CN117401185B - High-bearing-ratio micro-nano satellite structure suitable for large load and assembly mode thereof - Google Patents
High-bearing-ratio micro-nano satellite structure suitable for large load and assembly mode thereof Download PDFInfo
- Publication number
- CN117401185B CN117401185B CN202311713371.XA CN202311713371A CN117401185B CN 117401185 B CN117401185 B CN 117401185B CN 202311713371 A CN202311713371 A CN 202311713371A CN 117401185 B CN117401185 B CN 117401185B
- Authority
- CN
- China
- Prior art keywords
- plate
- bottom plate
- bearing plate
- bearing
- nano satellite
- 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
- 238000000034 method Methods 0.000 claims abstract description 12
- 238000009413 insulation Methods 0.000 claims description 15
- 230000001681 protective effect Effects 0.000 claims description 10
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 6
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 239000004917 carbon fiber Substances 0.000 claims description 6
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 210000001503 joint Anatomy 0.000 claims description 4
- 238000013461 design Methods 0.000 abstract description 11
- 238000003032 molecular docking Methods 0.000 abstract description 3
- 238000010586 diagram Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 5
- 238000009434 installation Methods 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 3
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000012545 processing Methods 0.000 description 3
- 235000015842 Hesperis Nutrition 0.000 description 2
- 235000012633 Iberis amara Nutrition 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000012546 transfer Methods 0.000 description 2
- 229910000733 Li alloy Inorganic materials 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 239000001989 lithium alloy Substances 0.000 description 1
- GCICAPWZNUIIDV-UHFFFAOYSA-N lithium magnesium Chemical compound [Li].[Mg] GCICAPWZNUIIDV-UHFFFAOYSA-N 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- 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
-
- 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)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Laminated Bodies (AREA)
Abstract
The invention provides a high-bearing-ratio micro-nano satellite structure suitable for a large load and an assembly mode thereof, and belongs to the technical field of space product structural design. The problem that the existing micro-nano satellite configuration is difficult to meet the requirements of large load and high bearing ratio is solved. The satellite comprises a high-bearing-ratio micro-nano satellite structure, wherein the high-bearing-ratio micro-nano satellite structure comprises a central bearing plate, a bottom plate and a top plate, the bottom plate is a satellite docking cabin plate, a bottom plate Liang Maijian is arranged in the bottom plate, the upper surface of the bottom plate is provided with the central bearing plate, the lower surface of the bottom plate is provided with a carrying adapter, the central bearing plate and the carrying adapter are connected with a bottom plate beam embedded part inside the bottom plate, the central bearing plate is of a cross structure which is orthogonal to each other, the upper end of the central bearing plate is connected with the top plate, and four plate ends of the side face of the central bearing plate are respectively positioned at four corners of the bottom plate and the top plate. The method is mainly used for the high-bearing-ratio micro-nano satellite with large load.
Description
Technical Field
The invention belongs to the technical field of space product structure design, and particularly relates to a high-bearing-ratio micro-nano satellite structure suitable for large load and an assembly mode thereof.
Background
With the continuous development of the aerospace technology, the satellite design is gradually miniaturized, so that the space utilization rate of the available envelope of the fairing of the micro-nano satellite is increased on the premise of improving the rigidity and main bearing capacity for adapting to various carrier rockets and meeting the envelope requirements and mechanical environment requirements of the carrier rockets. Meanwhile, because of the high performance and complex functions of the partial load, a large volume and a large weight are required, and therefore, a large load layout design and a high bearing ratio become one of important technical requirements of the satellite.
Conventional satellite configurations include: box-plate type, bearing cylinder type, truss type and the like. Different configurations have different advantages and also have respective disadvantages. The box plate type structure is simple and compact, the cost is low, but the main bearing capacity and the bearing capacity are poor; the bearing cylinder type main bearing capacity and bearing capacity are large, but the space utilization rate is low, the bearing cylinder occupies excessive space in the cabin to influence the layout of large load, and the bearing cylinder greatly increases the structural weight; the truss type structure is flexible to assemble and disassemble, easy to integrate and universal in design, but is complex in truss type structure, low in resource utilization rate and large in layout difficulty, and is not suitable for large-load installation.
Disclosure of Invention
In view of the above, the present invention is directed to providing a micro-nano satellite structure with high load bearing ratio and its assembly method, so as to solve the problem that the existing micro-nano satellite configuration is difficult to meet the requirements of high load bearing ratio.
In order to achieve the above purpose, the present invention adopts the following technical scheme: the utility model provides a high bearing ratio micro-nano satellite structure suitable for big load, it includes central bearing plate, bottom plate and roof, the bottom plate is the satellite butt joint cabin board, be provided with bottom plate Liang Maijian in the bottom plate, the bottom plate upper surface is provided with central bearing plate, the bottom plate lower surface is provided with the delivery adapter, central bearing plate and delivery adapter all link to each other with the inside bottom plate roof beam buries of bottom plate, central bearing plate is the cross structure of mutual quadrature, central bearing plate upper end links to each other with the roof, four board ends of central bearing plate side are located the four corners of bottom plate and roof respectively, central bearing plate includes first bearing plate, second bearing plate and third bearing plate are coplanar, and second bearing plate and third bearing plate are connected respectively in the both sides of first bearing plate, the outside of micro-nano satellite structure is provided with protective structure, protective structure's upper and lower both ends link to each other with roof and bottom plate respectively.
Furthermore, the central bearing plate, the bottom plate and the top plate are all aluminum skin honeycomb plates.
Further, the protection structure is an outer cabin plate, and the outer cabin plate is an aluminum skin honeycomb plate with a planar structure.
Furthermore, the protection structure comprises a plane outer frame and a multi-layer heat insulation assembly, wherein the plane outer frame is of a hollow structure made of carbon fiber materials, the upper end and the lower end of the plane outer frame are respectively connected with the top plate and the bottom plate, and the multi-layer heat insulation assembly is adhered to the outer surface of the plane outer frame.
Furthermore, the protection structure comprises a three-dimensional outer frame and a multi-layer heat insulation assembly, the three-dimensional outer frame is of a hollow structure made of carbon fiber materials, the outer side of the three-dimensional outer frame is of an arc-shaped structure, the upper end and the lower end of the three-dimensional outer frame are respectively connected with the top plate and the bottom plate, and the multi-layer heat insulation assembly is adhered to the outer surface of the three-dimensional outer frame.
Furthermore, the number of the protection structures is four, and the four protection structures are respectively arranged on the periphery of the outer side of the micro-nano satellite structure.
Furthermore, the number of the protective structures is three, the three protective structures are respectively arranged on three sides of the outer side of the micro-nano satellite structure, and the other side is provided with a solar wing.
Furthermore, the central bearing plate is connected with the bottom plate and the top plate and the protective structure is connected with the bottom plate and the top plate through the connection corner pieces and the standard parts.
The invention also provides an assembly mode of the high-bearing-ratio micro-nano satellite structure suitable for large load, which comprises the following specific steps: the first bearing plate is fixedly arranged on the upper surface of the bottom plate, the second bearing plate and the third bearing plate are fixedly arranged on the bottom plate respectively, the second bearing plate and the third bearing plate are fixedly arranged on the first bearing plate, and the top plate is fixedly arranged on the top of the central bearing plate.
Compared with the prior art, the invention has the beneficial effects that: the invention provides a micro-nano satellite structure with high bearing ratio and an assembly mode thereof, which are suitable for large load, realize the simplification of the satellite structure, improve the main bearing capacity and rigidity, simultaneously meet the layout and installation of large-volume and large-weight load, and realize the design with high bearing ratio. The method comprises the following steps:
(1) The high-bearing-ratio micro-nano satellite structure has the structural advantages of various traditional configurations, and comprises the following components: 1. the box plate type structure has the advantages of simple and compact structure and low cost; 2. the bearing cylinder type main bearing and bearing capacity are high; 3. the truss type structure has the advantages of flexible disassembly and assembly and easy integration, and meanwhile, the corresponding defects are avoided or reduced.
(2) The micro-nano satellite structure with high bearing ratio realizes the integrated design of main bearing capacity and bearing capacity through the central bearing plate, reduces the weight of structural members on the premise of improving the bearing capacity, and realizes the effect of high bearing ratio.
(3) The high-bearing-ratio micro-nano satellite has the advantages of simple structure composition, less number of structural parts, simple structure and easiness in processing, and can reduce the processing cost and shorten the processing period.
(4) In the micro-nano satellite structure with high bearing ratio, the platform equipment and the load can be directly or through a bracket arranged on the surface of the central bearing plate, and the force is directly transferred to the satellite-rocket butting surface through the central bearing plate, so that the force transfer path is short and the bearing capacity is high.
(5) The high-bearing-capacity micro-nano satellite has a more open layout space than the micro-nano satellite structure, and the utilization rate of the available envelope of the fairing is high.
(6) The high-bearing-ratio micro-nano satellite structure has small assembly difficulty, can shorten the total assembly period and reduce the total assembly risk.
(7) The high-bearing-ratio micro-nano satellite structure is beneficial to reverse dismantling of equipment and structural parts, and can shorten the period of assembly and test procedures of equipment software fall welding, vibration modification, thermal control modification and the like.
(8) The high-bearing-ratio micro-nano satellite structure cabin external meter is flexible, the cabin external protection selection can be carried out according to the specific micro-nano satellite requirement, and the weight is increased less.
The present invention also relates to an invention in which elements are omitted. The conventional satellite structure needs to provide a separate bearing structure to resist the main bearing force during the launching process, and then needs to provide another separate equipment bearing structure for the installation of equipment or load, resulting in the complex overall structure of the satellite. The method combines the main bearing structure and the equipment bearing structure in the traditional satellite into a whole through a very simple method, and after the original parts are omitted, the original whole functions are still kept, the bearing capacity is improved, and the structural size is reduced. And the whole structure of the structure is realized by using common parts in the aerospace field, the manufacturing difficulty of the structure is not increased, the structure is easy to realize, and the application value is high.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic diagram of a high-load-carrying-ratio micro-nano satellite structure suitable for large load according to the present invention;
FIG. 2 is an exploded view of a high-loading-ratio micro-nano satellite structure suitable for large loads according to the present invention;
FIG. 3 is a schematic view of a first corner piece according to the present invention;
FIG. 4 is a schematic view of a second gusset structure according to the present invention;
FIG. 5 is a schematic diagram showing an assembly process of a high-load-carrying-ratio micro-nano satellite structure suitable for large load according to the present invention;
FIG. 6 is a schematic diagram illustrating a high-load-carrying-ratio micro-nano satellite structure assembly process for large load according to the present invention;
FIG. 7 is a schematic diagram III illustrating an assembly process of a high-load-carrying-ratio micro-nano satellite structure suitable for large loads according to the present invention;
FIG. 8 is a schematic diagram showing an assembly process of a high-load-carrying-ratio micro-nano satellite structure suitable for a large load according to the present invention;
FIG. 9 is a schematic diagram of a high-load-carrying-ratio micro-nano satellite structure cabin separation and force transfer for a large load according to the present invention;
FIG. 10 is a schematic diagram of a high-load-ratio micro-nano satellite structure force transmission path suitable for large loads according to the invention;
FIG. 11 is a schematic view of a third triangular plate according to the present invention;
FIG. 12 is a schematic view of an outer deck structure according to the present invention;
FIG. 13 is a schematic view of a planar outer frame according to the present invention;
FIG. 14 is a schematic view of a three-dimensional outer frame according to the present invention;
FIG. 15 is a schematic view of a high loading ratio micro-nano satellite for mounting an outer deck according to the present invention;
FIG. 16 is a schematic view of a high load-bearing micro-nano satellite for mounting a planar outer frame and a multi-layered insulation assembly according to the present invention;
FIG. 17 is a schematic view of a high load-bearing ratio micro-nano satellite for mounting a three-dimensional outer frame and a multi-layer heat insulation assembly according to the present invention;
FIG. 18 is a schematic view of a high duty ratio micro-nano satellite envelope in a fairing for a large load according to the present invention;
fig. 19 is a schematic view of a solar wing mounted on a high-load-ratio micro-nano satellite structure according to the present invention.
In the figure:
1: center load board, 2: bottom plate, 3: top plate, 4: connecting corner pieces, 5: outer deck, 6: plane outer frame, 7: three-dimensional outer frame, 8: multilayer insulation assembly, 9: body-mounted solar wing, 10: carrying adapter, 11: carrying fairings, 12: platform device, 13: load, 1-1: first bearing plate, 1-2: second bearing plate, 1-3: third bearing plate, 2-1: bottom plate roof beam buries, 4-1: first corner piece, 4-1-1: first pin hole, 4-1-2: first through hole, 4-2: second corner piece, 4-2-1: second pin hole, 4-2-2: second through hole, 4-3: third gusset, 4-3-1: screw hole, 4-3-2: and a third through hole.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It should be noted that, in the case of no conflict, embodiments of the present invention and features of the embodiments may be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.
Referring to fig. 1-19 for illustrating the present embodiment, a micro-nano satellite structure with high bearing ratio suitable for large load includes a central bearing plate 1, a bottom plate 2 and a top plate 3, the bottom plate 2 is a satellite docking cabin plate, a bottom plate Liang Maijian-1 is disposed in the bottom plate 2, a central bearing plate 1 is disposed on an upper surface of the bottom plate 2, a carrying adapter 10 is disposed on a lower surface of the bottom plate 2, the central bearing plate 1 and the carrying adapter 10 are both connected with the bottom plate Liang Maijian-1 inside the bottom plate 2, the central bearing plate 1 is in a cross structure orthogonal to each other, an upper end of the central bearing plate 1 is connected with the top plate 3, four plate ends on a side surface of the central bearing plate 1 are respectively located at four corners of the bottom plate 2 and the top plate 3, the central bearing plate 1 includes a first bearing plate 1-1, a second bearing plate 1-2 and a third bearing plate 1-3, the second bearing plate 1-2 and the third bearing plate 1-3 are coplanar, and the second bearing plate 1-2 and the third bearing plate 1-2 are respectively connected to two sides of the first bearing plate 1-3.
The high-bearing-ratio micro-nano satellite structure suitable for large load is assembled by the following steps: the first bearing plate 1-1 is installed and fixed on the upper surface of the bottom plate 2, the second bearing plate 1-2 and the third bearing plate 1-3 are installed and fixed with the bottom plate 2 respectively, the second bearing plate 1-2 and the third bearing plate 1-3 are installed and fixed with the first bearing plate 1-1, and the top plate 3 is installed and fixed on the top of the central bearing plate 1. After the micro-nano satellite structure with high bearing ratio is assembled, a plurality of cabin boards are in an orthogonal relationship, so that the rigidity of the structure is improved to a great extent; the central bearing plates 1 are mutually orthogonal and are directly arranged on the surface of the bottom plate 2 and connected with the bottom plate Liang Maijian-1 in the bottom plate 2, so that the main bearing effect of the structure is improved.
The bottom plate 2 is a satellite-rocket docking deck, the bottom plate beam embedded part 2-1 is designed in the bottom plate to enhance the main bearing effect, and the bottom plate Liang Maijian-1 is matched with the central bearing plate 1 and the carrying adapter 10 to complete the design, as shown in fig. 9. The cabin body of the high bearing ratio micro-nano satellite structure is divided into four parts by the central bearing plate 1 and is used for installing the platform equipment 12 and the load 13, the platform equipment 12 and the load 13 can be directly or through a bracket installed on the surface of the central bearing plate 1 and directly transmit force to the bottom plate Liang Maijian-1 on the satellite-rocket butting surface through the central bearing plate 1, the bottom plate Liang Maijian-1 on the satellite-rocket butting surface directly transmits force to the carrying adapter 10, the force transmission path is short, the bearing capacity can be improved, and the whole satellite force transmission path is shown in figure 10.
In this embodiment, the central bearing plate 1, the bottom plate 2 and the top plate 3 are all aluminum skin honeycomb plates.
In this embodiment, a protection structure may be additionally disposed on the outer side of the micro-nano satellite structure, and the upper and lower ends of the protection structure are respectively connected with the top plate 3 and the bottom plate 2.
The guard structure described in the above embodiment includes the following forms:
form 1: as shown in fig. 15, the protection structure is an outer cabin board 5, and the outer cabin board 5 is an aluminum skin honeycomb board with a planar structure. The protection of equipment and load in the cabin is realized, and the effect of the equipment installation surface is increased.
Form 2: as shown in fig. 16, the protection structure includes a planar outer frame 6 and a multi-layer heat insulation component 8, where the planar outer frame 6 is a hollow structure made of carbon fiber, and the weight of the planar outer frame is reduced by hollow design, the upper and lower ends of the planar outer frame 6 are respectively connected with the top plate 3 and the bottom plate 2, and the multi-layer heat insulation component 8 is adhered to the outer surface of the planar outer frame 6. The increased weight is reduced while achieving a protective effect against equipment and loads in the cabin.
Form 3: as shown in fig. 17, the protection structure includes a three-dimensional outer frame 7 and a multi-layer heat insulation component 8, the three-dimensional outer frame 7 is a hollow structure made of carbon fiber, and by means of hollow design, the weight of the three-dimensional outer frame 7 is reduced, the outer side of the three-dimensional outer frame 7 is in an arc structure, the upper end and the lower end of the three-dimensional outer frame 7 are respectively connected with the top plate 3 and the bottom plate 2, and the multi-layer heat insulation component 8 is adhered to the outer surface of the three-dimensional outer frame 7. While achieving the protection effect on the cabin equipment and the load, the weight is reduced, the layout space of the platform equipment 12 and the load 13 is increased, and the full utilization of the available envelope of the carrying fairing 11 is achieved, as shown in fig. 18.
The number of the protection structures in the mode is four, and the four protection structures are respectively arranged on the periphery of the outer side of the micro-nano satellite structure. Or as shown in fig. 19, the number of the protection structures is three, the three protection structures are respectively arranged on three sides of the outer side of the micro-nano satellite structure, and the body-mounted solar wing 9 is arranged on the other side, so that the protection of the equipment and the load in the cabin is realized, and meanwhile, a mounting way of the body-mounted solar wing 9 is provided. The above components may be selectively installed according to the specific requirements of the micro-nano satellite platform device 12 and the load 13.
In the above embodiment, the central bearing plate 1 is connected with the bottom plate 2 and the top plate 3, and the protection structure is connected with the bottom plate 2 and the top plate 3 through the connection corner pieces 4 and the standard parts.
The connecting corner piece 4 comprises a first corner piece 4-1, a second corner piece 4-2 and a third corner piece 4-3, wherein the first corner piece 4-1 is used for fixing the second bearing plate 1-2 or the third bearing plate 1-3 and the first bearing plate 1-1 and the bottom plate 2, the second corner piece 4-2 is used for fixing the second bearing plate 1-2 or the third bearing plate 1-3 or the first bearing plate 1-1 and the bottom plate 2, and the third corner piece 4-3 is used for connecting the protective structure or the body-mounted solar wing 9 with the top plate 3 and the bottom plate 2.
The central bearing plate 1, the bottom plate 2 and the top plate 3 are internally provided with standard embedded parts and connected embedded parts, so that the surface of the cabin plate is provided with pin holes and threaded holes, wherein the pin holes are used for positioning, and the threaded holes are used for fixing. The materials of the first corner piece 4-1, the second corner piece 4-2 and the third corner piece 4-3 are preferably magnesium-lithium alloy so as to reduce the weight of the structural part.
As shown in fig. 3, the first corner piece 4-1 is provided with a first pin hole 4-1-1 and a first through hole 4-1-2, and as shown in fig. 4, the second corner piece 4-2 is provided with a second pin hole 4-2-1 and a second through hole 4-2-2. The first pin holes 4-1-1 and the second pin holes 4-2-1 are used for positioning the central bearing plate 1, the bottom plate 2 and the top plate 3, and the first through holes 4-1-2 and the second through holes 4-2-2 are used for being matched with threaded holes of the central bearing plate 1, the bottom plate 2 and the top plate 3 to complete fixation. The first bearing plate 1-1 is installed and fixed on the surface of the bottom plate 2 through the first corner piece 4-1 and the second corner piece 4-2, the second bearing plate 1-2 and the bottom plate 2 are installed and fixed with the first bearing plate 1-1, and finally the top plate 3 is installed and fixed on the top of the central bearing plate 1 through the first corner piece 4-1 and the second corner piece 4-2.
As shown in fig. 11, the third triangular plate 4-3 is provided with a threaded hole 4-3-1 and a third through hole 4-3-2, and as shown in fig. 12, the outer deck plate 5 is provided with a counter bore for fixing the third triangular plate 4-3. As shown in fig. 13 and 14, through holes are designed at the fixing positions of the plane outer frame 6, the three-dimensional outer frame 7 and the third triangular plate 4-3. The third through holes 4-3-2 are used for being fixedly arranged on the bottom plate 2 and the top plate 3, and the threaded holes 4-3-1 are used for being fixedly arranged on the protective structure.
The micro-nano satellite structure with high bearing ratio and the assembly mode thereof suitable for large load realize the simplification of the satellite structure, improve the main bearing capacity and rigidity, simultaneously meet the layout and installation of large-volume and large-weight load and realize the design with high bearing ratio.
The embodiments of the invention disclosed above are intended only to help illustrate the invention. The examples are not intended to be exhaustive or to limit the invention to the precise forms disclosed. Many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention.
Claims (9)
1. The utility model provides a high bearing ratio micro-nano satellite structure suitable for big load which characterized in that: the satellite protection device comprises a central bearing plate (1), a bottom plate (2) and a top plate (3), wherein the bottom plate (2) is a satellite butt joint cabin plate, the bottom plate (2) is internally provided with the bottom plate Liang Maijian (2-1), the upper surface of the bottom plate (2) is provided with the central bearing plate (1), the lower surface of the bottom plate (2) is provided with a carrying adapter (10), the central bearing plate (1) and the carrying adapter (10) are both connected with the bottom plate Liang Maijian (2-1) in the bottom plate (2), the central bearing plate (1) is of a cross structure which is mutually orthogonal, the upper end of the central bearing plate (1) is connected with the top plate (3), the four plate ends on the side surface of the central bearing plate (1) are respectively positioned at four corners of the bottom plate (2) and the top plate (3), the central bearing plate (1) comprises a first bearing plate (1-1), a second bearing plate (1-2) and a third bearing plate (1-3), the second bearing plate (1-2) and the third bearing plate (1-3) are both connected with the two sides of the satellite protection structure (1-3) which are respectively arranged at two sides of the bottom plate (1-3), the platform device (12) and the load (13) are directly or through the support to be installed on the surface of the central force bearing plate (1), and are directly transferred to the bottom plate Liang Maijian (2-1) on the satellite and rocket butt joint surface through the central force bearing plate (1), and are directly transferred to the carrying adapter (10) through the bottom plate Liang Maijian (2-1) on the satellite and rocket butt joint surface.
2. The high-load-carrying ratio micro-nano satellite structure suitable for large loads according to claim 1, wherein: the central bearing plate (1), the bottom plate (2) and the top plate (3) are all aluminum skin honeycomb plates.
3. The high-load-carrying ratio micro-nano satellite structure suitable for large loads according to claim 1, wherein: the protection structure is an outer cabin plate (5), and the outer cabin plate (5) is an aluminum skin honeycomb plate with a planar structure.
4. The high-load-carrying ratio micro-nano satellite structure suitable for large loads according to claim 1, wherein: the protection structure comprises a plane outer frame (6) and a multi-layer heat insulation assembly (8), wherein the plane outer frame (6) is of a hollow structure made of carbon fiber materials, the upper end and the lower end of the plane outer frame (6) are respectively connected with the top plate (3) and the bottom plate (2), and the multi-layer heat insulation assembly (8) is adhered to the outer surface of the plane outer frame (6).
5. The high-load-carrying ratio micro-nano satellite structure suitable for large loads according to claim 1, wherein: the protection structure comprises a three-dimensional outer frame (7) and a multi-layer heat insulation assembly (8), wherein the three-dimensional outer frame (7) is of a hollow structure made of carbon fiber materials, the outer side of the three-dimensional outer frame (7) is of an arc-shaped structure, the upper end and the lower end of the three-dimensional outer frame (7) are respectively connected with the top plate (3) and the bottom plate (2), and the multi-layer heat insulation assembly (8) is adhered to the outer surface of the three-dimensional outer frame (7).
6. A high aspect ratio micro-nano satellite structure suitable for large loads according to any one of claims 3-5, wherein: the number of the protection structures is four, and the four protection structures are respectively arranged on the periphery of the outer side of the micro-nano satellite structure.
7. A high aspect ratio micro-nano satellite structure suitable for large loads according to any one of claims 3-5, wherein: the number of the protective structures is three, the three protective structures are respectively arranged on three sides of the outer side of the micro-nano satellite structure, and the other side is provided with a body-mounted solar wing (9).
8. A high aspect ratio micro-nano satellite structure suitable for large loads according to any one of claims 3-5, wherein: the central bearing plate (1) is connected with the bottom plate (2) and the top plate (3) and the protection structure is connected with the bottom plate (2) and the top plate (3) through the cooperation of the connecting corner pieces (4) and the standard parts.
9. The method for assembling a high-load-carrying-ratio micro-nano satellite structure suitable for large loads according to claim 1, wherein the method comprises the following steps: the first bearing plate (1-1) is installed and fixed on the upper surface of the bottom plate (2), the second bearing plate (1-2) and the third bearing plate (1-3) are installed and fixed with the first bearing plate (1-1), and the top plate (3) is installed and fixed at the top of the central bearing plate (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311713371.XA CN117401185B (en) | 2023-12-14 | 2023-12-14 | High-bearing-ratio micro-nano satellite structure suitable for large load and assembly mode thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311713371.XA CN117401185B (en) | 2023-12-14 | 2023-12-14 | High-bearing-ratio micro-nano satellite structure suitable for large load and assembly mode thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117401185A CN117401185A (en) | 2024-01-16 |
| CN117401185B true CN117401185B (en) | 2024-03-19 |
Family
ID=89500283
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311713371.XA Active CN117401185B (en) | 2023-12-14 | 2023-12-14 | High-bearing-ratio micro-nano satellite structure suitable for large load and assembly mode thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117401185B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235916A (en) * | 2015-10-27 | 2016-01-13 | 上海微小卫星工程中心 | Integration satellite compact in layout |
| CN114148546A (en) * | 2021-11-17 | 2022-03-08 | 北京九天微星科技发展有限公司 | Satellite configuration |
| CN217125165U (en) * | 2022-01-14 | 2022-08-05 | 中国科学院微小卫星创新研究院 | Satellite power cabin structure capable of bearing high-capacity propellant |
-
2023
- 2023-12-14 CN CN202311713371.XA patent/CN117401185B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105235916A (en) * | 2015-10-27 | 2016-01-13 | 上海微小卫星工程中心 | Integration satellite compact in layout |
| CN114148546A (en) * | 2021-11-17 | 2022-03-08 | 北京九天微星科技发展有限公司 | Satellite configuration |
| CN217125165U (en) * | 2022-01-14 | 2022-08-05 | 中国科学院微小卫星创新研究院 | Satellite power cabin structure capable of bearing high-capacity propellant |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117401185A (en) | 2024-01-16 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN103863577B (en) | The board-like satellite configuration of frame surface and modularization satellite | |
| CN100575191C (en) | A kind of main load-carrying structure of spacecraft | |
| CN105235916B (en) | A kind of integrated satellite of compact layout | |
| CN109850186B (en) | Plate frame type satellite structure for one-rocket multi-satellite parallel transmission and assembly method | |
| CN102975867A (en) | Satellite module and modularized satellite | |
| CN111703592B (en) | Large commercial remote sensing satellite platform configuration and assembly method | |
| CN212951088U (en) | Unmanned aerial vehicle outer wing that contains whole oil tank | |
| CN112298617B (en) | On-orbit separable satellite propulsion service cabin main structure | |
| CN112319851B (en) | Large-scale boxboard formula communication cabin structure | |
| CN102139757A (en) | Framed front center fuselage suitable for unmanned plane and model plane | |
| CN105539878A (en) | Large truss type vibration isolation platform structure facing various effective loads | |
| CN117401185B (en) | High-bearing-ratio micro-nano satellite structure suitable for large load and assembly mode thereof | |
| CN211869687U (en) | Convenient detachable mixed wing unmanned aerial vehicle | |
| CN112918702A (en) | Satellite platform structure with high stability and low thermal deformation | |
| CN113911393A (en) | Cone-prism transition type honeycomb interlayer bearing cylinder structure | |
| CN112298605B (en) | Plate-and-bar type satellite main structure | |
| CN105819006B (en) | A kind of gas support for spacecraft | |
| CN107331940B (en) | Adapt to the antisymmetry high rigidity mixed structure of spaceborne big front antenna H-type installation | |
| CN110683077A (en) | Trapezoidal satellite structure suitable for radar antenna and manufacturing method | |
| CN114394259B (en) | Main bearing structure of satellite-rocket four-point connection satellite | |
| CN216805791U (en) | Sectional type aircraft ventral fin structure | |
| CN212998380U (en) | Light fuselage skeleton structure of airplane model | |
| CN111792056B (en) | Bearing and satellite-rocket connection integrated satellite structural slab | |
| CN215323338U (en) | Little cable cubic star framework device | |
| CN202529143U (en) | Cementing interlayer airfoil structure with single main strength bearing box type beam |
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 |