CN109204889B - Flexible solar wing mechanism - Google Patents
Flexible solar wing mechanism Download PDFInfo
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- CN109204889B CN109204889B CN201811320480.4A CN201811320480A CN109204889B CN 109204889 B CN109204889 B CN 109204889B CN 201811320480 A CN201811320480 A CN 201811320480A CN 109204889 B CN109204889 B CN 109204889B
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- wing mechanism
- flexible solar
- shape memory
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- 238000010438 heat treatment Methods 0.000 claims abstract description 44
- 229920000431 shape-memory polymer Polymers 0.000 claims abstract description 29
- 239000000463 material Substances 0.000 claims description 19
- 210000004027 cell Anatomy 0.000 claims description 9
- 230000001681 protective effect Effects 0.000 claims description 8
- 239000004593 Epoxy Substances 0.000 claims description 6
- XLJMAIOERFSOGZ-UHFFFAOYSA-M cyanate Chemical compound [O-]C#N XLJMAIOERFSOGZ-UHFFFAOYSA-M 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 5
- 210000000170 cell membrane Anatomy 0.000 claims description 4
- 239000004642 Polyimide Substances 0.000 claims description 3
- NIXOWILDQLNWCW-UHFFFAOYSA-N acrylic acid group Chemical group C(C=C)(=O)O NIXOWILDQLNWCW-UHFFFAOYSA-N 0.000 claims description 3
- 239000003733 fiber-reinforced composite Substances 0.000 claims description 3
- 239000002245 particle Substances 0.000 claims description 3
- 229920001721 polyimide Polymers 0.000 claims description 3
- 238000000034 method Methods 0.000 abstract description 5
- 230000008569 process Effects 0.000 abstract description 4
- 230000009477 glass transition Effects 0.000 description 14
- 238000005452 bending Methods 0.000 description 6
- 239000002952 polymeric resin Substances 0.000 description 5
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- 230000009471 action Effects 0.000 description 3
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- 230000002787 reinforcement Effects 0.000 description 3
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- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 235000010627 Phaseolus vulgaris Nutrition 0.000 description 2
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
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- ZOXJGFHDIHLPTG-UHFFFAOYSA-N Boron Chemical compound [B] ZOXJGFHDIHLPTG-UHFFFAOYSA-N 0.000 description 1
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
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- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
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- 229920006231 aramid fiber Polymers 0.000 description 1
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- SZVJSHCCFOBDDC-UHFFFAOYSA-N ferrosoferric oxide Chemical compound O=[Fe]O[Fe]O[Fe]=O SZVJSHCCFOBDDC-UHFFFAOYSA-N 0.000 description 1
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
Abstract
The invention discloses a flexible solar wing mechanism, which relates to the technical field of aerospace and comprises a solar energy collecting device; the stretching device is made of shape memory polymer, is in a pod rod shape and drives the solar energy collecting device to be folded and unfolded; and a heating device that heats the stretching device. Compared with the traditional mechanical unfolding mechanism, the flexible solar wing mechanism has obvious advantages of being capable of effectively reducing the complexity of the mechanical structure and the unfolding difficulty, being slow in unfolding process, small in impact on a spacecraft, capable of realizing self-locking and self-unfolding, simple in structure, lower in cost, higher in rigidity after unfolding and capable of improving the unfolding stability of the solar wing.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a flexible solar wing mechanism.
Background
Along with development of aerospace technology, as requirements of people on unfolding mechanisms are higher, power and quality requirements on solar wings are higher, but as power is increased, quality of a traditional mechanical rigid solar wing panel is also linearly increased, and overall frequency of a satellite is reduced due to the increase of quality. The traditional solar wing is mostly unfolded mechanically, and has the defects of complex mechanical structure, easy impact damage, high quality, high cost and the like.
In view of the above drawbacks, the present inventors have finally achieved the present invention through long-time studies and practices.
Disclosure of Invention
In order to solve the technical defects, the invention adopts the technical proposal that a flexible solar wing mechanism is provided, which comprises
A solar energy collection device;
the stretching device is made of shape memory polymer, is in a pod rod shape and drives the solar energy collecting device to be folded and unfolded;
and a heating device that heats the stretching device.
Further, the solar energy collecting device comprises a plurality of solar cell membranes, and the solar cell membranes are fixed between two adjacent stretching devices.
Further, the solar wing mechanism further comprises a base plate, and the stretching device is fixedly connected with the base plate.
Further, the stretching device is fixedly connected with the substrate through a connecting piece, the connecting piece comprises an inner core and a protective sheet, and the inner core and the protective sheet clamp and fix the stretching device.
Further, the solar wing mechanism further comprises a sleeve, and the stretching device drives the solar cell film to be folded around the sleeve to be curled.
Further, a slot is arranged on the sleeve, an inserting sheet matched with the slot is arranged on the stretching device, and the inserting sheet is inserted into the slot to be fixedly connected.
Further, the heating device comprises a heating film, and the heating film is arranged on the surface and/or the inside of the stretching device.
Further, the heating film is adhered to the surface of the stretching device through a high-temperature resistant polyimide double faced adhesive tape or a high-temperature resistant acrylic double faced adhesive tape, and/or the heating film is fixed inside the stretching device.
Further, the shape memory polymer comprises an epoxy shape memory polymer or a cyanate shape memory polymer.
Further, the shape memory polymer contains a fiber reinforced composite material or a particle reinforced composite material.
Compared with the prior art, the invention has the beneficial effects that:
1. compared with the traditional mechanical unfolding mechanism, the flexible solar wing mechanism has obvious advantages of being capable of effectively reducing the complexity of the mechanical structure and the unfolding difficulty, being slow in unfolding process, small in impact on a spacecraft, capable of realizing self-locking and self-unfolding, simple in structure, lower in cost, higher in rigidity after unfolding and capable of improving the unfolding stability of the solar wing.
2. The flexible solar wing mechanism has the shape of self-locking before unfolding, controllable unfolding process, rapid rigidification after unfolding, high rigidity and large-size forming, and the pod-shaped stretching device is in a pod shape, so that the strain energy stored in a material deformation state and the rigidity of an unfolding state can be greatly improved, and the self-adaptability of the unfolding mechanism enables the flexible solar wing mechanism to have a great application prospect in a flexible solar wing unfolding technology.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are used in the description of the embodiments will be briefly described below.
FIG. 1 is a schematic view of an extension device of the present invention;
FIG. 2 is a cross-sectional view of the extension device of the present invention;
FIG. 3 is a schematic cross-sectional view of the extension device of the present invention;
FIG. 4 is a flexible sun spanwise schematic of the present invention;
FIG. 5 is a schematic diagram of a socket according to the present invention;
FIG. 6 is a schematic view of a connector of the present invention;
FIG. 7 is a schematic drawing of a flexible solar wing gather of the present invention;
FIG. 8 is an expanded schematic view of the shape memory hinge of the present invention;
FIG. 9 is a drawing in schematic view of a shape memory hinge of the present invention;
FIG. 10 is an expanded schematic view of the shape memory hinge of the present invention connected in series;
FIG. 11 is a schematic drawing of the shape memory hinge of the present invention in series connection;
FIG. 12 is an expanded schematic view of the shape memory hinge of the present invention connected in parallel;
FIG. 13 is a drawing in schematic view of the shape memory hinge of the present invention connected in parallel.
The figures represent the numbers:
1-stretching device, 11-middle arc part, 12-side arc part, 13-end straight part, 2-heating film, 3-solar cell film, 4-connecting piece, 41-inner core, 411-annular bulge, 42-protective sheet, 5-sleeve, 51-slot, 6-substrate and 7-fixture.
Detailed Description
The above and further technical features and advantages of the present invention are described in more detail below with reference to the accompanying drawings.
Example 1
The invention provides a flexible solar wing mechanism which comprises an extension device, a solar collecting device and a heating device, wherein the heating device can excite the extension device to fold or unfold, the solar collecting device is fixedly connected with the extension device, the extension device drives the solar collecting device to fold and unfold, when a solar wing is not required to work, the extension device can drive the solar collecting device to fold into a smaller volume, when a spacecraft runs to a formulated track, and when the solar wing is required to collect solar energy, the extension device drives the solar collecting device to unfold, the receiving area of the solar collecting device is enlarged, and the unfolding of the flexible solar wing is completed.
Referring to fig. 1-4, the stretching device 1 is in a long rod shape, the cross section of the stretching device 1 is in a bean shape, the stretching device 1 is in a hollow bean pod rod type structure, the stretching device 1 is made of a shape memory polymer material, and specifically, an epoxy shape memory polymer resin or a cyanate shape memory polymer resin is adopted, and the glass transition temperature of the epoxy shape memory polymer resin or the cyanate shape memory polymer resin is selected according to actual needs; the shape memory polymer material is a novel intelligent material with shape memory effect, firstly, the material can be prepared into a body with an initial shape, when the temperature of the material is higher than the inherent glass transition temperature Tg, the material is changed from rigidity to flexibility, at the moment, deformation such as bending or curling can be carried out under the action of external force, when the temperature is reduced and lower than the glass transition temperature Tg, even if the external force is removed, the material can keep the deformed shape and be in a rigid state, when the temperature of the material is increased and higher than the inherent glass transition temperature Tg, the material is not influenced by the external force, the material becomes flexible and can be restored to the initial shape by itself, and after the temperature is reduced and lower than the glass transition temperature Tg again, the material is restored to rigidity and keeps the initial shape.
According to the embodiment, the stretching device 1 prepared from the shape memory polymer material is used in a device to be stretched in a spacecraft by utilizing the special properties of the shape memory polymer, the temperature of the stretching device 1 is controlled by matching with a heating device, in an initial state, the stretching device 1 is in a stretched straight rod shape, the heating device heats the stretching device 1, when the temperature of the stretching device 1 rises and exceeds the glass transition temperature Tg of the shape memory polymer, the stretching device 1 is converted into a flexible state, the stretching device is bent or curled and folded under the action of external force, after the stretching device is bent to a preset shape, the heating device stops heating, the stretching device 1 is restored to a rigid state, the external force is removed, the stretching device 1 keeps the bent and folded shape, and at the moment, the stretching device 1 can drive other devices to be in a folded state together, so that the stretching area of the spacecraft is reduced, and the spacecraft is folded to a smaller volume; when the spacecraft enters a predetermined orbit and needs to be deployed on the component device, the heating device heats the stretching device 1 again, and when the stretching device 1 reaches and exceeds the glass transition temperature Tg of the shape memory polymer again, the stretching device 1 automatically returns to the initial deployed shape, and at the moment, the device which needs to be deployed in the spacecraft reaches the deployed shape.
The heating device can adopt one or more combination modes of externally-attached heating films, internally-buried resistance wire heating, externally-coated conductive adhesive heating, sunlight irradiation, ultraviolet irradiation driving, magnetic field driving or microwave driving and the like to heat the stretching device 1, wherein the heating device can be arranged outside the stretching device 1 or inside the stretching device 1; in this embodiment, the heating device adopts an electric heating mode to heat the stretching device 1, specifically, the heating film 2 is fixed on the outer surface of the stretching device 1, the heating film 2 is adhered on the curved side wall of the stretching device 1, the adhesion mode is that polyimide double faced adhesive tape with high temperature resistance or acrylic double faced adhesive tape with high temperature resistance is used for adhesion, the connection firmness of the heating film 2 and the stretching device 1 is improved, and the falling of the heating film 2 caused by the rising of temperature is avoided.
The flexible solar wing mechanism can effectively reduce the complexity and the unfolding difficulty of a mechanical structure when applied to the technical field of aviation, has obvious advantages compared with the traditional method of using a mechanical stretching device, has the advantages that the damping of a shape memory polymer is larger, the unfolding process is slower, the impact on a spacecraft is small, the self-locking and the self-unfolding can be realized, the structure is simple, the flexible solar wing mechanism can be endowed with a desired shape according to the requirement when heated, the folding state can be kept after cooling, and the stretching of the shape memory pod rod can be completed when the stretching is required, so that a new idea is provided for a future space-expandable structure; in addition, the stretching device 1 is designed into a pod rod shape, so that the strain energy stored in the deformation state of the stretching device 1 and the rigidity in the unfolding state are greatly improved.
Example two
The embodiment provides a specific structure of a flexible solar wing, which is shown in fig. 4, and comprises an expansion device 1, a heating film 2, a solar cell film 3, a connecting piece 4, a sleeve 5 and a substrate 6, wherein the solar cell film 3 is a flexible cell film and can be deformed such as curled; the excitation mode of the stretching device 1 in the embodiment is that a heating film 2 is stuck on the surface; the sleeve 5 is of a hollow cylindrical structure, the extension device 1 is fixed on curved surfaces at two ends of the sleeve 5, preferably, as shown in fig. 5, the sleeve 5 is provided with a slot 51 at the position where the extension device 1 is connected, the top end of the extension device 1 is provided with an inserting sheet 11 matched with the slot 51, the inserting sheet 11 is a straight sheet part at two ends of the pod-shaped extension device 1, which is left after the middle pod-shaped part is cut off, the inserting sheet 11 is inserted into the slot 51, and the fixed connection between the extension device 1 and the sleeve 5 is realized through a screw; the lower end of the stretching device 1 is fixedly connected with the base plate 6 through a connecting piece 4, and as shown in fig. 6, the connecting piece 4 comprises an inner core 41 and a protective piece 42, an annular bulge 411 is arranged on the inner core 41, the annular bulge 411 is inserted into the bottom end of the stretching device 1, two protective pieces 42 are arranged on the outer side of the circumference of the annular bulge 411, the protective piece 42 and the stretching device 1 are fixedly connected with the inner core 21 through screws, the stretching device 1 is fixedly connected with the connecting piece 4, preferably, the bottom corners of the solar cell film 3 are inserted between the protective piece 42 and the inner core 41, and the solar cell film 3 is fixedly connected with the connecting piece 4 through screws; the bottom of connecting piece 4 passes through screw and base plate 6 fixed connection, and base plate 6 is fixed on the spacecraft.
In the flexible solar wing described in this embodiment, as shown in fig. 7, before the spacecraft in which the flexible solar wing is located is launched, the stretching device 1 is heated to the glass transition temperature Tg of the material and then curled into a cylindrical shape around the sleeve 5 at the end, and at this time, the flexible solar wing is in a folded state; after the spacecraft enters a preset orbit, the heating film 2 gives temperature excitation to the stretching device 1, and at the moment, the stretching device 1 in a curled state returns to an original straight rod state, so that the middle flexible solar cell film 3 is driven to be unfolded.
The screw connection in this embodiment is only one of the fixing connection modes described in the example, and the connection modes with the fixing connection function can be used in the present invention, but the fixing connection mode of the present invention is not limited to the screw connection.
Example III
In this embodiment, based on the above embodiment, the stretching device 1 is made of a shape memory polymer composite material, the shape memory polymer composite material includes a base material and a reinforcing material, the base material is an epoxy shape memory polymer or cyanate shape memory polymer resin, and the glass transition temperature Tg of the epoxy shape memory polymer is 80 ℃, 100 ℃, 120 ℃, 150 ℃, 170 ℃, or the like; the cyanate is selected from glass transition temperature Tg of 180 ℃ or 210 ℃ and the like according to the required glass transition temperature Tg; the reinforcing material is fiber reinforced composite material or particle reinforced composite material, and specifically, glass fiber, carbon fiber, aramid fiber, boron fiber, graphene, nickel powder, carbon nano tube or one or more combinations of hollow nano ferroferric oxide particles are selected.
In this embodiment, the shape memory polymer composite material may be prepared by vacuum assisted resin molding, and when the composite material reinforcement may be performed by continuous fiber reinforcement such as continuous carbon fiber or glass fiber reinforcement, the fiber laying angle may be a symmetrical orthogonal laying or an angular symmetrical laying, and the laying angle may be selected from 0 °, 45 °, 90 °, and other angles.
Example IV
In this embodiment, on the basis of the above embodiment, as shown in fig. 3, the cross section of the stretching device 1 is in a symmetrical pod shape, the stretching device 1 is made of two half-pod sheet materials, preferably, the thickness t of the sheet materials forming the stretching device 1 is in the range of 0.5-1.5mm, the stretching device 1 comprises a middle arc part 11, side arc parts 12 and end straight parts 13, the middle arc part 11 is located between the two side arc parts 12, the two end straight parts 13 are located at the outer ends of the two side arc parts 12 respectively, and the end straight parts 13 are in a flat plate shape.
According to a beam section bending stiffness calculation formula ei=m/(1/R) =m/phi, when the maximum bending moment M is fixed, the larger the section curvature radius R is, namely the smaller the section curvature is, so that the section stiffness EI is larger, in this embodiment, the larger the arc radius R1 of the middle arc portion 11 and the arc radius R2 of the side arc portion 12 are, the larger the section stiffness of the formed stretching device 1 is; the magnitude of the middle arc angle beta influences the roundness of the cross section, and the smaller the middle arc angle beta is, the simpler the bending and shaping of the stretching device 1 is.
In this embodiment, the stretching device 1 is a symmetrical pod rod, and when in manufacture, half pod rod parts are firstly manufactured, and then the two half pod rod parts are bonded and cured by using the same shape memory polymer, or are directly cured and molded by adopting integrated laid fibers.
Example five
According to the embodiment, on the basis of the embodiment, the heating film 2 and the laminated plate are wrapped with the heat shrinkage pipe, and meanwhile, the heat insulation material or the aluminum foil is sleeved on the heat shrinkage pipe, so that heat dissipation of the heater and the laminated plate can be reduced, and heating efficiency of the heating film 2 is improved.
Example six
In this embodiment, based on the foregoing embodiment, the stretching device 1 in the foregoing embodiment may form a shape memory hinge stretching structure, as shown in fig. 8-9, including the stretching device 1 in any one of the foregoing embodiments, where two ends of the stretching device 1 are provided with clamps 7, the clamps 7 are used to connect two other devices of the stretching device 1, in this embodiment, the clamps only represent one implementation mode, and the structure capable of connecting the stretching device 1 with two other devices of the two ends may be used in this embodiment, so as to implement the shape memory hinge stretching structure in this embodiment, where the stretching device 1 is heated by a heating device and is bent into a folded state when the temperature exceeds its glass transition temperature Tg, such as a U shape, after the temperature is reduced, the stretching device 1 maintains the folded state, and bending of the hinge achieves folding of the two devices of the two ends; when the spacecraft enters space and runs to a preset orbit, the heating device heats the stretching device 1 again, after the temperature exceeds the glass transition temperature Tg of the stretching device 1, the hinges drive the two side devices to realize the stretching of the device in the spacecraft, and in the embodiment, the stretching device is heated in a mode of sticking a heating film on the surface of the stretching device 1.
Example seven
Based on the above embodiment, the hinge unfolding structure may be used alone or in multiple series or parallel when used in series, and when used in series, as shown in fig. 10-11, the two stretching devices 1 and two ends of the two stretching devices are both fixed with connecting rods through the clamp 7, so as to form a connection mode of connecting the three connecting rods of the two stretching devices 1 in series, in the initial stage, the hinges and the connecting rods are in a straight rod state, the heating film gradually heats the stretching devices 1 in the hinges, when exceeding the glass transition temperature Tg of the heating film, the stretching devices 1 are bent into a "U" shape under the action of external force, at the moment, the two hinges with opposite bending directions are in the two U shapes, so that the overall structure is similar to an "S" shape, at the moment, the three connecting rods are in a folded state, and after the spacecraft drives the hinges to enter a space preset track, the heating film gradually heats the stretching devices 1 in the hinges, and the stretching devices 1 are gradually unfolded and restored to the initial state, so that the stretching of the connecting rods is realized.
In this embodiment, when the hinge expansion structures are used in parallel, as shown in fig. 12-13, one end of the two hinge expansion structures in the same direction is connected with a solar panel, the other end of the two hinge expansion structures is connected with another solar panel, and the two hinge expansion structures are used in parallel, so that the expansion stability of the solar panel and the connection strength after expansion can be increased.
The foregoing description of the preferred embodiment of the invention is merely illustrative of the invention and is not intended to be limiting. It will be appreciated by persons skilled in the art that many variations, modifications, and even equivalents may be made thereto without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (10)
1. A flexible solar wing mechanism, comprising
A solar energy collection device;
the expansion device (1), the expansion device (1) is made of shape memory polymer, the expansion device (1) is pod rod type, and the expansion device (1) drives the solar energy collecting device to be folded and unfolded;
-heating means for heating the stretching means (1);
the cross section of the stretching device (1) is in a symmetrical pod shape, the stretching device (1) is made of two half-pod sheet materials, and the thickness t of the sheet materials forming the stretching device (1) is in the range of 0.5-1.5 mm.
2. A flexible solar wing mechanism according to claim 1, characterized in that the solar energy collecting means comprises a plurality of solar cell membranes (3), the stretching means (1) being a plurality, the solar cell membranes (3) being fixed between adjacent two of the stretching means (1).
3. A flexible solar wing mechanism according to claim 1, characterized in that the solar wing mechanism further comprises a base plate (6), the stretching means (1) being fixedly connected to the base plate (6).
4. A flexible solar wing mechanism according to claim 3, characterised in that the stretching means (1) is fixedly connected to the base plate (6) by means of a connecting piece (4), the connecting piece (4) comprising an inner core (41) and a protective sheet (42), the inner core (41) and the protective sheet (42) clamping and fixing the stretching means (1).
5. A flexible solar wing mechanism according to claim 2, characterized in that the solar wing mechanism further comprises a sleeve (5), the stretching means (1) bringing the solar cell film (3) around the sleeve (5) into a rolled shape.
6. The flexible solar wing mechanism according to claim 5, characterized in that the sleeve (5) is provided with a slot (51), the extension device (1) is provided with an inserting sheet (11) matched with the slot (51), and the inserting sheet (11) is inserted into the slot (51) to be fixedly connected.
7. Flexible solar wing mechanism according to claim 1, characterized in that the heating means comprise a heating film (2), the heating film (2) being arranged at the surface and/or inside the stretching means (1).
8. Flexible solar wing mechanism according to claim 7, characterized in that the heating film (2) is glued on the surface of the stretching device (1) by means of a high temperature resistant polyimide double sided tape or a high temperature resistant acrylic double sided tape and/or that the heating film (2) is fixed inside the stretching device (1).
9. The flexible solar wing mechanism of claim 1, wherein the shape memory polymer comprises an epoxy-based shape memory polymer or a cyanate-based shape memory polymer.
10. The flexible solar wing mechanism of claim 9, wherein the shape memory polymer comprises a fiber reinforced composite or a particle reinforced composite.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811320480.4A CN109204889B (en) | 2018-11-07 | 2018-11-07 | Flexible solar wing mechanism |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811320480.4A CN109204889B (en) | 2018-11-07 | 2018-11-07 | Flexible solar wing mechanism |
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| CN109204889A CN109204889A (en) | 2019-01-15 |
| CN109204889B true CN109204889B (en) | 2024-02-09 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112078778A (en) * | 2019-06-13 | 2020-12-15 | 海鹰航空通用装备有限责任公司 | Folding expansion device of intelligence |
| CN114162351A (en) * | 2021-12-31 | 2022-03-11 | 中国航天空气动力技术研究院 | Pod-shaped supporting rod device |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103240894A (en) * | 2013-05-06 | 2013-08-14 | 南京航空航天大学 | Pod rod pultrusion device and method capable of ensuring straightness accuracy |
| CN107628270A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of bean-pod shaped bracing stick casts development mechanism aside |
| CN209225429U (en) * | 2018-11-07 | 2019-08-09 | 哈尔滨工业大学 | A kind of flexibility sun wing mechanism |
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2018
- 2018-11-07 CN CN201811320480.4A patent/CN109204889B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103240894A (en) * | 2013-05-06 | 2013-08-14 | 南京航空航天大学 | Pod rod pultrusion device and method capable of ensuring straightness accuracy |
| CN107628270A (en) * | 2017-07-31 | 2018-01-26 | 上海宇航系统工程研究所 | A kind of bean-pod shaped bracing stick casts development mechanism aside |
| CN209225429U (en) * | 2018-11-07 | 2019-08-09 | 哈尔滨工业大学 | A kind of flexibility sun wing mechanism |
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