CN114435627A - Satellite structure and satellite assembly method - Google Patents
Satellite structure and satellite assembly method Download PDFInfo
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- CN114435627A CN114435627A CN202210169552.XA CN202210169552A CN114435627A CN 114435627 A CN114435627 A CN 114435627A CN 202210169552 A CN202210169552 A CN 202210169552A CN 114435627 A CN114435627 A CN 114435627A
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- 238000000034 method Methods 0.000 title claims abstract description 18
- 238000005192 partition Methods 0.000 claims abstract description 31
- 238000003860 storage Methods 0.000 claims description 16
- 239000000446 fuel Substances 0.000 claims description 14
- 238000009434 installation Methods 0.000 claims description 8
- 239000002828 fuel tank Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 abstract description 5
- 238000009826 distribution Methods 0.000 abstract description 3
- 238000004519 manufacturing process Methods 0.000 description 6
- 230000008569 process Effects 0.000 description 6
- 238000010586 diagram Methods 0.000 description 5
- 230000009471 action Effects 0.000 description 3
- 230000007246 mechanism Effects 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000002775 capsule Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005304 joining Methods 0.000 description 1
- 210000001503 joint Anatomy 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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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
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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
- B64G1/40—Arrangements or adaptations of propulsion systems
- B64G1/402—Propellant tanks; Feeding propellants
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- Engineering & Computer Science (AREA)
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- 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, wherein the satellite structure 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 side plates are spliced with one another to enclose a satellite cabin, and the projection of the satellite cabin on the plane where the bottom plate is located is a regular polygon; the central bearing cylinder is arranged inside the satellite cabin body and is fixedly combined 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, far away from the bottom plate, of the second side plate, and the partition plate is positioned between the first side plate and the second side plate and divides the satellite cabin 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. The central bearing cylinder with the regular polygonal structure and the satellite cabin body with the regular polygonal structure are adopted, and the side plates and the cylinder plates are assembled in a symmetrical distribution mode, so that the force transmission of the whole satellite is more uniform, and the local overload is avoided.
Description
Technical Field
The invention relates to the field of space product structure design. And more particularly, to a satellite structure and a satellite assembly method.
Background
In recent years, various large constellations composed of small satellites are proposed, the application of the small satellites is more and more extensive, and meanwhile, more and more requirements are put on the structural design of the small satellites. In order to adapt to the 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 small satellite needs to realize higher equipment density; in order to reduce the carrying cost as much as possible, the structural layout of the small satellites needs to improve the utilization rate of carrying space; due to the increase of equipment density and the higher and higher requirements of precision equipment on the mechanical environment and the installation precision of the whole satellite, 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 problems, it is an object of the present invention to provide a satellite structure that can ensure high rigidity and dimensional stability of the whole satellite structure.
Another object of the present invention is to provide a method for assembling a satellite of the above satellite structure.
In order to achieve the purpose, the invention adopts the following technical scheme:
according to one aspect of the invention, there is provided a satellite structure comprising:
the bottom plate, the side plates, the partition plate, the top plate and the central bearing cylinder are arranged on the bottom plate;
the bottom plate, the top plate and the side plates are spliced with one another to form a satellite cabin body, and the projection of the satellite cabin body on the plane where the bottom plate is located is a regular polygon;
the central bearing cylinder is configured to provide an installation space for the fuel storage tank, and the central bearing cylinder is arranged inside the satellite cabin body and is fixedly combined 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, far away from the bottom plate, of the second side plate, and the partition plate is positioned between the first side plate and the second side plate and divides the satellite cabin into a load cabin and an equipment cabin;
the first side plate, the top plate, the partition plate and the cylinder wall of the central bearing cylinder are encircled to form a load cabin for mounting load;
and the second side plate, the bottom plate, the partition plate and the wall of the central bearing cylinder enclose an equipment cabin for installing equipment.
In addition, preferably, the central bearing cylinder is in a regular polygon structure and is formed by mutually splicing and enclosing a plurality of cylinder plates.
In addition, preferably, a tank holder is disposed inside the central force-bearing cylinder, and the fuel tank is mounted inside the cylinder body through the tank holder.
Further, it is preferable that the tank holder includes a body portion and a joining portion formed by an edge of the body portion extending downward;
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;
and adjacent side plates are spliced and fixed through the connecting corner piece.
In addition, preferably, the side plates and the bottom plate, the side plates and the partition plate, the side plates and the top plate and the central bearing cylinder and the bottom plate are fixedly connected through connecting angle 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, the preferable scheme is that the bottom plate, the partition plate, the side plates, the top plate and the central bearing cylinder are all made of honeycomb plate materials.
According to another aspect of the present invention, there is provided a satellite mounting method comprising the steps of:
s01, mounting the fuel storage box in the central bearing cylinder;
s02, combining and fixing the central bearing cylinder with the bottom plate and the partition plate respectively;
s03, installing loads and equipment in the load cabin and the equipment cabin;
and S04, mounting the side plates and the top plate.
The beneficial effect of this application is as follows:
aiming at the technical problems in the prior art, the embodiment of the application provides a satellite structure and a satellite matching method, wherein a central bearing cylinder with a regular polygonal structure and a satellite cabin body with the regular polygonal structure are adopted, and a side plate and a cylinder plate are assembled in a symmetrical distribution mode, so that the force transmission of the whole satellite is more uniform, and the local load is prevented from being overlarge; compared with a cylindrical surface mounting surface, a plane mounting surface formed by a central bearing cylinder of a regular polygon structure and a satellite cabin body can effectively simplify the design, manufacture and mounting process of equipment or an equipment support and a mechanical interface of the central bearing cylinder; the central bearing cylinder with the regular polygon structure can also effectively solve the problem of difficult installation of a storage box and the like caused by poor openness of the central bearing cylinder with the shape of a cylinder or a combination of the cylinder and a cone; in addition, the functional area in the satellite cabin body is divided into a fuel storage box installation cabin at the center, a load cabin at the upper part and an equipment cabin at the lower part, and the body-mounted solar wing or the deployable solar wing, other mechanisms, other single-machine equipment and the like can be installed outside the side plate, so that the function density of the whole satellite is improved; the application of the honeycomb plate corner piece splicing structure in a large quantity reduces the manufacturing cost of a small satellite structure part, the honeycomb plate structure is light in weight and high in rigidity, and the rigidity and the size stability of the whole satellite structure can be effectively improved.
Drawings
The following describes embodiments of the present invention in further detail with reference to the accompanying drawings.
Fig. 1 shows a schematic structural diagram of a satellite structure provided in 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 structural schematic diagram of the central force bearing cylinder provided by the embodiment of the invention.
Fig. 4 shows a schematic diagram of the internal structure of the central force bearing cylinder provided by the embodiment of the invention.
Fig. 5 shows a schematic structural view of a tank cradle provided by an embodiment of the present invention.
Fig. 6 shows a schematic structural diagram of a connecting corner fitting provided by an embodiment of the invention.
Fig. 7 shows a schematic view of a backplane provided by an embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the invention, the invention is further described below with reference to preferred embodiments and the accompanying drawings. Similar parts in the figures 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 is not to be taken as limiting the scope of the invention.
In the description of the present application, it should be noted that the terms "upper", "lower", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, which are only for convenience in describing the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Unless expressly stated or limited otherwise, the terms "mounted," "connected," and "connected" are intended to be inclusive and mean, for example, that they may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected 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 as appropriate.
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. Also, 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 an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
In order to overcome the defects in the prior art, an embodiment of the invention provides a satellite structure, which is shown in fig. 1-6 and comprises a satellite cabin body and a central bearing cylinder, wherein 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 positioned inside the satellite cabin body and is fixedly combined on the bottom plate 1, and the internal space of the central bearing cylinder is mainly used for mounting a fuel storage tank to form a fuel storage tank mounting cabin 40.
In this embodiment, a projection of a satellite cabin enclosed by a bottom plate 1, a top plate 3 and a plurality of side plates 2 on a plane where the bottom plate 1 is located is a regular octagon, and correspondingly, the shapes of the bottom plate 1 and the top plate 3 are also a regular octagon. The satellite cabin is internally provided with a partition plate 5, the partition plate 5 divides the satellite cabin into a load cabin 100 and an equipment cabin 200, and similarly, the partition plate 5 is also in the shape of a regular octagon. In other embodiments, the satellite capsule may also be a regular hexagon structure or other regular polygon structures, and may be specifically designed according to the actual configuration and layout conditions of the satellite structure, which is not limited in this 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 at the upper side and the lower side of the partition board 5, and the first side plate 21 is located at a side of the second side plate 22 away from the bottom plate 1. The quantity of first curb plate 21 and second curb plate 22 is the same, and for this embodiment, the satellite cabin body is in projection on the plane of bottom plate 1 is regular octagon, and then the quantity of first curb plate 21 and second curb plate 22 is eight, and the mutual concatenation of eight first curb plates 21 forms the first curb plate assembly of regular octagon structure, constitutes the lateral wall of load compartment 100, the mutual concatenation of eight second curb plates 22 form the second curb plate assembly of regular octagon structure, constitute the lateral wall of equipment compartment 200, first curb plate assembly and second curb plate assembly combine the upper and lower both sides that are fixed in baffle 5 respectively to constitute promptly the lateral 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 local overload of the satellite structure is avoided.
In one embodiment, the central portion of the partition plate 5 further includes a hollow for a central force bearing cylinder to pass through, and the partition plate 5 is sleeved on the central force bearing cylinder. The partition board 5 divides the satellite cabin into an upper part and a lower part, specifically, an upper space enclosed by the first side board 21, the top board 3, the partition board 5 and the cylinder wall of the central bearing cylinder is mainly used for mounting a load to form a load cabin 100 of the satellite cabin, and a lower space enclosed by the second side board 22, the bottom board 1, the partition board 5 and the cylinder wall of the central bearing cylinder is mainly used for mounting various single-machine equipment to form an equipment cabin 200 of the satellite cabin.
In the embodiment, the outer side of the bottom plate 1 is a butt joint surface between 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 mounting an antenna, a body-mounted solar wing or a folding solar wing. The whole star force transmission path is as follows: the whole star is subjected to various dynamic forces and static forces, and the dynamic forces and the static forces are transmitted to the star-arrow adapter through the top plate 1 and the partition plate 2 along the first side plate 21, the second side plate 22, the bottom plate 1 and the barrel plate 4 of the central bearing barrel, and then transmitted to the carrier.
In a specific embodiment, the central bearing cylinder is fixedly combined on the bottom plate 1, is in a regular polygon structure, and is 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 mounting the fuel storage tank. The bottom plate 1 and the barrel plates 4 are used as main components of a central bearing barrel, the barrel plates 4 are used for providing mounting surfaces and mechanical interfaces for satellite-borne equipment, equipment supports, a fuel storage box and the like, and the barrel plates 4 are spliced into a barrel body with a regular polygonal structure and then provide mounting space for the fuel storage box; 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 parts of satellite-borne equipment, equipment brackets and the like, and provides a mounting surface and a mechanical interface for connection of the satellite and a carrier and the like.
In a particular embodiment, as shown in fig. 2, the interior of the central weighted cylinder is configured with a tank holder 6, the tank holder 6 being used to assist in the installation of the fuel tank inside the cylinder.
As shown in fig. 5, the tank holder 6 includes a body 61 and a connecting portion 62 formed by extending the edge of the body 61 downward, the body 61 is used for mounting and supporting the fuel tank, the connecting portion 61 is fixedly connected to the inner wall of the central force-bearing cylinder, and specifically, the connecting portion 62 is fixedly connected to the corresponding cylinder plate 4.
In a specific embodiment, the satellite structure further comprises a connecting corner piece 7, and as shown in fig. 6, a pin hole 71 is formed on the connecting corner piece 7. The pin holes 71 are matched with the positioning pins to realize the fixed connection among all parts of the satellite structure. Specifically, the side walls of the load compartment 100 are formed by splicing and fixing two adjacent first side plates 21 through connecting angle pieces 7, and the side walls of the equipment compartment 200 are formed by splicing and fixing two adjacent second side plates 22 through connecting angle pieces 7.
In this embodiment, the connecting angle 7 is further used for realizing the connection and fixation between the first side plate 21 and the top plate 3 and the partition plate 5, the connection and fixation between the second side plate 22 and the bottom plate 1 and the partition plate 5, and the fixation between the central force bearing cylinder and the bottom plate. Further, the cylinder plates 4 of the central bearing cylinder are also connected and fixed through a connecting angle piece 7. It should be noted that, the connection relationship between the components is not limited to be realized by connecting the corner fittings, and the invention is not limited thereto.
In a specific embodiment, the central bearing cylinder and the satellite cabin body are regular octagonal structures and are formed by splicing and enclosing eight cylinder plates 4. In other embodiments, the shape of the regular polygon formed by the central force bearing cylinder, the number of the cylinder plates 4 forming the central force bearing cylinder, the included angle formed between the mounting surfaces at two sides of the connecting angle piece 7, and the like can be designed in detail according to the actual configuration layout of the satellite.
In a specific embodiment, as shown in fig. 7, the bottom plate 1 comprises a through hole 10 therethrough, and the axis of the through hole 10 is coincident with the axis of the central bearing cylinder. The through hole 10 is formed in the bottom plate 1, so that a worker can conveniently observe the operation condition inside the cylinder body in the assembling process, the fuel storage tank pipeline can conveniently pass through the through hole, and the effect of integrally reducing the weight of the central bearing cylinder can be achieved.
In this embodiment, bottom plate 1, curb plate 2, roof 3, bobbin board 4 and baffle 5 all adopt the honeycomb panel material, and the honeycomb panel can effectively reduce cost through adopting the honeycomb panel as a low-cost ripe sandwich shell structure, simplifies manufacturing process through adopting the honeycomb panel, and because honeycomb panel structure light in weight rigidity is higher, can effectively improve whole star structural rigidity and dimensional stability. In the actual use process, according to the condition that the side plates, the barrel plates and the bottom plate actually bear loads, the honeycomb plate can be locally reinforced by installing the reinforcing embedded parts in the honeycomb plate.
The satellite structure provided by the embodiment adopts the central bearing cylinder with the regular polygon structure and the satellite cabin body with the regular polygon structure, and the side plates and the cylinder plates are assembled in a symmetrical distribution mode, so that the force transmission of the whole satellite is more uniform, and the local load is avoided being overlarge; in addition, the functional area inside the satellite cabin body is divided into a fuel storage tank installation cabin at the center, a load cabin at the upper part and an equipment cabin at the lower part, and the body-mounted solar wing or the deployable solar wing, other mechanisms, other single-machine equipment and the like can be installed outside 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 by applying a large number of honeycomb plate corner piece splicing structures, and the structural rigidity and the dimensional stability of the whole satellite can be effectively improved due to the light weight and high rigidity of the honeycomb plate structure.
Another embodiment of the present invention provides a satellite assembling method of the above satellite structure, including the steps of:
s01, combining the partial cylinder plates 4 through the connecting angle piece 7 to form a cylinder plate partial assembly, and mounting the storage tank bracket 6 on the cylinder plate partial assembly, at this time, mounting the fuel storage tank;
s02, mounting the residual barrel plates 4 on the barrel plate part assembly through the connecting angle piece 7 to form a regular polygon barrel plate assembly, namely a central bearing barrel; connecting the central bearing cylinder with the bottom plate 1 and the partition plate 5 through a connecting corner fitting 2;
s03, installing loads, equipment and the like in the load cabin and the equipment cabin;
and S04, continuing to install the first side plate 21, the second side plate 22 and the top plate 3 through the connecting angle piece 7, and at this time, completing installation of other satellite equipment and the like.
It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.
Claims (9)
1. A satellite structure is characterized by comprising a bottom plate, side plates, partition plates, a top plate and a central bearing cylinder;
the bottom plate, the top plate and the side plates are spliced with one another to form a satellite cabin body, and the projection of the satellite cabin body on the plane where the bottom plate is located is a regular polygon;
the central bearing cylinder is configured to provide an installation space for the fuel storage tank, and the central bearing cylinder is arranged inside the satellite cabin body and is fixedly combined 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, far away from the bottom plate, of the second side plate, and the partition plate is positioned between the first side plate and the second side plate and divides the satellite cabin into a load cabin and an equipment cabin;
the first side plate, the top plate, the partition plate and the cylinder wall of the central bearing cylinder are encircled to form a load cabin for mounting load;
and the second side plate, the bottom plate, the partition plate and the wall of the central bearing cylinder enclose an equipment cabin for installing equipment.
2. The satellite structure according to claim 1, wherein the central force bearing cylinder is a regular polygon structure and is formed by mutually splicing and enclosing a plurality of cylinder plates.
3. The satellite structure according to claim 1, wherein a tank holder is provided inside the central bearing cylinder, and the fuel tank is mounted inside the cylinder body through the tank holder.
4. The satellite structure according to claim 3, wherein the tank cradle comprises a body portion and a junction portion formed by an edge of the body portion extending downwardly;
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 connecting corner piece having a pin hole formed therein;
and adjacent side plates are spliced and fixed through the connecting corner piece.
6. The satellite structure according to claim 5, wherein the side plates and the bottom plate, the side plates and the partition plate, the side plates and the top plate, and the central bearing cylinder and the bottom plate are fixedly connected through connecting angle pieces.
7. The satellite structure according to claim 1, wherein the bottom plate includes a through hole therethrough, and an axis of the through hole coincides with an axis of the central bearing cylinder.
8. The satellite structure of claim 1, wherein the bottom plate, the partition plate, the side plate, the top plate and the central bearing cylinder are made of honeycomb plate materials.
9. A method of assembling a satellite of the satellite architecture of any one of claims 1-8, comprising the steps of:
s01, mounting the fuel storage box in the central bearing cylinder;
s02, combining and fixing the central bearing cylinder with the bottom plate and the partition plate respectively;
s03, installing loads and equipment in the load cabin and the equipment cabin;
and S04, mounting the side plates and the top plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
|---|---|---|---|
| CN202210169552.XA CN114435627B (en) | 2022-02-23 | 2022-02-23 | Satellite structure and satellite assembly method |
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| CN114435627A true CN114435627A (en) | 2022-05-06 |
| CN114435627B CN114435627B (en) | 2024-07-12 |
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| RU2778178C1 (en) * | 2022-05-24 | 2022-08-15 | Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | Spacecraft payload module |
| CN116513487A (en) * | 2023-07-05 | 2023-08-01 | 北京未来宇航空间科技研究院有限公司 | Multifunctional upper-level configuration and space carrier |
| 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 |
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