CN110775307A - High-flux satellite transponder equipment layout - Google Patents
High-flux satellite transponder equipment layout Download PDFInfo
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- CN110775307A CN110775307A CN201910955527.2A CN201910955527A CN110775307A CN 110775307 A CN110775307 A CN 110775307A CN 201910955527 A CN201910955527 A CN 201910955527A CN 110775307 A CN110775307 A CN 110775307A
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- cabin
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- transponder
- satellite
- auxiliary cabin
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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
Abstract
A high-flux satellite transponder equipment layout belongs to the technical field of satellites. According to the invention, the independent auxiliary cabin is constructed near the antenna feed source of the extra-cabin antenna, and the transponder receiving equipment is arranged in the auxiliary cabin near the antenna feed source of the extra-cabin antenna, so that the shortest length of a connecting waveguide between the antenna feed source and the transponder receiving equipment is ensured, the signal loss is reduced, and the G/T value performance of the satellite is improved; the middle plate of the auxiliary cabin provides an installation interface of equipment, the heat generated by the equipment is conducted to a radiating surface of a communication cabin to be radiated through the pre-buried heat pipe and the coupling heat pipe, the auxiliary cabin is integrally coated through the thermal control multilayer, the thermal isolation between the auxiliary cabin and an external space environment is realized, the working temperature environment of the equipment in the auxiliary cabin is ensured, meanwhile, the material of the cover plate of the auxiliary cabin is reasonably selected, the sufficient equivalent aluminum thickness is provided, and the sufficient anti-irradiation condition is provided for the equipment in the cabin; by arranging the transponder receiving equipment in the auxiliary cabin, the space requirements of equipment installation and cabin-crossing waveguide trend are reduced in the satellite cabin, and the layout space in the cabin is saved.
Description
Technical Field
The invention relates to a high-flux satellite transponder equipment layout, and belongs to the technical field of satellites.
Background
The high-flux satellite load equipment and the number of the waveguides are large, so that the layout space in the cabin is tense, meanwhile, the G/T value index requirement of a coverage area is high, the loss of effective load signals is extremely sensitive, and the important part of the signal loss comes from the loss of the waveguides, the cables and the like which are connected with the equipment in a connection link when the signals are transmitted. In the traditional satellite layout, an antenna feed source is generally arranged outside a satellite cabin, and transponder equipment is arranged in the cabin so as to ensure that the equipment in the cabin has a proper installation position, a stable environment temperature, a good radiation-resistant environment and the like, but the feed source outside the cabin is far away from the receiving equipment of the transponder in the cabin, so that the waveguide distance for connecting the antenna feed source and the receiving equipment of the transponder in the cabin to carry out signal transmission is long, and the signal loss is large; meanwhile, the waveguide occupies a large amount of layout space in the cabin, and the high-flux satellite loading equipment is large in number, so that the layout space of the equipment in the cabin is insufficient. The two problems are called key problems for restricting the performance index and the layout realizability of the high-throughput satellite.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the high-flux satellite transponder equipment layout is provided, the signal loss between an antenna feed source and transponder receiving equipment is reduced, the G/T value performance of a satellite is improved, and meanwhile the equipment layout space in a satellite cabin is saved.
The technical solution of the invention is as follows: a high-flux satellite transponder equipment layout comprises an auxiliary cabin, a connecting waveguide, an antenna feed source, a coupling heat pipe, a satellite radiating surface, a cable and an auxiliary cabin mounting plate; a transponder receiving device of a satellite is arranged in the auxiliary cabin; the transponder receiving equipment is connected with the antenna feed source through the connecting waveguide and is connected with external equipment through a cable; one end of the coupling heat pipe is arranged on the auxiliary cabin, and the other end of the coupling heat pipe is connected to the satellite radiating surface; the auxiliary cabin is arranged on the auxiliary cabin mounting plate, so that the length of a connecting waveguide between the auxiliary cabin and the antenna feed source is shortest; the auxiliary cabin mounting plate is positioned on the outer surface of the satellite cabin plate.
Further, the auxiliary cabin comprises a cover plate, an upper connecting support, a middle plate and a lower connecting support; the cover plate and the middle plate are fixedly connected through an upper connecting support, the middle plate and the auxiliary cabin mounting plate are fixedly connected through a lower connecting support, and the transponder receiving equipment is arranged on the upper end face and the lower end face of the middle plate.
Furthermore, the upper connecting support and the lower connecting support are arranged on one side surface direction of the auxiliary cabin to form a closed structure on the side surface direction of the auxiliary cabin, and the other side surface direction of the auxiliary cabin is an open structure and is used for connecting the waveguide and the cable.
Furthermore, one end of the coupling heat pipe is positioned on the middle plate, and the other end of the coupling heat pipe is connected to the satellite radiating surface.
Furthermore, a plurality of pre-buried heat pipes are arranged in the middle plate, and the transponder receiving equipment needing heat dissipation is positioned above the pre-buried heat pipes; the embedded heat pipes are connected to the coupling heat pipe; the transponder receiving equipment needing heat dissipation is equipment with heat consumption larger than a preset value.
Further, the transponder receiving device is connected to the remaining transponder devices through a high frequency cable for transmitting radio frequency signals.
Furthermore, be equipped with the adapter on the medium plate, the transponder receiving equipment all is connected with adapter one end, and the adapter other end is connected to satellite energy supply equipment and controller equipment through the low frequency cable for transponder receiving equipment power supply and transmission control signal.
Compared with the prior art, the invention has the advantages that:
(1) the receiving equipment of the traditional satellite transponder is arranged in the cabin, the antenna feed source is arranged outside the cabin, so that the length of a connecting waveguide between the feed source and the receiving equipment of the satellite transponder is long, and the loss of signals received by the feed source is large;
(2) the traditional satellite transponder receiving equipment is arranged in the cabin, the antenna feed source is arranged outside the cabin, so that a connecting waveguide between the feed source and the transponder receiving equipment needs to penetrate through a satellite cabin plate, the satellite cabin plate needs to be provided with a waveguide opening, and when the number of waveguides is large, the opening area of the cabin plate is too large, so that the structural strength of the cabin plate is insufficient;
(3) the receiving equipment of the traditional satellite transponder is arranged in the cabin, the antenna feed source is arranged outside the cabin, so that the length of a connecting waveguide between the feed source and the receiving equipment of the transponder is long, and a large-area satellite layout space is occupied on a waveguide path;
(4) the traditional satellite realizes that transponder equipment outside a cabin is installed by establishing a closed box structure outside the satellite cabin and installing equipment inside the box, but the invention designs the auxiliary cabin which is in a tripod-shaped structure, the equipment is installed on the upper surface and the lower surface of the middle plate of the auxiliary cabin, the space utilization rate is high, the direction of connecting the waveguide and the high-frequency cable is an open structure, the waveguide and the high-frequency cable are convenient to assemble, and the weight of the whole auxiliary cabin is reduced.
Drawings
FIG. 1 is a diagram of a conventional payload schematic diagram corresponding to device layout partitioning;
FIG. 2 is a schematic diagram of payload partitioning for device layout according to the present invention;
FIG. 3 is a schematic view of a satellite layout according to the present invention;
FIG. 4 is a schematic view of a bilge assembly configuration of the present invention;
fig. 5 is an exploded pictorial view of the bilge assembly of the present invention.
Detailed Description
The invention is described in detail below with reference to the figures and specific examples.
As shown in fig. 1, a typical satellite transponder receiving device includes an input preselector, a switch, a low noise amplifier, and the like, and the transponder receiving device mainly functions to amplify a signal received by an antenna feed source, the signal transmitted to a satellite on the ground is transmitted through a spatial long distance, when the signal is received by the antenna feed source, the signal strength is very weak, and before the signal is transmitted to the transponder receiving device, the signal loss is very sensitive to the loss of the signal, the main source of the loss of the signal is the loss caused by the signal being conducted in a waveguide connecting the antenna feed source to the transponder receiving device, the loss value is positively correlated with the length of the waveguide.
Referring to fig. 2, a high flux satellite transponder device layout includes a sub-bay 1, a connection waveguide 2, an antenna feed source 3, a coupling heat pipe 4, a satellite cooling surface 5, a cable 6, and a sub-bay mounting plate 7; a transponder receiving device 13 of a satellite is arranged in the auxiliary cabin 1; the transponder receiving device 13 is connected with the antenna feed source 3 through the connecting waveguide 2 and is connected with external equipment through the cable 6; one end of the coupling heat pipe 4 is arranged on the auxiliary cabin 1, and the other end is connected to the satellite radiating surface 5; the auxiliary cabin 1 is arranged on the auxiliary cabin mounting plate 7, so that the length of the connecting waveguide 2 between the antenna feed source 3 and the auxiliary cabin is the shortest; the auxiliary cabin mounting plate 7 is positioned on the outer surface of the satellite cabin plate. Namely, the auxiliary cabin 1 is arranged at a position near the antenna feed source 3, the transponder receiving equipment 13 is arranged in the auxiliary cabin 1 to ensure that the length of the connecting waveguide 2 from the antenna feed source 3 to the transponder receiving equipment 13 is shortest and the signal loss is minimum, after a signal received by the antenna feed source 3 is amplified by the transponder receiving equipment 13, the signal is insensitive to the loss at the moment, and the signal is introduced into the cabin through the high-frequency cable 6 at the moment, so that the G/T value performance of the signal is ensured.
Fig. 3 is a typical example of the layout of an auxiliary cabin 1 in a satellite, wherein the auxiliary cabin 1 is arranged at a position as close to an antenna feed source 3 as possible outside the cabin, the whole auxiliary cabin 1 is coated with a plurality of thermal control layers and isolated from heat flow outside the space, so as to ensure a relatively stable thermal environment, a connection waveguide 2 is arranged between the antenna feed source 3 and the auxiliary cabin 1, one auxiliary cabin 1 can be used in cooperation with a plurality of antenna feed sources 3, one end of a coupling heat pipe 4 is positioned on a middle plate 10, a plurality of embedded heat pipes 14 are arranged in the middle plate 10, and a transponder receiving device 13 which needs to dissipate heat is positioned above the embedded heat pipes 14; the embedded heat pipes 14 are connected to the coupling heat pipe 4; the transponder receiving device 13 requiring heat dissipation is the transponder receiving device 13 having heat consumption greater than a preset value. Namely, one end of the coupling heat pipe 4 is tightly attached to the middle plate 10, the other end of the coupling heat pipe is tightly attached to the satellite radiating surface 5, heat of equipment installed on the middle plate 10 in the auxiliary cabin 1 is collected through the pre-embedded heat pipe 14 and then conducted to the satellite radiating surface 5 through the coupling heat pipe 4 for radiating, signals received by the antenna feed source 3 are amplified through equipment in the auxiliary cabin 1 and then converted into high-frequency cables for transmission, and the auxiliary cabin installation plate 7 is a structural cabin plate of a satellite.
Fig. 4 is an exploded view of the assembly configuration of the auxiliary cabin 1, wherein the auxiliary cabin 1 comprises a cover plate 8, an upper connecting bracket 9, a middle plate 10 and a lower connecting bracket 11; the cover plate 8 and the middle plate 10 are fixedly connected through an upper connecting support 9, the middle plate 10 and the auxiliary cabin mounting plate 7 are fixedly connected through a lower connecting support 11, and the transponder receiving device 13 is arranged on the upper end face and the lower end face of the middle plate 10. The upper connecting support 9 and the lower connecting support 11 are arranged on one side surface direction of the auxiliary cabin 1 to form a closed structure on one side surface direction of the auxiliary cabin 1, and the other side surface direction of the auxiliary cabin 1 is an open structure and is used for connecting the waveguide 2 and the cable 6. The whole auxiliary cabin 1 is tripod-shaped in configuration, the repeater equipment is arranged on the middle plate 10, so that the main weight of the auxiliary cabin 1 is concentrated on the middle plate 10, the area of the bottom surface of the installation formed by the lower connecting support 11 is larger than that of the middle plate 10, the configuration structure is stable, and the mechanical property is good. Meanwhile, the area of the cover plate 8 of the auxiliary cabin 1 is larger than that of the middle plate 10, so that the space irradiation on the equipment on the middle plate 10 can be shielded, and the space irradiation on the equipment can meet the use requirement of the equipment. The equipment is installed on the upper surface and the lower surface of the plate 10 in the auxiliary cabin 1, the space utilization rate is high, the direction of connecting the waveguide 2 and the high-frequency cable 6 is of an open structure, the waveguide and the high-frequency cable 6 can be conveniently assembled, and meanwhile, the weight of the whole auxiliary cabin 1 is effectively reduced.
Wherein the transponder receiving device 13 is connected to the other transponder devices through a high frequency cable for transmitting radio frequency signals. Be equipped with the adapter on the medium plate 10, transponder receiving equipment 13 all is connected with adapter one end, and the adapter other end passes through low frequency cable and is connected to satellite energy supply equipment and controller equipment for supply power and transmission control signal for transponder receiving equipment 13. Constitute and be enclosed construction on 1 side direction in vice cabin for carry out the structural connection, 1 another side direction in vice cabin is the structure of opening, is convenient for carry out waveguide and high frequency cable 6 and connects, and wherein, apron 8 has three effect: providing shielding thickness for equipment in the auxiliary cabin 1; secondly, providing a fixed surface for the thermal control multilayer; thirdly, the auxiliary cabin 1 is formed into a closed structure to ensure the mechanical property of the auxiliary cabin 1, 9 is an upper connecting support 9, a cover plate 8 and a middle plate 10 are fixedly connected through the upper connecting support and the middle plate, equipment is arranged on the upper surface and the lower surface of the middle plate 10, the middle plate 10 and a satellite cabin plate are fixedly connected through a lower connecting support 11, a transponder receiving device 13 is connected with one end of an adapter, and the other end of the adapter is connected to a satellite energy supply device and a controller device through a low-frequency cable 6 and used for supplying power to the transponder receiving device 13 and transmitting control signals.
As shown in fig. 5, the layout of devices on the midplane 10, 13 is a transponder receiving device 13, which generally includes devices such as an input preselector, a switch, and a low noise amplifier, 14 is an embedded heat pipe 14, which is embedded in the midplane 10, the transponder receiving device 13 to be cooled is located above the embedded heat pipe 14, and the transponder receiving device 13 to be cooled is a transponder receiving device 13 with heat consumption greater than a preset value. The heat of the equipment on the middle plate 10 is conducted to the coupling heat pipe 4 through the embedded heat pipe 14, and finally conducted to the satellite cooling surface 5 through the coupling heat pipe 4.
The invention provides a high flux satellite layout method of an 'extra-cabin', an independent 'auxiliary cabin 1' is constructed near an antenna feed source 3 outside the cabin, and a transponder receiving device 13 is arranged in the auxiliary cabin 1 at a position near the antenna feed source 3 outside the cabin, so that the shortest length of a connecting waveguide 2 between the antenna feed source 3 and the transponder receiving device 13 is ensured, the signal loss is reduced, and the G/T value performance of a satellite is improved; the plate 10 in the auxiliary cabin 1 provides an installation interface of equipment, the heat generated by the equipment is conducted to a radiating surface of a communication cabin to be radiated through the pre-buried heat pipe 14 and the coupling heat pipe 4, the auxiliary cabin 1 is integrally coated through a heat control multilayer, the thermal isolation between the auxiliary cabin 1 and an external space environment is realized, the working temperature environment of the equipment in the auxiliary cabin 1 is ensured, and meanwhile, the cover plate 8 material of the auxiliary cabin 1 is reasonably selected to provide enough equivalent aluminum thickness and provide enough anti-irradiation conditions for the equipment in the cabin; by arranging the transponder receiving equipment 13 in the auxiliary cabin 1, the space requirements of equipment installation and cabin-crossing waveguide trend are reduced in the satellite cabin, and the layout space in the cabin is saved.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (7)
1. A high-throughput satellite transponder device topology, comprising: the device comprises an auxiliary cabin (1), a connecting waveguide (2), an antenna feed source (3), a coupling heat pipe (4), a satellite radiating surface (5), a cable (6) and an auxiliary cabin mounting plate (7); a satellite transponder receiving device (13) is arranged in the auxiliary cabin (1); the transponder receiving device (13) is connected with the antenna feed source (3) through the connecting waveguide (2) and is connected with external equipment through a cable (6); one end of the coupling heat pipe (4) is arranged on the auxiliary cabin (1), and the other end is connected to the satellite radiating surface (5); the auxiliary cabin (1) is arranged on the auxiliary cabin mounting plate (7) so that the length of the connecting waveguide (2) between the auxiliary cabin and the antenna feed source (3) is the shortest; the auxiliary cabin mounting plate (7) is positioned on the outer surface of the satellite cabin plate.
2. A high throughput satellite transponder arrangement according to claim 1, wherein: the auxiliary cabin (1) comprises a cover plate (8), an upper connecting support (9), a middle plate (10) and a lower connecting support (11); the cover plate (8) is fixedly connected with the middle plate (10) through an upper connecting support (9), the middle plate (10) is fixedly connected with the auxiliary cabin mounting plate (7) through a lower connecting support (11), and the transponder receiving equipment (13) is arranged on the upper end face and the lower end face of the middle plate (10).
3. A high throughput satellite transponder arrangement according to claim 2, wherein: the upper connecting support (9) and the lower connecting support (11) are arranged on one side surface direction of the auxiliary cabin (1) to form a closed structure on the side surface direction of the auxiliary cabin (1), and the other side surface direction of the auxiliary cabin (1) is an open structure and is used for connecting the waveguide (2) and the cable (6).
4. A high throughput satellite transponder arrangement according to claim 2, wherein: one end of the coupling heat pipe (4) is positioned on the middle plate (10), and the other end of the coupling heat pipe is connected to the satellite radiating surface (5).
5. A high throughput satellite transponder apparatus arrangement according to claim 4, wherein: a plurality of embedded heat pipes (14) are arranged in the middle plate (10), and transponder receiving equipment needing heat dissipation is positioned above the embedded heat pipes (14); the embedded heat pipes (14) are connected to the coupling heat pipe (4); the transponder receiving equipment needing heat dissipation is equipment with heat consumption larger than a preset value.
6. A high throughput satellite transponder arrangement according to claim 1, wherein: the transponder receiving device (13) is connected to the remaining transponder devices by a high frequency cable for transmitting radio frequency signals.
7. A high throughput satellite transponder arrangement according to claim 1, wherein: be equipped with the adapter on medium plate (10), transponder receiving equipment (13) all are connected with adapter one end, and the adapter other end is connected to satellite energy supply equipment and controller equipment through the low frequency cable for supply power and transmission control signal for transponder receiving equipment (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910955527.2A CN110775307A (en) | 2019-10-09 | 2019-10-09 | High-flux satellite transponder equipment layout |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910955527.2A CN110775307A (en) | 2019-10-09 | 2019-10-09 | High-flux satellite transponder equipment layout |
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| CN110775307A true CN110775307A (en) | 2020-02-11 |
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| CN201910955527.2A Pending CN110775307A (en) | 2019-10-09 | 2019-10-09 | High-flux satellite transponder equipment layout |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111918535A (en) * | 2020-08-17 | 2020-11-10 | 中国科学院微小卫星创新研究院 | Spaceborne and ground single-phase fluid loop heat dissipation system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060238414A1 (en) * | 2003-08-05 | 2006-10-26 | Miyamoto Ryan Y | Microwave self-phasing antenna arrays for secure data transmission & satellite network crosslinks |
| CN102299425A (en) * | 2011-06-14 | 2011-12-28 | 西安空间无线电技术研究所 | High-power low-PIM (passive intermodulation) broadband polarized frequency duplexing feed assembly in Ku frequency band |
| CN105633584A (en) * | 2015-12-30 | 2016-06-01 | 中国电子科技集团公司第三十九研究所 | Log periodic feed source array based on spaceborne multi-beam antenna space three-dimensional structure layout |
| CN105745786A (en) * | 2013-09-18 | 2016-07-06 | 国家科学研究中心 | A wave shaping device, an electronic device, and a system |
| CN207217741U (en) * | 2017-10-13 | 2018-04-10 | 南京瑞安腾企业管理咨询有限公司 | A kind of high flux satellite network signal ship-board antenna |
-
2019
- 2019-10-09 CN CN201910955527.2A patent/CN110775307A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20060238414A1 (en) * | 2003-08-05 | 2006-10-26 | Miyamoto Ryan Y | Microwave self-phasing antenna arrays for secure data transmission & satellite network crosslinks |
| CN102299425A (en) * | 2011-06-14 | 2011-12-28 | 西安空间无线电技术研究所 | High-power low-PIM (passive intermodulation) broadband polarized frequency duplexing feed assembly in Ku frequency band |
| CN105745786A (en) * | 2013-09-18 | 2016-07-06 | 国家科学研究中心 | A wave shaping device, an electronic device, and a system |
| CN105633584A (en) * | 2015-12-30 | 2016-06-01 | 中国电子科技集团公司第三十九研究所 | Log periodic feed source array based on spaceborne multi-beam antenna space three-dimensional structure layout |
| CN207217741U (en) * | 2017-10-13 | 2018-04-10 | 南京瑞安腾企业管理咨询有限公司 | A kind of high flux satellite network signal ship-board antenna |
Non-Patent Citations (2)
| Title |
|---|
| 刘天雄: "《卫星导航系统概论》", 30 November 2018, 中国宇航出版社 * |
| 景莉莉等: "航天器用双层双面立体布局及装配技术", 《空间电子技术》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111918535A (en) * | 2020-08-17 | 2020-11-10 | 中国科学院微小卫星创新研究院 | Spaceborne and ground single-phase fluid loop heat dissipation system |
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Application publication date: 20200211 |
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