CN111431587A - Communication satellite return link and forward link testing method - Google Patents
Communication satellite return link and forward link testing method Download PDFInfo
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- CN111431587A CN111431587A CN202010340285.9A CN202010340285A CN111431587A CN 111431587 A CN111431587 A CN 111431587A CN 202010340285 A CN202010340285 A CN 202010340285A CN 111431587 A CN111431587 A CN 111431587A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18517—Transmission equipment in earth stations
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B1/00—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission
- H04B1/005—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission adapting radio receivers, transmitters andtransceivers for operation on two or more bands, i.e. frequency ranges
- H04B1/0053—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission adapting radio receivers, transmitters andtransceivers for operation on two or more bands, i.e. frequency ranges with common antenna for more than one band
- H04B1/006—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission adapting radio receivers, transmitters andtransceivers for operation on two or more bands, i.e. frequency ranges with common antenna for more than one band using switches for selecting the desired band
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B3/00—Line transmission systems
- H04B3/54—Systems for transmission via power distribution lines
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L43/00—Arrangements for monitoring or testing data switching networks
- H04L43/50—Testing arrangements
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Radio Relay Systems (AREA)
Abstract
The invention belongs to the technical field of communication satellite ground test. The embodiment of the invention provides a testing method for a return link of a communication satellite, which uses a shunt component, wherein an uplink signal is gated and shunted through the shunt component, and the shunt component comprises a power divider and a switch; the invention also provides a communication satellite forward link testing method, which is characterized in that the forward link testing method uses a combining component, downlink signals are gated and combined through the combining component, and the combining component comprises a switch and a combiner. The invention can effectively reduce cabin-penetrating plugs and cables for testing and improve the testing efficiency.
Description
Technical Field
The invention belongs to the technical field of communication satellite ground test, and particularly relates to a method for testing a return link and a forward link of a communication satellite.
Background
Communications satellites require load testing on the ground, including forward link and return link testing. The traditional communication satellite transponder has fewer paths (less than 10 paths), the communication cabin has fewer test configurations (less than 100 paths), and a conventional test method can be adopted. However, in the newly developed high-throughput communication satellite in China, more than 90 user beams are configured for the whole satellite, the number of test configurations which completely cover all working conditions is as high as 4000, and the minimum number of test configurations is 1300 by optimizing and reducing the configurations. If adopt traditional communication cabin test mode, need use more than 90 cable junction ground equipment and satellite to go up waveguide (ripples with the conversion mouth), the problem that brings like this has: 1. when a communication cabin (along with the whole satellite) thermal vacuum test is carried out, more than 180 cables and more than 180 wall-penetrating connectors are required inside and outside a vacuum tank during the thermal test, and the scheme is not feasible; 2. the beam switching and synthesizing efficiency is low, and the testing time is long.
Disclosure of Invention
The embodiment of the invention mainly aims to provide a method for testing a return link and a forward link of a communication satellite, which can effectively reduce cabin-penetrating plugs and cables for testing and improve the testing efficiency.
In order to achieve the above object, an embodiment of the present invention provides a method for testing a return link of a communication satellite, where the method for testing a return link of a communication satellite uses a branch component through which an uplink signal is gated and branched, and the branch component includes a power divider and a switch. The embodiment of the invention can effectively reduce cabin penetrating plugs and cables for testing and improve the testing efficiency.
The embodiment of the invention also provides a method for testing the forward link of the communication satellite, wherein the method for testing the forward link uses a combining component, downlink signals are gated and combined through the combining component, and the combining component comprises a switch and a combiner. The embodiment of the invention can effectively reduce cabin penetrating plugs and cables for testing and improve the testing efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required to be used in the description of the embodiments will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive labor.
FIG. 1 is a method for testing a return link and a forward link of a communication satellite;
FIG. 2 is a shunt assembly;
fig. 3 is a combining assembly.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
As shown in fig. 1, an embodiment of the present invention provides a return link testing method for a communication satellite, which uses a branch component through which an uplink signal is gated and branched. As shown in fig. 2, the shunt component includes a power divider and a switch. The embodiment of the invention can effectively reduce cabin penetrating plugs and cables for testing and improve the testing efficiency. The test flow of the embodiment of the invention is as follows: (1) installing a communication cabin transponder, namely a communication satellite load, connecting a cable and installing a high-power waveguide load; (2) carrying out test system, namely ground equipment calibration and cable and high-power waveguide load calibration (attenuation value); (3) according to the attached figure 1, a communication cabin transponder, a test system, a shunt component, a wave synchronization conversion component, a combiner component, a cable and a high-power waveguide load are connected; (4) starting up and self-checking a test system; (5) starting up a communication bin transponder; (6) setting parameters such as the state and the gear of a communication cabin transponder according to specific configuration requirements in test rules, testing and recording main electrical properties from an input port of a corresponding input test coupler to a coupling port of an output test coupler; (7) and sending a power-off command sequence of the communication cabin equipment to complete the test, and the following describes the invention in detail by combining the attached drawings.
Preferably, the power divider is a 1-to-8 power divider, as shown in fig. 2. The number of test bulkhead plugs and cables can be reduced to 1/8 and the test efficiency can be improved.
Preferably, the method is applied to single-channel uplink signal testing and multi-channel simultaneous uplink signal testing in a thermal vacuum scene. The number of cabin penetrating plugs and cables for testing can be reduced, so that a thermal vacuum scene can be kept, and the testing efficiency is improved.
Preferably, the uplink signals are 90 uplink ku frequency band user beams. The cabin penetrating plugs and cables for testing can be effectively reduced, and the testing efficiency is improved.
Preferably, the communications satellite is a multi-spot beam, multi-transponder communications satellite. The cabin penetrating plugs and cables for testing can be effectively reduced, and the testing efficiency is improved.
Preferably, the communications satellite is a high-throughput communications satellite. The cabin penetrating plugs and cables for testing can be effectively reduced, and the testing efficiency is improved.
Considering the polarization condition of the wave beams, a certain type of high-flux communication satellite returns to more than 90 uplink Ku frequency band user wave beams and about 10 downlink Ka frequency band gateway wave beams. The Ka feed down connection can adopt the traditional connection scheme, namely, each path of down output direct port is connected with Ka high-power load for power absorption, and the test coupling port is directly connected to the ground switch matrix 2 (figure 1) through a test cable. At the upstream of the front-end user beam signal (switch matrix 1), gating and shunting can be carried out through a 1-in-8-shunting component so as to reduce the connection quantity of the switch matrix to the satellite. The shunt component is shown in figure 2, and adopts a power divider combined with a switch mode, so that the single-channel uplink signal test of a conventional test project is supported, and the requirement of a thermal test on simultaneous uplink signals of multiple channels is met.
The embodiment of the invention can effectively reduce cabin-penetrating plugs and cables for testing, improve the testing efficiency and solve the problems caused by the fact that more than 90 cables are required to be used for connecting the ground equipment and the satellite uplink waveguide (wave common conversion port) in the traditional communication cabin testing mode: 1. when a communication cabin (along with the whole satellite) thermal vacuum test is carried out, more than 180 cables and more than 180 wall-penetrating connectors are required inside and outside a vacuum tank during the thermal test, and the scheme is not feasible; 2. the beam switching and synthesizing efficiency is low, and the testing time is long.
As shown in fig. 1, an embodiment of the present invention further provides a method for testing a forward link of a communication satellite, where the method for testing a forward link uses a combining component, and a downlink signal is gated and combined by the combining component. As shown in fig. 3, the combining assembly includes a switch and a combiner. The embodiment of the invention can effectively reduce cabin penetrating plugs and cables for testing and improve the testing efficiency. The test flow of the embodiment of the invention is as follows: (1) installing a communication cabin transponder, namely a communication satellite load, connecting a cable and installing a high-power waveguide load; (2) carrying out test system, namely ground equipment calibration and cable and high-power waveguide load calibration (attenuation value); (3) according to the attached figure 1, a communication cabin transponder, a test system, a shunt component, a wave synchronization conversion component, a combiner component, a cable and a high-power waveguide load are connected; (4) starting up and self-checking a test system; (5) starting up a communication bin transponder; (6) setting parameters such as the state and the gear of a communication cabin transponder according to specific configuration requirements in test rules, testing and recording main electrical properties from an input port of a corresponding input test coupler to a coupling port of an output test coupler; (7) and sending a power-off command sequence of the communication cabin equipment to complete the test, and the following describes the invention in detail by combining the attached drawings.
Preferably, the combiner is an 8-in-1 combiner, as shown in fig. 3. The number of test bulkhead plugs and cables can be reduced to 1/8 and the test efficiency can be improved.
Preferably, the method is applied to single-channel downlink signal testing and multi-channel simultaneous downlink signal testing in a thermal vacuum scene. The number of cabin penetrating plugs and cables for testing can be reduced, so that a thermal vacuum scene can be kept, and the testing efficiency is improved.
Preferably, the downlink signal is a 90-path downlink ku-band user beam. The cabin penetrating plugs and cables for testing can be effectively reduced, and the testing efficiency is improved.
Preferably, the communications satellite is a multi-spot beam, multi-transponder communications satellite. The cabin penetrating plugs and cables for testing can be effectively reduced, and the testing efficiency is improved.
Preferably, the communications satellite is a high-throughput communications satellite. The cabin penetrating plugs and cables for testing can be effectively reduced, and the testing efficiency is improved.
Considering the wave beam polarization condition, the forward direction of a certain type of high-flux communication satellite has 10 uplink Ka frequency band feed wave beams in total and about 90 downlink Ku frequency band user wave beams in total. The forward transponder feed beam Ka uplink can adopt the traditional connection scheme, namely installing Ka wave simultaneous transformation at a waveguide port, and then adopting cable connection (a switch matrix 1); the forward transponder user wave beam Ku downlink part has large quantity of paths, and the connection of a high-power absorption path and a small signal test path needs to be considered at the same time. And an 8-in-1 combiner component is adopted for gating and combining so as to reduce the connection quantity from the switch matrix 2 to the satellite terminal. The combiner assembly is shown in figure 3, and adopts a switch and combiner mode, so that the single-channel downlink signal test of a conventional test item is supported, and the simultaneous monitoring requirement of the thermal test multi-channel downlink signals is met.
The embodiment of the invention can effectively reduce cabin-penetrating plugs and cables for testing, improve the testing efficiency and solve the problems caused by the fact that more than 90 cables are required to be used for connecting the ground equipment and the satellite uplink waveguide (wave common conversion port) in the traditional communication cabin testing mode: 1. when a communication cabin (along with the whole satellite) thermal vacuum test is carried out, more than 180 cables and more than 180 wall-penetrating connectors are required inside and outside a vacuum tank during the thermal test, and the scheme is not feasible; 2. the beam switching and synthesizing efficiency is low, and the testing time is long.
It will be understood by those skilled in the art that all or part of the steps in the method for implementing the above embodiments may be implemented by relevant hardware instructed by a program, and the program may be stored in a computer readable storage medium, such as ROM/RAM, magnetic disk, optical disk, etc.
The above-mentioned embodiments are intended to illustrate the objects, technical solutions and advantages of the present invention in further detail, and it should be understood that the above-mentioned embodiments are only exemplary embodiments of the present invention, and are not intended to limit the scope of the present invention, and any modifications, equivalent substitutions, improvements and the like made within the spirit and principle of the present invention should be included in the scope of the present invention.
Claims (12)
1. A communication satellite return link test method is characterized in that the return link test method uses a shunt component through which an uplink signal is gated and shunted, and the shunt component comprises a power divider and a switch.
2. The method of claim 1, wherein the power divider is a 1-to-8 power divider.
3. The communication satellite return link testing method of claim 1, wherein said method is applied to single channel uplink signal testing and thermal vacuum scenario multi-channel simultaneous uplink signal testing.
4. The method according to claim 1, wherein the uplink signal comprises 90 uplink ku band user beams.
5. The method of claim 1, wherein said communication satellite is a multi-spot beam, multi-transponder communication satellite.
6. The communication satellite return link testing method of claim 4, wherein said communication satellite is a high throughput communication satellite.
7. A forward link test method of a communication satellite is characterized in that the forward link test method uses a combiner component, downlink signals are gated and combined through the combiner component, and the combiner component comprises a switch and a combiner.
8. The method of claim 7, wherein the combiner is an 8-in-1 combiner.
9. The method of claim 7, wherein said method is applied to single channel downlink signal testing and thermal vacuum scenario multi-channel simultaneous downlink signal testing.
10. The method according to claim 7, wherein the downlink signal is 90 downlink ku band user beams.
11. The method of claim 7 wherein said communications satellite is a multi-spot beam, multi-transponder communications satellite.
12. The communication satellite forward link test method of claim 11 wherein said communication satellite is a high throughput communication satellite.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202010340285.9A CN111431587A (en) | 2020-04-26 | 2020-04-26 | Communication satellite return link and forward link testing method |
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| CN202010340285.9A CN111431587A (en) | 2020-04-26 | 2020-04-26 | Communication satellite return link and forward link testing method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114389731A (en) * | 2022-01-19 | 2022-04-22 | 中国人民解放军32039部队 | Automatic on-orbit testing system and method for communication satellite |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6407986B1 (en) * | 1996-09-30 | 2002-06-18 | Mobile Satellite Ventures Lp | Methods of dynamically switching return channel transmissions of time-division multiple-access (TDMA) communication systems between signaling burst transmissions and message transmissions |
| CN105049108A (en) * | 2015-06-30 | 2015-11-11 | 中国空间技术研究院 | High-power mobile broadcasting GEO satellite device and transmission method |
| CN105119028A (en) * | 2015-07-14 | 2015-12-02 | 西安空间无线电技术研究所 | Satellite bandwidth switchable cross-linking repeater realized by microwave switch matrix |
| CN106199508A (en) * | 2016-06-17 | 2016-12-07 | 中国科学院国家授时中心 | A kind of multifunction test platform based on pseudo satellite, pseudolite principle |
| CN106911404A (en) * | 2017-03-08 | 2017-06-30 | 中国空间技术研究院 | A kind of method of testing of the transponder channel frequence response based on arrow net |
| CN106990417A (en) * | 2017-03-08 | 2017-07-28 | 中国空间技术研究院 | A kind of satellite repeater test system calibration method |
| CN108964697A (en) * | 2018-07-19 | 2018-12-07 | 航天恒星科技有限公司 | A kind of digital channelizing transponder system and retransmission method realized based on FPGA |
| CN109286449A (en) * | 2018-10-08 | 2019-01-29 | 中兵通信科技股份有限公司 | A kind of equipment tester of error code testing and analog satellite transponder |
| CN110474971A (en) * | 2019-08-05 | 2019-11-19 | 西安天宸量子通信技术有限公司 | A kind of wide area low-power consumption Internet of Things communication system and its transmission method |
-
2020
- 2020-04-26 CN CN202010340285.9A patent/CN111431587A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6407986B1 (en) * | 1996-09-30 | 2002-06-18 | Mobile Satellite Ventures Lp | Methods of dynamically switching return channel transmissions of time-division multiple-access (TDMA) communication systems between signaling burst transmissions and message transmissions |
| CN105049108A (en) * | 2015-06-30 | 2015-11-11 | 中国空间技术研究院 | High-power mobile broadcasting GEO satellite device and transmission method |
| CN105119028A (en) * | 2015-07-14 | 2015-12-02 | 西安空间无线电技术研究所 | Satellite bandwidth switchable cross-linking repeater realized by microwave switch matrix |
| CN106199508A (en) * | 2016-06-17 | 2016-12-07 | 中国科学院国家授时中心 | A kind of multifunction test platform based on pseudo satellite, pseudolite principle |
| CN106911404A (en) * | 2017-03-08 | 2017-06-30 | 中国空间技术研究院 | A kind of method of testing of the transponder channel frequence response based on arrow net |
| CN106990417A (en) * | 2017-03-08 | 2017-07-28 | 中国空间技术研究院 | A kind of satellite repeater test system calibration method |
| CN108964697A (en) * | 2018-07-19 | 2018-12-07 | 航天恒星科技有限公司 | A kind of digital channelizing transponder system and retransmission method realized based on FPGA |
| CN109286449A (en) * | 2018-10-08 | 2019-01-29 | 中兵通信科技股份有限公司 | A kind of equipment tester of error code testing and analog satellite transponder |
| CN110474971A (en) * | 2019-08-05 | 2019-11-19 | 西安天宸量子通信技术有限公司 | A kind of wide area low-power consumption Internet of Things communication system and its transmission method |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114389731A (en) * | 2022-01-19 | 2022-04-22 | 中国人民解放军32039部队 | Automatic on-orbit testing system and method for communication satellite |
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