CN109164325B - Rapid detection method for electromagnetic compatibility of mass production satellite - Google Patents
Rapid detection method for electromagnetic compatibility of mass production satellite Download PDFInfo
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- CN109164325B CN109164325B CN201811123681.5A CN201811123681A CN109164325B CN 109164325 B CN109164325 B CN 109164325B CN 201811123681 A CN201811123681 A CN 201811123681A CN 109164325 B CN109164325 B CN 109164325B
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Abstract
The invention discloses a rapid detection method for electromagnetic compatibility of a mass production satellite, which comprises the following steps: detecting the electromagnetic compatibility of the flight mode of the active section; detecting the electromagnetic compatibility of the relay mode after the track is entered; carrying out electromagnetic compatibility detection in a data transmission playback mode; carrying out electromagnetic compatibility detection of a load and a data transmission starting mode; carrying out electromagnetic compatibility detection of a load and broadcast distribution starting mode; detecting the electromagnetic compatibility of the satellite in a full-state working mode; detecting the electromagnetic compatibility of the maximum working mode of the satellite; performing electromagnetic compatibility detection of a rotary table in a rotation-up working mode; and performing shadow mode electromagnetic compatibility detection.
Description
Technical Field
The invention relates to the technical field of satellite detection, in particular to a rapid detection method for electromagnetic compatibility of a mass production satellite.
Background
The satellite is a system with very dense, powerful and technically complex electronic and electrical equipment of various types, not only has wide frequency coverage, but also has highly concentrated various high-power equipment and high-sensitivity equipment, and has quite complex electromagnetic environment. In order to ensure that the satellite can withstand the internal and external electromagnetic environments encountered in the processes of development and transmission until in-orbit operation, and design normal work according to preset functions and performances to complete the in-orbit normal flight task, the experimental verification of the electromagnetic compatibility technology needs to be carried out in the process of the development of the whole satellite of the satellite, so as to test the working compatibility among subsystems when the satellite works.
Although the existing satellite system electromagnetic compatibility test standard is perfect, the test items are more, the test flow is complex, the mass production satellite to be tested has no pertinence, and the possible defects and hidden dangers of the whole satellite can not be rapidly eliminated after the problem occurs.
In order to overcome the problems that in the prior art, a satellite system has more electromagnetic compatibility test items, a test flow is complex, the pertinence is not achieved, and the possible defects and hidden dangers of the whole satellite cannot be rapidly eliminated after problems occur, a novel detection system and a novel detection method are urgently needed to solve the problems.
Disclosure of Invention
Aiming at the problems that in the prior art, a satellite system has more electromagnetic compatibility test items, a test flow is complex, the satellite system has no pertinence, and defects and hidden dangers possibly existing in the whole satellite cannot be rapidly eliminated after the problems occur, the invention provides a rapid detection method for electromagnetic compatibility of a mass production satellite according to one embodiment of the invention, which comprises the following steps:
detecting the electromagnetic compatibility of the flight mode of the active section;
detecting the electromagnetic compatibility of the relay mode after the track is entered;
carrying out electromagnetic compatibility detection in a data transmission playback mode;
carrying out electromagnetic compatibility detection of a load and a data transmission starting mode;
carrying out electromagnetic compatibility detection of a load and broadcast distribution starting mode;
detecting the electromagnetic compatibility of the satellite in a full-state working mode;
detecting the electromagnetic compatibility of the maximum working mode of the satellite;
performing electromagnetic compatibility detection of a rotary table in a rotation-up working mode; and
and carrying out shadow region mode electromagnetic compatibility detection.
In an embodiment of the present invention, a test system adopted by the method for rapidly detecting electromagnetic compatibility of mass production satellites includes:
the system comprises a Beidou transmitting antenna, a data transmission receiving antenna, a broadcast distribution receiving antenna, a measurement and control transmitting antenna, a radar transmitting antenna and a monitoring antenna;
the front-end equipment comprises an energy front-end, a satellite front-end, a Beidou simulator, a measurement and control front-end and special equipment thereof, a data transmission front-end and special equipment thereof, a signal analyzer and load special equipment; and
and the terminal equipment is connected with the front-end equipment through an Ethernet and comprises a control center, a housekeeping monitoring terminal, an attitude control monitoring terminal, a measurement and control monitoring terminal, a data transmission monitoring terminal and a load monitoring terminal.
In one embodiment of the invention, the test field adopted by the method for rapidly detecting the electromagnetic compatibility of the mass production satellite is a 3-meter-method anechoic chamber.
In an embodiment of the present invention, the method further includes determining the state of each subsystem in the current whole star state by using a wireless calibration method.
In one embodiment of the present invention, the wireless calibration includes uplink signal calibration, downlink signal calibration, and load calibration, wherein:
the uplink signal calibration is used for calibrating the total insertion loss from a transmission source in a field to an inlet of the satellite receiver and preparing for sensitivity test of the satellite receiver;
the downlink signal calibration mainly ensures that the level of an entrance of the ground detection equipment is a medium-intensity level so as to ensure that the ground detection equipment can normally receive data issued on the satellite; and
the load calibration adopts the wireless calibration of a radar antenna, an environment monitoring antenna is arranged beside the load antenna, and space signals which possibly enter the load and space signals generated by the whole satellite are monitored and intercepted.
In one embodiment of the present invention, the method for performing active segment flight mode electromagnetic compatibility detection further comprises:
powering up the whole satellite, controlling the power supply and the attitude and orbit, starting up the satellite affair and starting up the experiment;
the test control transponder and the transmitter are started;
checking whether there is an effect by a signal analyzer and telemetry;
if the influence is influenced, the problem is positioned as measurement and control; and
no effect, test pass.
In one embodiment of the present invention, the method for performing post-track relay mode electromagnetic compatibility detection further comprises:
on the basis of the active section flight mode, the Beidou satellite system is started;
checking whether there is an effect by a signal analyzer and telemetry;
if the influence is influenced, the problem is positioned to be Beidou;
no influence is caused, and the relay is started;
checking whether there is an effect by a signal analyzer and telemetry;
if the problem is influenced, the problem is positioned as a relay; and
and (4) no influence is caused, the relay is shut down, and the test is passed.
In one embodiment of the present invention, the method for performing electromagnetic compatibility detection in data transfer playback mode further comprises:
starting up the data transmission on the basis that the relay mode passes after the track is entered;
checking whether there is an effect by a signal analyzer and telemetry;
if the problem is influenced, the problem is positioned as data transmission; and
no effect, test pass.
In an embodiment of the present invention, the method for performing load and data transmission boot-mode electromagnetic compatibility detection further includes:
starting the load on the basis of passing the data transmission playback mode;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no influence, load shutdown, data transmission shutdown and test passing.
In an embodiment of the present invention, the method for detecting electromagnetic compatibility of a load and broadcast distribution boot mode further comprises:
on the basis of passing the data transmission playback mode, broadcasting, distributing and starting up;
starting up a load;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no influence, load shutdown, test pass.
In one embodiment of the present invention, the method for performing electromagnetic compatibility detection of the full-state operating mode of the satellite further comprises:
starting up the data transmission on the basis of passing the data transmission playback mode;
starting up a load;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no effect, test pass.
In one embodiment of the present invention, the method for performing the electromagnetic compatibility detection of the maximum operating mode of the satellite further comprises:
on the basis that the satellite full-state working mode passes, starting up the relay;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
and (4) no influence is caused, the relay is shut down, and the test is passed.
In one embodiment of the present invention, the method for performing the detection of the electromagnetic compatibility of the turntable spin-up operation mode further comprises:
rotating the rotary table on the basis of passing the maximum working mode of the satellite;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no effect, test pass.
In one embodiment of the present invention, the method of performing a shadow mode electromagnetic compatibility test further comprises:
the whole star is cut and prepared for inspection;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no effect, pass test and end test.
In one embodiment of the invention, the electromagnetic compatibility detection of the active segment flight mode, the after-track relay mode and the data transfer playback mode determines the interference source by observing the interference situation from the frequency spectrum of the signal analyzer after the single machines are sequentially started.
In an embodiment of the invention, the load data transmission starting mode, the load broadcast distribution starting mode, the satellite full-state working mode, the satellite maximum working mode, the turntable rotation-up working mode and the shadow region mode electromagnetic compatibility detection jointly judge whether other subsystems of the whole satellite have interference on load detection and reception by observing the frequency spectrum, remote measurement and load data of a signal analyzer, give out the reason of the result quick positioning problem through data import software, and process related problems.
The invention provides a rapid detection method for electromagnetic compatibility of a mass production satellite, which is characterized in that a detection system is set up in a specific test field, a detection flow is set based on multiple task modes of a whole satellite, the electromagnetic compatibility of the subsystems of the whole satellite in cooperative work in the multiple task modes is detected, and defects and hidden dangers in the aspect of electromagnetic compatibility which may influence the work of a load task can be timely found and rapidly eliminated. Compared with the existing satellite electromagnetic compatibility detection scheme, the detection system and the detection method can better perform electromagnetic compatibility tests on mass production satellites, and quickly eliminate possible defects and hidden dangers of the whole satellite.
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To further clarify the above and other advantages and features of the present invention, a more particular description of 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 testing system 100 for a rapid electromagnetic compatibility testing method for a production satellite according to an embodiment of the present invention.
Fig. 2 shows a schematic diagram 200 of a test site layout adopted by a rapid electromagnetic compatibility detection method for a production satellite according to an embodiment of the present invention.
Fig. 3 shows an electromagnetic compatibility detection general flow chart 300 of a rapid electromagnetic compatibility detection method for a production satellite according to an embodiment of the present invention.
Fig. 4A to 4I illustrate a sub-process of detecting electromagnetic compatibility of cooperative work in each task mode of a satellite in a method for rapidly detecting electromagnetic compatibility of a mass-produced satellite according to an embodiment of the present invention.
Fig. 5 shows a schematic data analysis situation of the whole satellite electromagnetic compatibility test software of the rapid mass production satellite electromagnetic compatibility detection method according to an embodiment of the present invention.
Detailed Description
In the following description, the invention is described with reference to various embodiments. One skilled in the relevant art will recognize, however, that the embodiments may be practiced without one or more of the specific details, or with other alternative and/or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of embodiments of the invention. Similarly, for purposes of explanation, specific numbers, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention may be practiced without specific details. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
It should be noted that, in the embodiments of the present invention, the process steps are described in a specific order, however, this is only for convenience of distinguishing the steps, and the order of the steps is not limited, and in different embodiments of the present invention, the order of the steps may be adjusted according to the adjustment of the process.
The invention provides a rapid detection method for electromagnetic compatibility of a mass production satellite, which is characterized in that a detection system is set up in a specific test field, a detection flow is set based on multiple task modes of a whole satellite, the electromagnetic compatibility of the subsystems of the whole satellite in cooperative work in the multiple task modes is detected, and defects and hidden dangers in the aspect of electromagnetic compatibility which may influence the work of a load task can be timely found and rapidly eliminated. Compared with the existing satellite electromagnetic compatibility detection scheme, the detection system and the detection method can better perform electromagnetic compatibility tests on mass production satellites, and quickly eliminate possible defects and hidden dangers of the whole satellite.
The following describes in detail the test system and test site setup required by a rapid electromagnetic compatibility testing method for a mass production satellite according to an embodiment of the present invention with reference to fig. 1 and 2. FIG. 1 illustrates a testing system 100 for a rapid electromagnetic compatibility testing method for a production satellite according to an embodiment of the present invention; fig. 2 shows a schematic diagram 200 of a test site layout adopted by a rapid electromagnetic compatibility detection method for a production satellite according to an embodiment of the present invention.
As shown in fig. 1, the test system 100 adopted by the rapid detection method for electromagnetic compatibility of a mass production satellite further includes a big dipper transmitting antenna, a data transmission receiving antenna, a broadcast distribution receiving antenna, a measurement and control transmitting antenna, a radar transmitting antenna and a monitoring antenna; the system comprises an energy front end, a house service front end, a Beidou simulator, a measurement and control front end and special equipment thereof, a data transmission front end and special equipment thereof, a signal analyzer and special load equipment; and the control center, the star affair monitoring terminal, the attitude control monitoring terminal, the measurement and control monitoring terminal, the data transmission monitoring terminal and the load monitoring terminal are connected with the front-end equipment through the Ethernet.
As shown in fig. 2, the test field adopted by the method for rapidly detecting the electromagnetic compatibility of the mass production satellite is a 3-meter-method anechoic chamber, the external dimension of the shielding shell of the main anechoic chamber is 9.1 meters by 8.1 meters by 6.75 meters (length by width by height), the internal clear space after the wave-absorbing material of the main anechoic chamber is laid is 8.0 meters by 6.9 meters by 6 meters (length by width by height), and the anechoic chamber has a good electromagnetic wave shielding effect and ensures the test environment; in a darkroom, the environment monitoring antenna is arranged beside the antenna 2 in consideration of the fact that a satellite turntable rotation-up working mode needs to be tested under a rotating condition, and the environment and the condition of the test are combined, so that the space environment signals detected and received by the antenna 2 can be effectively detected and received.
The system firstly adopts a wireless calibration method to determine the state of each subsystem in the current whole star state. The calibration includes signal calibration for both uplink and downlink. The uplink calibration is used for calibrating the total insertion loss from a transmission source in a field to an inlet of the satellite receiver and preparing for sensitivity test of the satellite receiver. The downlink calibration mainly ensures that the inlet level of the ground detection equipment is a medium-intensity level so as to ensure that the ground detection equipment can normally receive data issued on the satellite. The load calibration is realized by adopting the wireless calibration of a radar antenna, an environment monitoring antenna is arranged beside the load antenna, and space signals which possibly enter the load and space signals generated by the whole satellite are monitored and intercepted.
And according to the test requirements, designing specific test working condition modes, including an active section flight mode, a relay mode after orbit entering, a data transmission playback mode, a load and data transmission starting mode, a load and broadcast distribution starting mode, a satellite full-state working mode, a satellite maximum working mode, a turntable starting working mode and a shadow region mode.
Wherein, the first three working condition modes are respectively aimed at the interference analysis of the transponder receiving and transmitting; analyzing interference of relay transmission on measurement and control uplink and Beidou reception; and (4) analyzing the interference of the measurement and control downlink and the data transmission on the measurement and control uplink and the Beidou reception. The fourth to seventh working condition modes are to analyze the interference of load, measurement and control uplink and Beidou reception by measuring and controlling downlink, data transmission, broadcast distribution, relay transmitting startup or simultaneous startup in steps. And the eighth is to analyze the influence of the rotation of the turntable on the satellite under the full-state operation of the satellite (except for the relay). The last condition is to perform interference analysis in the whole satellite backup mode.
Each working condition is designed on the basis of the previous working condition, so that the testing steps are simplified.
A method for fast detecting electromagnetic compatibility of a production satellite according to an embodiment of the present invention is described in detail below with reference to fig. 3 and fig. 4A to 4I. FIG. 3 is a general flowchart 300 of electromagnetic compatibility testing for a rapid yield satellite electromagnetic compatibility testing method according to an embodiment of the present invention; fig. 4A to 4I illustrate a sub-process of detecting electromagnetic compatibility of cooperative work in each task mode of a satellite in a method for rapidly detecting electromagnetic compatibility of a mass-produced satellite according to an embodiment of the present invention.
First, in step 301, as shown in fig. 4A, an active segment flight mode electromagnetic compatibility test is performed. In one embodiment of the present invention, the specific detecting step includes: 1) starting a whole satellite power-up experiment, and starting a power supply, attitude and orbit control and satellite affairs; 2) the test control transponder and the transmitter are started; 3) checking whether there is an effect by a signal analyzer and telemetry; 4) a, if the influence is influenced, the problem is positioned as measurement and control; b. if no influence exists, the test is passed to the next step.
Next, at step 302, as shown in fig. 4B, a post-track relay mode electromagnetic compatibility test is performed. In another embodiment of the present invention, upon the test passing in step 301, the further detecting step comprises: 1) starting the Beidou satellite vehicle; 2) checking whether there is an effect by a signal analyzer and telemetry; 3) a, if the influence is influenced, the problem is positioned to be Beidou; b. if no influence exists, the relay is started; 4) checking whether there is an effect by a signal analyzer and telemetry; 3) a, if the influence is influenced, the problem is positioned as a relay; b. if no influence exists, the relay is shut down, and the next step is carried out after the test is passed.
Then, in step 303, as shown in fig. 4C, a data transfer playback mode electromagnetic compatibility test is performed. In one embodiment of the present invention, upon the test passing in step 302, further detecting steps include: 1) starting up the data transmission; 2) checking whether there is an effect by a signal analyzer and telemetry; 3) a, if the influence is influenced, the problem is positioned as data transmission; b. if no influence exists, the test is passed to the next step.
Next, at step 304, as shown in FIG. 4D, a load, data-transfer, power-on mode electromagnetic compatibility test is performed. In one embodiment of the present invention, upon the test passing in step 303, further detecting steps include: 1) starting up a load; 2) a, passing a signal analyzer and telemetering inspection; b. checking the payload data by data processing software; 3) jointly judging whether influence is caused; 4) a, if the influence is influenced, positioning and processing the problem according to the software result; b. if no influence exists, the test is passed; 5) and (4) load shutdown, data transmission shutdown and the next step.
Then, at step 305, as shown in FIG. 4E, a payload, broadcast distribution power-on mode electromagnetic compatibility test is performed. In one embodiment of the present invention, upon the test passing in step 304, further detecting steps include: 1) starting up the broadcast distribution; 2) starting up a load; 3) a, passing a signal analyzer and telemetering inspection; b. checking the payload data by data processing software; 4) is there an impact? (ii) a 5) a, if the influence is influenced, positioning and processing the problem according to the software result; b. if no influence exists, the test is passed; 6) and (4) shutting down the load and entering the next step.
Next, at step 306, as shown in FIG. 4F, a satellite full-state operating mode electromagnetic compatibility test is performed. In one embodiment of the present invention, upon the test passing in step 305, further testing steps include: 1) starting up the data transmission; 2) starting up a load; 3) a, passing a signal analyzer and telemetering inspection; b. checking the payload data by data processing software; 4) jointly judging whether influence is caused; 5) a, if the influence is influenced, positioning and processing the problem according to the software result; b. if no influence exists, the test is passed; 6) proceed to the next step.
Then, in step 307, as shown in FIG. 4G, a maximum operating mode electromagnetic compatibility test for the satellite is performed. In one embodiment of the present invention, upon the test passing in step 306, further testing steps include: 1) starting up a relay; 2) a, passing a signal analyzer and telemetering inspection; b. checking the payload data by data processing software; 3) jointly judging whether influence is caused; 4) a, if the influence is influenced, positioning and processing the problem according to the software result; b. if no influence exists, the relay is shut down, and the test is passed; 5) proceed to the next step.
Next, at step 308, as shown in fig. 4H, a turntable cranking operation mode electromagnetic compatibility test is performed. In one embodiment of the present invention, upon the test passing in step 307, further detecting steps include: 1) rotating the rotary table; 2) a, passing a signal analyzer and telemetering inspection; b. checking the payload data by data processing software; 3) jointly judging whether influence is caused; 4) a, if the influence is influenced, positioning and processing the problem according to the software result; b. if no influence exists, the test is passed; 5) proceed to the next step.
Finally, at step 309, as shown in FIG. 4H, a shadow mode electromagnetic compatibility test is performed. In one embodiment of the present invention, upon the test passing in step 308, further detection steps include: 1) the whole star is cut and prepared for inspection; 2) a, passing a signal analyzer and telemetering inspection; b. checking the payload data by data processing software; 3) jointly judging whether influence is caused; 4) a, if the influence is influenced, positioning and processing the problem according to the software result; b. if no influence exists, the test is passed; 5) the test was completed.
The first three operating modes can determine the interference source by observing the interference situation on the frequency spectrum by starting up the single machines in sequence. From the fourth working condition, whether the other subsystems of the whole satellite interfere with load detection can be jointly judged by observing the frequency spectrum, the remote measurement and the load data of the signal analyzer, and the reason of the problem of quick positioning of the result is given through data importing software, for example, a certain experimental data is shown in fig. 5, fig. 5 shows a data analysis condition of the whole satellite electromagnetic compatibility test software of the method for quickly detecting the electromagnetic compatibility of the mass production satellite provided by one embodiment of the invention, and it can be seen that each harmonic of a clock, a relayed 3-th harmonic and a broadcast 3-th harmonic exist in two rotation tests of the whole satellite experiment. Through the analysis of software on the problem, the on-satellite raised intermediate frequency detection threshold can be used for the interference of clock 60MHz, the 3-order harmonic of relay and the 3-order harmonic of broadcast under the condition of not influencing the sensitivity of indexes, or the interference can be quickly inhibited in a special frequency band attenuation mode, so that the original effect is achieved.
According to the rapid detection method for the electromagnetic compatibility of the mass production satellite, provided by the invention, a detection system is set up in a specific test field, a detection process is set based on multiple task modes of the whole satellite, the electromagnetic compatibility of the subsystems of the whole satellite in the cooperative work in the multiple task modes is detected, and defects and hidden dangers in the aspect of electromagnetic compatibility which possibly influence the work of a load task can be timely found and rapidly eliminated. Compared with the existing satellite electromagnetic compatibility detection scheme, the detection system and the detection method can better perform an electromagnetic compatibility test on the mass-production satellite to be tested, and can quickly eliminate possible defects and hidden dangers of the whole satellite.
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 (15)
1. A rapid detection method for mass production satellite electromagnetic compatibility comprises the following steps:
performing electromagnetic compatibility detection in an active section flight mode, and entering the next step when the detection is passed;
performing relay mode electromagnetic compatibility detection after track entry, and entering the next step when the test is passed;
performing electromagnetic compatibility detection in a data transmission playback mode, and entering the next step when the detection is passed;
carrying out load and data transmission startup mode electromagnetic compatibility detection, comprising: starting up a load; checking the load data by a signal analyzer and telemetry check, and by data processing software; jointly judging whether influence is caused; influencing, positioning and processing problems according to software results; no influence, load shutdown, data transmission shutdown, passing test and entering the next step;
carrying out electromagnetic compatibility detection of a load and broadcast distribution startup mode, and entering the next step when the test is passed;
performing electromagnetic compatibility detection of the satellite in a full-state working mode, and entering the next step when the electromagnetic compatibility detection passes;
performing electromagnetic compatibility detection of the maximum working mode of the satellite, and entering the next step when the electromagnetic compatibility detection passes;
performing electromagnetic compatibility detection of a rotary table rotation-up working mode, and entering the next step when the detection is passed; and
and carrying out shadow region mode electromagnetic compatibility detection.
2. The method of claim 1, wherein the method for rapidly detecting electromagnetic compatibility of mass production satellites adopts a test system comprising:
the system comprises a Beidou transmitting antenna, a data transmission receiving antenna, a broadcast distribution receiving antenna, a measurement and control transmitting antenna, a radar transmitting antenna and a monitoring antenna;
the front-end equipment comprises an energy front-end, a satellite front-end, a Beidou simulator, a measurement and control front-end and special equipment thereof, a data transmission front-end and special equipment thereof, a signal analyzer and load special equipment; and
and the terminal equipment is connected with the front-end equipment through an Ethernet and comprises a control center, a housekeeping monitoring terminal, an attitude control monitoring terminal, a measurement and control monitoring terminal, a data transmission monitoring terminal and a load monitoring terminal.
3. The method of claim 1, wherein the test site for the rapid electromagnetic compatibility test of mass production satellites is a 3-meter anechoic chamber.
4. The method of claim 1, further comprising using a wireless calibration method to determine the state of each subsystem in the current full star state.
5. The method of claim 4, wherein the wireless calibration comprises an uplink signal calibration, a downlink signal calibration, and a load calibration, wherein:
the uplink signal calibration is used for calibrating the total insertion loss from a transmission source in a field to an inlet of the satellite receiver and preparing for sensitivity test of the satellite receiver;
the downlink signal calibration mainly ensures that the level of an entrance of the ground detection equipment is a medium-intensity level so as to ensure that the ground detection equipment can normally receive data issued on the satellite; and
the load calibration adopts the wireless calibration of a radar antenna, an environment monitoring antenna is arranged beside the load antenna, and space signals which possibly enter the load and space signals generated by the whole satellite are monitored and intercepted.
6. The method of claim 1, wherein the method of performing active segment flight mode electromagnetic compatibility testing further comprises:
powering up the whole satellite, controlling the power supply and the attitude and orbit, starting up the satellite affair and starting up the experiment;
the test control transponder and the transmitter are started;
checking whether there is an effect by a signal analyzer and telemetry;
if the influence is influenced, the problem is positioned as measurement and control; and
no effect, test pass.
7. The method of claim 1, wherein the method of performing post-track relay mode electromagnetic compatibility testing further comprises:
on the basis that the electromagnetic compatibility detection of the flight mode of the active section passes, the Beidou satellite vehicle is started;
checking whether there is an effect by a signal analyzer and telemetry;
if the influence is influenced, the problem is positioned to be Beidou;
no influence is caused, and the relay is started;
checking whether there is an effect by a signal analyzer and telemetry;
if the problem is influenced, the problem is positioned as a relay; and
and (4) no influence is caused, the relay is shut down, and the test is passed.
8. The method of claim 1, wherein the method of performing data transfer playback mode electromagnetic compatibility testing further comprises:
starting up the data transmission on the basis that the relay mode electromagnetic compatibility detection passes after the track is entered;
checking whether there is an effect by a signal analyzer and telemetry;
if the problem is influenced, the problem is positioned as data transmission; and
no effect, test pass.
9. The method of claim 1, wherein the method of performing payload, broadcast distribution power-on mode electromagnetic compatibility detection further comprises:
on the basis that the electromagnetic compatibility detection of the load and data transmission startup modes passes, broadcasting, distributing and starting up;
starting up a load;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no influence, load shutdown, test pass.
10. The method of claim 1, wherein the method of performing a full state mode of operation electromagnetic compatibility test for a satellite further comprises:
on the basis that the electromagnetic compatibility detection of the load and broadcast distribution startup mode passes, starting up the data transmission;
starting up a load;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no effect, test pass.
11. The method of claim 1, wherein the method of performing a maximum operating mode electromagnetic compatibility test for a satellite further comprises:
on the basis that the electromagnetic compatibility detection of the satellite full-state working mode passes, starting up the relay;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
and (4) no influence is caused, the relay is shut down, and the test is passed.
12. The method of claim 1, wherein said method of performing a turntable cranking mode of operation electromagnetic compatibility test further comprises:
rotating the rotary table on the basis that the electromagnetic compatibility detection of the maximum working mode of the satellite passes;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no effect, test pass.
13. The method of claim 1, wherein the method of performing a shadow mode electromagnetic compatibility test further comprises:
on the basis that the electromagnetic compatibility detection of the turntable starting working mode passes, the whole satellite is prepared for inspection;
checking the load data by a signal analyzer and telemetry check, and by data processing software;
jointly judging whether influence is caused;
influencing, positioning and processing problems according to software results; and
no effect, pass test and end test.
14. The method of claim 1, wherein the electromagnetic compatibility testing of the active flight mode, the post-track relay mode, and the data transfer playback mode determines the source of interference by observing the interference over the frequency spectrum of the signal analyzer when each individual machine is turned on in sequence.
15. The method of claim 1, wherein the load data transmission boot-up mode, the load broadcast distribution boot-up mode, the satellite full-state operation mode, the satellite maximum operation mode, the turntable cranking operation mode and the shadow region mode electromagnetic compatibility detection jointly determine whether the whole satellite other subsystems interfere with load detection by observing the frequency spectrum, the remote measurement and the load data of the signal analyzer, give a cause of a result fast positioning problem through data import software, and process related problems.
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