able to implement variously the pattern shape of the rigid region, maintaining the pattern between curing processes, and maintaining the uniform thickness of the cured composite material because the thickness of the film is constant. . It is possible to prevent the silicone or shape memory polymer resin used to form the flexible structure region from being impregnated with the carbon fiber in the rigid region by being positioned between the layers of carbon fibers and adhering to the film-type epoxy resin.

In addition, silicone resin or shape memory polymer resin and film-type epoxy resin have different curing temperatures. Silicone or shape memory polymer resin can be cured in a short time at a curing temperature at a relatively low temperature compared to epoxy resin, and it is possible to manufacture a dual-matrix composite of this composite material through a continuous curing process by adjusting the curing temperature cycle. .

This application can be applied to large deployable space structures (Antenna, Reflector, Solar array, etc.), can contribute to the weight reduction of the space deployment device structure, small and portable tents and ground antennas, extra large/ultra-light It can be applied as a source technology for the development of space structures, and compared to the existing space structures, the weight is reduced by 1/100, the storage efficiency is about 40 times, and the development cost of the space structure is reduced to less than 1/10 by reducing the launch cost. can be expected to do

The foregoing description of the present application is for illustration, and those of ordinary skill in the art to which the present application pertains will understand that it can be easily modified into other specific forms without changing the technical spirit or essential features of the present application. Therefore, it should be understood that the embodiments described above are illustrative in all respects and not restrictive. For example, each component described as a single type may be implemented in a dispersed form, and likewise components described as distributed may be implemented in a combined form.

The scope of the present application is indicated by the following claims rather than the above detailed description, and all changes or modifications derived from the meaning and scope of the claims and their equivalent concepts should be construed as being included in the scope of the present application.

1: Double resin composite member with shape restoring force
11: inner carbon fiber layer
12: hinge
13: rigid part
14: outer carbon fiber layer
100: Variable deployment type tube comprising a double resin composite member with shape restoring force
10: tube body
120: hinge
130: rigid portion
20: spa
30: stiffener

Claims (18)

As a double resin composite member having shape restoration power,
an inner carbon fiber layer made of a material containing carbon fibers;
a hinge portion provided on an outer surface of the inner carbon fiber layer; and
Including a rigid portion provided in a portion not provided with the hinge portion on the outer surface of the inner carbon fiber layer,
The rigid portion includes a plurality of rigid members disposed on the outer surface of the inner carbon fiber layer at a distance from each other,
The hinge part is provided with a material having an elastic restoring force against bending, and is formed in a gap region between the plurality of rigid members to correspond to an area in which the double resin composite member is folded,
The plurality of rigid members,
It has a closed cross-sectional shape based on a cross section orthogonal to the inner and outer directions,
Provided in the form of a film containing an epoxy resin to prevent at least a portion of the shape restoration material made of a material containing at least one of a shape memory polymer (SMP) resin and a silicone resin from being impregnated into the inner carbon fiber layer corresponding to the rigid portion becomes,
The hinge part and the rigid part are, after disposing the plurality of rigid members in the film form on the outer surface of the inner carbon fiber layer, and applying the shape restoration material to the gap region between the plurality of rigid members, hardening formed by the method,
The hinge part is cured before the rigid part at a first curing temperature for curing the shape restoration material, and the rigid part is a temperature for curing the epoxy resin in the film form. At a second curing temperature higher than the first curing temperature A double resin composite member having a shape restoring force that is formed by curing subsequent to the hinge part. delete According to claim 1,
The hinge part, a shape memory polymer (SMP) resin and a double resin composite member having a shape restoring force made of a material containing at least one of a silicone resin. According to claim 1,
The hinge part is deformable in a first state that is low temperature based on a preset temperature, and is restored to an initial shape in a second state that is high based on the preset temperature. Material containing a shape memory polymer (SMP) resin A double resin composite member having a shape restoring force that is made of. delete According to claim 1,
The inner carbon fiber layer, characterized in that made of a material containing WF (Woven Fabric) carbon fiber, a double resin composite member having a shape restoring force. delete delete According to claim 1,
A double resin composite member having a shape restoring force, which is provided on the outer surfaces of the hinge part and the rigid part, and further comprises an outer carbon fiber layer made of a material containing carbon fibers. A variable development type tube comprising a double resin composite member having shape restoring force,
A tube body including a double resin composite member having a shape restoring force of any one of claims 1, 3, 4, 6, and 9 but having a hollow tube shape inside; and
A spar which is disposed extending in the longitudinal direction inside the tube body;
Containing, variable deployment tube. 11. The method of claim 10,
The hinge portion of the tube body is made of a material containing a shape memory polymer (SMP) resin or the spar is made of a shape memory material having a shape restoring force, a variable deployment type tube. 12. The method of claim 11,
The spar has a shape extending along the longitudinal direction of the tube body as an initial shape, and characterized in that it has a shape restoring force to be restored to the initial shape at a high temperature based on a preset temperature. 12. The method of claim 11,
The tube body is
A variable deployment type tube comprising a plurality of hinges disposed on the outer surface of the inner carbon fiber layer spaced apart from each other at a predetermined longitudinal distance along the longitudinal direction of the tube body. 14. The method of claim 13,
The tube body is
Deployed to extend along the longitudinal direction of the tube body or folded along the longitudinal direction in a form in which one longitudinal end of the tube body is disposed on the inside and the other longitudinal end of the tube body is disposed on the outside,
In the tube body, the longitudinal distance between the plurality of hinge parts disposed close to one end in the longitudinal direction is greater than or equal to the longitudinal distance between the plurality of hinge parts disposed close to the other end in the longitudinal direction, characterized in that , variable deployment tube. 14. The method of claim 13,
When each of the plurality of hinge portions is folded at a preset angle, the tube body is bent along the longitudinal direction to form a preset polygonal accommodation pattern and the lengthwise distance between the plurality of hinge portions is determined. , a variable-deployable tube. 16. The method of claim 15,
The tube body is
Doedoe folding (folding) so as to form a plurality of layers of a polygonal shape according to the polygonal accommodation pattern to be wound layer by layer,
Variable deployment type tube, characterized in that provided that the plurality of hinge parts are disposed corresponding to the outer layer of the plurality of layers so that the longitudinal distance between the plurality of hinge parts is increased. 17. The method of claim 16,
The plurality of hinge parts,
A variable-deployable tube that is arranged to be spaced apart from each other at a predetermined circumferential distance along the circumferential direction of the inner carbon fiber layer from the outer surface of the inner carbon fiber layer. 17. The method of claim 16,
Variable development, characterized in that the polygonal accommodation pattern is provided such that wrinkle formation is reduced when the variable development type tube is accommodated, and the storage volume of the variable development type tube is reduced compared to the tube accommodated by the circular accommodation pattern. mold tube.

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