CN115743603A - Satellite structure with large antenna and platform integrated - Google Patents
Satellite structure with large antenna and platform integrated Download PDFInfo
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- CN115743603A CN115743603A CN202211354867.8A CN202211354867A CN115743603A CN 115743603 A CN115743603 A CN 115743603A CN 202211354867 A CN202211354867 A CN 202211354867A CN 115743603 A CN115743603 A CN 115743603A
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Abstract
The invention discloses a satellite structure integrating a large antenna and a platform, which comprises a satellite platform and the large antenna; the satellite platform adopts a modular structure and comprises a propelling cabin, a load cabin and an upper cabin which are fixedly connected from bottom to top along the vertical direction; a longitudinal installation groove which penetrates through the propulsion cabin, the load cabin and the upper cabin in the vertical direction is formed in one side of the propulsion cabin, the load cabin and the upper cabin, and installation interfaces for installing large antenna hoops are arranged in the propulsion cabin, the load cabin and the upper cabin; the large antenna is fixedly arranged in the antenna mounting groove. The satellite structure adopts a slot type interface form of upper, middle and lower distributed supports, a satellite platform and an antenna force transmission path are designed in a unified mode, the structural efficiency is effectively improved, and the dynamic response of the annular antenna is reduced.
Description
Technical Field
The invention relates to the technical field of spacecraft structures, in particular to a satellite structure integrating a large antenna and a platform.
Background
The satellite-borne large-scale annular antenna has large transverse and longitudinal sizes in a folded state, the longitudinal size of the satellite-borne large-scale annular antenna is generally equivalent to that of a satellite platform and even exceeds the size of a satellite body, and along with the increase of the aperture of the antenna, the difficulty of the design of an installation interface and the mechanical response control of the antenna is increased.
Aiming at a large-scale annular antenna, in order to improve the bearing efficiency of a satellite structure, an antenna force transmission path and a main force transmission path of a satellite platform structure need to be designed in a unified mode, the problems of antenna installation, bearing, unfolding path, response control and the like are considered, and a good transmitting section mechanical environment is provided for the antenna.
Disclosure of Invention
In view of the above, the invention provides a satellite structure with a large antenna integrated with a platform, which adopts a slot type interface form supported in an upper, middle and lower distributed manner, and designs a satellite platform and an antenna force transmission path in a unified manner, thereby effectively improving the structural efficiency and reducing the dynamic response of a loop antenna.
The invention adopts the following specific technical scheme:
a satellite structure integrating a large antenna and a platform comprises a satellite platform and the large antenna;
the satellite platform adopts a modular structure and comprises a propelling cabin, a load cabin and an upper cabin which are fixedly connected from bottom to top along the vertical direction;
a longitudinal installation groove which penetrates through the propulsion cabin, the load cabin and the upper cabin in the vertical direction is formed in one side of the propulsion cabin, the load cabin and the upper cabin, and installation interfaces for installing a large antenna hoop are arranged in the propulsion cabin, the load cabin and the upper cabin;
the large antenna is fixedly arranged in the antenna mounting groove.
Furthermore, the propulsion cabin comprises a bearing cylinder and a bottom cabin surrounding the bottom end of the bearing cylinder;
the bottom cabin comprises a bottom cabin top plate, a bottom cabin bottom plate, two bottom cabin partition plates and bottom cabin side plates which are in one-to-one correspondence with the bottom cabin partition plates; the bottom cabin top plate, the bottom cabin bottom plate and the bottom cabin partition plate are fixedly connected with the bearing cylinder; the bottom cabin side plates and the bottom cabin partition plates are fixedly connected between the bottom cabin top plate and the bottom cabin bottom plate; the two bottom cabin partition plates are oppositely arranged; the bottom cabin side plates are fixedly connected to one ends of the corresponding bottom cabin partition plates, which are far away from the bearing cylinder;
the load cabin is sleeved on the outer side of the bearing cylinder and comprises a load cabin top plate, two load cabin partition plates and load cabin side plates in one-to-one correspondence with the load cabin partition plates; the load cabin top plate is fixedly connected to the top end of the bearing cylinder; the two load compartment partition plates and the load compartment side plates are fixedly connected between the load compartment top plate and the bottom compartment top plate; the two load cabin partition plates are oppositely arranged and fixedly connected between the bearing cylinder and the corresponding load cabin side plate;
the upper cabin comprises an upper cabin top plate, an upper cabin middle plate, two upper cabin partition plates arranged oppositely and a plurality of upper cabin side plates; the upper cabin top plate, the upper cabin middle plate and the load cabin top plate are arranged in parallel, and the upper cabin middle plate is positioned between the upper cabin top plate and the load cabin top plate; a plurality of upper cabin side plates are fixedly connected between the load cabin top plate and the upper cabin middle plate and between the load cabin top plate and the upper cabin top plate; the upper cabin partition plate is fixedly connected between the load cabin top plate and the upper cabin middle plate, and two sides of the upper cabin partition plate are fixedly connected with the upper cabin side plates;
the bottom cabin top plate, the bottom cabin bottom plate, the load cabin top plate and the upper cabin middle plate are all provided with arc-shaped openings for mounting the large-scale antenna;
the antenna mounting groove is formed by surrounding the bottom cabin top plate, the bottom cabin bottom plate, the two bottom cabin partition plates, the force bearing cylinder, the load cabin top plate, the two load cabin partition plates, the upper cabin middle plate and the two upper cabin partition plates.
Furthermore, four upper cabin connecting corner boxes are connected between one upper cabin partition plate and the corresponding upper cabin side plate, and mounting interfaces for mounting the upper hoops of the large-scale antenna are arranged on the upper cabin side plates and the upper cabin connecting corner boxes;
a middle embracing ring mounting upper support and a middle embracing ring mounting lower support are fixedly connected to the outer side wall of the bearing cylinder between the two load cabin clapboards; the load compartment side plate, the middle surrounding ring mounting upper support and the middle surrounding ring mounting lower support are provided with mounting interfaces for mounting a middle surrounding ring of a large-scale antenna;
a lower embracing ring support is fixedly connected to the outer side wall of the bearing cylinder between the two bottom cabin clapboards; the bottom cabin side plate and the lower embracing ring support are provided with installation interfaces for installing a lower embracing ring of the large antenna.
Furthermore, reinforcing corner boxes for improving the installation rigidity of the installation interface are arranged between the bottom cabin side plate and the bottom cabin partition plate, between the bottom cabin partition plate and the bottom cabin bottom plate and between the bottom cabin side plate and the bottom cabin bottom plate;
a horizontal upper triangular support and a horizontal lower triangular support are connected between each load cabin partition and the bearing cylinder;
one of the horizontal upper triangular supports is fixedly connected with the middle embracing ring mounting upper support, and the other horizontal lower triangular support is fixedly connected with the middle embracing ring mounting lower support;
and a bearing area of each mounting interface is reinforced by adopting an externally-attached carbon fiber panel and an encrypted honeycomb core.
Furthermore, the propulsion cabin partition plate, the load cabin partition plate and the upper cabin partition plate are all made of carbon fiber skin sandwich structural plates;
the propulsion cabin partition plate and the load cabin partition plate are connected with the bearing cylinder through corner strips;
the upper cabin clapboard is connected with the load cabin top plate through a corner strip.
Has the beneficial effects that:
1. according to the satellite structure, longitudinal mounting grooves which penetrate through in the vertical direction are formed in one side of a propulsion cabin, a load cabin and an upper cabin which form a satellite platform, and mounting interfaces for mounting large-scale antenna hoops are arranged in the propulsion cabin, the load cabin and the upper cabin; the large antenna is fixedly arranged in the antenna mounting groove; therefore, the longitudinal installation space provided for the large antenna by adopting the structure is greatly increased, the installation and load transfer requirements of the large antenna can be met under the constraint conditions of configuration size and satellite structure weight index, and a good dynamic environment is provided for the large antenna; a groove-shaped interface form of upper, middle and lower distributed supports is adopted, a satellite platform and an antenna force transmission path are designed in a unified mode, the structural efficiency is effectively improved, and the dynamic response of the loop antenna is reduced.
2. According to the satellite structure, the arc-shaped openings for mounting the large-scale antenna are formed in the top plate of the bottom cabin, the bottom plate of the bottom cabin, the top plate of the load cabin and the middle plate of the upper cabin, so that a through longitudinal space is provided for mounting the large-scale loop antenna, and meanwhile, the transverse mounting rigidity of the large-scale loop antenna is improved.
3. According to the satellite structure, the reinforcing angle boxes are respectively arranged between the bottom cabin side plate and the bottom cabin partition plate, between the bottom cabin partition plate and the bottom cabin bottom plate and between the bottom cabin side plate and the bottom cabin bottom plate, so that the mounting rigidity of the large-scale annular antenna can be effectively improved through the reinforcing angle boxes, and the problems of weakening influence of a large opening on the mounting rigidity and insufficient rigidity caused by mounting of a cantilever of an expansion motor are solved; a horizontal upper triangular support and a horizontal lower triangular support are connected between each load cabin partition and the load bearing cylinder, the horizontal upper triangular support is fixedly connected with the middle embracing ring mounting upper support, and the horizontal lower triangular support is fixedly connected with the middle embracing ring mounting lower support, so that the mounting rigidity of the middle embracing ring of the large-scale annular antenna is improved through the horizontal upper triangular support and the horizontal lower triangular support.
Drawings
FIG. 1 is a schematic diagram of a satellite platform in a satellite structure according to the present invention;
FIG. 2 is a schematic view of the propulsion pod of FIG. 1;
FIG. 3 is a schematic view of the structure of the load compartment of FIG. 1;
fig. 4 is a schematic structural view of the upper deck of fig. 1.
The device comprises a 1-bottom cabin and a Y partition plate, a 2-bottom cabin-Y partition plate, a 3-load cabin and a Y partition plate, a 4-load cabin-Y partition plate, a 5-upper cabin and a Y partition plate, a 6-upper cabin-Y partition plate, a 7-bottom cabin bottom plate, an 8-bottom cabin top plate, a 9-load cabin top plate, a 10-upper cabin middle plate, an 11-upper cabin first side plate, a 13-upper cabin second side plate, a 15-upper cabin third side plate, a 16-upper cabin fourth side plate, a 17-upper cabin outer partition plate, an 18-upper cabin top plate, a 19-upper cabin connecting corner box I, a 20-upper cabin connecting corner box II, a 21-upper cabin connecting corner box III, a 22-upper cabin connecting corner box IV, a 23-load cabin-Y side plate, a 24-load cabin and a Y side plate, an upper support seat arranged in a 25-middle holding ring, a lower support arranged in a 26-middle holding ring, a 27-Y side horizontal upper triangular support seat, a 28-Y side horizontal lower triangular support seat, a 29-bearing side cylinder, a 30-Y side upper triangular support seat, a Y side support seat arranged in a Y ring and a reinforcing triangular support seat arranged in a reinforcing triangle, and a reinforcing triangle.
Detailed Description
The invention is described in detail below by way of example with reference to the accompanying drawings.
The embodiment of the invention provides a large-scale antenna and platform integrated satellite structure, which comprises a satellite platform and a large-scale antenna; as shown in the structures of fig. 1, 2, 3 and 4, the satellite platform adopts a modular structure, and comprises a propulsion cabin, a load cabin and an upper cabin which are fixedly connected along the vertical direction from bottom to top; a longitudinal mounting groove which penetrates through the propulsion cabin, the load cabin and the upper cabin in the vertical direction is formed in one side of the propulsion cabin, the load cabin and the upper cabin, and mounting interfaces for mounting the large antenna hoops are arranged in the propulsion cabin, the load cabin and the upper cabin; the large antenna is fixedly arranged in the antenna mounting groove. In this embodiment, the large antenna is described by taking a large loop antenna as an example.
The satellite structure is provided with longitudinal mounting grooves which are penetrated in the vertical direction on one side of a propulsion cabin, a load cabin and an upper cabin which form a satellite platform, and mounting interfaces for mounting a large antenna hoop are arranged on the propulsion cabin, the load cabin and the upper cabin; the large antenna is fixedly arranged in the antenna mounting groove; therefore, the longitudinal installation space provided for the large antenna by adopting the structure is greatly increased, the installation and load transfer requirements of the large antenna can be met under the constraint conditions of configuration size and satellite structure weight index, and a good dynamic environment is provided for the large antenna; a groove-shaped interface form of upper, middle and lower distributed supports is adopted, a satellite platform and an antenna force transmission path are designed in a unified mode, the structural efficiency is effectively improved, and the dynamic response of the loop antenna is reduced.
In one specific embodiment, as shown in fig. 1, the propulsion compartment comprises a force-bearing cylinder 29 and a bottom compartment surrounding the bottom end of the force-bearing cylinder 29; the bearing cylinder 29 is a circular structure, and the bottom cabin is positioned at the bottom end of the bearing cylinder 29;
the bottom cabin comprises a bottom cabin top plate 8, a bottom cabin bottom plate 7, two bottom cabin partition plates and bottom cabin side plates which are in one-to-one correspondence with the bottom cabin partition plates; the bottom cabin top plate 8, the bottom cabin bottom plate 7 and the bottom cabin partition plate are fixedly connected with a bearing cylinder 29; the bottom cabin side plates and the bottom cabin partition plates are fixedly connected between the bottom cabin top plate 8 and the bottom cabin bottom plate 7; the two bottom cabin partition plates are oppositely arranged; the bottom cabin side plates are fixedly connected to one ends of the corresponding bottom cabin partition plates, which are far away from the bearing cylinder 29; as shown in fig. 1 and fig. 2, referring to the coordinate system in fig. 1, the two bottom cabin partitions are a bottom cabin + Y partition 1 and a bottom cabin-Y partition 2, respectively, the bottom cabin + Y partition 1 is located on the + Y side of the bottom cabin, and the bottom cabin-Y partition 2 is located on the-Y side of the bottom cabin; the bottom cabin side plates are respectively a bottom cabin-Y side plate 32 correspondingly connected with the bottom cabin-Y partition plate 2 and a bottom cabin + Y side plate 33 correspondingly connected with the bottom cabin + Y partition plate 1; the inner end of the bottom cabin + Y partition plate 1 is fixedly connected with the force bearing cylinder 29, the outer end of the bottom cabin + Y partition plate is fixedly connected with the bottom cabin + Y side plate 33, the bottom end of the bottom cabin + Y partition plate is fixedly connected with the bottom cabin bottom plate 7, and the top end of the bottom cabin + Y partition plate is fixedly connected with the bottom cabin top plate 8; the inner end of the bottom cabin-Y clapboard 2 is fixedly connected with the force bearing cylinder 29, the outer end is fixedly connected with the bottom cabin-Y side plate 32, the bottom end is fixedly connected with the bottom cabin bottom plate 7, and the top end is fixedly connected with the bottom cabin top plate 8; the bottom part of an antenna mounting groove is formed among the bearing cylinder 29, the bottom cabin + Y partition plate 1, the bottom cabin-Y partition plate 2, the bottom cabin top plate 8 and the bottom cabin bottom plate 7;
as shown in fig. 1 and 3, the load cabin is sleeved outside the bearing cylinder 29 and includes a load cabin top plate 9, two load cabin partition plates, and load cabin side plates corresponding to the load cabin partition plates one by one; the load cabin top plate 9 is fixedly connected to the top end of the bearing cylinder 29; the two load cabin partition plates and the load cabin side plates are fixedly connected between the load cabin top plate 9 and the bottom cabin top plate 8; the two load cabin partition plates are oppositely arranged and fixedly connected between the bearing cylinder 29 and the corresponding load cabin side plate; the two load compartment partition plates are respectively a load compartment + Y partition plate 3 and a load compartment-Y partition plate 4, the load compartment + Y partition plate 3 is positioned on the + Y side of the load compartment, and the load compartment-Y partition plate 4 is positioned on the-Y side of the load compartment; the load compartment side plates comprise a load compartment-Y side plate 23 and a load compartment + Y side plate 24; the inner end of the load cabin + Y partition plate 3 is fixedly connected with the bearing cylinder 29, the outer end of the load cabin + Y partition plate is fixedly connected with one end of the load cabin + Y side plate 24, the top end of the load cabin + Y partition plate is fixedly connected with the load cabin top plate 9, and the bottom end of the load cabin + Y partition plate is fixedly connected with the bottom cabin top plate 8; the inner end of the load cabin-Y partition plate 4 is fixedly connected with the bearing cylinder 29, the outer end of the load cabin-Y partition plate is fixedly connected with one end of the load cabin-Y side plate 23, the top end of the load cabin-Y partition plate is fixedly connected with the load cabin top plate 9, and the bottom end of the load cabin-Y partition plate is fixedly connected with the bottom cabin top plate 8; the middle part of an antenna mounting groove is formed among the load cabin + Y partition plate 3, the load cabin-Y partition plate 4, the bearing cylinder 29, the bottom cabin top plate 8 and the load cabin top plate 9;
as shown in fig. 1 and 4, an upper cabin is arranged on the + Z side of the load cabin roof 9, and comprises an upper cabin roof 18, an upper cabin middle plate 10, two oppositely arranged upper cabin partition plates and a plurality of upper cabin side plates; the upper cabin top plate 18, the upper cabin middle plate 10 and the load cabin top plate 9 are arranged in parallel, and the upper cabin middle plate 10 is positioned between the upper cabin top plate 18 and the load cabin top plate 9; a plurality of upper cabin side plates are fixedly connected between the load cabin top plate 9 and the upper cabin middle plate 10 and the upper cabin top plate 18; the upper cabin partition plate is fixedly connected between the load cabin top plate 9 and the upper cabin middle plate 10, and both sides of the upper cabin partition plate are fixedly connected with the upper cabin side plates; the two upper cabin partition plates are an upper cabin + Y partition plate 5 and an upper cabin-Y partition plate 6, the upper cabin + Y partition plate 5 is positioned on the + Y side of the upper cabin, and the upper cabin-Y partition plate 6 is positioned on the-Y side of the upper cabin; the upper cabin side plates comprise an upper cabin first side plate 11, an upper cabin second side plate 13, an upper cabin third side plate 15 and an upper cabin fourth side plate 16; the upper cabin first side plate 11 is fixedly connected between the upper cabin-Y clapboard 6 and the upper cabin first side plate 11; the second side plate 13 of the upper cabin is fixedly connected between the upper cabin and the Y clapboard 5 as well as between the upper cabin and the Y clapboard 6; the third upper cabin side plate 15 is fixedly connected with the upper cabin and the Y-shaped partition plate 5; the upper cabin + Y partition plate 5, the upper cabin-Y partition plate 6, the upper cabin middle plate 10 and the upper cabin second side plate 13 form the top part of an antenna mounting groove; the top of the upper cabin-Y clapboard 6 is also connected with an upper cabin outer clapboard 17, and the upper cabin outer clapboard 17 is fixedly connected between the upper cabin middle plate 10 and the upper cabin top plate 18 along the vertical direction;
the bottom cabin top plate 8, the bottom cabin bottom plate 7, the load cabin top plate 9 and the upper cabin middle plate 10 are all provided with arc-shaped openings for mounting large-scale antennas; the arc-shaped opening is matched with the outer peripheral surface of the large antenna in shape, and the radius of the arc-shaped opening is not less than 300mm;
the antenna mounting groove is formed by surrounding a bottom cabin top plate 8, a bottom cabin bottom plate 7, two bottom cabin partition plates, a force bearing cylinder 29, a load cabin top plate 9, two load cabin partition plates, an upper cabin middle plate 10 and two upper cabin partition plates.
It should be noted that the lower compartment, the load compartment and the upper compartment include, in addition to the respective panels configured as described above, other side panels and partition panels for configuring the structure of the compartment.
In the satellite structure, the two bottom cabin partition plates, the two load cabin partition plates and the two upper cabin partition plates for forming the antenna mounting groove are arranged oppositely and positioned on the + Y side and the-Y side of the bearing cylinder, so that a main force transmission path of the satellite is ensured, and more longitudinal spaces are provided for a large-scale annular antenna; arc-shaped openings for installing large-scale antennas are formed in the bottom cabin top plate 8, the bottom cabin bottom plate 7, the load cabin top plate 9 and the upper cabin middle plate 10, a through longitudinal space is provided for installation of the large-scale loop antennas, and meanwhile, the transverse installation rigidity of the large-scale loop antennas is improved.
Furthermore, four upper cabin connecting corner boxes are connected between one upper cabin partition plate and the corresponding upper cabin side plate, and mounting interfaces for mounting the upper hoops of the large-scale antenna are arranged on the upper cabin side plates and the upper cabin connecting corner boxes; as shown in fig. 1, the upper cabin + Y partition 5 is connected with the third side plate 15 of the upper cabin through a first upper cabin connecting corner box 19, a second upper cabin connecting corner box 20, a third upper cabin connecting corner box 21 and a fourth upper cabin connecting corner box 22; the upper cabin first side plate 11, the upper cabin second side plate 13 and the upper cabin connecting corner box I19 are provided with mounting interfaces, and the mounting interfaces are used for fixedly connecting an upper embracing ring of the large antenna;
as shown in fig. 1, a middle embracing ring mounting upper support 25 and a middle embracing ring mounting lower support 26 are fixedly connected to the outer side wall of a bearing cylinder 29 between two load compartment partition plates; the load compartment side plate, the middle embracing ring mounting upper support 25 and the middle embracing ring mounting lower support 26 are provided with mounting interfaces for mounting middle embracing rings of the large-scale antenna, namely, the load compartment-Y side plate 23, the load compartment + Y side plate 24, the middle embracing ring mounting upper support 25 and the middle embracing ring mounting lower support 26 are provided with mounting interfaces for fixedly connecting the middle embracing rings of the large-scale antenna;
the outer side wall of the bearing cylinder 29 between the two bottom cabin partition plates is fixedly connected with a lower embracing ring support 34; the bottom cabin side plate and the lower embracing ring support 34 are provided with mounting interfaces for mounting the lower embracing ring of the large antenna, namely, the bottom cabin-Y side plate 32, the bottom cabin + Y side plate 33 and the lower embracing ring support 34 are provided with mounting interfaces for fixedly mounting the lower embracing ring of the large antenna.
Through setting up in the installation interface of upper and lower different positions, can carry out fixed mounting to the last armful of ring, well armful of ring and lower armful of ring of large-scale antenna, conveniently realize the fixed mounting of large-scale antenna, can also fasten large-scale antenna from each position about from the top down simultaneously.
Specifically, as shown in fig. 1, reinforcing corner boxes for improving the mounting rigidity of the mounting interface are mounted between the bottom cabin side plate and the bottom cabin partition plate, between the bottom cabin partition plate and the bottom cabin bottom plate 7, and between the bottom cabin side plate and the bottom cabin bottom plate 7; a first reinforcing angle box 35 is designed between the bottom cabin-Y side plate 32 and the bottom cabin-Y partition plate 2, and a second reinforcing angle box 36 is designed between the bottom cabin-Y partition plate 2 and the bottom cabin bottom plate 7 so as to improve the installation rigidity of the lower embracing ring-Y side installation interface; a third reinforcing corner box 37 is designed between the bottom cabin-Y side plate 32 and the bottom cabin bottom plate 7 so as to provide the installation rigidity of the installation interface of the large-scale antenna unfolding motor.
A horizontal upper triangular support and a horizontal lower triangular support are connected between each load cabin partition and the bearing cylinder 29; as shown in fig. 1, a + Y side horizontal upper triangular support 30 and a + Y side horizontal lower triangular support 31 are connected between the bearing cylinder 29 and the load compartment + Y partition 3, and a-Y side horizontal upper triangular support 27 and a-Y side horizontal lower triangular support 28 are connected between the bearing cylinder 29 and the load compartment-Y partition 4; the + Y-side horizontal upper triangular support 30 is fixedly connected with the middle embracing ring mounting upper support 25, and the + Y-side horizontal lower triangular support 31 is fixedly connected with the middle embracing ring mounting lower support 26;
and a bearing area of each mounting interface for mounting the large antenna is structurally reinforced by adopting an externally-attached carbon fiber panel and an encrypted honeycomb core.
The propulsion cabin partition plate, the load cabin partition plate and the upper cabin partition plate are all carbon fiber skin sandwich structural plates; the propulsion cabin partition plate and the load cabin partition plate are both connected with the bearing cylinder 29 through angle bars; the upper cabin partition is connected with the load cabin top plate 9 through a corner strip.
According to the satellite structure, the reinforcing angle boxes are respectively arranged between the bottom cabin side plate and the bottom cabin partition plate, between the bottom cabin partition plate and the bottom cabin bottom plate 7 and between the bottom cabin side plate and the bottom cabin bottom plate 7, so that the mounting rigidity of the large-scale annular antenna can be effectively improved through the reinforcing angle boxes, and the problems of weakening influence of a large opening on the mounting rigidity and insufficient rigidity caused by cantilever mounting of a unfolding motor are solved; a horizontal upper triangular support and a horizontal lower triangular support are connected between each load cabin partition and the load bearing cylinder 29, the horizontal upper triangular support is fixedly connected with the middle embracing ring mounting upper support, and the horizontal lower triangular support is fixedly connected with the middle embracing ring mounting lower support, so that the mounting rigidity of the middle embracing ring of the large-scale loop antenna is improved through the horizontal upper triangular support and the horizontal lower triangular support.
For the satellite structure, structural strength analysis under the emission working condition is carried out by adopting Patran/Nastran finite ELEMENT software, SHELL ELEMENTs (SHELL ELEMENTs) are adopted for simulating side plates and partition plates, the Nastran analysis result comprises stress, strain and safety margin of each part, and final design parameters are determined by optimizing the structural weight on the premise of meeting the safety margin standard requirement, wherein the final design parameters comprise: the thickness of the baffle, the side plate, the panel layer, and the area size and thickness of the reinforcing sheet.
In order to verify the effect, a structural star is manufactured, and the verification of an identification-level mechanical environment test is carried out, wherein the test result shows that: the structural scheme described by the invention is correct, the parameters are reasonably selected, and the bearing requirement of the ultra-large loop antenna can be met.
In practical applications, parameters such as the side plate and the partition plate may be adjusted according to the size of the large loop antenna, which is not specifically limited in the present invention.
The above description is only a preferred embodiment of the present invention, and is not intended to limit the scope of the present invention. Any modification, equivalent replacement, or improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (5)
1. A satellite structure with a large antenna and a platform integrated is characterized by comprising a satellite platform and the large antenna;
the satellite platform adopts a modular structure and comprises a propelling cabin, a load cabin and an upper cabin which are fixedly connected from bottom to top along the vertical direction;
a longitudinal installation groove which penetrates through the propulsion cabin, the load cabin and the upper cabin in the vertical direction is formed in one side of the propulsion cabin, the load cabin and the upper cabin, and installation interfaces for installing large antenna hoops are arranged in the propulsion cabin, the load cabin and the upper cabin;
the large antenna is fixedly arranged in the antenna mounting groove.
2. The satellite structure of claim 1 wherein the propulsion pod comprises a catenary cylinder and a bottom pod surrounding a bottom end of the catenary cylinder;
the bottom cabin comprises a bottom cabin top plate, a bottom cabin bottom plate, two bottom cabin partition plates and bottom cabin side plates in one-to-one correspondence with the bottom cabin partition plates; the bottom cabin top plate, the bottom cabin bottom plate and the bottom cabin partition plate are fixedly connected with the bearing cylinder; the bottom cabin side plates and the bottom cabin partition plates are fixedly connected between the bottom cabin top plate and the bottom cabin bottom plate; the two bottom cabin partition plates are oppositely arranged; the bottom cabin side plates are fixedly connected to one ends, away from the bearing cylinders, of the corresponding bottom cabin partition plates;
the load cabin is sleeved on the outer side of the bearing cylinder and comprises a load cabin top plate, two load cabin partition plates and load cabin side plates which are in one-to-one correspondence with the load cabin partition plates; the load cabin top plate is fixedly connected to the top end of the bearing cylinder; the two load compartment partition plates and the load compartment side plates are fixedly connected between the load compartment top plate and the bottom compartment top plate; the two load cabin partition plates are oppositely arranged and fixedly connected between the bearing cylinder and the corresponding load cabin side plate;
the upper cabin comprises an upper cabin top plate, an upper cabin middle plate, two upper cabin partition plates arranged oppositely and a plurality of upper cabin side plates; the upper cabin top plate, the upper cabin middle plate and the load cabin top plate are arranged in parallel, and the upper cabin middle plate is positioned between the upper cabin top plate and the load cabin top plate; a plurality of upper cabin side plates are fixedly connected between the load cabin top plate and the upper cabin middle plate and between the load cabin top plate and the upper cabin top plate; the upper cabin partition plate is fixedly connected between the load cabin top plate and the upper cabin middle plate, and two sides of the upper cabin partition plate are fixedly connected with the upper cabin side plates;
the bottom cabin top plate, the bottom cabin bottom plate, the load cabin top plate and the upper cabin middle plate are all provided with arc-shaped openings for mounting the large-scale antenna;
the antenna mounting groove is formed by surrounding the bottom cabin top plate, the bottom cabin bottom plate, the two bottom cabin partition plates, the force bearing cylinder, the load cabin top plate, the two load cabin partition plates, the upper cabin middle plate and the two upper cabin partition plates.
3. The satellite structure according to claim 2, wherein four upper-cabin connection corner boxes are connected between one of the upper-cabin partition plates and the corresponding upper-cabin side plate, and mounting interfaces for mounting the upper hoops of the large antennas are arranged on the upper-cabin side plates and the upper-cabin connection corner boxes;
a middle embracing ring mounting upper support and a middle embracing ring mounting lower support are fixedly connected to the outer side wall of the bearing cylinder between the two load cabin partition plates; the load compartment side plate, the middle surrounding ring mounting upper support and the middle surrounding ring mounting lower support are provided with mounting interfaces for mounting a middle surrounding ring of a large-scale antenna;
a lower embracing ring support is fixedly connected to the outer side wall of the bearing cylinder between the two bottom cabin clapboards; the bottom cabin side plate and the lower embracing ring support are provided with installation interfaces for installing the lower embracing ring of the large antenna.
4. The satellite structure according to claim 3, wherein reinforcing corner boxes for improving the mounting rigidity of the mounting interface are mounted between the bottom deck side panels and the bottom deck partitions, between the bottom deck partitions and the bottom deck plate, and between the bottom deck side panels and the bottom deck plate;
a horizontal upper triangular support and a horizontal lower triangular support are connected between each load cabin partition and the bearing cylinder;
one of the horizontal upper triangular supports is fixedly connected with the middle embracing ring mounting upper support, and the other horizontal lower triangular support is fixedly connected with the middle embracing ring mounting lower support;
and the bearing area of each mounting interface is reinforced by adopting an externally-attached carbon fiber panel and an encrypted honeycomb core.
5. The satellite structure according to any one of claims 1-4, wherein the propulsion compartment baffle, the load compartment baffle, and the upper compartment baffle are all carbon fiber skin sandwich structural plates;
the propulsion cabin partition plate and the load cabin partition plate are connected with the bearing cylinder through angle bars;
the upper cabin clapboard is connected with the load cabin top plate through a corner strip.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211354867.8A CN115743603A (en) | 2022-11-01 | 2022-11-01 | Satellite structure with large antenna and platform integrated |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211354867.8A CN115743603A (en) | 2022-11-01 | 2022-11-01 | Satellite structure with large antenna and platform integrated |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115743603A true CN115743603A (en) | 2023-03-07 |
Family
ID=85354969
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211354867.8A Pending CN115743603A (en) | 2022-11-01 | 2022-11-01 | Satellite structure with large antenna and platform integrated |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115743603A (en) |
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2022
- 2022-11-01 CN CN202211354867.8A patent/CN115743603A/en active Pending
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