CN113067631A - Laser communication load ground test method under whole-satellite condition - Google Patents
Laser communication load ground test method under whole-satellite condition Download PDFInfo
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- H—ELECTRICITY
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- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/07—Arrangements for monitoring or testing transmission systems; Arrangements for fault measurement of transmission systems
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B10/00—Transmission systems employing electromagnetic waves other than radio-waves, e.g. infrared, visible or ultraviolet light, or employing corpuscular radiation, e.g. quantum communication
- H04B10/07—Arrangements for monitoring or testing transmission systems; Arrangements for fault measurement of transmission systems
- H04B10/075—Arrangements for monitoring or testing transmission systems; Arrangements for fault measurement of transmission systems using an in-service signal
- H04B10/077—Arrangements for monitoring or testing transmission systems; Arrangements for fault measurement of transmission systems using an in-service signal using a supervisory or additional signal
- H04B10/0779—Monitoring line transmitter or line receiver equipment
Abstract
The invention relates to the field of space laser communication, and provides a laser communication load ground test method under the condition of a whole satellite, which comprises the following steps: carrying out ground wired test on the laser communication load under the condition of the whole satellite; and carrying out ground wireless test on the laser communication load under the condition of the whole satellite. The invention establishes a standardized ground test method and a standardized ground test flow of the laser communication load under the condition of the whole satellite by adopting the ground test equipment of the universal laser communication terminal and the ground test equipment of the satellite platform, and the test process has high reliability and strong applicability.
Description
Technical Field
The invention relates to the field of space laser communication, in particular to a laser communication load ground test method under the condition of a whole satellite.
Background
The satellite-borne laser communication takes extremely narrow laser as a carrier, and establishes a link in space to complete wireless data transmission. The laser communication has the advantages of high transmission rate, large communication capacity, strong anti-interference capability, high safety and confidentiality and the like, particularly has great application potential in the aspects of solving the bottleneck of radio frequency communication, constructing space-based networking and the like, and has urgent requirements on the application of satellite-borne laser communication in the military aspect. Therefore, satellite-borne laser communication becomes one of the development trends of future satellite communication links, and the research enthusiasm of various aerospace strong countries is triggered.
The existing ground test method for the satellite communication load under the condition of the whole satellite in China mainly aims at the radio frequency communication load, and because the laser communication terminal introduces the test content of an optical system, the load function and the interface between the laser communication terminal and the satellite are greatly changed, so that the adaptive ground test system needs to be re-developed, and the existing ground test equipment for the radio frequency load and the test verification process cannot be directly adopted. In addition, as the laser communication terminal carried on the satellite platform in China starts late to perform on-orbit verification, and a mature and standardized test method and test flow can not be used for reference, the problems of incompatible test method, inconsistent test flow, inconsistent test items, too many test mode combinations, difficult test environment construction and the like exist when the terminals of different manufacturers perform ground test verification in the whole satellite environment, so that the reliability of a test system is low, the applicability is not enough, the test cost is high, and the study and the inheritance of the test method are not facilitated.
Disclosure of Invention
The invention provides a ground test method for a laser communication load under the condition of a whole satellite, aiming at the problems that the ground test method for the radio frequency communication load under the whole satellite state in the prior art is not suitable for the laser communication load test, and the test system reliability is not high, the applicability is not enough and the test cost is high when the ground butt joint test is carried out by the laser communication load terminals of different manufacturers under the whole satellite environment, the ground test method for the laser communication load under the whole satellite condition comprises the following steps:
the ground wired test of the laser communication load under the condition of the whole satellite comprises the following steps:
connecting a test interface of the satellite platform and peripheral reference equipment by using optical fibers, and calibrating optical power;
establishing a laser link between the satellite platform and peripheral equipment for participating in test;
receiving, by a satellite platform, a signal;
judging the receiving correctness of the satellite platform according to the signals received by the satellite platform;
recording the signals, and filling the result of the correctness received by the satellite platform into a test record table;
configuring network parameters of a satellite platform; and
testing the correctness and the matching of the two-way communication of the satellite platform; and
and carrying out ground wireless test on the laser communication load under the condition of the whole satellite.
In the present invention, the term "whole satellite condition" refers to the satellite load integrated on the satellite platform.
In one embodiment of the invention it is provided that the peripheral participant device comprises one or more of the following: the optical fiber space optical interface interchange device comprises an optical wavelength meter, an optical power meter, an oscilloscope, an optical combiner, an optical splitter, an optical attenuator, an optical fiber delayer and an optical fiber space optical interface interchange device.
In one embodiment of the invention, it is provided that establishing a laser link between the satellite platform and the peripheral reference device comprises: and the satellite platform sends a remote control command to set the symbol rate of the peripheral equipment to be tested so as to establish a laser link.
In one embodiment of the invention, it is provided that the signals received by the satellite platform comprise: the monitoring value of the optical power and the telemetering information, wherein the telemetering information comprises a locking mark, CRC information, decoding information and a bit error rate.
In one embodiment of the invention, it is provided that the network parameters comprise one or more of the following: link configuration table, link establishment schedule table, and static routing table.
In one embodiment of the invention, the test for the correctness and the matching of the bidirectional communication of the satellite platform comprises the following steps:
generating data by a first satellite platform and transmitting to a second satellite platform;
forwarding, by the second satellite platform, the received data to the ground detection device of the second satellite platform;
receiving and storing data by the ground detection device of the second satellite platform;
comparing the data sent by the first satellite platform with the data received by the second ground detection equipment to check the correctness and the matching of the data forwarded by the second satellite platform to the first satellite platform, and filling the test results of the correctness and the matching into a test record table; and
and interchanging the transceiving of the first satellite platform and the second satellite platform and repeating the steps.
In one embodiment of the invention, the ground wireless test of the laser communication load under the condition of the whole satellite comprises the following steps:
configuring a test platform, the test platform comprising: a collimator and a surveillance camera.
Pairing laser communication loads on a satellite platform;
aligning the laser communication load with the optical axis of the collimator;
setting the wavelength and the polarization state of a laser communication load transmitting/receiving space optical signal;
adjusting the attenuation value of the wireless space optical link and the beacon light and signal light emission power of the laser communication load;
setting an initial offset value of a laser communication load;
capturing and tracking beacon light of a laser communication load;
when the beacon light of the laser communication load stably tracks in a signal light tracking field, signal light tracking of the laser communication load is carried out;
when the tracking detector of the laser communication load continuously detects the optical signal, switching to the fine tracking detector of the laser communication load, reading the capturing time and filling the capturing time into a test record table;
when the output signal level of the fine tracking detector of the laser communication load keeps the communication requirement, capturing and phase-locking the signal light frequency of the laser communication load to complete correct demodulation of fixed data so as to complete link establishment, reading link establishment time and filling the link establishment time into a test record table; and
and turning off the beacon light when the laser communication load keeps the fine tracking mode for more than 60 seconds, detecting and evaluating the stability of the capture tracking of the laser communication load according to the monitoring image of the monitoring camera to obtain tracking accuracy, and filling the tracking accuracy into a test record table.
In one embodiment of the invention, it is provided that performing acquisition tracking of a beacon light of a laser communication payload comprises:
scanning by the first laser communication load, staring at the second laser communication load, and monitoring and timing the scanning condition of the first laser communication load by the monitoring camera;
after the second laser communication load receives the beacon light of the first laser communication load, the self direction is automatically adjusted, so that the beacon light of the second laser communication load aims at the first laser communication load; and
and after the first laser communication load receives the beacon light of the second laser communication load, stopping scanning and automatically adjusting the self direction so as to aim the beacon light of the first laser communication load at the second laser communication load.
In an embodiment of the present invention, it is provided that the method further includes traversing preset test conditions, including:
the test platform also comprises a two-dimensional satellite turntable, and the rotation state of the two-dimensional satellite turntable is set so as to simulate the orbital motion of a satellite;
ephemeris information is injected into the satellite platform; and
the initial bias values for the simulated conditions and the laser communication load are changed.
In one embodiment of the invention, it is provided that the method further comprises: the roles of scanning and capturing of the first laser communication payload and the second laser communication payload are swapped.
The invention has at least the following beneficial effects: a laser communication load ground test method and a laser communication load ground test flow under a standardized whole-satellite condition are established by adopting universal laser communication terminal ground test equipment and satellite platform ground test equipment, and the test process has high reliability and strong applicability.
Drawings
To further clarify the advantages and features that may be present in various embodiments of the present invention, a more particular description of various embodiments of the 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, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
Fig. 1 shows a connection diagram of an apparatus for ground wired testing of laser communication payload under whole-star conditions in one embodiment of the present invention.
Fig. 2 shows a connection diagram of an apparatus for ground-based wireless testing of laser communication payload under full-satellite conditions in an embodiment of the invention.
Detailed Description
It should be noted that the components in the figures may be exaggerated and not necessarily to scale for illustrative purposes. In the figures, identical or functionally identical components are provided with the same reference symbols.
In the present invention, "disposed on …", "disposed over …" and "disposed over …" do not exclude the presence of an intermediate therebetween, unless otherwise specified. Further, "disposed on or above …" merely indicates the relative positional relationship between two components, and may also be converted to "disposed below or below …" and vice versa in certain cases, such as after reversing the product direction.
In the present invention, the embodiments are only intended to illustrate the aspects of the present invention, and should not be construed as limiting.
In the present invention, the terms "a" and "an" do not exclude the presence of a plurality of elements, unless otherwise specified.
It is further 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, given the teachings of the present invention, required components or assemblies may be added as needed in a particular scenario. Furthermore, features from different embodiments of the invention may be combined with each other, unless otherwise indicated. For example, a feature of the second embodiment may be substituted for a corresponding or functionally equivalent or similar feature of the first embodiment, and the resulting embodiments are likewise within the scope of the disclosure or recitation of the present application.
It is also noted herein that, within the scope of the present invention, the terms "same", "equal", and the like do not mean that the two values are absolutely equal, but allow some reasonable error, that is, the terms also encompass "substantially the same", "substantially equal". By analogy, in the present invention, the terms "perpendicular", "parallel" and the like in the directions of the tables also cover the meanings of "substantially perpendicular", "substantially parallel".
The numbering of the steps of the methods of the present invention does not limit the order of execution of the steps of the methods. Unless specifically stated, the method steps may be performed in a different order.
The invention is further elucidated with reference to the drawings in conjunction with the detailed description.
The technical scheme adopted by the embodiment comprises a wired docking test between laser satellites and a wireless docking test between the laser satellites, wherein the wired docking test is used for checking whether a bidirectional laser communication link of the laser terminal with the satellite is correctly decoded, whether the relevant field data of a transmission frame is correctly analyzed, whether a network protocol is correctly operated and testing the relevant functions and performances of bidirectional communication; and verifying the space optical scanning staring capture following process, testing the capture time and the capture probability and testing the communication performance of the space laser link through a wireless docking test.
Wired butt joint participating in equipment includes: the system comprises a to-be-butted test satellite platform with a laser communication terminal, a double-end laser terminal ground detection device, an optical wavelength meter, an optical power meter, an oscilloscope, an optical combiner, an optical splitter, an optical attenuator, an optical fiber time delay device and an optical fiber space optical interface interchange device;
the wireless docking participating device comprises: the system comprises a to-be-butted test satellite platform with a laser communication terminal, double-end laser terminal ground detection equipment, a direct-current power supply, an optical power meter, a high-precision two-dimensional satellite rotary table, a collimator, an optical fiber coupler, an optical attenuator and a monitoring camera.
Before starting a butt joint test, confirming the electromechanical thermal interface function and performance of the laser terminal on the whole satellite platform to ensure that the technical state of carrying out a laser communication load ground butt joint test is achieved; checking the state of the equipment to be tested, confirming whether the equipment to be tested, the instrument, the matched cable and the optical fiber are complete or not, and ensuring that the functions, the performance and the valid period of the equipment meet the use requirements; preparing the relevant test data such as test outline, test detailed rule and test record table.
The wired butt joint test of the laser communication load under the condition of the whole satellite comprises the following steps:
connecting an optical fiber to a satellite platform wired test interface reserved for a laser communication load, and connecting peripheral equipment for participating in test; developing optical power calibration, comprising: adjusting the optical controllable attenuator, and setting the optical power of a link entrance as the optical power of a sensitivity threshold;
step two, double ends send satellite remote control instructions, symbol rate of satellite laser inter-satellite link terminal equipment is set, and a laser receiving and transmitting link between a satellite platform and laser inter-satellite link butt joint equipment is established;
after the satellite stably receives the signals, judging the receiving correctness of the satellite through relevant telemetering information such as a locking mark, CRC information, decoding information, an error rate and the like, recording the optical power monitoring value and the relevant telemetering information at the moment, and filling the test result into a test record table;
respectively configuring network parameters such as a link configuration table, a link establishment schedule table, a static routing table and the like of the double-end satellite platform according to the test cases;
fifthly, the A-end satellite platform simulates to generate data such as the satellite telemetering and the like, the data are sent to the B-end satellite platform through the laser terminal optical fiber output interface, the B-end satellite platform forwards the received A-end data to the B-end ground detection equipment through the laser data interface to receive and store the data, the information sent by the A-end satellite platform is compared with the information received by the B-end ground detection equipment, the correctness and the matching of the A-end data forwarded by the B-end satellite are checked, and the test result is filled in a test record table;
and step six, exchanging the satellite platform at the A, B end for receiving and transmitting, repeating the step five, and filling the test result into a test record table.
The wireless butt joint test of laser communication load under whole star condition includes:
step one, matching laser communication loads (laser terminals) of a satellite platform to be tested according to a test case, wherein the two matched terminals are respectively numbered as a device A to be tested (laser terminal A) and a device B to be tested (laser terminal B) to be tested for distinguishing;
step two, aligning the laser terminal A and the laser terminal B with the optical axis of the collimator of the test platform respectively;
setting the emission wavelength and the polarization state of the space optical signals emitted/received by the laser terminal A and the laser terminal B according to the test detailed rule, so that the light received and emitted by the two ends can be matched;
adjusting the attenuation value of the wireless space optical link and the beacon light and signal light emission power of the laser terminal A and the laser terminal B, so that the beacon light and signal light power received by the entrance pupils of the laser terminal A and the laser terminal B reach a specified light power value;
step five, setting initial bias values of the two laser terminals according to the test case, and starting corresponding test condition simulation;
step six, according to the capturing and tracking process, the laser terminal A starts scanning, the laser terminal B starts staring, the test platform monitors the scanning condition of the laser terminal A by a camera, and timing is started from the scanning;
step seven, after the laser terminal B receives the beacon light of the laser terminal A, automatically adjusting the self direction according to the tracking process to enable the beacon light to aim at the laser terminal A;
step eight, after the laser terminal A receives the beacon light of the laser terminal B, stopping scanning according to the tracking flow, and automatically adjusting the self direction to enable the beacon light to aim at the laser terminal B; the two ends stably track the beacon light of the opposite side in a signal light tracking field and switch to signal light tracking;
step nine, under the condition that the tracking detector continuously detects the optical signal, switching to a fine tracking mode, wherein the read timing value is the capture time;
step ten, when the laser terminal A, B precisely tracks the output signal level of the detector to meet the communication requirement and keeps the required time period, starting signal light frequency capture and phase locking to finish the correct demodulation of fixed data, the link has the measurement communication condition, the link building process is finished, and the read timing value is the link building time; filling the two timing results into a test record table;
step eleven, the laser terminal A, B keeps the fine tracking mode for more than 60s, the beacon light is turned off, the tracking stability of the two ends is detected and evaluated according to the monitoring images of the full-waveband monitoring cameras at the two ends, the tracking precision of the two ends is processed, and the result is filled in a test record table;
step twelve, setting a rotation state of the two-dimensional turntable according to the test case, wherein the rotation state is used for simulating the orbital motion of the satellite, injecting ephemeris information into the double-end satellite platform, changing the test simulation condition and the double-end initial bias value, and repeating the step one to the step eleven until various preset test working conditions are traversed;
step thirteen, exchanging A, B roles of the two-end reference equipment, changing the scanning end and the capturing end, repeating the steps one to twelve, and recording data.
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 persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention 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 (10)
1. A laser communication load ground test method under the condition of a whole satellite comprises the following steps:
the ground wired test of the laser communication load under the condition of the whole satellite comprises the following steps:
connecting a test interface of the satellite platform and peripheral reference equipment by using optical fibers, and calibrating optical power;
establishing a laser link between the satellite platform and peripheral equipment for participating in test;
receiving, by a satellite platform, a signal;
judging the receiving correctness of the satellite platform according to the signals received by the satellite platform;
recording the signals, and filling the result of the correctness received by the satellite platform into a test record table;
configuring network parameters of a satellite platform; and
testing the correctness and the matching of the two-way communication of the satellite platform; and
and carrying out ground wireless test on the laser communication load under the condition of the whole satellite.
2. The laser communication payload ground test method of claim 1, wherein the peripheral reference device comprises one or more of: the optical fiber space optical interface interchange device comprises an optical wavelength meter, an optical power meter, an oscilloscope, an optical combiner, an optical splitter, an optical attenuator, an optical fiber delayer and an optical fiber space optical interface interchange device.
3. The ground test method for laser communication loads under whole-satellite conditions according to claim 1, wherein establishing a laser link between the satellite platform and the peripheral reference device comprises: and the satellite platform sends a remote control command to set the symbol rate of the peripheral equipment to be tested so as to establish a laser link.
4. The ground test method for laser communication loads under whole-satellite conditions according to claim 1, wherein the signals received by the satellite platform comprise: the monitoring value of the optical power and the telemetering information, wherein the telemetering information comprises a locking mark, CRC information, decoding information and a bit error rate.
5. The laser communication load ground test method under whole-satellite conditions of claim 1, wherein the network parameters include one or more of: link configuration table, link establishment schedule table, and static routing table.
6. The ground test method for laser communication load under the condition of whole satellite according to claim 1, wherein the test for correctness and matching of the bidirectional communication of the satellite platform comprises the following steps:
generating data by a first satellite platform and transmitting to a second satellite platform;
forwarding, by the second satellite platform, the received data to the ground detection device of the second satellite platform;
receiving and storing data by the ground detection device of the second satellite platform;
comparing the data sent by the first satellite platform with the data received by the second ground detection equipment to check the correctness and the matching of the data forwarded by the second satellite platform to the first satellite platform, and filling the test results of the correctness and the matching into a test record table; and
and interchanging the transceiving of the first satellite platform and the second satellite platform and repeating the steps.
7. The ground test method for the laser communication load under the whole-satellite condition according to claim 1, wherein the ground wireless test for the laser communication load under the whole-satellite condition comprises the following steps:
configuring a test platform, the test platform comprising: a collimator and a surveillance camera.
Pairing laser communication loads on a satellite platform;
aligning the laser communication load with the optical axis of the collimator;
setting the wavelength and the polarization state of a laser communication load transmitting/receiving space optical signal;
adjusting the attenuation value of the wireless space optical link and the beacon light and signal light emission power of the laser communication load;
setting an initial offset value of a laser communication load;
capturing and tracking beacon light of a laser communication load;
when the beacon light of the laser communication load stably tracks in a signal light tracking field, signal light tracking of the laser communication load is carried out;
when the tracking detector of the laser communication load continuously detects the optical signal, switching to the fine tracking detector of the laser communication load, reading the capturing time and filling the capturing time into a test record table;
when the output signal level of the fine tracking detector of the laser communication load keeps the communication requirement, capturing and phase-locking the signal light frequency of the laser communication load to complete correct demodulation of fixed data so as to complete link establishment, reading link establishment time and filling the link establishment time into a test record table; and
and turning off the beacon light when the laser communication load keeps the fine tracking mode for more than 60 seconds, detecting and evaluating the stability of the capture tracking of the laser communication load according to the monitoring image of the monitoring camera to obtain tracking accuracy, and filling the tracking accuracy into a test record table.
8. The ground test method for laser communication loads under whole-satellite conditions according to claim 7, wherein the capturing and tracking of the beacon light of the laser communication loads comprises:
scanning by the first laser communication load, staring at the second laser communication load, and monitoring and timing the scanning condition of the first laser communication load by the monitoring camera;
after the second laser communication load receives the beacon light of the first laser communication load, the self direction is automatically adjusted, so that the beacon light of the second laser communication load aims at the first laser communication load; and
and after the first laser communication load receives the beacon light of the second laser communication load, stopping scanning and automatically adjusting the self direction so as to aim the beacon light of the first laser communication load at the second laser communication load.
9. The ground test method for laser communication loads under the whole-satellite condition according to claim 7, further comprising traversing preset test conditions, including:
the test platform also comprises a two-dimensional satellite turntable, and the rotation state of the two-dimensional satellite turntable is set so as to simulate the orbital motion of a satellite;
ephemeris information is injected into the satellite platform; and
the initial bias values for the simulated conditions and the laser communication load are changed.
10. The ground test method for laser communication load under the condition of whole star according to one of claims 7 to 9, characterized by further comprising: the roles of scanning and capturing of the first laser communication payload and the second laser communication payload are swapped.
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| CN114221697A (en) * | 2022-02-21 | 2022-03-22 | 中北大学 | Wireless passive bidirectional laser communication module |
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Application publication date: 20210702 |