CN113548200A - Semi-rigid base plate of lightweight chord-tightening type solar wing - Google Patents
Semi-rigid base plate of lightweight chord-tightening type solar wing Download PDFInfo
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- CN113548200A CN113548200A CN202110767090.7A CN202110767090A CN113548200A CN 113548200 A CN113548200 A CN 113548200A CN 202110767090 A CN202110767090 A CN 202110767090A CN 113548200 A CN113548200 A CN 113548200A
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- 239000000758 substrate Substances 0.000 claims abstract description 49
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 26
- 239000000463 material Substances 0.000 claims abstract description 15
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 14
- 238000007906 compression Methods 0.000 claims abstract description 12
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 11
- 239000004917 carbon fiber Substances 0.000 claims abstract description 11
- 230000006835 compression Effects 0.000 claims abstract description 11
- 239000004642 Polyimide Substances 0.000 claims abstract description 6
- 229910001069 Ti alloy Inorganic materials 0.000 claims abstract description 6
- 239000000956 alloy Substances 0.000 claims abstract description 6
- 238000005056 compaction Methods 0.000 claims abstract description 6
- 229920001721 polyimide Polymers 0.000 claims abstract description 6
- 230000002787 reinforcement Effects 0.000 claims description 7
- 238000004026 adhesive bonding Methods 0.000 claims description 6
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 239000003351 stiffener Substances 0.000 claims 1
- 239000003292 glue Substances 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 239000007769 metal material Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 229910052755 nonmetal Inorganic materials 0.000 description 2
- 238000010248 power generation Methods 0.000 description 2
- 238000003825 pressing Methods 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
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- 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
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
- H02S30/00—Structural details of PV modules other than those related to light conversion
- H02S30/10—Frame structures
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/50—Photovoltaic [PV] energy
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- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
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- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a lightweight strung-string type solar wing semi-rigid substrate.A substrate frame of the semi-rigid substrate comprises a plurality of transverse main beams, a plurality of longitudinal main beams, a limiting beam and a compression point reinforcing piece; the string stretching assembly comprises a plurality of transverse strings, a plurality of longitudinal strings and a plurality of string stretching brackets; the plurality of guy wire brackets are fixedly connected with the rectangular frame; the transverse guy wires are arranged in parallel with the transverse main beam, and the two ends of the transverse guy wires are respectively wound around the symmetrically arranged guy wire brackets and then are fixedly connected with the longitudinal main beam; the longitudinal guy wires are arranged in parallel with the longitudinal main beam, and the two ends of the longitudinal guy wires are respectively wound around the symmetrically arranged guy wire brackets and then are fixedly connected with the transverse main beam; the limiting beam is used for limiting the amplitude of the transverse guy wires and the longitudinal guy wires; the string stretching bracket is made of polyimide material; the transverse main beam, the longitudinal main beam and the limiting beam are all made of high-modulus carbon fiber materials; the compaction point reinforcing piece is made of titanium alloy material. The semi-rigid substrate can effectively reduce the weight area ratio of the solar wing substrate.
Description
Technical Field
The invention relates to the technical field of solar wings, in particular to a light-weight chord-tightening type semi-rigid solar wing substrate.
Background
With the development of technology, the power demand of the spacecraft is also increasing, and the power demand of the large-scale communication satellite reaches dozens of kilowatts at present, so that the solar wing is required to have a larger area, but the weight of the solar wing is increased in the same proportion with the increase of the area, and the weight of the spacecraft is required to be as light as possible due to the limitation of carrying thrust, so that the weight of the solar wing is also required to be as light as possible.
The traditional rigid solar wing substrate adopts a carbon fiber panel and aluminum honeycomb structure form, and the weight area ratio of the traditional rigid solar wing substrate is about (1.6-2) kg/m2Along with the increase of the area, the weight of the solar wing substrate is increased in the same proportion, and when the area of the solar wing reaches 60m2In the case of the solar cell, the weight of only the substrate portion is as high as 100kg, and the weight of the solar cell circuit portion, which is a portion directly supplying power, is only 60kg, which is much smaller than that of the structure portion, so that it is required to provide a solar panel substrate having a lower weight to area ratio. .
Disclosure of Invention
In view of the above, the invention provides a lightweight chord-stretched solar wing semi-rigid substrate, which can effectively reduce the weight-area ratio of a solar wing substrate, further reduce the weight of a solar wing structure part, and solve the problem of overlarge weight of the solar wing structure part of a large spacecraft.
The invention adopts the following specific technical scheme:
a lightweight strung-string type solar wing semi-rigid substrate comprises a substrate frame and a strung-string component;
the base plate frame comprises a plurality of transverse main beams, a plurality of longitudinal main beams, a limiting beam and a compression point reinforcing piece; the transverse main beams and the longitudinal main beams are arranged in a criss-cross mode to form a rectangular frame, and the transverse main beams and the longitudinal main beams are fixedly connected at the cross points through the compression point reinforcing pieces; the limiting beam is arranged in parallel with the longitudinal main beam and is fixedly connected to one side of the rectangular frame;
the string tensioning assembly comprises a plurality of transverse strings, a plurality of longitudinal strings and a plurality of string tensioning brackets; the plurality of guy wire brackets are distributed along the outer peripheral side of the rectangular frame and are fixedly connected with the rectangular frame; the transverse guy wires are arranged in parallel with the transverse main beam, and two ends of the transverse guy wires are fixedly connected with the longitudinal main beam after respectively bypassing the symmetrically arranged guy wire brackets; the longitudinal guy wires are arranged in parallel with the longitudinal main beam, and two ends of the longitudinal guy wires are respectively wound around the symmetrically arranged guy wire brackets and then are fixedly connected with the transverse main beam;
the limiting beam is used for limiting the amplitude of the transverse guy wires and the longitudinal guy wires;
the string stretching bracket is made of polyimide material;
the transverse main beam, the longitudinal main beam and the limiting beam are all made of high-modulus carbon fiber materials;
the compaction point reinforcing piece is made of a titanium alloy material.
Furthermore, the transverse main beam and the longitudinal main beam are both of thin-wall hollow carbon fiber structures.
Furthermore, the guy bracket, the transverse guy, the longitudinal guy, the transverse main beam and the longitudinal main beam are connected by gluing.
Still further, the base frame further includes a plurality of stiffening beams disposed parallel to the transverse main beams;
the reinforcing beams are distributed among the transverse main beams and are fixedly connected with the longitudinal main beams.
Furthermore, the reinforcing beam is made of high-modulus carbon fiber materials.
Furthermore, the transverse main beam and the longitudinal main beam, the longitudinal main beam and the reinforcing beam, and the transverse main beam and the limiting beam are connected through gluing.
Furthermore, the compression point reinforcing piece is provided with a central circular tube and four connecting bosses uniformly distributed on the circumference of the central circular tube;
the axial direction of the central circular tube is superposed with the thickness direction of the rectangular frame;
the connecting lug boss is fixedly connected with the transverse main beam and the longitudinal main beam.
Furthermore, the connecting bosses are inserted into the transverse main beam and the longitudinal main beam and connected through gluing.
Further, a pretension tension is applied to both the transverse and longitudinal guy wires.
Has the advantages that:
the light-weight string-tightening type solar wing semi-rigid substrate is composed of a substrate frame and string-tightening components, a string-tightening support is made of polyimide materials, a transverse main beam, a longitudinal main beam and a limiting beam are made of high-modulus carbon fiber materials, a compression point reinforcing piece is made of titanium alloy materials, accordingly, the requirements of light weight, high rigidity and high strength of the substrate are met, the light weight of a panel is achieved to the maximum extent structurally, all the parts except the compression point reinforcing piece are made of non-metal materials, and the area of the panel is 10m2The weight area ratio of the semi-rigid substrate reaches 0.8kg/m2Is much smaller than the prior rigid substrate 1.6kg/m2The index of (2) can effectively reduce the weight of the structural part of the solar wing on the ultra-large solar wing.
In addition, because the battery circuit is arranged on the flexible guy wire, under the condition of the active section load, the mechanical load on the battery piece can be effectively reduced, the temperature of the battery circuit can be effectively reduced when the battery circuit is in orbit, and the power generation efficiency of the battery circuit can be improved.
The light-weight taut string type semi-rigid solar wing substrate is suitable for spacecrafts with light-weight requirements on solar wings.
Drawings
FIG. 1 is a schematic structural view of a semi-rigid substrate of a lightweight taut-string solar wing according to the invention;
FIG. 2 is a partially enlarged schematic view of portion A of FIG. 1;
FIG. 3 is a schematic structural diagram of a substrate frame of the semi-rigid substrate of the lightweight strung solar wing of FIG. 1;
FIG. 4 is a cross-sectional view of section B-B of FIG. 3;
FIG. 5 is a schematic view of a connection structure of a transverse guy wire and a longitudinal main beam;
fig. 6 is a perspective view of the pinch point reinforcement of fig. 4.
Wherein, 1-transverse tension string, 2-longitudinal tension string, 3-tension string bracket, 4-transverse main beam, 5-longitudinal main beam, 6-reinforcing beam, 7-limiting beam, 8-compression point reinforcing piece, 9-adhesive, 81-central circular tube, 82-connecting lug boss
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The invention provides a lightweight strung-string type solar wing semi-rigid substrate, which can be used as a large-scale spacecraft solar wing substrate and provides a bearing structure for a battery circuit part as shown in structures of figures 1, 2 and 3; the semi-rigid substrate includes a substrate frame and a guy wire assembly;
the baseplate frame comprises a plurality of transverse main beams 4, a plurality of longitudinal main beams 5, a limiting beam 7 and a compaction point reinforcing piece 8; the transverse main beams 4 and the longitudinal main beams 5 are arranged in a criss-cross mode to form a rectangular frame, and the frame of the rectangular frame is formed by alternately connecting the two transverse main beams 4 and the two longitudinal main beams 5 which are arranged oppositely; as shown in the structure of fig. 3, a plurality of transverse main beams 4 extend along the horizontal direction (transverse direction) and are arranged at intervals, and the intervals between the transverse main beams 4 may be equal or different; similarly, the plurality of longitudinal main beams 5 extend in the vertical direction (longitudinal direction) and are arranged at intervals, and the distances between the longitudinal main beams 5 can be equal or different; the transverse main beam 4 and the longitudinal main beam 5 are in the same plane; the transverse main beam 4 and the longitudinal main beam 5 are fixedly connected at the intersection point through a compression point reinforcing piece 8, and the structure of the compression point reinforcing piece 8 can refer to fig. 6; the limiting beam 7 is arranged in parallel with the longitudinal main beam 5 and is fixedly connected to one side of the rectangular frame; a plurality of limiting beams 7 are also arranged and distributed at intervals;
as shown in the configuration of fig. 2, the stretching assembly comprises a plurality of transverse stretching wires 1, a plurality of longitudinal stretching wires 2 and a plurality of stretching wire brackets 3; the plurality of guy wire supports 3 are distributed along the outer peripheral side of the rectangular frame and are fixedly connected with the rectangular frame, namely, the plurality of guy wire supports 3 are arranged on the outer peripheral sides of two transverse main beams 4 and two longitudinal main beams 5 which form the frame of the rectangular frame, the guy wire supports 3 arranged on the two transverse main beams 4 are symmetrically arranged, and the guy wire supports 3 arranged on the two longitudinal main beams 5 are symmetrically arranged; the transverse guy wires 1 are arranged in parallel with the transverse main beam 4, the transverse guy wires 1 extend along the horizontal direction (transverse direction) and are arranged at intervals, and two ends of the transverse guy wires 1 are fixedly connected with the longitudinal main beam 5 after respectively bypassing the symmetrically arranged guy wire brackets 3; the longitudinal guy wires 2 are arranged in parallel with the longitudinal main beam 5, the longitudinal guy wires 2 extend in the vertical direction (longitudinal direction) and are arranged at intervals, and two ends of the longitudinal guy wires 2 are fixedly connected with the transverse main beam 4 after respectively bypassing the symmetrically arranged guy wire brackets 3; as shown in the structure of fig. 5, which is a schematic view of an assembly structure of one end of a transverse guy wire 1 and a longitudinal main beam 5, the end part of the transverse guy wire 1 is wound on the top of a guy wire bracket 3 in a semi-surrounding manner and then is bonded on the outer side surface of the longitudinal main beam 5 through an adhesive 9, and the connection structure of the longitudinal guy wire 2 and the transverse main beam 4 is the same; the transverse guy wires 1 and the longitudinal guy wires 2 are flexible ropes;
the limiting beam 7 limits the transverse guy wires 1 and the longitudinal guy wires 2 on one side of a rectangular frame formed by the transverse main beam 4 and the longitudinal main beam 5, and limits the moving range of the transverse guy wires 1 and the longitudinal guy wires 2 through the distance between the limiting beam 7 and the rectangular frame, so that the limiting beam 7 is used for limiting the amplitude of the transverse guy wires 1 and the longitudinal guy wires 2;
the string stretching bracket 3 is made of polyimide material;
the transverse main beam 4, the longitudinal main beam 5 and the limiting beam 7 are all made of high-modulus carbon fiber materials;
the pinch point reinforcement 8 is made of a titanium alloy material.
The lightweight string-tightening type solar wing semi-rigid substrate adopts a structural form of a carbon fiber frame and a flexible rope, the substrate frame formed by longitudinally and transversely crossed connection of the transverse main beams 4 and the longitudinal main beams 5 is used as a main bearing structure, the string-tightening component is arranged on the substrate frame, the string-tightening support 3 is made of polyimide materials, the transverse main beams 4, the longitudinal main beams 5 and the limiting beams 7 are made of high-modulus carbon fiber materials, and the pressing point reinforcement 8 is made of titanium alloy materials, so that the lightweight string-tightening type solar wing semi-rigid substrate is solidThe requirements of light weight, high rigidity and high strength of the base plate are met, the solar panel is structurally lightened to the maximum degree, all the other parts except the compression point reinforcing piece 8 are made of non-metal materials, and the area of the solar panel is 10m2The weight area ratio of the semi-rigid substrate reaches 0.8kg/m2Is much smaller than the prior rigid substrate 1.6kg/m2The index of (2) can effectively reduce the weight of the structural part of the solar wing on the ultra-large solar wing.
In addition, because the battery circuit is arranged on the flexible guy wire, under the condition of the active section load, the mechanical load on the battery piece can be effectively reduced, the temperature of the battery circuit can be effectively reduced when the battery circuit is in orbit, and the power generation efficiency of the battery circuit can be improved.
Because the transverse main beams 4 and the longitudinal main beams 5 are both thin-wall hollow carbon fiber structures, the weight of the substrate frame is further reduced, and the weight-area ratio of the semi-rigid substrate is improved.
In the assembling process, the tightening support 3, the transverse tightening strings 1, the longitudinal tightening strings 2, the transverse main beam 4 and the longitudinal main beam 5 are all connected by glue, namely, the tightening support 3 is fixedly arranged on the transverse main beam 4 and the longitudinal main beam 5 by a glue connection method, and meanwhile, the transverse tightening strings 1, the longitudinal tightening strings 2 and the corresponding tightening support 3 are fixedly connected by a glue connection mode, so that the two ends of the transverse tightening strings 1 and the longitudinal tightening strings 2 are fixedly connected by two fixed points, and the fixed connection of the transverse tightening strings 1 and the longitudinal tightening strings 2 is firmer and more reliable.
In order to further improve the structural strength and rigidity of the substrate frame, as shown in the structure of fig. 3, the substrate frame further includes a plurality of reinforcing beams 6 arranged in parallel with the transverse main beams 4, only two reinforcing beams 6 are shown in the figure, in the actual design and manufacturing process, a plurality of reinforcing beams 6 can be additionally arranged according to actual needs, and the reinforcing beams 6 can be made of high-modulus carbon fiber materials; the stiffening beams 6 are arranged parallel to the transverse main beams 4, i.e. extending in the horizontal direction (transverse), and the stiffening beams 6 are distributed between the transverse main beams 4 and fixedly connected with the longitudinal main beams 5.
In order to simplify the assembly structure, the transverse main beam 4 is connected with the longitudinal main beam 5, the longitudinal main beam 5 is connected with the reinforcing beam 6, and the transverse main beam 4 is connected with the limiting beam 7 through gluing.
The compaction point reinforcing part 8 is used for bearing compaction force when the solar wing is folded and compacted, and transferring load borne by each transverse main beam 4 and each longitudinal main beam 5 to the star body. As shown in the structure of fig. 4 and 6, the pressing point reinforcing member 8 is provided with a central circular tube 81 and four connecting bosses 82 uniformly distributed in the circumferential direction of the central circular tube 81; the axial direction of the central circular tube 81 coincides with the thickness direction of the rectangular frame, that is, the axial direction of the central circular tube 81 is perpendicular to a plane formed by the extending direction of the transverse main beam 4 and the extending direction of the longitudinal main beam 5; the central circular tube 81 is used to transfer the main load; the connecting bosses 82 are fixedly connected with the transverse main beam 4 and the longitudinal main beam 5, as shown in the structure of fig. 4, the connecting bosses 82 are inserted into the transverse main beam 4 and the longitudinal main beam 5 and are connected with each other by gluing. The pinch point reinforcement 8 shown in fig. 6 is suitable for the cross position of the transverse main beam 4 and the longitudinal main beam 5 inside the base plate frame, and when the transverse main beam 4 and the longitudinal main beam 5 of the frame portion are connected, the pinch point reinforcement 8 provided with two connection bosses 82 or three connection bosses 82 may be used for assembly, for example: when two connecting bosses 82 are arranged, the two connecting bosses 82 can be oppositely arranged in a straight-line shape or in a right-angle shape; when the pinch point reinforcement 8 is provided with three connecting bosses 82, the three connecting bosses 82 are distributed in a T shape, which is not described in detail in this embodiment.
On the basis of the various embodiments, the transverse guy wires 1 and the longitudinal main beams 5 and the longitudinal guy wires 2 and the transverse main beams 4 are connected through the guy wire brackets 3, when the transverse guy wires 1 and the longitudinal guy wires 2 bypass the guy wire brackets 3, the transverse guy wires 1 and the longitudinal guy wires 2 are applied with pre-tightening tension, and meanwhile, the top of the guy wire brackets 3 is higher than the substrate frame, so that the surface formed by the transverse guy wires 1 and the longitudinal guy wires 2 is higher than the surface of the substrate frame, more battery pieces can be pasted, and higher battery piece arranging efficiency is obtained.
In summary, the above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A lightweight strung-string type semi-rigid solar wing substrate is characterized by comprising a substrate frame and a strung-string component;
the base plate frame comprises a plurality of transverse main beams (4), a plurality of longitudinal main beams (5), limiting beams (7) and a compression point reinforcing piece (8); the transverse main beams (4) and the longitudinal main beams (5) are arranged in a criss-cross mode to form a rectangular frame, and the transverse main beams (4) and the longitudinal main beams (5) are fixedly connected at the cross points through the compression point reinforcements (8); the limiting beam (7) is arranged in parallel with the longitudinal main beam (5) and is fixedly connected to one side of the rectangular frame;
the string stretching assembly comprises a plurality of transverse strings (1), a plurality of longitudinal strings (2) and a plurality of string stretching brackets (3); the plurality of guy wire brackets (3) are distributed along the outer peripheral side of the rectangular frame and are fixedly connected with the rectangular frame; the transverse guy wires (1) are arranged in parallel with the transverse main beam (4), and the two ends of the transverse guy wires are respectively wound around the symmetrically arranged guy wire support (3) and then are fixedly connected with the longitudinal main beam (5); the longitudinal guy wires (2) are arranged in parallel with the longitudinal main beam (5), and two ends of the longitudinal guy wires respectively bypass the symmetrically arranged guy wire brackets (3) and then are fixedly connected with the transverse main beam;
the limiting beam (7) is used for limiting the amplitude of the transverse guy wires (1) and the longitudinal guy wires (2);
the string stretching bracket (3) is made of polyimide material;
the transverse main beam (4), the longitudinal main beam (5) and the limiting beam (7) are all made of high-modulus carbon fiber materials;
the compaction point reinforcing piece (8) is made of a titanium alloy material.
2. The semi-rigid substrate of a lightweight tied-chord solar wing according to claim 1, characterized in that the transverse main beams (4) and the longitudinal main beams (5) are both thin-walled hollow carbon fiber structures.
3. The semi-rigid substrate of a lightweight tied-string solar wing according to claim 1, wherein the tied-string support (3) is adhesively connected to the transverse tied strings (1), the longitudinal tied strings (2), the transverse main beams (4) and the longitudinal main beams (5).
4. The lightweight chorded solar wing semi-rigid baseplate of claim 1, wherein the baseplate frame further includes a plurality of stiffening beams (6) disposed parallel to the transverse main beams;
the reinforcing beams (6) are distributed among the transverse main beams and are fixedly connected with the longitudinal main beams.
5. The semirigid lightweight chordal solar panel substrate according to claim 4, wherein the stiffening beam (6) is made of a high modulus carbon fiber material.
6. The semi-rigid substrate of a lightweight tied-chord solar wing according to claim 5, characterized in that the connections between the transverse main beams (4) and the longitudinal main beams (5), between the longitudinal main beams (5) and the stiffening beams (6), and between the transverse main beams and the limiting beams (7) are glued.
7. The lightweight tied-chord solar wing semi-rigid substrate according to any of claims 1 to 6, wherein the pinch point stiffener (8) is provided with a central circular tube (81) and four connecting bosses (82) evenly distributed in the circumferential direction of the central circular tube (81);
the axial direction of the central circular tube (81) is superposed with the thickness direction of the rectangular frame;
the connecting boss (82) is fixedly connected with the transverse main beam (4) and the longitudinal main beam (5).
8. The semirigid substrate of a lightweight tied solar wing according to claim 7, characterized in that said connection bosses (81) are inserted in said transverse main beams (4) and said longitudinal main beams (5) and are connected by gluing.
9. The semirigid lightweight tied-string solar wing substrate according to any of claims 1 to 6, wherein both the transverse (1) and longitudinal (2) ties are applied with a pretension.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110767090.7A CN113548200B (en) | 2021-07-07 | 2021-07-07 | Lightweight string-stretching solar wing semi-rigid substrate |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110767090.7A CN113548200B (en) | 2021-07-07 | 2021-07-07 | Lightweight string-stretching solar wing semi-rigid substrate |
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| CN113548200A true CN113548200A (en) | 2021-10-26 |
| CN113548200B CN113548200B (en) | 2023-09-15 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105474801B (en) * | 2006-08-18 | 2011-06-08 | 上海宇航系统工程研究所 | Spacecraft solar battery array semirigid substrates |
| CN105515503A (en) * | 2015-11-26 | 2016-04-20 | 中国电子科技集团公司第十八研究所 | Solar cell module fixation structure of string-tightening type semi-rigid board and fixation method thereof |
| US20190326851A1 (en) * | 2018-04-20 | 2019-10-24 | Jia-Shou WANG | Solar panel frame assembly |
| CN112343907A (en) * | 2020-10-30 | 2021-02-09 | 北京卫星制造厂有限公司 | Adhesive joint assembly process method of taut-string semi-rigid substrate frame |
-
2021
- 2021-07-07 CN CN202110767090.7A patent/CN113548200B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105474801B (en) * | 2006-08-18 | 2011-06-08 | 上海宇航系统工程研究所 | Spacecraft solar battery array semirigid substrates |
| CN105515503A (en) * | 2015-11-26 | 2016-04-20 | 中国电子科技集团公司第十八研究所 | Solar cell module fixation structure of string-tightening type semi-rigid board and fixation method thereof |
| US20190326851A1 (en) * | 2018-04-20 | 2019-10-24 | Jia-Shou WANG | Solar panel frame assembly |
| CN112343907A (en) * | 2020-10-30 | 2021-02-09 | 北京卫星制造厂有限公司 | Adhesive joint assembly process method of taut-string semi-rigid substrate frame |
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| CN113548200B (en) | 2023-09-15 |
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