CN113135301B - Integrated system of satellite - Google Patents
Integrated system of satellite Download PDFInfo
- Publication number
- CN113135301B CN113135301B CN202110596816.5A CN202110596816A CN113135301B CN 113135301 B CN113135301 B CN 113135301B CN 202110596816 A CN202110596816 A CN 202110596816A CN 113135301 B CN113135301 B CN 113135301B
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- data transmission
- satellite
- transmission system
- antenna
- cabin
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- 230000005540 biological transmission Effects 0.000 claims abstract description 61
- 238000012546 transfer Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 abstract description 4
- 230000017525 heat dissipation Effects 0.000 abstract description 2
- 238000013461 design Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004020 conductor Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009432 framing Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000011160 research Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
- B64G1/50—Arrangements or adaptations of devices for control of environment or living conditions for temperature control
- B64G1/506—Heat pipes
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Health & Medical Sciences (AREA)
- General Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Physics & Mathematics (AREA)
- Life Sciences & Earth Sciences (AREA)
- Biodiversity & Conservation Biology (AREA)
- Environmental & Geological Engineering (AREA)
- Environmental Sciences (AREA)
- General Health & Medical Sciences (AREA)
- Toxicology (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Details Of Aerials (AREA)
Abstract
The invention relates to the technical field of aerospace, and provides an integrated system of a satellite, which comprises: a data transmission system; a satellite structural plate; a fixing device. The data transmission system is arranged on the satellite structural plate through the fixing device. The integrated system of the satellite structural plate and the data transmission system has compact structure, good processing, assembling and adjusting manufacturability, high stability and good mechanical environment adaptability; the heat pipes are embedded in the satellite structural plate and used for heat dissipation of all components of the data transmission system and the whole satellite, so that the structure is compact; and the field of view requirement of the data transmission antenna is met.
Description
Technical Field
The present invention relates generally to the field of aerospace technology. In particular, the present invention relates to an integrated system for satellites.
Background
Due to the rapid increase in the state of the art and the need to develop new application fields, modern satellites are rapidly evolving towards high functional density, light and small satellites. The integrated design method is different from the prior method of decomposing each function of the satellite into each subsystem, and the satellite as a whole is subjected to unified design and resource planning balance from the large system level. The current integrated design concept is embodied in a plurality of aerospace pre-research projects and satellite engineering projects, and mainly is integrated design of comprehensive electronic integrated design and hardware and software. However, the integrated design of the data transmission system involves less, and the data transmission system occupies too much space inside the satellite.
Disclosure of Invention
To at least partially solve the above-mentioned problems in the prior art, the present invention proposes an integrated system of satellites, comprising:
a satellite architecture board for arranging components of the data transmission system; and
a data transmission system, the components of the data transmission system comprising:
the data transmission system cabin inner part is compactly arranged on the plate surface of the satellite structural plate in the satellite cabin body through the fixing device; and
the data transmission system cabin outer part comprises a first data transmission antenna and a second data transmission antenna, wherein the first data transmission antenna and the second data transmission antenna are respectively arranged at two side plate positions of the satellite structural plate and are positioned at two sides outside the satellite cabin body.
In the present invention, the term "data transmission system" refers to a system for transmitting data in each band on and/or between satellites, such as a data transmission channel in the X band.
In the present invention, the term "integrated" refers to the unified combined construction and/or control of the components and/or systems.
In one embodiment of the invention, it is provided that the data transfer system in-cabin components include one or more of the following:
a modem;
the traveling wave tube amplifier comprises a traveling wave tube, an EPC and an isolator;
waveguide device, waveguide switch and waveguide tube; and
a filter.
In one embodiment of the invention, it is provided that the fastening means comprise flanges and/or screws.
In one embodiment of the invention, it is provided that the integrated system of satellites further comprises a cradle for supporting components of the data transmission system; the bracket is configured with an interface for connection with the satellite structural board.
In one embodiment of the invention, the satellite architecture board comprises:
the socket is used for being connected with the bracket; and/or
And a perforation for arranging components of the data transmission system.
In one embodiment of the invention, it is provided that the first data transmission antenna, the second data transmission antenna, the waveguide device, the waveguide switch, the isolator and the traveling wave tube are connected by the waveguide tube;
the waveguide tube is supported by the bracket; and
the waveguide device passes through the perforation and is connected with the satellite structural board through an interface on the bracket.
In one embodiment of the invention, it is provided that the satellite structural board further comprises a heat pipe, which is embedded inside the satellite structural board.
In one embodiment of the invention, it is provided that the first and/or second data transmission antennas comprise a back-radiating double helical antenna.
In one embodiment of the invention, it is provided that the first and/or second digital transmitting antennas have a cone angle field of view of ±70°, and are configured such that the antenna gain is greater than 0dB, the antenna axis ratio is less than 5dB, and the antenna standing wave ratio is less than 1.1.
The invention has the following unexpected beneficial effects: the integrated system of the satellite structural plate and the data transmission system has compact structure, good processing, assembling and adjusting manufacturability, high stability and good mechanical environment adaptability; the heat pipes are embedded in the satellite structural plate and used for heat dissipation of all components of the data transmission system and the whole satellite, so that the structure is compact; and the data transmission antenna is arranged at the two side plate positions of the structural plate and is positioned at the side surface position of the whole satellite, so that the shielding of other parts of the satellite can be effectively avoided while the whole structure is compact, and the +/-70-degree cone angle view field of the data transmission antenna is ensured.
Drawings
To further clarify the advantages and features present in various embodiments of the present invention, a more particular description of various embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, for clarity, the same or corresponding parts will be designated by the same or similar reference numerals.
Fig. 1A and 1B are schematic structural views of an integrated system of satellites in an embodiment of the present invention.
FIG. 2 shows a schematic diagram of the components of a data transmission system in one embodiment of the invention.
FIG. 3 illustrates a schematic support of components of a data transfer system in accordance with one embodiment of the invention.
Fig. 4 is a schematic plan view of a satellite structure board with heat pipes embedded in an embodiment of the invention.
Figure 5 shows a schematic plan view of an integrated system of satellites in an embodiment of the invention.
Fig. 6 shows a schematic view of the field of view of a satellite antenna in one embodiment of the invention.
Detailed Description
It should be noted that the components in the figures may be shown exaggerated for illustrative purposes and are not necessarily to scale. In the drawings, identical or functionally identical components are provided with the same reference numerals.
In the present invention, unless specifically indicated otherwise, "disposed on …", "disposed over …" and "disposed over …" do not preclude the presence of an intermediate therebetween. Furthermore, "disposed on or above" … merely indicates the relative positional relationship between the two components, but may also be converted to "disposed under or below" …, and vice versa, under certain circumstances, such as after reversing the product direction.
In the present invention, the embodiments are merely intended to illustrate the scheme of the present invention, and should not be construed as limiting.
In the present invention, the adjectives "a" and "an" do not exclude a scenario of a plurality of elements, unless specifically indicated.
It should also be noted herein that in embodiments of the present invention, only a portion of the components or assemblies may be shown for clarity and simplicity, but those of ordinary skill in the art will appreciate that the components or assemblies may be added as needed for a particular scenario under the teachings of the present invention. In addition, features of different embodiments of the invention may be combined with each other, unless otherwise specified. For example, a feature of the second embodiment may be substituted for a corresponding feature of the first embodiment, or may have the same or similar function, and the resulting embodiment would fall within the disclosure or scope of the disclosure.
It should also be noted herein that, within the scope of the present invention, the terms "identical", "equal" and the like do not mean that the two values are absolutely equal, but rather allow for some reasonable error, that is, the terms also encompass "substantially identical", "substantially equal". By analogy, in the present invention, the term "perpendicular", "parallel" and the like in the table direction also covers the meaning of "substantially perpendicular", "substantially parallel".
The numbers of the steps of the respective methods of the present invention are not limited to the order of execution of the steps of the methods. The method steps may be performed in a different order unless otherwise indicated.
The invention is further elucidated below in connection with the embodiments with reference to the drawings.
As shown in fig. 1A and 1B, the integrated system of satellites includes a data transmission system and a satellite structural plate that are integrally arranged.
As shown in fig. 2, the data transmission system includes a modem, a traveling wave tube amplifier, a waveguide device, a waveguide switch a\b, a waveguide filter, a data transmission antenna a\b and a matched cable, wherein the traveling wave tube amplifier a\b includes a traveling wave tube, an EPC (Electric Power Conductor power modulator) and an isolator. The components of the data transmission system may be arranged on the satellite building board by means of fastening means, such as flanges and screws.
When the data transmission system is arranged, other components are arranged in the cabin except that the data transmission antenna is arranged outside the cabin of the satellite. As shown in fig. 3, the data transmission antenna a\b, the waveguide device, the waveguide switch, the isolator a\b and the traveling wave tube a\b are connected together through the waveguide tube. Because the span of the waveguide tube is large, the waveguide tube is supported by the partition section through the support, and meanwhile, the support is provided with an interface connected with the satellite structure plate for connecting the waveguide device and the satellite structure plate.
As shown in fig. 4, the base of the satellite structural board may be an aluminum skin honeycomb board configured with sockets for the connection of the brackets in the data transmission system and with perforations for the placement of components of the data transmission system, such as waveguide devices, through the perforations, on the satellite structural board. The satellite structure board also comprises a heat pipe for integrated temperature control of the whole satellite and the data transmission system.
The waveguide filter, modem and EPC are independent single units, so that the waveguide filter, modem and EPC can be arranged on a structural board nearby, the length of a direct connection cable of each component in the data transmission system is reduced, and the assembly is finished as shown in fig. 5.
As shown in FIG. 6, the data transmission antenna A/B is arranged at two side plate positions of the structural plate and is positioned at the side surface position of the whole satellite, so that the shielding of other parts of the satellite can be effectively avoided while the whole structure is compact, and the circular cone angle view field of +/-70 degrees of the data transmission antenna is ensured. Taking an X-band data transmission system as an example, the system receives the load data from the load data processing unit and completes data processing such as framing, RS coding, interleaving, scrambling, convolution coding and the like. And then completing the modulation of the X wave band, and transmitting the radio frequency signal to a ground receiving station through a data transmission antenna after power amplification.
The data transmission antenna A/B can be a back-reflection double-spiral antenna, and can be configured to meet the conditions that in the working frequency band, the antenna gain is larger than 0dB, the antenna axis ratio is smaller than 5dB and the antenna standing wave ratio is smaller than 1.1 in the beam range of +/-70 degrees.
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to those skilled in the relevant art that various combinations, modifications, and variations can be made therein without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention as disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
Claims (5)
1. An integrated system for a satellite, comprising:
a satellite architecture board for arranging components of a data transmission system, the satellite architecture board comprising: the socket is used for being connected with the bracket; and/or perforations for arranging components of the data transmission system;
a data transmission system, the components of the data transmission system comprising:
the data transmission system cabin inner part is compactly arranged on the plate surface of the satellite structural plate in the satellite cabin body through the fixing device; and
the data transmission system comprises a data transmission system cabin outer part, a satellite cabin outer part and a satellite cabin outer part, wherein the data transmission system cabin outer part comprises a first data transmission antenna and a second data transmission antenna, and the first data transmission antenna and the second data transmission antenna are respectively arranged at two side plate positions of the satellite structural plate and are positioned at two sides outside the satellite cabin; and
a bracket for supporting components of the data transmission system; the support is provided with an interface which is used for being connected with the satellite structural plate;
wherein the data transfer system in-cabin components include one or more of the following:
a modem;
the traveling wave tube amplifier comprises a traveling wave tube, an EPC and an isolator;
waveguide device, waveguide switch and waveguide tube; and
a filter;
the data transmission system cabin inner part is compactly arranged on the plate surface of the satellite structural plate through a fixing device in the satellite cabin body, and comprises:
the first data transmission antenna, the second data transmission antenna, the waveguide device, the waveguide switch, the isolator and the traveling wave tube are connected through the waveguide tube;
the waveguide tube is supported by the bracket; and
the waveguide device passes through the perforation and is connected with the satellite structural board through an interface on the bracket.
2. The integrated system of satellites according to claim 1, wherein the fixing means comprise flanges and/or screws.
3. The integrated satellite system of claim 1, wherein the satellite structural board further comprises a heat pipe embedded within the satellite structural board.
4. The integrated system of satellites of claim 1 wherein the first and/or second data transmission antennas comprise a back-radiating double helical antenna.
5. The integrated system of satellites of claim 4 wherein the first and/or second digital antennas have a ±70° cone angle field of view and are configured with an antenna gain greater than 0dB, an antenna axis ratio less than 5dB and an antenna standing wave ratio less than 1.1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110596816.5A CN113135301B (en) | 2021-05-28 | 2021-05-28 | Integrated system of satellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110596816.5A CN113135301B (en) | 2021-05-28 | 2021-05-28 | Integrated system of satellite |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113135301A CN113135301A (en) | 2021-07-20 |
| CN113135301B true CN113135301B (en) | 2024-03-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110596816.5A Active CN113135301B (en) | 2021-05-28 | 2021-05-28 | Integrated system of satellite |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113135301B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113581496A (en) * | 2021-09-10 | 2021-11-02 | 中国科学院微小卫星创新研究院 | Thermal control system for mass production of small satellites |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05213283A (en) * | 1992-02-04 | 1993-08-24 | Nec Corp | Structure of artificial satellite |
| US5527001A (en) * | 1993-06-11 | 1996-06-18 | Teledesic Corporation | Modular communication satellite |
| CN110525688A (en) * | 2019-08-06 | 2019-12-03 | 北京空间飞行器总体设计部 | A kind of in-orbit restructural expansible satellite system |
| CN111786087A (en) * | 2020-08-07 | 2020-10-16 | 上海卫星工程研究所 | Earth data transmission antenna layout method suitable for inter-satellite transmission |
-
2021
- 2021-05-28 CN CN202110596816.5A patent/CN113135301B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05213283A (en) * | 1992-02-04 | 1993-08-24 | Nec Corp | Structure of artificial satellite |
| US5527001A (en) * | 1993-06-11 | 1996-06-18 | Teledesic Corporation | Modular communication satellite |
| CN110525688A (en) * | 2019-08-06 | 2019-12-03 | 北京空间飞行器总体设计部 | A kind of in-orbit restructural expansible satellite system |
| CN111786087A (en) * | 2020-08-07 | 2020-10-16 | 上海卫星工程研究所 | Earth data transmission antenna layout method suitable for inter-satellite transmission |
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| Publication number | Publication date |
|---|---|
| CN113135301A (en) | 2021-07-20 |
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