CN108327928B - Integrated solar wing supporting mechanism - Google Patents
Integrated solar wing supporting mechanism Download PDFInfo
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- CN108327928B CN108327928B CN201810267735.9A CN201810267735A CN108327928B CN 108327928 B CN108327928 B CN 108327928B CN 201810267735 A CN201810267735 A CN 201810267735A CN 108327928 B CN108327928 B CN 108327928B
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- 230000007246 mechanism Effects 0.000 title claims abstract description 56
- 238000007789 sealing Methods 0.000 claims abstract description 54
- 239000003292 glue Substances 0.000 claims description 7
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 4
- 239000004917 carbon fiber Substances 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims description 2
- 239000007924 injection Substances 0.000 claims description 2
- 230000001502 supplementing effect Effects 0.000 claims 1
- 230000003287 optical effect Effects 0.000 abstract description 6
- 238000004026 adhesive bonding Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 4
- 238000004804 winding Methods 0.000 description 2
- 229910000906 Bronze Inorganic materials 0.000 description 1
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052790 beryllium Inorganic materials 0.000 description 1
- ATBAMAFKBVZNFJ-UHFFFAOYSA-N beryllium atom Chemical compound [Be] ATBAMAFKBVZNFJ-UHFFFAOYSA-N 0.000 description 1
- 239000010974 bronze Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- KUNSUQLRTQLHQQ-UHFFFAOYSA-N copper tin Chemical compound [Cu].[Sn] KUNSUQLRTQLHQQ-UHFFFAOYSA-N 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000010935 stainless steel Substances 0.000 description 1
- 229910001220 stainless steel Inorganic materials 0.000 description 1
Classifications
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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
- B64G1/443—Photovoltaic cell 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
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Life Sciences & Earth Sciences (AREA)
- Sustainable Development (AREA)
- Photovoltaic Devices (AREA)
Abstract
An integrated solar wing supporting mechanism relates to the technical field of aerospace and solves the problems that the supporting mechanism is complex in structure and easy to cause non-coaxial jamming. The satellite body support seat, the first short support tube, the first strip spring, the first long support tube, the second strip spring, the second long support tube, the third strip spring, the second short support tube and the solar wing support seat are glued in sequence, the satellite body support seat is fixed on a satellite body, and the solar wing support seat is fixed on a solar wing; the cementing of the first strip spring, the second strip spring and the third strip spring is inner surface cementing; the six sealing rings are glued on the outer surfaces of the two ends of the first strip spring, the second strip spring and the third strip spring in a one-to-one correspondence mode. The supporting mechanism has the advantages of small number of structural parts, simple structure, self-unfolding and self-locking, high reliability, high unfolding rigidity of the solar wing, and high unfolding fundamental frequency of the solar wing of the optical satellite, and one or more of the supporting mechanisms are not easy to generate the phenomenon of non-coaxial jamming when used simultaneously.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to an integrated solar wing supporting mechanism.
Background
The folding solar wing is folded on the satellite star in the launching state, and the satellite and the arrow are unfolded after being separated. For the high-resolution optical satellite, when the fundamental frequency of the unfolded solar wing reaches a specified value, the image resolution and the attitude control precision of the high-resolution optical satellite are seriously affected. To address the low fundamental frequency problem, support mechanisms are often employed to increase deployment stiffness. However, when the supporting mechanism and the unfolding mechanism are unfolded in space, the phenomenon of non-coaxial jamming is very easy to occur, so that tasks fail, and the number of structural parts of the traditional supporting mechanism is large.
Disclosure of Invention
The invention provides an integrated solar wing supporting mechanism, which aims to solve the problems that the supporting mechanism is complex in structure and easy to be blocked without coaxial shafts.
The technical scheme adopted by the invention for solving the technical problems is as follows:
an integrated solar wing support mechanism comprising:
a satellite support fixed on the satellite;
a first short support tube with one end glued with the star support seat;
a first strip spring with one end glued with the outer surface of the other end of the first short supporting tube;
a first long support tube with one end of the outer surface glued with the other end of the first strip spring;
a second strip spring with one end glued with the outer surface of the other end of the first long support tube;
a second long support tube with one end of the outer surface glued with the other end of the second strip spring;
a third strip spring with one end glued with the outer surface of the other end of the second long support tube;
a second short support tube with one end of the outer surface glued with the other end of the third strip spring;
a solar wing supporting seat with one end glued with the other end of the second short supporting tube, wherein the solar wing supporting seat is fixed on a solar wing;
six sealing rings glued on the outer surfaces of the two ends of the first strip spring, the second strip spring and the third strip spring in a one-to-one correspondence mode.
Furthermore, the radians of the cementing parts of the first short support tube and the first long support tube and the first strip spring are not smaller than the radians of the first strip spring; radians of cementing positions of the first long supporting tube, the second long supporting tube and the second strip spring are not smaller than that of the second strip spring; radians of cementing positions of the second long support tube, the second short support tube and the third strip spring are not smaller than the radians of the third strip spring; the radian of the sealing ring is not smaller than the radian of two ends of the corresponding first strip spring, second strip spring and third strip spring.
Further, the first, second and third band springs have the same structure.
Further, the second long support tube and the first long support tube have the same structure, and the first short support tube and the second short support tube have the same structure.
Further, the thickness of the second long support tube, the first short support tube and the second short support tube is 0.4-1.5 mm.
Further, the second long support tube, the first short support tube, the second short support tube and the sealing ring are all made of carbon fiber composite materials.
Further, the lengths of the first strip spring, the second strip spring and the third strip spring are 60-120 mm, the thicknesses of the first strip spring, the second strip spring and the third strip spring are 0.1-0.3 mm, the radian is smaller than pi rad, and the widths of the first strip spring, the second strip spring and the third strip spring are larger than 5mm.
Further, the cross sections of the first short supporting tube, the first strip spring, the first long supporting tube, the second strip spring, the second long supporting tube, the third strip spring and the second short supporting tube are all elliptical.
Further, the cross sections of the first short supporting tube, the first strip spring, the first long supporting tube, the second strip spring, the second long supporting tube, the third strip spring and the second short supporting tube are elliptical closed patterns.
Further, the elliptical closed graph is formed by connecting a first section of arc, a second section of arc, a third section of arc and a fourth section of arc end to end, and the shapes of the first section of arc and the third section of arc are the same.
The beneficial effects of the invention are as follows:
1. the supporting mechanism has the advantages of small number of structural parts, simple structure and integrated molding.
2. The supporting mechanism can be self-unfolded, and has self-locking performance after being unfolded.
3. One or more supporting mechanisms are used simultaneously, so that the phenomenon of non-coaxial jamming is not easy to occur, the reliability is high, the unfolding rigidity of the solar wing is improved, and the base frequency of unfolding the solar wing of the optical satellite is improved.
Drawings
Fig. 1 is a schematic view of an unfolding structure of an integrated solar wing supporting mechanism according to the present invention.
Fig. 2 is a schematic view of a first strap spring hinge and a bonding mode of the integrated solar wing supporting mechanism of the present invention.
Fig. 3 is a sectional view of the 4-segment arc configuration of the integrated solar wing support mechanism of the present invention.
Fig. 4 is a schematic drawing showing a folding structure of the integrated solar wing supporting mechanism of the present invention.
Fig. 5 is an expanded schematic view of two parallel-use integrated solar wing support mechanisms of the present invention.
In the figure: 1. satellite star, 2, unfolding mechanism, 3, solar wing, 4, supporting mechanism, 5, star supporting seat, 6, first short supporting tube, 7, first sealing ring, 8, first strip spring, 9, second sealing ring, 10, first long supporting tube, 11, third sealing ring, 12, second strip spring, 13, fourth sealing ring, 14, second long supporting tube, 15, fifth sealing ring, 16, third strip spring, 17, sixth sealing ring, 18, solar wing supporting seat, 19, first section arc, 20, second section arc, 21, third section arc, 22, fourth section arc.
Detailed Description
The invention will be described in further detail with reference to the drawings and examples.
As shown in fig. 1, a solar wing 3 is connected with a satellite star 1 through a deployment mechanism 2, and one end of a supporting mechanism 4 of the integrated solar wing supporting mechanism is arranged on the satellite star 1, and the other end of the supporting mechanism is arranged on the solar wing 3, so that the deployment rigidity of the solar wing 3 is improved, and the fundamental frequency of deployment of the solar wing 3 of an optical satellite is improved. The support mechanism 4 comprises a star support 5, a first short support tube 6, a first seal ring 7, a first strip spring 8, a second seal ring 9, a first long support tube 10, a third seal ring 11, a second strip spring 12, a fourth seal ring 13, a second long support tube 14, a fifth seal ring 15, a third strip spring 16, a sixth seal ring 17, a second short support tube and a solar wing support 18.
The first, second and third band springs 8, 12 and 16 may be referred to herein as band springs, and the first, second, third, fourth, fifth and sixth bands 7, 9, 11, 13, 15 and 17 may be referred to herein as bands, and the first, second and third band spring hinges may be referred to herein as band spring hinges. The star supporting seat 5, the first short supporting tube 6, the first strip spring 8, the first long supporting tube 10, the second strip spring 12, the second long supporting tube 14, the third strip spring 16, the second short supporting tube and the solar wing supporting seat 18 are sequentially glued, sealing rings are sleeved at the connecting positions of the two ends of each strip spring, the inner surfaces of all the sealing rings are integrated with the strip springs in a gluing mode, and the sealing rings are sequentially a first sealing ring 7, a second sealing ring 9, a third sealing ring 11, a fourth sealing ring 13, a fifth sealing ring 15 and a sixth sealing ring 17. Specifically, a through hole is arranged on the star support seat 5, and a screw is used for fixedly mounting the star support seat 5 on the satellite star 1 through the through hole. The star support 5 is integrally formed with one end of the first short support tube 6 (the inner surface or the outer surface of the first short support tube 6) by cementing. The outer surface of the other end of the first short support tube 6 is glued to the inner surface of one end of the first strip spring 8. The first sealing ring 7 is glued on the outer surface of the first strip spring 8, and the specific position of the first sealing ring is the outer surface corresponding to the glued inner surface of the first strip spring 8 and the first short supporting tube 6. The inner surface of the other end of the first strip spring 8 is glued to the outer surface of one end of the first long support tube 10. The second sealing ring 9 is glued on the outer surface of the first strip spring 8, and the specific position is the outer surface corresponding to the glued inner surface of the first strip spring 8 and the first long supporting tube 10. The outer surface of the other end of the first long support tube 10 is cemented to the inner surface of one end of the second band spring 12. The third sealing ring 11 is glued on the outer surface of the second strip spring 12, and the specific position is the outer surface corresponding to the glued inner surface of the second strip spring 12 and the first long supporting tube 10. The inner surface of the other end of the second ribbon spring 12 is glued to the outer surface of one end of the second elongated support tube 14. The fourth sealing ring 13 is glued on the outer surface of the second strip spring 12, and the specific position is the outer surface corresponding to the glued inner surface of the second strip spring 12 and the second long supporting tube 14. The outer surface of the other end of the second elongated support tube 14 is cemented to the inner surface of one end of the third ribbon spring 16. The fifth sealing ring 15 is glued on the outer surface of the third strip spring 16, and the specific position is the outer surface corresponding to the glued inner surface of the third strip spring 16 and the second long support tube 14. The inner surface of the other end of the third ribbon spring 16 is glued to the outer surface of one end of the second short support tube. The sixth sealing ring 17 is glued on the outer surface of the third strip spring 16, and the specific position is the outer surface corresponding to the glued inner surface of the third strip spring 16 and the second short supporting tube. The other end (inner surface or outer surface) of the second short support tube is glued with the solar wing support base 18, and the second short support tube and the solar wing support base 18 are integrated in a gluing mode. The solar wing support base 18 is provided with a through hole, and the solar wing support base 18 is fixedly installed on the solar wing 3 through the through hole by a screw. The cementing mode of the first short support tube 6, the first sealing ring 7, the first strip spring 8, the second sealing ring 9 and the first long support tube 10 is shown in fig. 2, and the first strip spring hinge is formed after cementing; the second sealing ring 9, the first long supporting tube 10, the third sealing ring 11, the second ribbon spring 12, the fourth sealing ring 13 and the second long supporting tube 14 are glued in a manner similar to that of fig. 2, and a second ribbon spring hinge is formed after gluing; the second long support tube 14, the fifth sealing ring 15, the third strip spring 16, the sixth sealing ring 17 and the second short support tube are glued in a manner similar to that of fig. 2, and the third strip spring hinge is formed after gluing. And (3) coating curing glue on all glued positions, and carrying out glue injection on the glue-deficient areas. After cementing, the support mechanism 4 is uniformly solidified and molded, and the precision and cementing mechanical property are better. When the parts are glued, the gluing precision is ensured, and the stress is released after the gluing is finished. The supporting mechanism 4 is an integrated mechanism which is formed by cementing and curing.
The strip spring is formed by oppositely placing two arc-shaped strip springs, the length of each arc-shaped strip spring is generally 60mm to 120mm, the thickness is generally 0.10mm to 0.30mm, the radian is smaller than pi rad, the width is larger than 5mm, and the material can be stainless steel, titanium alloy, beryllium bronze or the like. The length, thickness, radian and width of the arc-shaped strip spring can be designed according to the driving force and the locking force. The ribbon spring stores elastic strain energy after being folded and bent, can spontaneously rebound and expand to an initial state, and has self-locking performance after expansion, namely, the ribbon spring keeps a supporting state of the solar wing 3. In the self-unfolding process of the ribbon spring hinge, a virtual joint shaft exists, the joint shaft has a large self-adaption characteristic and can self-adjust along with the unfolding mechanism, and the fact that the supporting mechanism 4 and the unfolding mechanism 2 cannot be blocked is guaranteed.
The shapes of the cementing parts of the first short supporting tube 6, the first sealing ring 7, the second sealing ring 9, the first long supporting tube 10, the third sealing ring 11, the fourth sealing ring 13, the second long supporting tube 14, the fifth sealing ring 15, the sixth sealing ring 17 and the second short supporting tube and the strip springs are matched with the strip springs, and the radian of the section of the cementing parts is not smaller than that of the corresponding strip springs. At the moment, the mechanical property of the strip spring can be ensured, and the locking moment of the strip spring can be ensured. Namely, the radian of the joint between the first short support tube 6 and the first strip spring 8 is not smaller than the radian of the first strip spring 8; the radian of the joint between the first long support pipe 10 and the first strip spring 8 is not smaller than the radian of the first strip spring 8; the radian of the joint between the first long support pipe 10 and the second belt spring 12 is not less than that of the second belt spring 12; the radian of the joint between the second long support pipe 14 and the second belt spring 12 is not less than the radian of the second belt spring 12; the radian of the joint between the second long support pipe 14 and the third strip spring 16 is not less than the radian of the third strip spring 16; the radian of the glued part of the second short supporting tube and the third strip spring 16 is not smaller than the radian of the third strip spring 16; the radian of the sealing ring is not smaller than that of the two ends of the corresponding first strip spring 8, second strip spring 12 and third strip spring 16. Specifically, the radian of the section of the glued joint of the first short support tube 6 and the first strip spring 8, the glued joint of the first seal ring 7 and the first strip spring 8, the glued joint of the second seal ring 9 and the first strip spring 8, and the glued joint of the first long support tube 10 and the first strip spring 8 is not smaller than the radian of the first strip spring 8. The radian of the section of the glued joint of the first long support pipe 10 and the second belt spring 12, the glued joint of the third sealing ring 11 and the second belt spring 12, the glued joint of the fourth sealing ring 13 and the second belt spring 12 and the glued joint of the second long support pipe 14 and the second belt spring 12 is not smaller than the radian of the second belt spring 12. The radian of the section of the joint between the second long support tube 14 and the third strip spring 16, the joint between the fifth sealing ring 15 and the third strip spring 16, the joint between the sixth sealing ring 17 and the third strip spring 16 and the joint between the second short support tube and the third strip spring 16 are not smaller than the radian of the third strip spring 16. The whole cross section shapes of the first short supporting tube 6, the first sealing ring 7, the second sealing ring 9, the first long supporting tube 10, the third sealing ring 11, the fourth sealing ring 13, the second long supporting tube 14, the fifth sealing ring 15, the sixth sealing ring 17 and the second short supporting tube are matched with the radian of the strip spring, namely the radian of the glued contact surface of the cross section and the strip spring is not smaller than the radian of the strip spring.
All of the above (the first, second and third band springs 8, 12 and 16 are identical in structure), the first, second, third, fourth, fifth, sixth and second short support tubes 6, 7, 9, 10, 11, 13, 14, 15, 17 and 16 have the following cross-sectional shapes: an elliptic closed graph formed by N sections of circular arcs, wherein N is a positive integer greater than or equal to 4, so as to ensure the performance of the ribbon spring. Preferably, the cross section is an elliptical closed figure formed by ellipse or 4 sections of circular arcs, so that the unfolding performance of the strip spring can be better exerted. As shown in fig. 3, an elliptical closed graph formed by 4 sections of arcs is formed by connecting a first section of arc 19, a second section of arc 20, a third section of arc 21 and a fourth section of arc 22 end to end, wherein the first section of arc 19 and the third section of arc 21 are arcs with the same shape, the radian is not less than that of a strip spring, and the width is not less than that of the strip spring, namely, the first section of arc 19 and the third section of arc 21 are both glued with the strip spring. The second segment arc 20 and the fourth segment arc 22 are arcs of the same shape. The elliptic closed graph is of an integrated structure.
The first, second and third band springs 8, 12 and 16 are identical in structure, the first and second short support tubes 6 and 14 are identical in structure and material, and the first and second long support tubes 10 and 14 are identical in structure and material. The first short supporting tube 6, the second short supporting tube, the first long supporting tube 10 and the second long supporting tube 14 are all of thin-wall structures, the thickness of the first short supporting tube is 0.4-1.5 mm, the weight of the supporting mechanism 4 is greatly reduced, and the first short supporting tube, the second short supporting tube, the first long supporting tube and the second long supporting tube are all formed by winding carbon fiber composite materials. All sealing rings have the same shape, structure and material and are formed by winding carbon fiber composite materials.
When the supporting mechanism 4 is folded, the strip springs are required to be folded, and when three strip springs are manually folded, the supporting mechanism 4 is folded; or the second strip spring 12 is manually folded, when the second strip spring 12 is folded, the first strip spring 8 and the third strip spring 16 are automatically folded along with the second strip spring 12, and then the supporting mechanism 4 is folded. The folded state is shown in fig. 4, and when the belt-shaped spring hinge is in the folded state, elastic strain energy is stored, and the belt-shaped spring hinge can rebound spontaneously to be unfolded to an initial state. After the supporting mechanism 4 is folded, the solar wing 3 is pressed on the satellite star 1 by the self pressing mechanism of the solar wing 3, and the supporting mechanism 4 is kept in a folded state. When the compressing mechanism of the solar wing 3 is opened, the solar wing 3 is unfolded and locked under the common driving of the unfolding mechanism 2 and the supporting mechanism 4. When the unfolding mechanism 2 has no driving force, the supporting mechanism 4 can also be automatically opened by means of the elastic strain energy of the belt-shaped spring.
The supporting mechanisms 4 can be used in 2 or more groups simultaneously, namely in parallel, so that the fundamental frequency of the solar wing 3 can be effectively improved, and the situation of non-coaxial clamping between the supporting mechanisms 4 can be avoided. Fig. 5 shows the support mechanism 4 in a developed view when two support mechanisms are used in parallel.
The supporting mechanism 4 has the advantages of small number of structural parts, simple structure and integrated forming. The support mechanism 4 can be unfolded automatically, the operation is simple and convenient, and the folding is kept through the solar wing 3 and the satellite star 1. The plurality of supporting mechanisms 4 can be used simultaneously, the phenomenon of non-coaxial jamming is not easy to occur, the reliability is high, the unfolding rigidity of the solar wing 3 is improved, and the base frequency of unfolding the solar wing 3 of the optical satellite is improved.
Claims (1)
1. Integral type solar wing supporting mechanism, its characterized in that includes:
a satellite support seat (5) fixed on the satellite (1);
a first short supporting tube (6) with one end glued with the star supporting seat (5);
a first strip spring (8) with one end glued with the outer surface of the other end of the first short supporting tube (6);
a first long support tube (10) with one end of the outer surface glued with the other end of the first strip spring (8);
a second strip spring (12) with one end glued with the outer surface of the other end of the first long support tube (10);
a second long support tube (14) with one end of the outer surface glued with the other end of the second band spring (12);
a third strip spring (16) with one end glued with the outer surface of the other end of the second long support tube (14);
a second short support tube with one end of the outer surface glued with the other end of the third strip spring (16);
a solar wing supporting seat (18) with one end glued with the other end of the second short supporting tube, wherein the solar wing supporting seat (18) is fixed on the solar wing (3);
six sealing rings glued on the outer surfaces of two ends of the first strip spring (8), the second strip spring (12) and the third strip spring (16) in a one-to-one correspondence manner;
the radians of the cementing parts of the first short supporting pipes (6) and the first long supporting pipes (10) and the first strip springs (8) are not smaller than the radians of the first strip springs (8); the radians of the cementing parts of the first long supporting tube (10) and the second long supporting tube (14) and the second belt-shaped spring (12) are not smaller than the radians of the second belt-shaped spring (12); the radian of the cementing parts of the second long supporting tube (14) and the second short supporting tube and the third strip spring (16) is not smaller than that of the third strip spring (16); the radian of the sealing ring is not smaller than the radian of two ends of the corresponding first strip spring (8), second strip spring (12) and third strip spring (16);
the first strip spring (8), the second strip spring (12) and the third strip spring (16) are identical in structure; the strip springs are formed by oppositely placing two arc-shaped strip springs, the length of each arc-shaped strip spring is 60-120 mm, the thickness of each arc-shaped strip spring is 0.1-0.3 mm, the radian is smaller than pi rad, and the width of each arc-shaped strip spring is larger than 5mm;
the second long support tube (14) and the first long support tube (10) have the same structure, and the first short support tube (6) and the second short support tube have the same structure; the thicknesses of the second long support tube (14), the first long support tube (10), the first short support tube (6) and the second short support tube are all 0.4-1.5 mm;
the second long support tube (14), the first long support tube (10), the first short support tube (6), the second short support tube and the sealing ring are all made of carbon fiber composite materials;
the cross sections of the first short supporting tube (6), the first strip spring (8), the first long supporting tube (10), the second strip spring (12), the second long supporting tube (14), the third strip spring (16) and the second short supporting tube are all elliptical closed figures; the elliptical closed graph is formed by connecting a first section of arc (19), a second section of arc (20), a third section of arc (21) and a fourth section of arc (22) end to end, and the shapes of the first section of arc (19) and the third section of arc (21) are the same;
when the integrated solar wing supporting mechanism is manufactured, all cementing positions are coated with curing glue, glue supplementing is carried out on a glue shortage area in a glue injection mode, uniform curing and forming are carried out after cementing, and stress release is carried out after cementing is finished.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810267735.9A CN108327928B (en) | 2018-03-29 | 2018-03-29 | Integrated solar wing supporting mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810267735.9A CN108327928B (en) | 2018-03-29 | 2018-03-29 | Integrated solar wing supporting mechanism |
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| Publication Number | Publication Date |
|---|---|
| CN108327928A CN108327928A (en) | 2018-07-27 |
| CN108327928B true CN108327928B (en) | 2023-09-15 |
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|---|---|---|---|
| CN201810267735.9A Active CN108327928B (en) | 2018-03-29 | 2018-03-29 | Integrated solar wing supporting mechanism |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112173175B (en) * | 2020-10-12 | 2022-08-02 | 长光卫星技术股份有限公司 | Solar wing wire harness management device suitable for cube star |
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