CN105356029B - Plane reflection array antenna and its method of deploying based on shape memory polymer composite material hinge - Google Patents
Plane reflection array antenna and its method of deploying based on shape memory polymer composite material hinge Download PDFInfo
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- CN105356029B CN105356029B CN201510756620.2A CN201510756620A CN105356029B CN 105356029 B CN105356029 B CN 105356029B CN 201510756620 A CN201510756620 A CN 201510756620A CN 105356029 B CN105356029 B CN 105356029B
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- shape memory
- memory polymer
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- laminated plate
- reflective array
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- 229920000431 shape-memory polymer Polymers 0.000 title claims abstract description 82
- 239000002131 composite material Substances 0.000 title claims abstract description 30
- 238000000034 method Methods 0.000 title claims abstract description 22
- 238000010438 heat treatment Methods 0.000 claims abstract description 37
- 239000000463 material Substances 0.000 claims abstract description 4
- 239000000758 substrate Substances 0.000 claims description 28
- 230000008569 process Effects 0.000 claims description 13
- 230000007704 transition Effects 0.000 claims description 5
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 4
- 230000003014 reinforcing effect Effects 0.000 claims description 4
- 239000000853 adhesive Substances 0.000 claims description 3
- 230000001070 adhesive effect Effects 0.000 claims description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 3
- 229910052782 aluminium Inorganic materials 0.000 claims description 3
- 238000005485 electric heating Methods 0.000 claims description 3
- 239000011888 foil Substances 0.000 claims description 3
- 238000002360 preparation method Methods 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims description 3
- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 claims description 2
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 2
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 2
- 229920006231 aramid fiber Polymers 0.000 claims description 2
- 229910052796 boron Inorganic materials 0.000 claims description 2
- 239000004917 carbon fiber Substances 0.000 claims description 2
- 239000002041 carbon nanotube Substances 0.000 claims description 2
- 229910021393 carbon nanotube Inorganic materials 0.000 claims description 2
- 239000000835 fiber Substances 0.000 claims description 2
- 239000003733 fiber-reinforced composite Substances 0.000 claims description 2
- 239000003365 glass fiber Substances 0.000 claims description 2
- 239000011159 matrix material Substances 0.000 claims description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 2
- 239000002245 particle Substances 0.000 claims description 2
- 239000011208 reinforced composite material Substances 0.000 claims description 2
- 239000011810 insulating material Substances 0.000 claims 1
- 239000011120 plywood Substances 0.000 abstract 5
- 238000010586 diagram Methods 0.000 description 7
- 230000008859 change Effects 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 239000012774 insulation material Substances 0.000 description 2
- 238000011084 recovery Methods 0.000 description 2
- 229910000838 Al alloy Inorganic materials 0.000 description 1
- 239000004593 Epoxy Substances 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- XLJMAIOERFSOGZ-UHFFFAOYSA-M cyanate Chemical compound [O-]C#N XLJMAIOERFSOGZ-UHFFFAOYSA-M 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000003247 decreasing effect Effects 0.000 description 1
- 230000006870 function Effects 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000003446 memory effect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/08—Means for collapsing antennas or parts thereof
- H01Q1/084—Pivotable antennas
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/104—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces using a substantially flat reflector for deflecting the radiated beam, e.g. periscopic antennas
Landscapes
- Details Of Aerials (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
Plane reflection array antenna and its method of deploying based on shape memory polymer composite material hinge.Belong to aerospace antenna Material Field.It is existing using mechanical or inflatable space deployable antenna structure there are complicated in mechanical structure, be easily hit and damage, it is of high cost the problem of.A kind of plane reflection array antenna based on shape memory polymer composite material hinge, the shape memory polymer layer plywood (2) of two panels curved surface is fixedly mounted between two fixed end connections (1) of driving hinge (8) by briquetting (12), back to setting between two panels shape memory polymer layer plywood (2), the concave surface attachment heating layer (3) per plate shape memory polymer laminate (2).Heating layer (3) is driven shape memory polymer layer plywood (2), shape memory polymer layer plywood (2) is made to soften, mechanically, shape memory polymer layer plywood (2) folding is collapsed into O-shaped or Z-type.Present invention driving is small to the impact of system, avoids the severe impact load of expansion.
Description
Technical Field
The invention relates to a planar reflective array antenna based on a shape memory polymer composite material hinge and a spreading method thereof.
Background
The high-speed development of the aerospace industry puts higher and higher requirements on antennas. Because the antenna power required at present is higher, the speed of transmitting data is greater, therefore the demand for the size of the antenna aperture is gradually increased, and the space size of the carrier is limited, so that the structural form of the deployable antenna can be adopted to reduce the space and reduce the emission cost.
Most of traditional space expandable antenna structures adopt a mechanical or inflatable expansion mode, and have the defects of complex mechanical structure, high possibility of being damaged by impact, high cost and the like. With the development of Shape Memory Polymers (SMPs), smart deployment structures based on Shape Memory Polymer Composites (SMPCs) are now emerging. Due to the shape memory effect of the shape memory polymer composite material and the characteristics of high specific strength and specific rigidity of the shape memory polymer composite material, the mechanical structure complexity and the unfolding difficulty can be effectively reduced when the shape memory polymer composite material is applied to the unfolding structure, and due to the fact that the damping of the shape memory polymer composite material is large, the intelligent unfolding structure can be unfolded smoothly, and large impact on a system is relieved.
Disclosure of Invention
The invention aims to solve the problems of complex mechanical structure, easy damage caused by impact and high cost of the conventional mechanical or inflatable space expandable antenna structure, and provides a planar reflective array antenna based on shape memory polymer composite material hinge drive.
A planar reflective array antenna based on a shape memory polymer composite hinge is characterized in that: the planar reflection array antenna comprises a group of driving hinges and a group of substrate groups, wherein 2-16 substrate groups are connected with a satellite or a space station main body through a plurality of driving hinges, substrates in the same substrate group are connected through a plurality of driving hinges, and each substrate group comprises 2-5 substrates; each driving hinge comprises two fixed end connecting pieces, two curved shape memory polymer laminated plates are fixedly arranged between the two fixed end connecting pieces through a pressing block, the two curved shape memory polymer laminated plates are arranged back to back, a heating layer is attached to the concave surface of each shape memory polymer laminated plate, and each heating layer is connected with a power supply; wherein,
the two ends of each fixed end connecting piece are respectively a clamping end and a bearing end, two clamping pieces are arranged opposite to the clamping ends, the bearing end is provided with a bearing core, the clamping pieces and the curved bearing core are respectively provided with a mounting hole, and the curved bearing core is provided with two bearing surfaces matched with the shape memory polymer laminated plate.
A unfolding method of a planar reflective array antenna based on a shape memory polymer composite hinge is characterized in that in a preparation stage of a flexible solar cell array before emission, a shape memory polymer laminated plate is driven by a heating layer, a power supply supplies power to the heating layer to heat and raise the temperature of the heating layer, so that the shape memory polymer laminated plate is softened, the shape memory polymer laminated plate is folded and folded into an O shape or a Z shape in a mechanical mode, then the heating layer is powered off and stops heating, and the shape memory polymer laminated plate is cooled and hardened to obtain the planar reflective array antenna in the folded state; after the folded planar reflective array antenna is launched into a rail, the shape memory polymer laminated plate is excited, and after the heating layer is heated again, the folded shape memory polymer laminated plate deforms and gradually expands to push the planar reflective array antenna to expand, so that the expansion process is completed.
The invention has the beneficial effects that:
compared with the prior art, the invention has the following beneficial effects: the planar reflective array antenna driven by the shape memory polymer composite material hinge has the advantages of stable movement and reliable unfolding in the unfolding process; the hinge based on the shape memory polymer composite material has high rigidity and strength, large deformation restoring force, good shape maintaining capacity and low density in the unfolding process, can integrate power and locking functions, reduces the complexity of a deployable structure, overcomes the defects of the traditional mechanical space deployable structure and meets special space requirements. The number of the base plates can be designed according to actual requirements, and the size and the number of the hinges can be adjusted according to the size and the quality of the base plates. The invention has stable process of driving the unfolding, has small impact on the system, particularly avoids severe impact load at the beginning moment and the end stage of unfolding, and effectively improves the applicability of the planar reflective array antenna in various spacecrafts.
Drawings
FIG. 1 is a schematic view of a hinge-driving sleeve wrapped around a heat-shrinkable tube according to the present invention;
FIG. 2 is a schematic structural view of a fixed end connector according to the present invention;
FIG. 3 is a schematic diagram of the present invention in a closed state connected to a satellite or a space station body;
FIG. 4 is a schematic view of the present invention in an expanded state connected to a satellite or a space station body;
FIG. 5a is a schematic diagram of an original state of a change process from an original state to a fixed deformation state according to the working principle of the present invention;
FIG. 5b is a schematic diagram of the change process of the original state to the fixed deformation state according to the working principle of the present invention, wherein an external force is applied when the temperature is increased to T ≧ Tt;
FIG. 5c is a diagram illustrating the constraint force maintained when the temperature is decreased to T < Tt in the process of changing from the original state to the fixed state according to the working principle of the present invention;
FIG. 5d is a diagram of the temperature T < Tt maintaining deformation state in the process of changing from the original state to the fixed deformation state according to the working principle of the present invention;
FIG. 5e is a schematic diagram of the deformation recovery after T ≧ Tt due to temperature rise in the process of the fixed deformation recovery to the original state according to the working principle of the present invention;
FIG. 5f is a diagram illustrating that the temperature T < Tt returns to the original state in the change process of the permanent deformation returning to the original state according to the working principle of the present invention;
Detailed Description
The first embodiment is as follows:
as shown in fig. 1, 3 and 4, the planar reflective array antenna based on the shape memory polymer composite hinge of the present embodiment includes a set of driving hinges 8 and a set of substrate sets 9, wherein 2 to 16 substrate sets 9 are connected to a satellite or a space station main body 10 through a plurality of driving hinges, substrates 11 in the same substrate set are connected through a plurality of driving hinges 8, and each substrate set 9 includes 2 to 5 substrates 11; each driving hinge 8 comprises two fixed end connecting pieces 1, two curved shape memory polymer laminated plates 2 are fixedly arranged between the two fixed end connecting pieces 1 through pressing blocks 12, the two shape memory polymer laminated plates 2 are arranged back to back, a heating layer 3 is attached to the concave surface of each shape memory polymer laminated plate 2, and each heating layer 3 is connected with a power supply 4; wherein,
the two ends of each fixed end connecting piece 1 are respectively a clamping end and a bearing end, two clamping pieces 6 are arranged opposite to the clamping ends, a bearing core 7 is arranged at the bearing end, mounting holes 13 are respectively arranged on the clamping pieces 6 and the curved bearing core 7, and the curved bearing core 7 is provided with two bearing surfaces matched with the shape memory polymer laminated plate 2.
The fixed end connecting piece 1 is made of one of titanium alloy, aluminum alloy, epoxy composite material or cyanate composite material.
The second embodiment is as follows:
different from the first embodiment, in the planar reflective array antenna based on the shape memory polymer composite hinge of the present embodiment, the matrix of each of the shape memory polymer laminated plates 2 is the shape memory polymer, and the reinforcing phase embedded inside is the fiber reinforced composite material or the particle reinforced composite material; wherein, the reinforcing phase is made of glass fiber, carbon fiber, aramid fiber, boron fiber, graphite powder, nickel powder or carbon nano tube; the transition temperature Tt (transition temperature) of the shape memory polymer is designed by changing the material ratio to meet the working requirement, and the transition temperature Tt of the shape memory polymer is more than 170 ℃ and less than 300 ℃ under the condition of high rail working and is more than 100 ℃ and less than 200 ℃ under the condition of low rail working.
The third concrete implementation mode:
different from the first or second embodiment, in the planar reflective array antenna based on the shape memory polymer composite hinge of the present embodiment, the cross section of each of the shape memory polymer laminated plates 2 is rectangular or circular arc; wherein when the cross section of the shape memory polymer laminated plate 2 is in the shape of an arc, the arc angle corresponding to the arc is 90-180 degrees.
The fourth concrete implementation mode:
the planar reflective array antenna based on the shape memory polymer composite material hinge is different from the planar reflective array antenna based on the third specific embodiment in that the heating layer 3 is one of an embedded resistance wire, a coated conductive adhesive or a pasted electrothermal film.
The fifth concrete implementation mode:
different from the first, second or fourth embodiments, in the planar reflective array antenna based on the smp hinge of the present embodiment, when the thermal layer 3 is an attached electrothermal film, the exterior of the smp laminate 2 attached to the heating layer 3 is wrapped with the thermal shrinkage tube 5, and meanwhile, the thermal insulation material or the aluminum foil is sleeved on the exterior of the thermal shrinkage tube 5 on one side of the smp laminate 2, so as to reduce the heat dissipation between the heating layer 3 and the smp laminate 2.
The sixth specific implementation mode:
unlike the fifth embodiment, in the planar reflective array antenna based on the smp hinge of the present embodiment, the substrate group 9 is connected to the satellite or the space station main body 10 through 2 to 6 driving hinges 8, and the substrates 11 in the same substrate group 9 are connected through 2 to 6 driving hinges 8.
The seventh embodiment:
different from the first, second, fourth or sixth embodiments, in the planar reflective array antenna based on the smp hinge of the present embodiment, the substrates 11 in the same substrate group 9 are arranged in series or in parallel.
The specific implementation mode is eight:
in the planar reflective array antenna based on the shape memory polymer composite hinge according to the seventh embodiment, a sensor 14 is mounted on each of the driving hinges 8 to determine the speed and the accuracy of the shape memory polymer composite hinge during the unfolding process.
The specific implementation method nine:
in a preparation stage of a flexible solar cell array before emission, the shape memory polymer laminated plate 2 is driven by the heating layer 3, the power supply 4 supplies power to the heating layer 3 to heat the heating layer 3, so that the shape memory polymer laminated plate 2 is softened, the shape memory polymer laminated plate 2 is folded and folded into an O shape or a Z shape in a mechanical mode, then the heating layer 3 is powered off, heating is stopped, and the shape memory polymer laminated plate 2 is cooled and hardened to obtain the planar reflective array antenna in a folded state; after the folded planar reflective array antenna is launched into a rail, the shape memory polymer laminated plate 2 is excited, and after the heating layer 3 is heated again, the folded shape memory polymer laminated plate 2 deforms and gradually expands to push the planar reflective array antenna to expand, so that the expansion process is completed. The heating layer 3 is heated by direct heating, embedded resistance wire heating, conductive adhesive coating heating or external electric heating film heating, when the external electric heating film is heated, the outside of the shape memory polymer laminated plate 2 adhered with the heating layer 3 is wrapped with a heat shrink tube 5, and meanwhile, the outside of the heat shrink tube 5 at one side of the shape memory polymer laminated plate 2 is sleeved with a heat insulation material or an aluminum foil.
The detailed implementation mode is ten:
different from the ninth embodiment, the deployment method of the planar reflective array antenna based on the shape memory polymer composite hinge according to the present embodiment is that the planar reflective array antenna is deployed by the respective substrates 11 simultaneously or by the substrates 11 in stages.
The present invention is capable of other embodiments and its several details are capable of modifications in various obvious respects, all without departing from the spirit and scope of the present invention.
Claims (6)
1. A planar reflective array antenna based on a shape memory polymer composite hinge is characterized in that: the planar reflective array antenna comprises a group of driving hinges (8) and a group of substrate groups (9), wherein 2-16 substrate groups (9) are connected with a satellite or space station main body (10) through a plurality of driving hinges, substrates (11) in the same substrate group are connected through a plurality of driving hinges (8), and each substrate group (9) comprises 2-5 substrates (11); each driving hinge (8) comprises two fixed end connecting pieces (1), two curved shape memory polymer laminated plates (2) are fixedly arranged between the two fixed end connecting pieces (1) through pressing blocks (12), the two shape memory polymer laminated plates (2) are arranged back to back, a heating layer (3) is attached to the concave surface of each shape memory polymer laminated plate (2), and each heating layer (3) is connected with a power supply (4); wherein,
the two ends of each fixed end connecting piece (1) are respectively a clamping end and a bearing end, two clamping sheets (6) are arranged at the clamping ends in an opposite mode, a bearing core (7) is arranged at the bearing end, mounting holes (13) are respectively formed in the clamping sheets (6) and the curved bearing core (7), and the curved bearing core (7) is provided with two bearing surfaces matched with the shape memory polymer laminated plate (2);
the matrix of each piece of the shape memory polymer laminated plate (2) is a shape memory polymer, and the reinforcing phase embedded inside is a fiber reinforced composite material or a particle reinforced composite material; wherein, the reinforcing phase is made of glass fiber, carbon fiber, aramid fiber, boron fiber, graphite powder, nickel powder or carbon nano tube; under the condition of high rail work, the transition temperature Tt of the shape memory polymer is more than 170 ℃ and less than 300 ℃, and under the condition of low rail work, the transition temperature Tt of the shape memory polymer is more than 100 ℃ and less than 200 ℃;
the cross section of each piece of the shape memory polymer laminated plate (2) is rectangular or circular arc; when the cross section of the shape memory polymer laminated plate (2) is in the shape of an arc, the arc angle corresponding to the arc is 90-180 degrees;
the heating layer (3) is one of an embedded resistance wire, a coated conductive adhesive or a pasted electrothermal film;
when the thermal layer (3) is a bonded electric heating film, a heat-shrinkable tube (5) is wrapped outside the shape memory polymer laminated plate (2) bonded with the heating layer (3), and a heat-insulating material or an aluminum foil is sleeved outside the heat-shrinkable tube (5) on one side of the shape memory polymer laminated plate (2).
2. The planar reflective array antenna based on the shape memory polymer composite hinge as claimed in claim 1, wherein: the base plate group (9) is connected with the satellite or the space station main body (10) through 2-6 driving hinges (8), and the base plates (11) in the same base plate group (9) are connected through 2-6 driving hinges (8).
3. The planar reflective array antenna based on the shape memory polymer composite hinge as claimed in claim 1 or 2, wherein: the substrates (11) in the same substrate group (9) are arranged in a serial or parallel mode.
4. The planar reflective array antenna based on the shape memory polymer composite hinge as claimed in claim 3, wherein: a sensor (14) is arranged on each driving hinge (8).
5. A method of deploying a planar reflective array antenna based on a shape memory polymer composite hinge according to any of the preceding claims, wherein: in the preparation stage of the flexible solar cell array before emission, the shape memory polymer laminated plate (2) is driven by the heating layer (3), the power supply (4) supplies power to the heating layer (3) to heat and raise the temperature of the heating layer (3), so that the shape memory polymer laminated plate (2) is softened, the shape memory polymer laminated plate (2) is folded and folded into an O shape or a Z shape in a mechanical mode, then the heating layer (3) is powered off, heating is stopped, and the shape memory polymer laminated plate (2) is cooled and hardened to obtain the planar reflective array antenna in the folded and folded state; after the folded planar reflective array antenna is launched into a rail, the shape memory polymer laminated plate (2) is excited, after the heating layer (3) is heated again, the folded shape memory polymer laminated plate (2) deforms, and gradually expands to push the planar reflective array antenna to expand, so that the expansion process is completed.
6. The deployment method of the planar reflective array antenna based on the shape memory polymer composite hinge according to claim 5, wherein: the planar reflective array antenna is unfolded simultaneously through the substrates (11) or is unfolded step by step one by one (11).
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| CN201510756620.2A CN105356029B (en) | 2015-11-09 | 2015-11-09 | Plane reflection array antenna and its method of deploying based on shape memory polymer composite material hinge |
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| CN201510756620.2A CN105356029B (en) | 2015-11-09 | 2015-11-09 | Plane reflection array antenna and its method of deploying based on shape memory polymer composite material hinge |
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| CN105356029A CN105356029A (en) | 2016-02-24 |
| CN105356029B true CN105356029B (en) | 2018-06-22 |
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| CN107465449B (en) * | 2017-09-18 | 2021-01-05 | 云南电网有限责任公司红河供电局 | Control method and device for antenna of emergency communication system |
| GB2571740A (en) * | 2018-03-07 | 2019-09-11 | Oxford Space Systems Ltd | Deployable spacecraft body |
| CN110510150B (en) * | 2018-05-21 | 2022-06-21 | 哈尔滨工业大学 | Spider web capturing structure based on intelligent composite material and capturing method thereof |
| CN111071484B (en) * | 2018-10-19 | 2021-03-30 | 哈尔滨工业大学 | Space unfolding mechanism and method based on shape memory polymer composite material |
| CN109204886B (en) * | 2018-11-07 | 2024-01-30 | 哈尔滨工业大学 | Shape memory hinge unfolding structure |
| CN111328182A (en) * | 2018-12-13 | 2020-06-23 | 哈尔滨工业大学 | Deformed circuit board based on shape memory polymer composite material |
| CN109713420B (en) * | 2018-12-29 | 2020-07-17 | 长沙天仪空间科技研究院有限公司 | Inflatable antenna with expandable space |
| CN109466800B (en) * | 2018-12-29 | 2024-02-06 | 哈尔滨工业大学 | Guarantee system of space unfolding mechanism |
| CN113276440B (en) * | 2021-05-24 | 2022-03-01 | 哈尔滨工业大学 | Preparation method and unfolding and recycling method of thin-wall column shell structure |
| CN114408218B (en) * | 2022-02-15 | 2024-05-28 | 长沙天仪空间科技研究院有限公司 | Control system of space expandable mechanism |
| CN115246998A (en) * | 2022-08-15 | 2022-10-28 | 北京航空航天大学 | Composite material hinge based on folding and expansion of shape memory composite material control |
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