CN113548200B - Lightweight string-stretching solar wing semi-rigid substrate - Google Patents
Lightweight string-stretching solar wing semi-rigid substrate Download PDFInfo
- Publication number
- CN113548200B CN113548200B CN202110767090.7A CN202110767090A CN113548200B CN 113548200 B CN113548200 B CN 113548200B CN 202110767090 A CN202110767090 A CN 202110767090A CN 113548200 B CN113548200 B CN 113548200B
- Authority
- CN
- China
- Prior art keywords
- transverse
- longitudinal
- string
- stretching
- string stretching
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 239000000758 substrate Substances 0.000 title claims abstract description 51
- 238000007906 compression Methods 0.000 claims abstract description 22
- 230000006835 compression Effects 0.000 claims abstract description 21
- 230000003014 reinforcing effect Effects 0.000 claims abstract description 21
- 239000000463 material Substances 0.000 claims abstract description 16
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 14
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 11
- 239000004917 carbon fiber Substances 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
- 229920001721 polyimide Polymers 0.000 claims abstract description 6
- 230000002787 reinforcement Effects 0.000 claims description 12
- 239000000853 adhesive Substances 0.000 claims description 7
- 238000004026 adhesive bonding Methods 0.000 claims description 6
- 230000001070 adhesive effect Effects 0.000 claims description 6
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 238000003825 pressing Methods 0.000 claims description 2
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 238000010248 power generation Methods 0.000 description 2
- 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
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000003351 stiffener Substances 0.000 description 1
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
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Photovoltaic Devices (AREA)
Abstract
The invention discloses a lightweight string-stretching solar wing semi-rigid substrate, wherein a substrate frame of the semi-rigid substrate comprises a plurality of transverse girders, a plurality of longitudinal girders, a limiting girder and a compression point reinforcing piece; the string stretching assembly comprises a plurality of transverse strings stretching, a plurality of longitudinal strings stretching and a plurality of string stretching brackets; the plurality of string stretching brackets are fixedly connected with the rectangular frame; the transverse string stretching frame is arranged in parallel with the transverse main beam, and two ends of the transverse string stretching frame are fixedly connected with the longitudinal main beam after respectively bypassing the symmetrically arranged string stretching frames; the longitudinal string stretching brackets are arranged in parallel with the longitudinal main beams, and the two ends of the longitudinal string stretching brackets are fixedly connected with the transverse main beams after respectively bypassing the symmetrically arranged string stretching brackets; the limiting beam is used for limiting the amplitude of the transverse string stretching and the longitudinal string stretching; the string stretching bracket is made of polyimide material; the transverse girder, the longitudinal girder and the limiting girder are all made of high-modulus carbon fiber materials; the compression point reinforcing piece is made of titanium alloy materials. The semi-rigid substrate can effectively reduce the weight-to-area ratio of the solar wing substrate.
Description
Technical Field
The invention relates to the technical field of solar wings, in particular to a lightweight string-stretching solar wing semi-rigid substrate.
Background
With the development of technology, the power demand of the spacecraft is also larger and larger, and the power demand of the large-scale communication satellite is up to tens 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.
The traditional rigid solar wing substrate adopts a carbon fiber panel and aluminum honeycomb structure, and the weight area ratio of the traditional rigid solar wing substrate is about (1.6-2) kg/m 2 As the area increases, the weight of the solar wing base plate increases in the same proportion, and when the area of the solar wing reaches 60m 2 When the weight of the substrate part is up to 100kg, the solar-wing battery circuit part is used as the part for directly providing power, and the weight is only 60kg, which is far smaller than the structureIn part, there is therefore a need to provide solar wing substrates with lower weight to area ratios. .
Disclosure of Invention
In view of the above, the invention provides a lightweight string-stretched solar wing semi-rigid substrate, which can effectively reduce the weight-area ratio of the solar wing substrate, further reduce the weight of the 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 string-stretching solar wing semi-rigid substrate, comprising a substrate frame and a string-stretching assembly;
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 girders and the longitudinal girders are arranged in a crisscross manner to form a rectangular frame, and the transverse girders and the longitudinal girders are fixedly connected at the crossing 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 stretching assembly comprises a plurality of transverse strings stretching, a plurality of longitudinal strings stretching and a plurality of string stretching brackets; the string stretching brackets are distributed along the peripheral side of the rectangular frame and fixedly connected with the rectangular frame; the transverse string stretching brackets are arranged in parallel with the transverse main beams, and two ends of the transverse string stretching brackets are fixedly connected with the longitudinal main beams after respectively bypassing the symmetrically arranged string stretching brackets; the longitudinal string stretching brackets are arranged in parallel with the longitudinal main beams, and two ends of the longitudinal string stretching brackets are fixedly connected with the transverse main beams after respectively bypassing the symmetrically arranged string stretching brackets;
the limiting beam is used for limiting the amplitude of the transverse string stretching and the longitudinal string stretching;
the string stretching bracket is made of polyimide material;
the transverse girder, the longitudinal girder and the limiting girder are all made of high-modulus carbon fiber materials;
the compression point reinforcing piece is made of titanium alloy materials.
Further, the transverse girder and the longitudinal girder are both thin-wall hollow carbon fiber structures.
Furthermore, the string stretching bracket is connected with the transverse string stretching bracket, the longitudinal string stretching bracket, the transverse girder and the longitudinal girder by adopting adhesive.
Still further, the base plate frame further includes a plurality of reinforcement beams disposed in parallel with the transverse main beams;
the reinforcing beams are distributed among the transverse main beams and fixedly connected with the longitudinal main beams.
Still further, the reinforcement beam is made of a high modulus carbon fiber material.
Furthermore, the transverse girder and the longitudinal girder, the longitudinal girder and the stiffening girder, and the transverse girder and the limiting girder are all connected through gluing.
Further, 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 coincides with the thickness direction of the rectangular frame;
the connecting boss is fixedly connected with the transverse girder and the longitudinal girder.
Furthermore, the connecting boss is inserted into the transverse girder and the longitudinal girder and connected by gluing.
Still further, the transverse and longitudinal stretched strings are each applied with a pre-tension.
The beneficial effects are that:
the lightweight string-stretching solar wing semi-rigid substrate is composed of a substrate frame and a string-stretching assembly, wherein a string-stretching bracket is made of polyimide materials, a transverse girder, a longitudinal girder and a limiting girder are made of high-modulus carbon fiber materials, and a compression point reinforcing part is made of titanium alloy materials, so that the requirements of the substrate for lightweight, high rigidity and high strength are met, the panel is structurally light to the greatest extent, and all other parts except the compression point reinforcing part are non-identicalA metal material such that the area is 10m 2 The weight area ratio of the semi-rigid substrate of (2) reaches 0.8kg/m 2 Far smaller than the existing rigid substrate 1.6kg/m 2 The weight of the solar wing structure part can be effectively reduced on the ultra-large solar wing.
In addition, as the battery circuit is arranged on the flexible string, under the condition of active section load, the mechanical load born by the battery piece can be effectively reduced, and the temperature of the battery circuit can be effectively reduced during on-orbit operation, thereby being beneficial to improving the power generation efficiency of the battery circuit.
The lightweight string-stretched solar wing semi-rigid substrate is suitable for spacecrafts with lightweight requirements on solar wings.
Drawings
FIG. 1 is a schematic view of a lightweight string-stretched solar wing semi-rigid substrate according to the present invention;
FIG. 2 is a schematic view of a part of the enlarged structure of the portion A in FIG. 1;
FIG. 3 is a schematic view of the structure of a substrate frame of the lightweight string-stretched solar wing semi-rigid substrate of FIG. 1;
FIG. 4 is a cross-sectional view of section B-B of FIG. 3;
FIG. 5 is a schematic view of the connection structure of the transverse strings to the longitudinal girders;
fig. 6 is a schematic perspective view of the pinch point stiffener of fig. 4.
Wherein, 1-transverse string stretching, 2-longitudinal string stretching, 3-string stretching support, 4-transverse girder, 5-longitudinal girder, 6-reinforcing girder, 7-limiting girder, 8-compression point reinforcing piece, 9-adhesive, 81-central round tube and 82-connecting boss
Detailed Description
The invention will now be described in detail by way of example with reference to the accompanying drawings.
The invention provides a lightweight string-stretching solar wing semi-rigid substrate, which can be used for a solar wing substrate of a large spacecraft to provide a bearing structure for a battery circuit part, as shown in the structures of fig. 1, 2 and 3; the semi-rigid substrate includes a substrate frame and a string stretching assembly;
the base plate frame comprises a plurality of transverse main beams 4, a plurality of longitudinal main beams 5, a limit beam 7 and a compression point reinforcing piece 8; the transverse girders 4 and the longitudinal girders 5 are arranged in a crisscross manner to form a rectangular frame, and the frames of the rectangular frame are formed by alternately connecting two opposite transverse girders 4 and two longitudinal girders 5; as shown in the structure of fig. 3, the plurality of transverse girders 4 extend along the horizontal direction (transverse direction) and are arranged at intervals, and the intervals between the transverse girders 4 can be equal or unequal; similarly, the longitudinal girders 5 extend along the vertical direction (longitudinal direction) and are arranged at intervals, and the intervals between the longitudinal girders 5 can be equal or unequal; the transverse girder 4 and the longitudinal girder 5 are both positioned in the same plane; the transverse girder 4 and the longitudinal girder 5 are fixedly connected at the crossing point by a compression point reinforcement 8, and the structure of the compression point reinforcement 8 can be referred to as 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; the limiting beams 7 are also arranged in a plurality and are distributed at intervals;
as shown in the structure of fig. 2, the string stretching assembly comprises a plurality of transverse strings stretching 1, a plurality of longitudinal strings stretching 2 and a plurality of string stretching brackets 3; the plurality of string stretching brackets 3 are distributed along the peripheral side of the rectangular frame and are fixedly connected with the rectangular frame, namely, the plurality of string stretching brackets 3 are arranged on the peripheral sides of the two transverse girders 4 and the two longitudinal girders 5 which form the frame of the rectangular frame, the string stretching brackets 3 arranged on the two transverse girders 4 are symmetrically arranged, and the string stretching brackets 3 arranged on the two longitudinal girders 5 are symmetrically arranged; the transverse string stretching device comprises a transverse string stretching device 1 and a transverse main beam 4, wherein the transverse string stretching device 1 is arranged in parallel with the transverse main beam 4, the transverse string stretching device 1 extends along the horizontal direction (transversely) and is arranged at intervals, and two ends of the transverse string stretching device 1 are fixedly connected with the longitudinal main beam 5 after respectively bypassing a string stretching bracket 3 which is symmetrically arranged; the longitudinal strings 2 are arranged in parallel with the longitudinal main beams 5, the longitudinal strings 2 extend along the vertical direction (longitudinally) and are arranged at intervals, and two ends of the longitudinal strings 2 are fixedly connected with the transverse main beams 4 after respectively bypassing the symmetrically arranged strings stretching brackets 3; as shown in fig. 5, the structure shows a schematic diagram of an assembly structure of one end of the transverse string stretching 1 and the longitudinal girder 5, the end of the transverse string stretching 1 is wrapped around the top of the string stretching bracket 3 in a semi-surrounding manner and then is adhered to the outer side surface of the longitudinal girder 5 through an adhesive 9, and the connection structure of the longitudinal string stretching 2 and the transverse girder 4 is the same; the transverse string stretching 1 and the longitudinal string stretching 2 are flexible ropes;
the limiting beam 7 limits the transverse string stretching 1 and the longitudinal string stretching 2 on one side of a rectangular frame formed by the transverse main beam 4 and the longitudinal main beam 5, and limits the movable range of the transverse string stretching 1 and the longitudinal string stretching 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 string stretching 1 and the longitudinal string stretching 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 compression point reinforcement 8 is made of titanium alloy material.
The lightweight string-stretching solar wing semi-rigid substrate adopts the structural form of a carbon fiber frame and a flexible rope, adopts a substrate frame formed by connecting a transverse girder 4 and a longitudinal girder 5 in a crisscross manner as a main bearing structure, and is provided with a string-stretching component, because the string-stretching bracket 3 is made of polyimide materials, the transverse girder 4, the longitudinal girder 5 and a limiting girder 7 are all made of high-modulus carbon fiber materials, and a compression point reinforcing part 8 is made of titanium alloy materials, thereby realizing the requirements of lightweight, high rigidity and high strength of the substrate, realizing the maximum lightweight of the battery plate structurally, and all the rest parts except the compression point reinforcing part 8 are made of nonmetallic materials, so that the area is 10m 2 The weight area ratio of the semi-rigid substrate of (2) reaches 0.8kg/m 2 Far smaller than the existing rigid substrate 1.6kg/m 2 The weight of the solar wing structure part can be effectively reduced on the ultra-large solar wing.
In addition, as the battery circuit is arranged on the flexible string, under the condition of active section load, the mechanical load born by the battery piece can be effectively reduced, and the temperature of the battery circuit can be effectively reduced during on-orbit operation, thereby being beneficial to improving the power generation efficiency of the battery circuit.
Because the transverse main beams 4 and the longitudinal main beams 5 are of 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 assembly process, the string stretching brackets 3 are in adhesive connection with the transverse string stretching 1, the longitudinal string stretching 2, the transverse main beams 4 and the longitudinal main beams 5, namely, the string stretching brackets 3 are fixedly arranged on the transverse main beams 4 and the longitudinal main beams 5 through an adhesive connection method, and meanwhile, the transverse string stretching 1 and the longitudinal string stretching 2 are fixedly connected with the corresponding string stretching brackets 3 through an adhesive connection method, so that two ends of the transverse string stretching 1 and the longitudinal string stretching 2 are fixedly connected through two fixed points, and the fixed connection of the transverse string stretching 1 and the longitudinal string stretching 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 comprises 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, and 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 reinforcement beams 6 are arranged parallel to the transverse girders 4, i.e. extend in a horizontal direction (transverse direction), the reinforcement beams 6 being distributed between the transverse girders 4 and being fixedly connected to the longitudinal girders 5.
In order to simplify the assembly structure, the transverse girder 4 and the longitudinal girder 5, the longitudinal girder 5 and the stiffening girder 6 and the transverse girder 4 and the limiting girder 7 are all connected by gluing.
The compression point reinforcing piece 8 is used for bearing the compression force when the solar wing is folded and compressed, and transmitting the load born by each transverse girder 4 and each longitudinal girder 5 to the star. As shown in the structures of fig. 4 and 6, the compression point reinforcement 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, i.e., the axial direction of the central circular tube 81 is arranged 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 round tube 81 is used for transmitting main load; the connection boss 82 is fixedly connected with the transverse girder 4 and the longitudinal girder 5, and as shown in the structure of fig. 4, the connection boss 82 is inserted into the transverse girder 4 and the longitudinal girder 5 and is connected by gluing. The compression point reinforcement 8 shown in fig. 6 is applicable to the position where the transverse girders 4 and the longitudinal girders 5 cross inside the base plate frame, and when the transverse girders 4 and the longitudinal girders 5 of the frame part are connected, the compression point reinforcement 8 provided with two connection bosses 82 or three connection bosses 82 may be used for assembly, such as: when two connecting bosses 82 are arranged, the two connecting bosses 82 can be oppositely arranged in a straight shape or in a right angle; when the pressing point reinforcing member 8 is provided with three connection bosses 82, the three connection bosses 82 are distributed in a T shape, and will not be described in detail in this embodiment.
On the basis of the above embodiments, the transverse strings 1 and the longitudinal girders 5 and the longitudinal strings 2 and the transverse girders 4 are connected through the string stretching brackets 3, when the transverse strings 1 and the longitudinal strings 2 bypass the string stretching brackets 3, the transverse strings 1 and the longitudinal strings 2 are applied with pre-tightening tension, and meanwhile, the top of the string stretching brackets 3 is higher than the substrate frame, so that the surface formed by the transverse strings 1 and the longitudinal strings 2 is higher than the surface of the substrate frame, more battery pieces can be adhered, and higher battery piece distribution efficiency is obtained.
In summary, the above embodiments are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (7)
1. A lightweight string-stretching solar wing semi-rigid substrate is characterized by comprising a substrate frame and a string-stretching assembly;
the base plate frame comprises a plurality of transverse main beams (4), a plurality of longitudinal main beams (5), limiting beams (7) and pressing point reinforcements (8); the transverse main beams (4) and the longitudinal main beams (5) are arranged in a crisscross manner to form a rectangular frame, and the transverse main beams (4) and the longitudinal main beams (5) are fixedly connected at the crossing points through the compression point reinforcing pieces (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 string stretching brackets (3) are distributed along the peripheral side of the rectangular frame and are fixedly connected with the rectangular frame; the transverse string stretching bracket (3) is arranged symmetrically at two ends of the transverse string stretching bracket (1) in a parallel manner, and the two ends of the transverse string stretching bracket are fixedly connected with the longitudinal main beam (5); the longitudinal string stretching frames (2) are arranged in parallel with the longitudinal main beams (5), and two ends of the longitudinal string stretching frames are fixedly connected with the transverse main beams after bypassing the symmetrically arranged string stretching frames (3);
the limiting beam (7) is used for limiting the amplitude of the transverse string stretching (1) and the longitudinal string stretching (2);
the string stretching bracket (3) is made of polyimide material;
the transverse main beams (4), the longitudinal main beams (5) and the limiting beams (7) are all made of high-modulus carbon fiber materials;
the compression point reinforcing piece (8) is made of titanium alloy materials;
the transverse main beams (4) and the longitudinal main beams (5) are of thin-wall hollow carbon fiber structures;
the string stretching bracket (3) is connected with the transverse string stretching bracket (1), the longitudinal string stretching bracket (2), the transverse main beam (4) and the longitudinal main beam (5) by adopting adhesive;
the top of the string stretching bracket (3) is higher than the substrate frame, and the surface formed by the transverse string stretching (1) and the longitudinal string stretching (2) is higher than the surface of the substrate frame.
2. The lightweight, string-stretched solar wing semi-rigid substrate according to claim 1, characterized in that the substrate frame further comprises a plurality of stiffening beams (6) arranged in parallel with the transverse main beams;
the stiffening beams (6) are distributed among the transverse main beams and fixedly connected with the longitudinal main beams.
3. The lightweight string-stretched solar wing semi-rigid substrate according to claim 2, characterized in that the stiffening beams (6) are made of high modulus carbon fiber material.
4. A lightweight string-stretched solar wing semi-rigid substrate as claimed in claim 3, characterized in that the transverse girders (4) and the longitudinal girders (5), the longitudinal girders (5) and the stiffening girders (6) and the transverse girders and the limiting girders (7) are all connected by gluing.
5. The lightweight, string-stretched solar wing semi-rigid substrate according to any one of claims 1-4, characterized in that the pinch point reinforcement (8) is provided with a central circular tube (81) and four connecting bosses (82) uniformly distributed in the circumference of the central circular tube (81);
the axial direction of the central circular tube (81) coincides with the thickness direction of the rectangular frame;
the connecting boss (82) is fixedly connected with the transverse girder (4) and the longitudinal girder (5).
6. The lightweight, string-stretched solar wing semi-rigid substrate according to claim 5, characterized in that the connection boss (82) is inserted into the transverse girder (4) and the longitudinal girder (5) and connected by gluing.
7. A lightweight, strung solar wing semi-rigid substrate according to any of claims 1-4, characterized in that both the transverse strung (1) and the longitudinal strung (2) are applied with pre-tension.
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 |
Applications Claiming Priority (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 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113548200A CN113548200A (en) | 2021-10-26 |
| CN113548200B true CN113548200B (en) | 2023-09-15 |
Family
ID=78102946
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110767090.7A Active CN113548200B (en) | 2021-07-07 | 2021-07-07 | Lightweight string-stretching solar wing semi-rigid substrate |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113548200B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105474801B (en) * | 2006-08-18 | 2011-06-08 | 上海宇航***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 |
| 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 |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| TWI679388B (en) * | 2018-04-20 | 2019-12-11 | 王家壽 | Solar panel frame group |
-
2021
- 2021-07-07 CN CN202110767090.7A patent/CN113548200B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105474801B (en) * | 2006-08-18 | 2011-06-08 | 上海宇航***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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113548200A (en) | 2021-10-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US8485786B2 (en) | Reinforced blade for wind turbine | |
| CN102884309B (en) | The airfoil body strengthened | |
| CN201309598Y (en) | Coiling type Y-shaped cross frame space extending arm without articulation | |
| CN106892083B (en) | Bionic rack of crossed double-rotor helicopter | |
| CN106564621A (en) | X-shaped section extendable member capable of realizing folding and unfolding functions | |
| CN115506947B (en) | Multi-beam tension type wind power blade and manufacturing method thereof | |
| WO2017076096A1 (en) | Reinforced blade for wind-driven generator | |
| CN103963998A (en) | Main force-bearing satellite structure with hexagonal framework | |
| CN105508142A (en) | Multi-girder structure large size wind power blade and production method thereof | |
| WO2023019966A1 (en) | Flexible photovoltaic support and photovoltaic array | |
| CN218103001U (en) | Integrated cable-stayed device suitable for flexible photovoltaic support double cables | |
| CN108357661B (en) | Full-surrounding type nose cone device | |
| CN113548200B (en) | Lightweight string-stretching solar wing semi-rigid substrate | |
| US8141301B2 (en) | Externally braced inflatable structures | |
| CN112343907B (en) | Adhesive joint assembly process method of string stretching type semi-rigid substrate frame | |
| US9828772B2 (en) | Truss designs, materials, and fabrication | |
| CN112389683B (en) | Method for maintaining prestress of film of solar sail spacecraft | |
| CN201309599Y (en) | Coiling type triangular cross frame space extending arm with articulation | |
| CN221024135U (en) | Side pushing support of semi-rigid airship and semi-rigid airship | |
| JP3639228B2 (en) | Tower structure | |
| CN205273833U (en) | Four rotor craft structure reinforcing apparatus | |
| CN205135897U (en) | Strenghthened type blade subassembly, rotor, wind power installation and power generating equipment | |
| JP4912571B2 (en) | Rotating support | |
| CN112298605B (en) | Plate-and-bar type satellite main structure | |
| CN220915190U (en) | Photovoltaic support and photovoltaic module |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |