CN114435627B - Satellite structure and satellite assembly method - Google Patents
Satellite structure and satellite assembly method Download PDFInfo
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- CN114435627B CN114435627B CN202210169552.XA CN202210169552A CN114435627B CN 114435627 B CN114435627 B CN 114435627B CN 202210169552 A CN202210169552 A CN 202210169552A CN 114435627 B CN114435627 B CN 114435627B
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- 238000000034 method Methods 0.000 title claims abstract description 17
- 238000005192 partition Methods 0.000 claims abstract description 30
- 238000003860 storage Methods 0.000 claims description 16
- 239000000446 fuel Substances 0.000 claims description 15
- 238000009434 installation Methods 0.000 claims description 10
- 230000001413 cellular effect Effects 0.000 claims 1
- 239000000463 material Substances 0.000 claims 1
- 125000006850 spacer group Chemical group 0.000 claims 1
- 238000009826 distribution Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 5
- 230000005540 biological transmission Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 4
- 230000009471 action Effects 0.000 description 3
- 239000002828 fuel tank Substances 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 2
- 108091092919 Minisatellite Proteins 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000012938 design process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
- 230000003068 static effect Effects 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
- B64G1/10—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
-
- 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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Automatic Assembly (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
The embodiment of the invention discloses a satellite structure and a satellite assembly method, comprising a bottom plate, side plates, a partition plate, a top plate and a central bearing cylinder; the bottom plate, the top plate and the plurality of side plates are mutually spliced to form a satellite cabin body, and the projection of the satellite cabin body on the plane of the bottom plate is regular polygon; the central bearing cylinder is arranged in the satellite cabin and is combined and fixed with the bottom plate; the side plates comprise a first side plate and a second side plate, the first side plate is positioned at one side of the second side plate far away from the bottom plate, and the partition plate is positioned between the first side plate and the second side plate to divide the satellite cabin body into a load cabin and an equipment cabin; the first side plate, the top plate, the partition plate and the central bearing cylinder are enclosed to form a load cabin; the second side plate, the bottom plate, the partition plate and the central bearing cylinder are enclosed to form an equipment cabin. Through adopting the central bearing cylinder of regular polygon structure and the satellite cabin body of regular polygon structure, adopt the mode of symmetric distribution to assemble curb plate and barrel plate, make whole star biography power more even, avoid the local overload.
Description
Technical Field
The invention relates to the field of space product structural design. And more particularly to a satellite structure and satellite assembly method.
Background
In recent years, various large constellations composed of small satellites are continuously proposed, the small satellites are widely applied, and meanwhile, more and more requirements are put on the structural design of the small satellites. In order to adapt to mass production of the small satellites, the structure manufacturing process of the small satellites needs to be relatively mature, and the cost is low; in order to realize more task functions as much as possible, the structural layout of the minisatellite needs to realize higher equipment density; in order to reduce the carrying cost as much as possible, the structural layout of the small satellite needs to improve the carrying space utilization rate; due to the increase of the equipment density and the increasingly high requirements of precision equipment on the whole satellite mechanical environment and the installation precision, the structural layout of the small satellite needs to ensure that the whole satellite structure has higher rigidity and dimensional stability.
Disclosure of Invention
In view of the above, it is an object of the present invention to provide a satellite structure that can ensure high rigidity and dimensional stability of the entire satellite structure.
Another object of the present invention is to provide a satellite assembling method of the above satellite structure.
In order to achieve the above purpose, the invention adopts the following technical scheme:
according to one aspect of the present invention, there is provided a satellite structure comprising:
The device comprises a bottom plate, side plates, a partition plate, a top plate and a central bearing cylinder;
The bottom plate, the top plate and the plurality of side plates are mutually spliced to form a satellite cabin body, and the projection of the satellite cabin body on the plane of the bottom plate is regular polygon;
The central bearing cylinder is configured to provide an installation space for the fuel storage tank, and is arranged in the satellite cabin and combined and fixed with the bottom plate;
The side plates comprise a first side plate and a second side plate, the first side plate is positioned on one side of the second side plate away from the bottom plate, and the partition plate is positioned between the first side plate and the second side plate to divide the satellite cabin into a load cabin and an equipment cabin;
The first side plate, the top plate, the partition plate and the wall of the central bearing cylinder are enclosed to form a load cabin for installing a load;
The second side plate, the bottom plate, the partition plate and the cylinder wall of the central bearing cylinder are enclosed to form an equipment cabin for installing equipment.
In addition, preferably, the central bearing cylinder is of a regular polygon structure and is formed by mutually splicing and enclosing a plurality of cylinder plates.
In addition, preferably, a tank bracket is arranged in the central bearing cylinder, and the fuel tank is arranged in the cylinder body through the tank bracket.
Further, preferably, the tank bracket includes a body portion and a coupling portion formed by extending downward an edge of the body portion;
The combination part is fixedly connected with the inner wall of the central bearing cylinder.
In addition, preferably, the satellite structure further comprises a connecting corner piece, and a pin hole is formed in the connecting corner piece;
the adjacent side plates are spliced and fixed through the connecting corner fitting.
In addition, the preferable scheme is that the side plates are connected and fixed with the bottom plate, the side plates are connected and fixed with the partition plate, the side plates are connected with the top plate, and the central bearing cylinder is connected and fixed with the bottom plate through connecting corner pieces.
In addition, preferably, the bottom plate comprises a through hole, and the axis of the through hole is coincident with the axis of the central bearing cylinder.
In addition, preferably, the bottom plate, the partition plate, the side plates, the top plate and the central bearing cylinder are made of honeycomb plates.
According to another aspect of the present invention, there is provided a satellite assembling method comprising the steps of:
s01, installing a fuel storage tank in the central bearing cylinder;
S02, respectively combining and fixing the central bearing cylinder with the bottom plate and the partition plate;
S03, installing a load cabin and load and equipment in the equipment cabin;
s04, mounting a side plate and a top plate.
The beneficial effects of the application are as follows:
Aiming at the technical problems in the prior art, the embodiment of the application provides a satellite structure and a satellite assembling method, wherein a central bearing cylinder of a regular polygon structure and a satellite cabin of the regular polygon structure are adopted, and side plates and cylinder plates are assembled in a symmetrical distribution mode, so that the whole satellite force transmission is more uniform, and local overload is avoided; the plane installation surface formed by the central bearing cylinder of the regular polygon structure and the satellite cabin body can effectively simplify the design, manufacturing and installation process of the mechanical interface of the equipment or the equipment bracket and the central bearing cylinder compared with the cylindrical installation surface; the central bearing cylinder with the regular polygon structure can also effectively solve the problem of difficult installation of a storage tank and the like caused by poor openness of the central bearing cylinder with a cylindrical or cylindrical and conical combined shape; in addition, the functional area in the satellite cabin body is divided into a fuel storage tank installation cabin in the center, a load cabin in the upper part and an equipment cabin in the lower part, and the solar wing or an expandable solar wing, other mechanisms, other single-machine equipment and the like can be installed on the outer side of the side plate, so that the whole satellite functional density is improved; the honeycomb plate corner piece splicing structure is applied in a large amount, so that the manufacturing cost of a small satellite structure part is reduced, the honeycomb plate structure is light in weight and high in rigidity, and the rigidity and the dimensional stability of the whole satellite structure can be effectively improved.
Drawings
The following describes the embodiments of the present invention in further detail with reference to the drawings.
Fig. 1 shows a schematic structural diagram of a satellite structure according to an embodiment of the present invention.
Fig. 2 is a schematic diagram illustrating an internal structure of a satellite structure according to an embodiment of the present invention.
Fig. 3 shows a schematic structural diagram of a central bearing cylinder according to an embodiment of the present invention.
Fig. 4 is a schematic diagram illustrating an internal structure of a central bearing cylinder according to an embodiment of the present invention.
Fig. 5 shows a schematic structural view of a tank bracket according to an embodiment of the present invention.
Fig. 6 shows a schematic structural view of a connection corner fitting according to an embodiment of the present invention.
Fig. 7 shows a schematic view of a base plate provided by an embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the present invention, the present invention will be further described with reference to preferred embodiments and the accompanying drawings. Like parts in the drawings are denoted by the same reference numerals. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and that this invention is not limited to the details given herein.
In the description of the present application, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of describing the present application and simplifying the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present application. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.
It is further noted that in the description of the present application, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
To overcome the defects of the prior art, an embodiment of the present invention provides a satellite structure, and in combination with fig. 1-6, the satellite structure includes a satellite cabin body and a central bearing cylinder, the satellite cabin body is formed by mutually splicing and enclosing a bottom plate 1, a side plate 2 and a top plate 3, the central bearing cylinder is located in the satellite cabin body, and is combined and fixed on the bottom plate 1, and the inner space of the central bearing cylinder is mainly used for installing a fuel storage tank to form a fuel storage tank installation cabin 40.
In this embodiment, the projection of the satellite cabin formed by enclosing the bottom plate 1, the top plate 3 and the plurality of side plates 2 on the plane of the bottom plate 1 is regular octagon, and correspondingly, the shapes of the bottom plate 1 and the top plate 3 are regular octagon. The satellite cabin is internally provided with a partition board 5, the partition board 5 divides the satellite cabin into a load cabin 100 and an equipment cabin 200, and the shape of the partition board 5 is regular octagon. In other embodiments, the satellite cabin may also have a regular hexagonal structure or other regular polygonal structures, and may specifically be designed according to the actual configuration layout of the satellite structure, which is not limited by the present invention.
In one embodiment, the side plates 2 include a first side plate 21 and a second side plate 22, the first side plate 21 and the second side plate 22 are respectively located on the upper side and the lower side of the partition 5, and the first side plate 21 is located on the side of the second side plate 22 away from the bottom plate 1. For this embodiment, the projection of the satellite cabin body on the plane where the bottom plate 1 is located is a regular octagon, and then the number of the first side plates 21 and the second side plates 22 is eight, the eight first side plates 21 are mutually spliced to form a first side plate assembly with a regular octagon structure, so as to form the side wall of the load cabin 100, the eight second side plates 22 are mutually spliced to form a second side plate assembly with a regular octagon structure, so as to form the side wall of the equipment cabin 200, and the first side plate assembly and the second side plate assembly are respectively combined and fixed on the upper side and the lower side of the partition plate 5, so as to form the side wall of the satellite cabin body. Preferably, in order to ensure that the force transmission of the whole satellite is more uniform, the first side plate 21 and the second side plate 22 are symmetrically distributed during assembly, so that the satellite structure is prevented from being partially loaded too much.
In one embodiment, the central part of the partition board 5 further comprises a hollow through which the central bearing cylinder passes, and the partition board 5 is sleeved on the central bearing cylinder. The partition board 5 divides the satellite cabin into an upper part and a lower part, specifically, an upper space formed by the first side board 21, the top board 3, the partition board 5 and the wall of the central bearing cylinder is mainly used for installing a load to form a load cabin 100 of the satellite cabin, and a lower space formed by the second side board 22, the bottom board 1, the partition board 5 and the wall of the central bearing cylinder is mainly used for installing various stand-alone devices to form a device cabin 200 of the satellite cabin.
In this embodiment, the outer side of the bottom plate 1 is a docking surface of a satellite and a carrier, and is connected with the carrier through a satellite-rocket adapter; the inner sides of the bottom plate 1 and the top plate 3 can be used as mounting surfaces of thrusters; the outer sides of the first side plate 21 and the second side plate 22 are mainly used for installing an antenna, a body-mounted solar wing or a folding solar wing. The whole star force transmission path is as follows: the various dynamic forces and static forces applied to the whole satellite are conducted to the satellite adaptor and further to the carrier through the top plate 1, the partition plate 2, the first side plate 21, the second side plate 22, the bottom plate 1 and the barrel plate 4 of the central force bearing barrel.
In a specific embodiment, the central bearing cylinder is fixedly combined on the bottom plate 1, and is in a regular polygon structure and formed by mutually splicing and enclosing a plurality of cylinder plates 4. The fuel storage tank is arranged in the central bearing cylinder, and the inner wall of the central bearing cylinder is provided with a mounting surface for the fuel storage tank. The base plate 1 and the barrel plate 4 are used as main components of a central bearing barrel, the barrel plate 4 is used for providing a mounting surface and a mechanical interface for satellite-borne equipment, equipment brackets, fuel storage tanks and the like, and after the barrel plate 4 is spliced into a barrel body with a regular polygon structure, a mounting space is provided for the fuel storage tanks; the bottom plate 1 is used for bearing the weight of the cylinder and other parts of the satellite, and simultaneously provides a mounting surface and a mechanical interface for part of satellite-borne equipment, equipment brackets and the like, and provides a mounting surface and a mechanical interface for the connection of the satellite and a carrier and the like.
In a specific embodiment, as shown in fig. 2, the interior of the central force-bearing cartridge is provided with a tank support 6, which tank support 6 serves to assist in the mounting of the fuel tank inside the cartridge.
As shown in fig. 5, the tank bracket 6 includes a body portion 61 and a joint portion 62 formed by extending downward from an edge of the body portion 61, where the body portion 61 is used for mounting and supporting the fuel tank, and the joint portion 61 is fixedly connected to an inner wall of the central force-bearing cylinder, specifically, the joint portion 62 is fixedly connected to the corresponding cylinder plate 4.
In a specific embodiment, the satellite structure further comprises a connection corner piece 7, and as shown in fig. 6, a pin hole 71 is arranged on the connection corner piece 7. The pin holes 71 are matched with positioning pins to realize the fixation between the parts of the satellite structure. Specifically, the two adjacent first side plates 21 are spliced and fixed through the connecting corner pieces 7 to form the side wall of the load cabin 100, and the two adjacent second side plates 22 are spliced and fixed through the connecting corner pieces 7 to form the side wall of the equipment cabin 200.
In this embodiment, the connecting corner pieces 7 are further used to achieve connection and fixation between the first side plate 21 and the top plate 3 and between the second side plate 22 and the bottom plate 1 and between the second side plate 22 and the bottom plate 5, and between the central bearing cylinder and the bottom plate. Further, the barrel plates 4 of the central bearing barrel are also connected and fixed through the connecting corner pieces 7. It should be noted that the connection between the components is not limited to be realized by the connection angle, and the present invention is not limited thereto.
In a specific embodiment, the central bearing cylinder and the satellite cabin are of regular octagon structures and are formed by mutually splicing and enclosing eight cylinder plates 4. In other embodiments, the shape of the regular polygon formed by the central bearing cylinder, the number of the cylinder plates 4 forming the central bearing cylinder, the included angle formed between the mounting surfaces on two sides of the connecting corner piece 7, and the like can be designed in detail according to the actual configuration layout situation of the satellite.
In a specific embodiment, as shown in fig. 7, the bottom plate 1 includes a through hole 10 therethrough, and an axis of the through hole 10 coincides with an axis of the central bearing cylinder. The through holes 10 are formed in the bottom plate 1, so that workers can conveniently observe the operation condition inside the cylinder in the assembly process, the fuel storage tank pipeline can also conveniently pass through, and the effect of reducing the weight of the whole central bearing cylinder can be achieved.
In this embodiment, the bottom plate 1, the side plate 2, the top plate 3, the cylinder plate 4 and the partition plate 5 are made of honeycomb plates, and the honeycomb plates are used as a low-cost mature sandwich shell structure, so that the cost can be effectively reduced, the manufacturing process is simplified, and the rigidity and the dimensional stability of the whole structure can be effectively improved due to the fact that the honeycomb plates are light in weight and high in rigidity. In the actual use process, the honeycomb panel can be locally reinforced by installing reinforcing embedded parts according to the condition that the side plates, the cylinder plates and the bottom plates are actually loaded.
The satellite structure provided by the embodiment adopts the central bearing cylinder of the regular polygon structure and the satellite cabin body of the regular polygon structure, and the side plates and the cylinder plates are assembled in a symmetrical distribution mode, so that the whole satellite force transmission is more uniform, and local overload is avoided; in addition, the functional area in the satellite cabin body is divided into a fuel storage tank installation cabin in the center, a load cabin in the upper part and an equipment cabin in the lower part, and a solar wing or an expandable solar wing, other mechanisms, other single-machine equipment and the like can be installed on the outer side of the side plate, so that the functional density of the whole satellite is improved; in addition, the manufacturing cost of the small satellite structure part is reduced through a large number of applications of the honeycomb plate corner piece splicing structure, and the rigidity and the dimensional stability of the whole satellite structure can be effectively improved due to the fact that the honeycomb plate structure is light in weight and high in rigidity.
Another embodiment of the present invention provides a satellite assembling method of the above satellite structure, including the following steps:
S01, combining part of the cylinder plates 4 through connecting corner pieces 7 to form a cylinder plate part combination, and mounting the storage tank bracket 6 on the cylinder plate part combination, wherein a fuel storage tank can be mounted;
S02, mounting the rest barrel plates 4 on the barrel plate part assembly through the connecting corner pieces 7 to form a regular polygon barrel plate assembly, namely a central bearing barrel; the central bearing cylinder is connected with the bottom plate 1 and the partition plate 5 through the connecting corner fitting 2;
S03, installing a load cabin, loads in the equipment cabin, equipment and the like;
S04, the first side plate 21, the second side plate 22, and the top plate 3 are continuously installed through the connection angle 7, and at this time, the installation of other satellite devices and the like can be completed.
It should be understood that the foregoing examples of the present invention are provided merely for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention, and that various other changes and modifications may be made therein by one skilled in the art without departing from the spirit and scope of the present invention as defined by the appended claims.
Claims (9)
1. The satellite structure is characterized by comprising a bottom plate, side plates, a partition plate, a top plate and a central bearing cylinder;
The bottom plate, the top plate and the plurality of side plates are mutually spliced to form a satellite cabin body, and the projection of the satellite cabin body on the plane of the bottom plate is regular polygon;
The central bearing cylinder is configured to provide an installation space for the fuel storage tank, and is arranged in the satellite cabin and combined and fixed with the bottom plate;
The side plates comprise a first side plate and a second side plate, the first side plate is positioned on one side of the second side plate away from the bottom plate, and the partition plate is positioned between the first side plate and the second side plate to divide the satellite cabin into a load cabin and an equipment cabin;
The first side plate, the top plate, the partition plate and the wall of the central bearing cylinder are enclosed to form a load cabin for installing a load;
The second side plate, the bottom plate, the partition plate and the cylinder wall of the central bearing cylinder are enclosed to form an equipment cabin for installing equipment.
2. The satellite structure of claim 1, wherein the central force-bearing barrel is of a regular polygon structure and is formed by mutually splicing and enclosing a plurality of barrel plates.
3. The satellite structure of claim 1, wherein the central force bearing cartridge is internally configured with a reservoir bracket through which the fuel reservoir is mounted within the cartridge body.
4. A satellite structure according to claim 3, wherein the tank holder comprises a body portion and a junction formed by the downward extension of an edge of the body portion;
The combination part is fixedly connected with the inner wall of the central bearing cylinder.
5. The satellite structure of claim 1, further comprising a connection angle having a pin hole formed therein;
the adjacent side plates are spliced and fixed through the connecting corner fitting.
6. The satellite structure of claim 5, wherein the side plates are connected and fixed to the base plate, the side plates are connected and fixed to the partition plate, the side plates are connected and fixed to the top plate, and the central bearing cylinder is connected and fixed to the base plate through connecting corner pieces.
7. The satellite structure of claim 1, wherein the base plate includes a through hole therethrough, the axis of the through hole being coincident with the axis of the central bearing cartridge.
8. The satellite structure of claim 1, wherein the bottom plate, the spacer, the side plates, the top plate, and the central bearing cylinder are all made of cellular board materials.
9. A method of satellite assembly of a satellite structure according to any one of claims 1 to 8, comprising the steps of:
s01, installing a fuel storage tank in the central bearing cylinder;
S02, respectively combining and fixing the central bearing cylinder with the bottom plate and the partition plate;
S03, installing a load cabin and load and equipment in the equipment cabin;
s04, mounting a side plate and a top plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210169552.XA CN114435627B (en) | 2022-02-23 | 2022-02-23 | Satellite structure and satellite assembly method |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210169552.XA CN114435627B (en) | 2022-02-23 | 2022-02-23 | Satellite structure and satellite assembly method |
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| CN114435627B true CN114435627B (en) | 2024-07-12 |
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| CN116513487B (en) * | 2023-07-05 | 2023-09-15 | 北京未来宇航空间科技研究院有限公司 | Multifunctional upper-level configuration and space carrier |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329542A (en) * | 2019-06-04 | 2019-10-15 | 上海卫星工程研究所 | Satellite configuration suitable for super large flexible satellite Collaborative Control |
| CN113911393A (en) * | 2021-09-29 | 2022-01-11 | 北京空间飞行器总体设计部 | Cone-prism transition type honeycomb interlayer bearing cylinder structure |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4872625A (en) * | 1984-07-30 | 1989-10-10 | Filley Charles C | Universal module assembly for space structures |
| CN104260903B (en) * | 2014-09-16 | 2016-05-11 | 上海卫星工程研究所 | Possesses the propelling module structure of independent high rail satellite platform function |
| CN106742063A (en) * | 2016-11-30 | 2017-05-31 | 上海卫星工程研究所 | Internal satellite configuration |
| US10689131B2 (en) * | 2018-07-06 | 2020-06-23 | Lockheed Martin Corporation | Sectioned self-mating modular satellite buses |
| US10538341B1 (en) * | 2018-07-06 | 2020-01-21 | Vector Launch Inc. | Self-mating modular satellite bus |
| CN110065653B (en) * | 2019-05-23 | 2020-08-04 | 上海微小卫星工程中心 | Main framework of small high-orbit satellite common platform |
| CN111422377B (en) * | 2020-03-10 | 2021-10-15 | 上海卫星工程研究所 | Structure suitable for satellite and facilitating assembly of double-layer flange type bearing cylinder and laminate |
| CN112977882A (en) * | 2021-03-12 | 2021-06-18 | 上海卫星工程研究所 | High orbit satellite platform structure with central force bearing cylinder type storage boxes tiled in parallel |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110329542A (en) * | 2019-06-04 | 2019-10-15 | 上海卫星工程研究所 | Satellite configuration suitable for super large flexible satellite Collaborative Control |
| CN113911393A (en) * | 2021-09-29 | 2022-01-11 | 北京空间飞行器总体设计部 | Cone-prism transition type honeycomb interlayer bearing cylinder structure |
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