WO2021261676A1 - Revêtement composite polymère à mémoire de forme élastique ayant un coefficient de poisson nul - Google Patents

Revêtement composite polymère à mémoire de forme élastique ayant un coefficient de poisson nul Download PDF

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Publication number
WO2021261676A1
WO2021261676A1 PCT/KR2020/015251 KR2020015251W WO2021261676A1 WO 2021261676 A1 WO2021261676 A1 WO 2021261676A1 KR 2020015251 W KR2020015251 W KR 2020015251W WO 2021261676 A1 WO2021261676 A1 WO 2021261676A1
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WO
WIPO (PCT)
Prior art keywords
memory polymer
polymer composite
composite skin
shape memory
stretchable
Prior art date
Application number
PCT/KR2020/015251
Other languages
English (en)
Korean (ko)
Inventor
권오현
노진호
배재성
Original Assignee
한국항공대학교산학협력단
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
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Application filed by 한국항공대학교산학협력단 filed Critical 한국항공대학교산학협력단
Priority to DE112020007338.6T priority Critical patent/DE112020007338T5/de
Publication of WO2021261676A1 publication Critical patent/WO2021261676A1/fr

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/14—Layered products comprising a layer of metal next to a fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/04—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by at least one layer folded at the edge, e.g. over another layer ; characterised by at least one layer enveloping or enclosing a material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form
    • B32B3/02—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions
    • B32B3/08—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products having particular features of form characterised by features of form at particular places, e.g. in edge regions characterised by added members at particular parts
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/02—Composition of the impregnated, bonded or embedded layer
    • B32B2260/021—Fibrous or filamentary layer
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2260/00—Layered product comprising an impregnated, embedded, or bonded layer wherein the layer comprises an impregnation, embedding, or binder material
    • B32B2260/04—Impregnation, embedding, or binder material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
    • B32B2262/02—Synthetic macromolecular fibres
    • B32B2262/0261—Polyamide fibres
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/70—Other properties
    • B32B2307/732—Dimensional properties
    • B32B2307/734—Dimensional stability
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2605/00—Vehicles
    • B32B2605/18—Aircraft

Definitions

  • Various embodiments relate to a stretchable shape memory polymer composite skin having a zero Poisson ratio.
  • variable geometry aircraft or morphing structure aircraft is being actively conducted.
  • the skin of the morphing structure which can change shape according to flight conditions, should be able to have flexible rigidity in the direction in which the shape is changed and strong rigidity in the direction in which aerodynamic forces are generated.
  • a typical morphing skin manufacturing method includes a method using a thin elastomer, a method using a corrugated structure, and a method using a cellular structure. These conventional methods have a characteristic that it is not easy to manufacture because the structure is complicated, or the required load is rapidly increased at a strain rate above a certain level.
  • Various embodiments of the present invention provide a stretchable shape memory polymer composite skin having a zero Poisson ratio that does not have a complex structure and does not rapidly increase the load required for deformation to solve the problems of the prior art.
  • a stretchable shape memory polymer composite skin having a zero Poisson ratio includes a body made of conductive fibers, a plurality of metal frames disposed under the body to transmit power to the body, and the plurality of metals and a plurality of reinforcing materials coupled to a lower portion of the main body at a distance from the frame, and the main body may change in temperature based on electric power transmitted from the plurality of metal frames.
  • the plurality of metal frames and the plurality of reinforcing materials according to various embodiments of the present disclosure may be formed to cross the width of the main body along the width direction of the main body, respectively.
  • the length of the main body according to various embodiments of the present disclosure is increased by an external force applied to the main body at a reference temperature or higher, and when there is no external force, the original length of the main body may be restored.
  • the length of the body according to various embodiments of the present disclosure may be maintained in a deformed state below the reference temperature.
  • Each of the body and the plurality of metal frames according to various embodiments of the present disclosure may be formed in a 'C' shape with one side open.
  • Each of the plurality of metal frames according to various embodiments of the present disclosure may be connected to a wire for receiving power from the outside.
  • An adhesive layer for bonding to a morphing aircraft wing may be formed on one side of each of the plurality of metal frames according to various embodiments of the present disclosure.
  • both ends of the main body in the width direction may be bent to cover the lower portion of the morphing aircraft wing.
  • the skin proposed in the present disclosure is a shape memory polymer composite skin in which a shape memory polymer is impregnated into a stretchable and conductive fabric. have.
  • the skin proposed in the present disclosure may be used as a skin of a morphing wing having a variable shape and a sheet material of a space structure having a variable shape.
  • the skin proposed in the present disclosure can maintain a deformed shape without external force, and since it has a zero-Poisson ratio, it has less aerodynamic loss compared to the existing morphing skin, so that when applied to a morphing aircraft, low power and long flight time can be maintained. can do.
  • FIG. 1 is a diagram schematically illustrating a process of manufacturing the body 110 of the stretchable shape memory polymer composite skin 100 having a zero Poisson ratio according to an embodiment of the present invention.
  • FIG. 2 is a perspective view of a stretchable shape memory polymer composite skin 100 having a zero Poisson ratio according to an embodiment of the present invention.
  • FIG 3 is a view showing a rear view of the stretchable shape memory polymer composite skin 100 having a zero Poisson ratio according to an embodiment of the present invention.
  • FIG. 4 is a view showing a stretchable shape memory polymer composite skin 100 having a zero Poisson ratio in which the overall length is deformed, according to an embodiment of the present invention.
  • 5A and 5B are views illustrating a rear view of the stretchable shape memory polymer composite skin 100 having a zero Poisson ratio according to an embodiment of the present invention.
  • FIG. 6 is a perspective view of a stretchable shape memory polymer composite skin 100 having a zero Poisson ratio coupled to a morphing aircraft wing 200 according to an embodiment of the present invention.
  • FIGS. 7A to 7C are cross-sectional views illustrating a stretchable shape memory polymer composite skin 100 having a zero Poisson ratio coupled to a morphing aircraft wing 200 according to an embodiment of the present invention.
  • FIG. 1 is a diagram schematically illustrating a process of manufacturing the body 110 of the stretchable shape memory polymer composite skin 100 having a zero Poisson ratio according to an embodiment of the present invention.
  • the body 110 of the stretchable shape memory polymer composite skin 100 is impregnated with a shape memory polymer (SMP) liquid in which a conductive powder is mixed with a fabric such as nylon fiber having stretchability and conductive properties.
  • SMP shape memory polymer
  • the shape memory polymer (SMP) has the characteristic of memorizing the initial shape of the main body 110 by thermo-mechanical properties, so that it becomes flexible when the glass temperature (Tg) or higher, and the shape before deformation is remembered to be restored. Conversely, below the glass transition temperature (Tg), it may have a characteristic to maintain a deformed shape. That is, the body 110 may change the strength of the fabric depending on the properties of the shape memory polymer (SMP) above the glass transition temperature (Tg), and may be freely deformed in shape using this. In addition, the body 110 can maintain a deformed shape below the glass transition temperature (Tg) due to the properties of the shape memory polymer (SMP).
  • the body 110 may be made of a fabric of heat-generating fibers that generate heat using electric power applied from the outside.
  • the temperature of the body 110 may increase or decrease depending on the amount of power applied from the outside, and the shape may be deformed or maintained at a specific temperature by the properties of the shape memory polymer (SMP).
  • the body 110 is filled with a shape memory polymer (SMP) solution mixed with conductive powder, or a shape memory polymer (SMP) composite material using a metal mesh is formed, or heating paint. can be applied.
  • the stretchable shape memory polymer composite skin 100 having a zero Poisson ratio is coupled to a wing of a morphing aircraft having a variable shape, a space structure having a variable shape, etc. to affect the deformation of each structure
  • the main feature is to maintain a zero-Poisson's ratio without affecting
  • Poisson's ratio refers to the rate at which a material expands or contracts in another axial direction with respect to an axial stress, and a zero Poisson's ratio has no deformation in another axial direction due to an axial strain applied by the stress.
  • the stretchable shape memory polymer composite skin 100 capable of solving problems such as deformation of a structure and loss of aerodynamic force based on such a zero Poisson ratio will be described in more detail.
  • FIGS. 2 and 3 show a perspective view and a rear view, respectively, of the stretchable shape memory polymer composite skin 100 having a zero Poisson ratio according to an embodiment of the present invention.
  • the stretchable shape memory polymer composite skin 100 having a zero Poisson ratio is a body 110 and a metal frame 120 and a reinforcing material 130 coupled to the lower portion of the body 110, respectively. can be configured.
  • the body 110 may be manufactured by impregnating a liquid shape memory polymer (SMP) liquid in which a conductive powder is mixed with a fabric such as nylon fiber having elasticity and conductivity.
  • SMP liquid shape memory polymer
  • the temperature of the body 110 may increase or decrease by power supplied from the outside, and the shape may be deformed or maintained at a specific temperature.
  • the shape when the body 110 becomes above a preset glass temperature (Tg) by electric power supplied from the outside, the shape may be easily deformed by the properties of the shape memory polymer (SMP). . That is, the body 110 may be deformed in a direction in which a load acts by decreasing the stiffness (or strength) of the fabric above the glass transition temperature (Tg).
  • Tg glass temperature
  • SMP shape memory polymer
  • the main body 110 when power is not supplied to the main body 110 , when the main body 110 is below the glass transition temperature (Tg), the deformed shape may be maintained. In addition, when power is supplied from the outside and the main body 110 becomes above the glass transition temperature (Tg), the main body 110 restores to the initial shape by the property of the shape memory polymer (SMP) to return to the memorized shape.
  • SMP shape memory polymer
  • the metal frame 120 may transmit power supplied from the outside to the body 110 .
  • the metal frame 120 may be made of a metal aluminum material that transmits power to the body 110 made of conductive fiber, and the lower portion of the body 110 corresponds to the width in the horizontal direction of the body 110 . can be coupled to In this case, a wire for receiving power from the outside may be connected to both ends of the metal frame 120 .
  • a plurality of metal frames 120 may be provided.
  • the plurality of metal frames 120 may be disposed with a predetermined interval across the width of the body 110 , and preferably may be respectively coupled to the lower portion of the body 110 .
  • the magnitude of the power supplied to the plurality of metal frames 120 may be set differently, and the tensile strength of the main body 110 may be set differently for each region using this.
  • the reinforcing material 130 may be coupled to the body 110 at a distance from the metal frame 120 .
  • the reinforcing material 130 may be made of a light and strong material of synthetic resin or plastic material (eg, FRP material, ABS material, etc.).
  • a plurality of reinforcing materials 130 may be provided and disposed under the body 110 in parallel to the metal frame 120 .
  • the thickness of the reinforcing material 130 may be formed to be thicker than the thickness of the metal frame 120 .
  • Tg glass transition temperature
  • FIG. 4 is a view showing a stretchable shape memory polymer composite skin 100 having a zero Poisson ratio in which the overall length is deformed, according to an embodiment of the present invention.
  • the stretchable shape memory polymer composite skin 100 when electric power is applied from the outside, the stretchable shape memory polymer composite skin 100 is deformed in shape due to a decrease in stiffness (or strength) above a preset reference temperature (eg, glass transition temperature). Alternatively, it may be restored to its initial shape.
  • a preset reference temperature eg, glass transition temperature
  • a plurality of reinforcing materials 130 in the width (W) direction of the stretchable shape memory polymer composite skin 100 may be coupled to the lower portion of the stretchable shape memory polymer composite skin 100 at regular intervals, through which the stretchable shape
  • the memory polymer composite skin 100 may be made only by tensile deformation in the length (L) direction without deformation in the width (W) direction. That is, the stretchable shape memory polymer composite skin 100 may have an overall length (L+ ⁇ L) increased without a sharp increase in the load above the glass transition temperature (Tg).
  • the stretchable shape memory polymer composite skin 100 becomes below a preset reference temperature (eg, glass transition temperature), and in this case, the shape is changed due to the shape memory polymer (SMP) properties. can be maintained
  • a preset reference temperature eg, glass transition temperature
  • the stretchable shape memory polymer composite skin 100 has a memorized shape Due to the nature of the shape memory polymer (SMP) to return to its original shape, it can be restored to its initial shape.
  • 5A and 5B are views illustrating a rear view of the stretchable shape memory polymer composite skin 100 having a zero Poisson ratio according to an embodiment of the present invention.
  • FIGS. 1 to 5B refer to the same terms and reference numerals, and in order to avoid repeated description, reference is made to the descriptions of FIGS. 1 to 4 described above. Hereinafter, only differences between the embodiments will be described.
  • the body 110 constituting the stretchable shape memory polymer composite skin 100 has a metal frame 120 and a reinforcing material 130 across the width of the body 110, the body 110 may be coupled to the lower surface of the In this case, the metal frame 120 and the reinforcing material 130 may be formed in plurality.
  • the first metal frame 120-1 to the fifth metal frame 120-5, and the first reinforcing material 130-1 and the second reinforcing material 130-2 Each may be disposed to be spaced apart from the lower surface of the main body 110 at regular intervals.
  • the first metal frame 120-1 to the fourth metal frame 120-4 may be sequentially disposed from one end to the other end direction of the body 110 and coupled thereto, and the fourth metal frame 120-4 may be coupled thereto.
  • a first reinforcing material 130 - 1 and a second reinforcing material 130 - 2 may be respectively disposed between and coupled to the fifth metal frame 120 - 5 .
  • the first reinforcing material 130-1 is disposed between the first metal frame 120-1 and the second metal frame 120-2.
  • the second reinforcing material 130-2 is positioned between the second metal frame 120-2 and the third metal frame 120-3, and the second metal frame 120-3 and the fourth metal frame ( 120-4) may be coupled such that the third reinforcing member 130-3 and the fourth reinforcing member 130-4 are disposed between them.
  • a load required to increase the length of the main body 110 may be formed differently for each region of the main body 110 .
  • the embodiment of the present invention is not limited thereto, and the plurality of metal frames 120 and the plurality of reinforcing materials 130 may be coupled to the lower portion of the body 110 in various forms.
  • FIGS. 7A to 7C are According to an embodiment of the present invention, it is a view showing a cross-sectional view of a stretchable shape memory polymer composite skin 100 having a zero Poisson ratio coupled to a morphing aircraft wing 200 .
  • the body 110 and the metal frame 120 of the stretchable shape memory polymer composite skin 100 are bent at both ends to form a 'C'-shaped structure in cross section.
  • the body 110 may be coupled to closely contact the outer surface of the metal frame 120 coupled from one open side. That is, the body 110 may be coupled while surrounding the outside of the metal frame 120 .
  • the adhesive layer 121 may be applied to the inner surface of the metal frame 120 to strengthen the bonding with the morphing aircraft structure.
  • the metal frame ( 120 may be a metal frame 120 disposed in the middle region A in the longitudinal direction of the front and rear of the morphing aircraft wing 200 .
  • the adhesive layer 121 is applied to the inner surface of the metal frame 120 coupled to the lower portion of the body 110 corresponding to the middle region A of the morphing aircraft wing 200 .
  • the embodiment of the present invention is not limited thereto, and the adhesive layer 121 is applied and formed on the inner surface of each of the plurality of metal frames 120 disposed under the main body 110, so that the morphing aircraft wing 200 is formed. ) and the bonding state can be maintained more firmly.
  • the external force acting on the stretchable shape memory polymer composite skin 100 may be applied along the longitudinal direction of the stretchable shape memory polymer composite skin 100 while the morphing aircraft wing 200 is deformed.
  • the morphing aircraft wing 200 is stretched and unfolded above the glass transition temperature (Tg)
  • Tg glass transition temperature
  • an external force is applied to both ends of the stretchable shape memory polymer skin 100 coupled to the morphing aircraft wing 200 in the longitudinal direction.
  • Tg glass transition temperature
  • both ends of the main body 110 of the stretchable shape memory polymer composite skin 100 wrap around and support the lower part of the morphing aircraft wing 200 . It may be formed to extend to be curved in the inward direction so as to be able to do so.
  • the morphing aircraft wing 200 may be implemented as a structure in which a hollow is formed therein, as shown in FIG. 7C , and in this case, the body 110 of the stretchable shape memory polymer composite skin 100 is a morphing aircraft In order to support the wing 200 more stably, both ends may be formed to be bent toward the inside.
  • the skin proposed in the present disclosure increases or decreases the temperature of the skin in a simple way of controlling the power flowing through the conductive fabric as a shape memory polymer composite skin by impregnating the stretchable and conductive fabric with a shape memory polymer. It can be easily deformed.
  • the skin proposed in the present disclosure may be used as a skin of a morphing wing having a variable shape and a sheet material of a space structure having a variable shape.
  • the skin proposed in the present disclosure can maintain a deformed shape without external force, and since it has a zero-Poisson ratio, it has less aerodynamic loss compared to the existing morphing skin, so that when applied to a morphing aircraft, low power and long flight time can be maintained. can do.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Laminated Bodies (AREA)
  • Health & Medical Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Medicinal Chemistry (AREA)
  • Polymers & Plastics (AREA)
  • Organic Chemistry (AREA)
  • Manufacturing & Machinery (AREA)
  • Materials Engineering (AREA)

Abstract

Est divulgué, un revêtement composite polymère à mémoire de forme élastique ayant un coefficient de Poisson nul. Le revêtement composite polymère à mémoire de forme élastique comprend : un corps formé de fibres conductrices ; une pluralité de cadres métalliques qui sont disposés sur une partie inférieure du corps et fournissent de l'énergie électrique au corps ; et une pluralité d'éléments de renforcement qui sont accouplés à la partie inférieure du corps de façon à être espacés de la pluralité de cadres métalliques, le corps pouvant changer de température en fonction de l'énergie électrique fournie à partir de la pluralité de cadres métalliques. En conséquence, un vol à faible consommation énergétique et de longue durée dans un aéronef métamorphosable peut être maintenu en raison d'une faible perte aérodynamique.
PCT/KR2020/015251 2020-06-23 2020-11-03 Revêtement composite polymère à mémoire de forme élastique ayant un coefficient de poisson nul WO2021261676A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
DE112020007338.6T DE112020007338T5 (de) 2020-06-23 2020-11-03 Dehnbare formgedächtnis-polymer-verbundhaut mit poissonzahl von null

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
KR1020200076203A KR102343337B1 (ko) 2020-06-23 2020-06-23 제로 포아송 비를 갖는 신축성 형상기억 폴리머 복합재 스킨
KR10-2020-0076203 2020-06-23

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WO2021261676A1 true WO2021261676A1 (fr) 2021-12-30

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DE102023112229B3 (de) 2023-05-10 2024-04-25 Hochschule Bremen, Körperschaft des öffentlichen Rechts Morphing-Struktur mit kontrollierbaren Freiheitsgraden

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KR20130089148A (ko) * 2010-06-25 2013-08-09 더 보잉 컴파니 일체화된 보강부재를 갖는 복합 구조물 그 제조 방법
KR20130117589A (ko) * 2012-04-18 2013-10-28 한국과학기술원 가변형 모핑 날개
US20140255655A1 (en) * 2012-10-05 2014-09-11 The Procter & Gamble Company Fibrous paper structures utilizing waterborne shape memory polymers
KR20150056340A (ko) * 2013-11-15 2015-05-26 인제대학교 산학협력단 전기 활성 고분자를 이용한 가변 날개 시스템
KR20180084383A (ko) * 2017-01-17 2018-07-25 한국항공대학교산학협력단 키리가미 패턴을 이용한 형상기억 모핑 부재

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Publication number Priority date Publication date Assignee Title
JP5045330B2 (ja) * 2007-09-21 2012-10-10 東レ株式会社 繊維強化プラスチック構造体の製造方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20130089148A (ko) * 2010-06-25 2013-08-09 더 보잉 컴파니 일체화된 보강부재를 갖는 복합 구조물 그 제조 방법
KR20130117589A (ko) * 2012-04-18 2013-10-28 한국과학기술원 가변형 모핑 날개
US20140255655A1 (en) * 2012-10-05 2014-09-11 The Procter & Gamble Company Fibrous paper structures utilizing waterborne shape memory polymers
KR20150056340A (ko) * 2013-11-15 2015-05-26 인제대학교 산학협력단 전기 활성 고분자를 이용한 가변 날개 시스템
KR20180084383A (ko) * 2017-01-17 2018-07-25 한국항공대학교산학협력단 키리가미 패턴을 이용한 형상기억 모핑 부재

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DE112020007338T5 (de) 2023-04-06

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