CN114537709B - Load embedded type installation satellite platform configuration and assembly method thereof - Google Patents
Load embedded type installation satellite platform configuration and assembly method thereof Download PDFInfo
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- CN114537709B CN114537709B CN202210043024.XA CN202210043024A CN114537709B CN 114537709 B CN114537709 B CN 114537709B CN 202210043024 A CN202210043024 A CN 202210043024A CN 114537709 B CN114537709 B CN 114537709B
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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
- B64G1/66—Arrangements or adaptations of apparatus or instruments, not otherwise provided for
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Abstract
The application provides a load embedded installation satellite platform configuration and an assembly method thereof, wherein the satellite platform configuration comprises a propulsion cabin, a service upper cabin and lower cabin assembly, a bearing cylinder and a satellite platform load, wherein the propulsion cabin is arranged at the bottom of the service upper cabin and lower cabin assembly, and the bearing cylinder penetrates through the propulsion cabin and the service upper cabin and lower cabin assembly; the application adopts a load embedded type satellite platform configuration, does not change the inherent envelope and mature satellite configuration of the propulsion service cabin body, can realize the reliable installation of the load and the platform, meets the envelope requirement of a carrying fairing, and increases the area of the satellite platform to the ground.
Description
Technical Field
The application relates to the technical field of remote sensing satellite overall design and platform configuration, in particular to a load embedded installation satellite platform configuration and an assembly method thereof.
Background
In the field of aerospace technology, there are many mature satellite platforms, which are mainly used for service guarantee systems for developing earth artificial satellites, and provide services such as emission, on-orbit operation, working environment, energy supply, attitude control and the like for scientific detection instruments, remote sensing application loads and other space special equipment. The mature satellite platform can meet the application requirements of various forms, meets the requirements of different orbit conditions on satellites, particularly on remote sensing loads, can greatly reduce the satellite development cost and shorten the satellite development period, and effectively controls the satellite development risk. With the continuous development of national economy and scientific technology in China, the business requirements of space-based quantitative remote sensing are continuously upgraded, the detection means and modes are continuously enriched, various instruments and load combined observation technologies are mature, and the comprehensive performance requirements on satellite platforms are higher and higher.
Patent document CN108820263B discloses a hybrid nested layered stepped satellite platform configuration, which is a hybrid nested layered closed cabin stepped satellite platform configuration realized by overlapping regular and special-shaped cabin boards for propulsion service cabins and load cabins. A multi-device combined spark detector configuration as disclosed in patent document CN102717901B, comprising a small-sized inlet device, a surrounding device body, a large-sized high-resolution camera, a solar wing, a large-capacity storage tank, a high-pressure gas cylinder, a main engine, a large-caliber high-gain antenna, a small-capacity storage tank, a truss adapter, and a propeller body, wherein a corresponding forming method is also provided. As another example, patent document CN104309824a discloses an embedded compound eye camera loading satellite configuration, comprising: the compound eye camera comprises a configuration body, compound eye camera loads, star sensors and solar wings, wherein the configuration body is of a regular quadrilateral hexahedral configuration, the configuration body comprises a bottom plate, side plates, a top plate, a layer plate, a conical force-bearing barrel and an adapter ring, the top plate and the bottom plate are respectively connected to the upper end and the lower end of the side plate, the layer plate is arranged above the bottom plate and connected with the side plate, the conical force-bearing barrel is arranged between the bottom plate and the layer plate, the conical force-bearing barrel is connected with the layer plate, and the adapter ring is arranged on the other side of the layer plate and connected with the conical force-bearing barrel; the solar wing is connected with the side plate; the compound eye camera load part is arranged on the inner side of the top plate and connected with the adapter ring, and the star sensor is connected with the part of the compound eye camera load, which is positioned on the outer side of the top plate.
The satellite platform configurations in the above documents cannot solve the problem that the load mask exceeds the envelope of the fairing of the carrier rocket, so that the satellite ground utilization rate is reduced, and therefore, the load is required to be installed by utilizing the top area of the satellite platform.
In summary, there is a need to develop a load submersible mounting satellite platform configuration that addresses the deficiencies of the prior art.
Disclosure of Invention
In view of the drawbacks of the prior art, an object of the present application is to provide a load-embedded installation satellite platform configuration and method of assembling the same.
The application provides a load embedded installation satellite platform configuration, which comprises a propulsion cabin, a service upper cabin and lower cabin combination body, a bearing cylinder and a satellite platform load, wherein the propulsion cabin is connected with the service upper cabin and the service lower cabin combination body;
the propulsion cabin is arranged at the bottom of the service upper and lower cabin assembly, and the bearing cylinder penetrates through the propulsion cabin and the service upper and lower cabin assembly;
the satellite platform load is mounted on the side of the service upper and lower cabin assembly.
Preferably, the service upper and lower cabin assembly comprises a service lower cabin and a service upper cabin;
the propulsion cabin, the service lower cabin and the service upper cabin are sequentially arranged from bottom to top.
Preferably, the propulsion cabin comprises a propulsion cabin floor, the service lower cabin comprises a service lower cabin deck, and the service upper cabin comprises a service upper cabin ceiling and a service upper cabin deck;
the bearing cylinders are all arranged vertically and coaxially with the propulsion cabin bottom plate, the service lower cabin laminate, the service upper cabin top plate and the service upper cabin laminate;
the device comprises a propelling cabin bottom plate, a service lower cabin layer plate, a service upper cabin top plate, a service upper cabin layer plate, a first accommodating space, a second accommodating space and a third accommodating space, wherein symmetrically arranged baffle structures are respectively arranged in the first accommodating space, the second accommodating space and the third accommodating space along a bearing cylinder.
Preferably, the partition structures in the first accommodating space, the second accommodating space and the third accommodating space are all arranged in a groined structure.
Preferably, the upper and lower service cabin assembly further comprises a service cabin+Y side plate, a service cabin-Z side plate, a service cabin-Y side plate and a service cabin+Z side plate;
the service cabin +Y side plate is arranged on the front side of the lower service cabin and the upper service cabin, the service cabin-Y side plate is arranged on the rear side of the lower service cabin and the upper service cabin, the service cabin-Z side plate is arranged on the right side of the lower service cabin and the upper service cabin, the service cabin +Z side plate is arranged on the left side of the lower service cabin and the upper service cabin, the service cabin +Z side plate is respectively connected with the inner sides of the lower service cabin laminate, the service cabin +Y side plate, the upper service cabin top plate and the service cabin-Y side plate and is respectively provided with a gap with the left ends of the lower service cabin laminate, the service cabin +Y side plate, the upper service cabin top plate and the service cabin-Y side plate to jointly form a fourth accommodating space,
the satellite platform load is mounted on the service bay +Z side plate and is partially or fully arranged in the fourth accommodation space.
Preferably, a bearing cylinder mounting plate is arranged in the bearing cylinder, and the bearing cylinder mounting plate is used for mounting the storage box.
Preferably, a first support truss and a second support truss are respectively arranged on two sides of the satellite platform load;
the first support truss and the second support truss are both used for supporting the service upper cabin roof.
Preferably, the service upper deck plate has one or more load extension bits thereon for mounting loads.
Preferably, the dimensions of the propulsion pod, the lower service pod, the upper service pod, the first support truss and the second support truss are designed according to the envelope dimensions of the satellite platform load.
The application provides an assembly method of a load embedded installation satellite platform configuration, which comprises the following steps:
s1: installing a bearing cylinder mounting plate into the bearing cylinder;
s2: assembling a propulsion cabin bottom plate, a service lower cabin laminate, a service upper cabin top plate and the bearing cylinder into a satellite platform main body structure;
s3: installing a partition plate structure in the propulsion cabin, the service lower cabin and the service upper cabin so as to assemble the partition plate structure and the satellite platform main body structure into a satellite platform main bearing structure;
s4: assembling the propulsion cabin side plate, the service cabin side plate and the satellite platform main bearing structure into a satellite platform shell;
s5: the push-broom type imager is connected with a service cabin and a Z side plate on the satellite platform shell, and a first support truss and a second support truss are respectively arranged on two sides of the push-broom type imager and form a satellite platform configuration with the satellite platform shell.
Compared with the prior art, the application has the following beneficial effects:
1. the application adopts the load embedded type installation satellite platform configuration, does not change the inherent envelope and mature satellite configuration of the propulsion service cabin body, can realize the reliable installation of the load and the platform, meets the envelope requirement of the carrying fairing, and increases the area of the satellite platform to the ground.
2. The application adopts the load embedded type installation satellite platform configuration, does not change the main force transmission path of the satellite, effectively reduces the height of the satellite platform body and the height of the mass center of the satellite, improves the mechanical environment of the load installation surface and improves the fundamental frequency of the whole satellite.
3. The application adopts a load embedded type satellite platform installing structure, the service cabin supporting trusses are arranged on two sides of the load embedded in the satellite platform and used for supporting the service upper cabin top plate, improving the integral rigidity of the satellite and expanding the arrangement of other loads of the satellite platform.
4. The application adopts the load embedded installation satellite platform configuration, the forming method is simple and efficient, the assembly flow is clear, and the satellite development period can be effectively reduced.
5. The application adopts a load embedded installation satellite platform configuration, can adapt to different carrier rocket fairings and load mechanical sizes, and has high expansibility, adaptability and universality.
Drawings
Other features, objects and advantages of the present application will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic view of a satellite platform configuration in an embodiment of the application.
Fig. 2 is a schematic view of a propulsion pod configuration in an embodiment of the application.
Fig. 3 is a view showing a configuration of a service lower cabin in the embodiment of the present application.
Fig. 4 is a schematic view of a service upper cabin configuration in an embodiment of the application.
Fig. 5 is a schematic view of a service upper and lower cabin assembly configuration in an embodiment of the application.
Fig. 6 is a schematic diagram of an exploded structure of a satellite platform configuration in an embodiment of the application.
Fig. 7 is a schematic structural diagram of a satellite platform according to an embodiment of the present application when a lidar is mounted.
Fig. 8 is a schematic structural diagram of the force-bearing cartridge assembled with the mounting plate in the cartridge according to the embodiment of the present application.
Fig. 9 is a schematic diagram of a main structure of a satellite platform assembled by a propulsion cabin bottom plate, a service cabin lower cabin laminate, a service cabin upper cabin laminate, a service upper cabin top plate and a bearing cylinder in an embodiment of the application.
FIG. 10 is a schematic view of a main bearing structure of a satellite platform assembled by a propulsion compartment partition, a service compartment lower compartment partition, a service compartment upper compartment partition, and a main structure of the satellite platform according to an embodiment of the present application.
FIG. 11 is a schematic view of a satellite platform housing assembled from a side plate of a propulsion compartment and a side plate of a service compartment with a main load-carrying structure of the satellite platform according to an embodiment of the present application.
Fig. 12 is a schematic diagram of a push-broom imager connected to a satellite service cabin+z side plate, wherein a service cabin support truss and a satellite platform housing form the load embedded installation satellite platform configuration according to an embodiment of the present application.
The figure shows:
propulsion compartment 1 first service lower compartment + Z bulkhead 27
Lower service bay 2 second lower service bay + Z bulkhead 28
Service upper cabin 3 service upper cabin roof 30
Service upper cabin and lower cabin assembly 4 service upper cabin laminate 31
First service upper cabin+Y partition board 32 of bearing cylinder 5
Satellite platform load 6 second service upper cabin + Y spacer 33
Satellite platform body structure 7 first service upper pod-Z spacer 34
Second service upper cabin-Z partition 35 of satellite platform main bearing structure 8
First service upper cabin-Y partition 36 of satellite platform housing 9
Second service upper cabin-Y partition 37 of propulsion cabin floor 10
First propulsion cabin + Y partition 11 first service upper cabin + Z partition 38
Second propulsion cabin + Y partition 12 second upper service cabin + Z partition 39
First propulsion cabin-Z partition 13 service cabin + Y side plate 40
Second propulsion cabin-Z partition 14 service cabin-Z side plate 41
First propulsion cabin-Y partition 15 service cabin-Y side panels 42
Second propulsion cabin-Y partition 16 service cabin + Z side plate 43
First propulsion cabin + Z bulkhead 17 load carrier mounting plate 50
Second propulsion cabin + Z separator 18 tank 51
First support truss 60 of lower service deck laminate 20
First service lower cabin + Y bulkhead 21 second support truss 61
Second under-service cabin + Y bulkhead 22 active lidar 70
First service lower cabin-Z-partition 23+Y-side plate 101
Second under-service bay-Z bulkhead 24-Z side panel 102
First service lower cabin-Y partition 25-Y side plate 103
Second under-service bay-Y partition 26+Z side plate 104
Detailed Description
The present application will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present application, but are not intended to limit the application in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present application.
Example 1:
in order to meet the requirements of a carrier rocket fairing envelope and a load embedded installation satellite, the application provides a load embedded installation satellite platform configuration, which comprises a propulsion cabin 1, a service upper cabin assembly 4, a service lower cabin assembly 4, a bearing cylinder 5 and a satellite platform load 6.
For convenience of explanation, a layout coordinate system O-XYZ of satellites is established, and as shown in fig. 1, it is defined as follows:
origin of coordinates O: the center of the satellite-rocket separation surface;
and Z axis: the satellite points to the earth along the origin of coordinates in orbit;
x axis: pointing to the direction of the platform along the origin of coordinates, and keeping consistent with the flight direction of the satellite;
y axis: right handed with the X, Z shaft.
Specifically, as shown in fig. 1 and 9, the propulsion pod 1 is disposed at the bottom of the service upper and lower pod assembly 4, the bearing cylinder 5 penetrates through the propulsion pod 1 and the service upper and lower pod assembly 4, the satellite platform load 6 is mounted on the side of the service upper and lower pod assembly 4, and part or all of the satellite platform load 6 is embedded in the service upper and lower pod assembly 4.
Further, the upper and lower service cabin assembly 4 comprises a lower service cabin 2 and an upper service cabin 3, the lower service cabin 1, the lower service cabin 2 and the upper service cabin 3 are sequentially arranged from bottom to top, the lower service cabin 1 comprises a lower service cabin floor 10, the lower service cabin 2 comprises a lower service cabin floor 20, the upper service cabin 3 comprises an upper service cabin ceiling 30 and an upper service cabin floor 31, the bearing cylinders 5 are vertically and coaxially arranged with the lower service cabin floor 10, the lower service cabin floor 20, the upper service cabin ceiling 30 and the upper service cabin floor 31, circular through holes are formed in the centers of the lower service cabin floor 10, the lower service cabin floor 20 and the upper service cabin floor 31, and the bearing cylinders 5 penetrate through the circular through holes and are connected with the lower service cabin floor 10, the lower service cabin floor 20 and the upper service cabin floor 31.
First accommodation spaces, second accommodation spaces and third accommodation spaces are respectively formed between the propulsion cabin bottom plate 10 and the service lower cabin laminate 20, between the service lower cabin laminate 20 and the service upper cabin top plate 30 and between the service upper cabin top plate 30 and the service upper cabin laminate 31, and symmetrically arranged baffle structures are respectively arranged in the first accommodation spaces, the second accommodation spaces and the third accommodation spaces along the bearing cylinders 5.
The upper and lower service bay assembly 4 further comprises a service bay +y side plate 40, a service bay-Z side plate 41, a service bay-Y side plate 42 and a service bay +z side plate 43, wherein the service bay +y side plate 40 is mounted on the front side of the lower service bay 2 and the upper service bay 3, the service bay-Y side plate 42 is mounted on the rear side of the lower service bay 2 and the upper service bay 3, the service bay-Z side plate 41 is mounted on the right side of the lower service bay 2 and the upper service bay 3, the service bay +z side plate 43 is mounted on the left side of the lower service bay 2 and the upper service bay 3, the service bay +z side plate 43 is respectively connected with the inner sides of the lower service bay laminate 20, the service bay +y side plate 40, the upper service bay top plate 30 and the service bay-Y side plate 42 and has a gap with the left ends of the lower service bay laminate 20, the service bay +y side plate 40, the upper service bay top plate 30 and the service bay-Y side plate 42 to jointly form a fourth accommodation space,
the satellite platform load 6 is mounted on the service bay + Z side plate 43 and is partially or fully arranged in the fourth accommodation space.
As shown in fig. 8, a force-bearing cylinder mounting plate 50 is mounted in the force-bearing cylinder 5, and the force-bearing cylinder mounting plate 50 is used for mounting a storage tank 51.
As shown in fig. 6, a first support truss 60 and a second support truss 61 are respectively disposed on two sides of the satellite platform load 6, and the first support truss 60 and the second support truss 61 are both used for supporting the service upper cabin roof 30, so as to improve the overall rigidity of the satellite.
The satellite platform service upper deck plate 30 has one or more load extension bits thereon for mounting loads, which may provide other high mass and high volume load placement, extending satellite platform load layout capabilities and ground area, for example, as shown in fig. 7, with a high mass and high volume active lidar 70 mounted thereon.
In this embodiment, the satellite platform load 6 adopts a push-broom imager, so that the functions of cloud top temperature, cloud phase state, cloud optical thickness, cloud effective particle radius detection, true color cloud image imaging, cloud screening global cloud quantity observation and the like can be realized, and the cloud high-precision measurement in the global range can be realized by matching with other loads.
In practical application, the dimensions of the propulsion cabin 1, the service lower cabin 2, the service upper cabin 3, the first support truss 60 and the second support truss 61 can be reasonably designed according to the envelope dimensions of the satellite platform load 6, so as to meet the requirements of different application scenes.
The application also provides an assembly method of the load embedded installation satellite platform configuration, which comprises the following steps:
s1: mounting the force bearing cylinder mounting plate 50 into the force bearing cylinder 5;
s2: assembling a propulsion cabin bottom plate 10, a service lower cabin layer plate 20, a service upper cabin top plate 30 and the bearing cylinder 5 into a satellite platform main body structure 7;
s3: installing a partition plate structure in the propulsion cabin 1, the service lower cabin 2 and the service upper cabin 3 so as to assemble the partition plate structure and the satellite platform main body structure 7 into a satellite platform main bearing structure 8;
s4: assembling the propulsion cabin side plate, the service cabin side plate and the satellite platform main bearing structure 8 into a satellite platform shell 9;
s5: the push-broom imager is connected with a service cabin +Z side plate 43 on the satellite platform shell 9, and a first support truss 60 and a second support truss 61 are respectively installed on two sides of the push-broom imager and form the satellite platform configuration with the satellite platform shell 9.
Example 2:
this embodiment is a preferable example of embodiment 1.
In this embodiment, the partition structures in the first accommodating space, the second accommodating space, and the third accommodating space are all arranged in a groined structure.
In this embodiment, as shown in FIG. 2, the propulsion compartment 1 comprises a propulsion compartment bottom plate 10, a first propulsion compartment +Y partition plate 11, a second propulsion compartment +Y partition plate 12, a first propulsion compartment-Z partition plate 13, a second propulsion compartment-Z partition plate 14, a first propulsion compartment-Y partition plate 15, a second propulsion compartment-Y partition plate 16, a first propulsion compartment +Z partition plate 17, a second propulsion compartment +Z partition plate 18, +Y side plate 101, -Z side plate 102, -Y side plate 103 and +Z side plate 104, one end of the second propulsion compartment +Y partition plate 12 is connected with one end of the first propulsion compartment-Z partition plate 13, the other end of the second propulsion compartment +Y partition plate 12, the other end of the first propulsion compartment-Z partition plate 13 is respectively and vertically connected with +Y side plate 101, -Z side plate 102, one end of the first propulsion compartment-Z partition plate 14, the other end of the second propulsion compartment-Z partition plate 15, the other end of the first propulsion compartment-Y partition plate 15 is respectively connected with-Z side plate 102, -Y side plate 103, -Y side plate 16, the other end of the first propulsion compartment +Z partition plate 17 is respectively connected with one end of the first propulsion compartment +Z partition plate 101, +Z partition plate 18, the other end of the second propulsion compartment +Z partition plate 12 is vertically connected with +Z side plate 13, the other end of the first propulsion compartment +Z partition plate 12, +Z partition plate is respectively, the other end of the first propulsion compartment +Z partition plate is vertically connected with +Z partition plate 101, +Z partition plate 12, and one end of the other end of the first propulsion compartment-Z partition plate is vertically connected with +Z partition plate 12 is vertically connected with +Y side plate 101, +Z partition plate 12, the eight partition boards are arranged in a shape of a Chinese character 'jing', and jointly form a partition board structure in the propulsion cabin 1.
In this embodiment, as shown in fig. 3, the service lower cabin 2 includes a service lower cabin laminate 20, a first service lower cabin+y partition 21, a second service lower cabin+y partition 22, a first service lower cabin-Z partition 23, a second service lower cabin-Z partition 24, a first service lower cabin-Y partition 25, a second service lower cabin-Y partition 26, a first service lower cabin+z partition 27, and a second service lower cabin+z partition 28, wherein the eight partitions are arranged in a "well" shape to jointly form a partition structure in the service lower cabin 2.
In this embodiment, as shown in fig. 4, the upper service bay 3 includes an upper service bay top plate 30, an upper service bay laminate 31, a first upper service bay+y partition 32, a second upper service bay+y partition 33, a first upper service bay-Z partition 34, a second upper service bay-Z partition 35, a first upper service bay-Y partition 36, a second upper service bay-Y partition 37, a first upper service bay+z partition 38, and a second upper service bay+z partition 39, where eight partitions are arranged in a "well" shape to jointly form a partition structure in the upper service bay 3.
In this embodiment, as shown in fig. 5, the service upper and lower cabin assembly 4 is formed by butt-jointing the service upper cabin 3 and the service lower cabin 2, specifically, the side plates of the service upper cabin 3 and the service lower cabin 2 are used together, and are a service cabin+y side plate 40, a service cabin-Z side plate 41, a service cabin-Y side plate 42 and a service cabin+z side plate 43 respectively, wherein the service cabin+z side plate 43 is embedded into a platform by 250mm, so that the satellite platform load 6 can be embedded into the platform for installation, and the satellite platform load 6 is connected with the service cabin+z side plate 43, so that the size of a load light shield is prevented from exceeding the envelope of a carrier rocket fairing.
In the present embodiment, the satellite platform load 6 has a mass of 141Kg and a mechanical dimension of 1500 mm×1100 mm×900 mm.
As shown in fig. 9-12, the satellite platform configuration of the present application is formed as follows:
step 1, assembling a mounting plate in a bearing cylinder and the bearing cylinder;
step 2, assembling a propulsion cabin bottom plate, a service cabin lower cabin laminate, a service cabin upper cabin laminate and a bearing cylinder into a satellite platform main body structure 7;
step 3, on the basis of the step 1 and the step 2, a propulsion cabin partition board, a service cabin lower cabin partition board, a service cabin upper cabin partition board and a satellite platform main body structure 7 are assembled into a satellite platform main bearing structure 8;
step 4, on the basis of step 1, step 2 and step 3, assembling a satellite platform shell 9 by a propulsion cabin side plate, a service cabin side plate and a satellite platform main bearing structure 8;
and 5, on the basis of the steps 1, 2, 3 and 4, the push-broom imager is connected with a satellite service cabin plus Z side plate, and the service cabin support truss and the satellite platform shell 9 form the load embedded installation satellite platform.
In the description of the present application, it should be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present application.
The foregoing describes specific embodiments of the present application. It is to be understood that the application is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the application. The embodiments of the application and the features of the embodiments may be combined with each other arbitrarily without conflict.
Claims (7)
1. The load embedded installation satellite platform configuration is characterized by comprising a propulsion cabin (1), a service upper and lower cabin assembly (4), a bearing cylinder (5) and a satellite platform load (6);
the propulsion cabin (1) is arranged at the bottom of the service upper and lower cabin assembly (4), and the bearing cylinder (5) penetrates through the propulsion cabin (1) and the service upper and lower cabin assembly (4);
the satellite platform load (6) is arranged on the side surface of the service upper and lower cabin assembly (4);
the service upper and lower cabin assembly (4) comprises a service lower cabin (2) and a service upper cabin (3);
the propulsion cabin (1), the service lower cabin (2) and the service upper cabin (3) are sequentially arranged from bottom to top;
the propulsion cabin (1) comprises a propulsion cabin bottom plate (10), the service lower cabin (2) comprises a service lower cabin layer plate (20), and the service upper cabin (3) comprises a service upper cabin top plate (30) and a service upper cabin layer plate (31);
the bearing cylinders (5) are perpendicular to and coaxially arranged with the propulsion cabin bottom plate (10), the service lower cabin layer plate (20), the service upper cabin top plate (30) and the service upper cabin layer plate (31);
a first accommodating space, a second accommodating space and a third accommodating space are respectively formed between the propelling cabin bottom plate (10) and the service lower cabin layer plate (20), between the service lower cabin layer plate (20) and the service upper cabin top plate (30) and between the service upper cabin top plate (30) and the service upper cabin layer plate (31), and symmetrically arranged baffle structures are respectively arranged in the first accommodating space, the second accommodating space and the third accommodating space along the bearing cylinder (5);
the service upper and lower cabin assembly (4) further comprises a service cabin+Y side plate (40), a service cabin-Z side plate (41), a service cabin-Y side plate (42) and a service cabin+Z side plate (43);
the service cabin+Y side plate (40) is installed on the front side of the service lower cabin (2) and the service upper cabin (3), the service cabin-Y side plate (42) is installed on the rear side of the service lower cabin (2) and the service upper cabin (3), the service cabin-Z side plate (41) is installed on the right side of the service lower cabin (2) and the service upper cabin (3), the service cabin+Z side plate (43) is installed on the left side of the service lower cabin (2) and the service upper cabin (3), the service cabin+Z side plate (43) is respectively connected with the inner side of the service lower cabin layer plate (20), the service cabin+Y side plate (40), the service upper cabin top plate (30) and the service cabin-Y side plate (42) and is respectively in clearance with the service lower cabin layer plate (20), the service cabin+Y side plate (40), the service upper cabin top plate (30) and the left end of the service cabin-Y side plate (42) so as to jointly form a fourth accommodating space, and the satellite platform load (6) is installed on the service cabin+Z side plate (43) and is partially or fully arranged in the fourth accommodating space.
2. The load embedded installation satellite platform configuration of claim 1, wherein the spacer structures in the first, second, and third receiving spaces are all arranged in a herringbone structure.
3. The load embedded installation satellite platform configuration according to claim 1, wherein a force bearing cartridge mounting plate (50) is installed in the force bearing cartridge (5), and the force bearing cartridge mounting plate (50) is used for mounting a storage tank (51).
4. The load embedded installation satellite platform configuration according to claim 1, wherein a first support truss (60) and a second support truss (61) are respectively arranged on two sides of the satellite platform load (6);
the first support truss (60) and the second support truss (61) are used for supporting the service upper deck plate (30).
5. The load embedded installation satellite platform configuration of claim 4, wherein the service upper deck plate (30) has one or more load extension bits thereon for installing a load.
6. The load embedded installation satellite platform configuration according to claim 4, wherein the dimensions of the propulsion pod (1), the lower service pod (2), the upper service pod (3), the first support truss (60), the second support truss (61) are designed according to the envelope dimensions of the satellite platform load (6).
7. A method of assembling a load-embedded installation satellite platform configuration according to any one of claims 1 to 6, comprising the steps of:
s1: installing a bearing cylinder mounting plate (50) into the bearing cylinder (5);
s2: assembling a propulsion cabin bottom plate (10), a service lower cabin layer plate (20), a service upper cabin top plate (30) and the bearing cylinder (5) into a satellite platform main body structure (7);
s3: a partition plate structure is arranged in the propulsion cabin (1), the service lower cabin (2) and the service upper cabin (3) so as to assemble the partition plate structure and the satellite platform main body structure (7) into a satellite platform main bearing structure (8);
s4: assembling a propulsion cabin side plate, a service cabin side plate and a satellite platform main bearing structure (8) into a satellite platform shell (9);
s5: the push-broom imager is connected with a service cabin+Z side plate (43) arranged on a satellite platform shell (9), and a first support truss (60) and a second support truss (61) are respectively arranged on two sides of the push-broom imager and form a satellite platform configuration with the satellite platform shell (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210043024.XA CN114537709B (en) | 2022-01-14 | 2022-01-14 | Load embedded type installation satellite platform configuration and assembly method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210043024.XA CN114537709B (en) | 2022-01-14 | 2022-01-14 | Load embedded type installation satellite platform configuration and assembly method thereof |
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