CN112882070A - Navigation satellite EIRP and stability test system and method - Google Patents
Navigation satellite EIRP and stability test system and method Download PDFInfo
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- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
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Abstract
The invention provides a navigation satellite EIRP and stability test system and a method, comprising the following steps: a navigation payload configured to output a plurality of test signals; a high-power attenuator configured to attenuate the test signal; the programmable matrix switch is configured to gate the test signal according to the gating control signal for transmitting to the frequency spectrograph; the frequency spectrograph is configured to collect and measure the test signals gated by the program control matrix switch according to the test control signals to form a test result and a frequency spectrogram; and the test and control system is configured to compare the test result with the measurement threshold in real time, perform exception warning if the test result exceeds the measurement threshold, perform screenshot on the spectrogram at the moment and store the screenshot, provide a gating control signal for the program control matrix switch and provide a test control signal for the spectrometer.
Description
Technical Field
The invention relates to the technical field of space satellite measurement, in particular to a navigation satellite EIRP and stability test system and method.
Background
The power of the navigation landing signal is a prerequisite condition for navigation positioning of a ground user within the receiving range of the receiver, and the strength and stability of the navigation landing signal are directly related to the accuracy of the navigation positioning. Therefore, the Equivalent Isotropic Radiated Power (EIRP) of the navigation satellite and the stability thereof are one of the important indicators of the navigation satellite. Before the navigation satellite leaves a factory, EIRP and stability of the EIRP are measured for many times so as to ensure that the power of the satellite at each stage meets the index requirement.
The EIRP test of a satellite on the ground is classified into a wired test and a wireless test. Due to the limitation of a test field, the measurement requirement of the wireless EIRP is difficult to realize, so the measurement result of the wired EIRP is the most important basis for judging the satellite power conformity in each stage. Meanwhile, because satellite signals at different elevation angles have the requirement of approximate equal power when reaching the ground, a downlink signal transmitting channel of the navigation satellite is designed in a multi-channel mode, and the required equal power design is realized by matching with an RNSS downlink antenna array, so that the workload of a test process is large, and the progress is slow.
Disclosure of Invention
The invention aims to provide a navigation satellite EIRP and stability test system and method, which are used for solving the problems of large workload and complicated steps in the conventional navigation satellite EIRP and stability test process.
In order to solve the above technical problem, the present invention provides a navigation satellite EIRP and stability testing system, including:
a navigation payload configured to output a plurality of test signals;
a high-power attenuator configured to attenuate the test signal;
the programmable matrix switch is configured to gate the test signal according to the gating control signal for transmitting to the frequency spectrograph;
the frequency spectrograph is configured to collect and measure the test signals gated by the program control matrix switch according to the test control signals to form a test result and a frequency spectrogram;
the test and control system is configured to compare the test result with the measurement threshold in real time, alarm for abnormality if the test result exceeds the measurement threshold, and capture and store the spectrogram at the moment,
providing gating control signals to the programmable matrix switches, an
A test control signal is provided to the spectrometer.
Optionally, in the navigation satellite EIRP and stability test system, the navigation load is connected to the high-power attenuator through a radio frequency cable;
the high-power attenuator is connected with the program control matrix switch through a radio frequency cable;
the program control matrix switch is connected with the frequency spectrograph through a radio frequency cable;
the program control matrix switch is connected with the test and control system through a network cable;
the frequency spectrograph is connected with the test and control system through a network cable.
Optionally, the navigation satellite EIRP and stability testing system further includes a housing;
the high-power attenuator, the program control matrix switch, the frequency spectrograph and the network switch are arranged in the shell from top to bottom;
an upper computer carrying the test and control system is communicated with a network switch;
the fan and the heat dissipation plate are arranged inside the shell.
Optionally, in the navigation satellite EIRP and stability test system, the withstand power of the high-power attenuator is 500W.
Optionally, in the navigation satellite EIRP and stability testing system, the program-controlled matrix switch includes at least one single-pole multi-throw switch, and the single-pole multi-throw switch includes a plurality of input pins and an output pin;
when the number of the single-pole multi-throw switches is one, each input pin is electrically connected with a test signal, and the output pin is electrically connected with the frequency spectrograph;
when the number of the single-pole multi-throw switches is multiple, the single-pole multi-throw switches are divided into multiple stages, the input pins of the single-pole multi-throw switches at the lowest stage are respectively and electrically connected with a test signal, the output pins are electrically connected with the input pins of the single-pole multi-throw switches at the high stage, and the output pins of the single-pole multi-throw switches at the highest stage are electrically connected with the frequency spectrograph.
Optionally, in the navigation satellite EIRP and stability test system, the number ratio of the input pins to the output pins of the program control matrix switch is 15;
the frequency range of the program control matrix switch is 0-4 GHz;
the channel insertion loss of the program control matrix switch is less than 3 dB;
the maximum bearing power of the program control matrix switch is 1W;
the standing wave of the port of the program control matrix switch is less than 1.4;
the inter-channel isolation of the programmable matrix switch is greater than 90 dB.
Optionally, in the system for testing the navigation satellite EIRP and the stability, the test and control system includes:
the data analysis module is configured to receive a test case of a user and automatically generate a test item and a test sequence according to the test case;
a matrix switch control module configured to generate a gating control signal according to the test items and the test sequence;
the frequency spectrograph control module is configured to generate a test control signal according to the test items and the test sequence so as to set a measurement mode, a test frequency point, a measurement bandwidth and a frequency resolution of the frequency spectrograph and receive a test result and a frequency spectrogram of the frequency spectrograph;
a data analysis module further configured to analyze and store the test results and spectrogram;
and the human-computer interaction interface is configured to display the test result and the frequency spectrum, and allow a user to input the measurement mode, the test frequency point, the measurement bandwidth and the frequency resolution of the frequency spectrograph.
The invention also provides a navigation satellite EIRP and a stability testing method,
the navigation payload provides a plurality of test signals;
the high-power attenuator is used for attenuating the test signal;
the test and control system provides gating control signals to the program control matrix switch;
the programmable matrix switch gates a test signal according to the gating control signal and transmits the test signal to the frequency spectrograph;
the test and control system provides gating control signals to the program control matrix switch;
the frequency spectrograph collects and measures the test signals gated by the program control matrix switch according to the test control signals to form a test result and a frequency spectrogram;
and the test and control system compares the test result with the measurement threshold in real time, gives an abnormal alarm if the test result exceeds the measurement threshold, and captures and stores the spectrogram at the moment.
Optionally, in the navigation satellite EIRP and stability testing method, the method further includes:
initializing an EIRP and a stability test system of a navigation satellite;
starting up and preheating a navigation load;
the data analysis module receives a test case of a user, and automatically generates a test item and a test sequence according to the test case;
the matrix switch control module generates gating control signals according to the test items and the test sequence;
the frequency spectrograph control module generates a test control signal according to the test items and the test sequence;
after the test signal of the navigation load is subjected to signal attenuation through the high-power attenuator, the test signal is sent to the program control matrix switch through the radio frequency cable;
the program control matrix switch is connected with an upper computer through a network cable, and the upper computer gates a certain path of the program control matrix switch through a test and control system, so that a gated test signal is provided to the frequency spectrograph;
after receiving the gated test signal, the frequency spectrograph utilizes the channel power measurement function to measure the in-band power and transmits the test result to a test and control system of an upper computer through a network cable;
the test and control system records and stores the test result in real time;
and the test and control system compares the test result with the measurement threshold, and if the test result exceeds the measurement threshold, the exceeding data on the screen of the frequency spectrograph is marked with red and the frequency spectrogram at the abnormal moment is stored.
Optionally, in the navigation satellite EIRP and stability testing method, the method further includes:
if the test result does not exceed the measurement threshold, storing the test result and judging whether the fixed screenshot time is reached, if so, automatically screenshot and storing the spectrogram and then carrying out the next step, otherwise, directly carrying out the next step;
and judging whether the test time meets the requirement, if so, ending, and otherwise, returning to the execution of the upper computer to gate a certain path of the program control matrix switch through the test and control system.
The inventor of the invention finds that the traditional EIRP wired measurement method is to transmit a signal of one frequency point each time, then measure the power of each downlink signal channel of a satellite one by using a power meter, and calculate the transmission EIRP of the satellite by adding the gain of an RNSS antenna array. The method has the problems that only one frequency point can be measured each time, the test port needs to be replaced manually in the test process, long-time continuity test of EIRP stability cannot be performed, and the like. Therefore, there is a need to search for an automatic testing method for EIRP and its stability according to the characteristics of the navigation satellite.
Therefore, the invention provides a navigation satellite EIRP and stability test system and a method, a test and control system provides a gating control signal for a program control matrix switch, the program control matrix switch gates a test signal according to the gating control signal, and a frequency spectrograph collects and measures the test signal gated by the program control matrix switch according to the test control signal, thereby overcoming the trouble that the test port needs to be manually switched in the traditional EIRP test process; furthermore, the test result is compared with the measurement threshold value in real time through the test and control system, if the test result exceeds the measurement threshold value, an abnormal alarm is given, and the spectrogram at the moment is captured and stored, so that the defects that the EIRP measurement result cannot be automatically stored and does not have automatic test capability are overcome.
The invention provides a method for measuring EIRP and the stability thereof by using a program-controlled matrix switch, a frequency spectrograph and a test and control system, which can realize the rapid and accurate measurement of the EIRP transmitted by a navigation satellite and synchronously complete the continuous monitoring and measurement of the EIRP stability. Meanwhile, the test and control system can complete abnormal power alarm and abnormal frequency spectrum recording in the test process.
Compared with the prior art, the invention has the beneficial effects that:
and (4) testing automation. The invention carries out the gating setting of the test signal through the program control matrix switch, and carries out the control and measurement of the frequency spectrograph and the storage of the test result through the test and control system, thereby completing the automation of the EIRP test process.
Has the alarm function. The test and control system can compare the test result with the measurement threshold in real time, and if the test result exceeds the measurement threshold, abnormal alarm is given, and the abnormal frequency spectrum can be automatically stored.
And integrating an integrated design. The downlink complex link in the conventional power test project is integrated in a shell (test cabinet) to form a set of multi-input single-output black box system, so that the navigation satellite EIRP and the stability test system can be conveniently transferred and the connection relation can be stably tested, and the navigation satellite EIRP and the stability test system can be calibrated for multiple times.
Drawings
FIG. 1 is a schematic diagram of an EIRP and stability testing system for a navigation satellite according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of a test cabinet of a navigation satellite EIRP and stability test system according to an embodiment of the invention;
FIG. 3 is a schematic diagram of the programming matrix switch principle of an embodiment of the present invention;
FIG. 4 is a schematic diagram of a test and control system according to an embodiment of the present invention;
fig. 5 is a flowchart illustrating an EIRP and stability testing method for a navigation satellite according to an embodiment of the invention.
Detailed Description
The following describes the navigation satellite EIRP and the stability testing system and method according to the present invention in further detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
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.
The core idea of the invention is to provide a navigation satellite EIRP and stability test system and method, so as to solve the problems of large workload and complicated steps in the existing navigation satellite EIRP and stability test process.
In order to realize the thought, the invention provides a navigation satellite EIRP and stability testing system and a method, comprising the following steps: the navigation payload provides a plurality of test signals; the high-power attenuator is used for attenuating the test signal; the test and control system provides gating control signals to the program control matrix switch; the programmable matrix switch gates a test signal according to the gating control signal and transmits the test signal to the frequency spectrograph; the test and control system provides gating control signals to the program control matrix switch; the frequency spectrograph collects and measures the test signals gated by the program control matrix switch according to the test control signals to form a test result and a frequency spectrogram; and the test and control system compares the test result with the measurement threshold in real time, gives an abnormal alarm if the test result exceeds the measurement threshold, and captures and stores the spectrogram at the moment.
The present embodiment provides a navigation satellite EIRP and stability testing system, as shown in fig. 1, including: a navigation payload 10 configured to output a plurality of test signals; a high power attenuator 50 configured to attenuate the test signal; a programmable matrix switch 20 configured to gate the test signal according to a gate control signal for transmission to the spectrometer 30; the frequency spectrograph 30 is configured to collect and measure the test signal gated by the program control matrix switch 20 according to the test control signal, and form a test result and a frequency spectrogram; and the test and control system 40 is configured to compare the test result with the measurement threshold in real time, alarm an abnormality if the test result exceeds the measurement threshold, capture and store the spectrogram at the moment, provide a gating control signal to the programmable matrix switch 20 and provide a test control signal to the frequency spectrograph 30.
In an embodiment of the invention, in the navigation satellite EIRP and stability testing system, the navigation load 10 and the high-power attenuator 50 are connected by a radio frequency cable n-1; the high-power attenuator 50 is connected with the program control matrix switch 20 through a radio frequency cable n-2; the program-controlled matrix switch 20 is connected with the frequency spectrograph 30 through a radio frequency cable; the program control matrix switch 20 is connected with the test and control system 40 through a network cable; the spectrometer 30 and the test and control system 40 are connected by a network cable.
Meanwhile, in order to ensure the flexibility of the device and the stability of the testing environment, the high-power attenuator 50, the program-controlled matrix switch 20, the frequency spectrograph 30, and the like are all integrated in a movable testing cabinet in the embodiment. In order to ensure good heat dissipation of the cabinet, a fan 60 and a heat dissipation plate are arranged in the cabinet. As shown in fig. 2, the system for testing the navigation satellite EIRP and the stability further includes a housing; the high-power attenuator 50, the program control matrix switch 20, the frequency spectrograph 30 and the network switch 41 are arranged in the shell from top to bottom; the upper computer carrying the test and control system 40 communicates with the network switch 41; a fan 60 and a heat sink are disposed inside the housing. In order to ensure the safety of the navigation satellite, the endurance power of the high-power attenuator 50 needs to be much larger than the power of the downlink signal for navigation, and the power of the high-power attenuator 50 used in this embodiment is 500W, which can meet the requirement of the measurement safety of the navigation signal.
A functional block diagram of the program-controlled matrix switch 20 of this embodiment is shown in fig. 3, where the program-controlled matrix switch 20 includes at least one single-pole multi-throw switch, and the single-pole multi-throw switch includes a plurality of input pins and an output pin; when the number of the single-pole multi-throw switches is one, each input pin is electrically connected with a test signal, and the output pin is electrically connected with the frequency spectrograph 30; when the number of the single-pole multi-throw switches is multiple, the single-pole multi-throw switches are divided into multiple stages, the input pins of the lowest stage of the single-pole multi-throw switches are respectively and electrically connected with a test signal, the output pins of the lowest stage of the single-pole multi-throw switches are electrically connected with the input pins of the higher stage of the single-pole multi-throw switches, and the output pins of the highest stage of the single-pole multi-throw switches are electrically connected with the frequency spectrograph 30. The programmable matrix switch in fig. 3 comprises 2 stages, the first stage comprises three single-pole six-throw switches SP6T with 18 input pins, each of which is electrically connected with a test signal; the second stage is a single-pole four-throw switch SP4T, the output pins of the three single-pole six-throw switches are respectively connected with the input pin of the single-pole four-throw switch SP4T, and the output pin of the single-pole four-throw switch SP4T is connected with the frequency spectrograph 30.
Further, single pole, multiple throw switches (rf microwave switch matrix) are capable of automatically routing rf microwave signals between the test instrument (spectrometer 30) and the device under test (navigation load 10), which may provide a consistent signal path, support automatic testing, and typically include signal conditioning capabilities. Some key electrical specifications are considered in designing radio frequency switching systems, including crosstalk (path isolation), insertion loss, Voltage Standing Wave Ratio (VSWR), and bandwidth. Other factors that may affect the performance of a switching system include impedance matching, termination, power transfer, signal filters, phase distortion, and wiring. The use of switches inevitably reduces the performance of the measurement system and therefore requires significant consideration of key parameters which can significantly affect the performance of the system. The main technical indexes of the program control matrix switch 20 are as follows, the EIRP measurement requirements of navigation signals can be met, and the number ratio of input pins to output pins of the program control matrix switch 20 is 15; the frequency range of the program control matrix switch 20 is 0-4 GHz; the channel insertion loss of the program controlled matrix switch 20 is less than 3 dB; the maximum power of the program control matrix switch 20 is 1W; the standing wave of the port of the program controlled matrix switch 20 is less than 1.4; the inter-channel isolation of the programmable matrix switch 20 is greater than 90 dB.
In addition, the test and control system 40 is run on a PC of Windows system software, and outputs a strobe control signal, a test control signal, and receives a test result through a network cable. Fig. 4 shows a block diagram of a testing and control system 40, in the system for testing navigation satellite EIRP and stability, the testing and control system 40 includes: a data analysis module 43 configured to receive a test case of a user, and automatically generate a test item and a test sequence according to the test case; a matrix switch control module 41 configured to generate a gate control signal according to the test items and the test order; a spectrometer control module 42 configured to generate a test control signal according to the test item and the test sequence to set a measurement mode, a test frequency point, a measurement bandwidth, and a frequency resolution of the spectrometer 30, and receive a test result and a frequency spectrum of the spectrometer 30; a data analysis module 43, further configured to analyze and store the test results and spectrogram; and the human-computer interaction interface 44 is configured to display the test result and the frequency spectrum, and allow the user to input the measurement mode, the test frequency point, the measurement bandwidth and the frequency resolution of the frequency spectrograph 30.
Specifically, the matrix switch control module 41 mainly functions to control gating of the programmable matrix switch 20, the gating between the switches is mutually exclusive, only one channel can be gated each time during measurement, and meanwhile, the gated branch has a matched load inside the matrix switch, so that the output power of the gated branch can be matched. The spectrometer control module 42 is mainly used for setting parameters such as a measurement mode, a test frequency point, a measurement bandwidth, a frequency resolution and the like of the spectrometer 30 and receiving a measurement result of the spectrometer 30. The data analysis module 43 analyzes and stores the received spectrometer 30 data. Meanwhile, the data analysis module 43 compares the measured data with a threshold set by a user in real time during testing, and controls the spectrometer 30 to capture and store the frequency spectrum if the measured data exceeds the threshold.
The embodiment also provides a navigation satellite EIRP and a stability testing method, as shown in fig. 5, a navigation load 10 provides a plurality of test signals; the high-power attenuator 50 attenuates the test signal; the test and control system 40 provides gating control signals to the programming matrix switch 20; the program control matrix switch 20 gates the test signal according to the gate control signal and transmits the test signal to the frequency spectrograph 30; the test and control system 40 provides gating control signals to the programming matrix switch 20; the frequency spectrograph 30 collects and measures the test signal gated by the program control matrix switch 20 according to the test control signal to form a test result and a frequency spectrogram; the test and control system 40 compares the test result with the measurement threshold in real time, gives an abnormal alarm if the test result exceeds the measurement threshold, and captures and stores the spectrogram at the moment.
In an embodiment of the present invention, as shown in fig. 5, in the method for testing navigation satellite EIRP and stability, the method further includes: initializing an EIRP and a stability test system of a navigation satellite; starting up and preheating the navigation load 10; the data analysis module receives a test case of a user, and automatically generates a test item and a test sequence according to the test case; the matrix switch control module generates gating control signals according to the test items and the test sequence; the control module of the frequency spectrograph 30 generates a test control signal according to the test items and the test sequence; after the test signal of the navigation load 10 is attenuated by the high-power attenuator 50, the test signal is sent to the program control matrix switch 20 through the radio frequency cable; the program control matrix switch 20 is connected with an upper computer through a network cable, and the upper computer gates a certain path of the program control matrix switch 20 through a test and control system 40, so that a gated test signal is provided to the frequency spectrograph 30; after receiving the gated test signal, the spectrometer 30 performs in-band power measurement by using a channel power measurement function, and transmits a test result to the test and control system 40 of the upper computer through a network cable; the test and control system 40 records and stores the test result in real time; the test and control system 40 compares the test result with the measurement threshold, and if the test result exceeds the measurement threshold, the excess data on the screen of the spectrometer 30 is marked with red and the spectrogram at the abnormal moment is saved.
Further, in the navigation satellite EIRP and stability testing method, the method further includes: if the test result does not exceed the measurement threshold, storing the test result and judging whether the fixed screenshot time is reached, if so, automatically screenshot and storing the spectrogram and then carrying out the next step, otherwise, directly carrying out the next step; and judging whether the test time meets the requirement, if so, ending, otherwise, returning to the execution of the upper computer to gate a certain path of the program control matrix switch 20 through the test and control system 40.
In summary, the above embodiments describe the detailed descriptions of different configurations of the navigation satellite EIRP and the stability testing system and method, and it is understood that the present invention includes, but is not limited to, the configurations listed in the above embodiments, and any modifications made on the configurations provided in the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. For the system disclosed by the embodiment, the description is relatively simple because the system corresponds to the method disclosed by the embodiment, and the relevant points can be referred to the method part for description.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (10)
1. A navigation satellite EIRP and stability test system is characterized by comprising:
a navigation payload configured to output a plurality of test signals;
a high-power attenuator configured to attenuate the test signal;
the programmable matrix switch is configured to gate the test signal according to the gating control signal for transmitting to the frequency spectrograph;
the frequency spectrograph is configured to collect and measure the test signals gated by the program control matrix switch according to the test control signals to form a test result and a frequency spectrogram;
the test and control system is configured to compare the test result with the measurement threshold in real time, alarm for abnormality if the test result exceeds the measurement threshold, and capture and store the spectrogram at the moment,
providing gating control signals to the programmable matrix switches, an
A test control signal is provided to the spectrometer.
2. The navigation satellite EIRP and stability testing system of claim 1, wherein the navigation payload is coupled to the high power attenuator via a radio frequency cable;
the high-power attenuator is connected with the program control matrix switch through a radio frequency cable;
the program control matrix switch is connected with the frequency spectrograph through a radio frequency cable;
the program control matrix switch is connected with the test and control system through a network cable;
the frequency spectrograph is connected with the test and control system through a network cable.
3. The navigation satellite EIRP and stability testing system of claim 1, further comprising a housing;
the high-power attenuator, the program control matrix switch, the frequency spectrograph and the network switch are arranged in the shell from top to bottom;
an upper computer carrying the test and control system is communicated with a network switch;
the fan and the heat dissipation plate are arranged inside the shell.
4. The navigation satellite EIRP and stability testing system of claim 1, wherein the high power attenuator has a power tolerance of 500W.
5. The navigation satellite EIRP and stability testing system of claim 1, wherein the programming matrix switch comprises at least one single-pole, multi-throw switch comprising a plurality of input pins and an output pin;
when the number of the single-pole multi-throw switches is one, each input pin is electrically connected with a test signal, and the output pin is electrically connected with the frequency spectrograph;
when the number of the single-pole multi-throw switches is multiple, the single-pole multi-throw switches are divided into multiple stages, the input pins of the single-pole multi-throw switches at the lowest stage are respectively and electrically connected with a test signal, the output pins are electrically connected with the input pins of the single-pole multi-throw switches at the high stage, and the output pins of the single-pole multi-throw switches at the highest stage are electrically connected with the frequency spectrograph.
6. The navigation satellite EIRP and stability testing system of claim 1, wherein the ratio of the number of input pins to the number of output pins of the programmable matrix switch is 15;
the frequency range of the program control matrix switch is 0-4 GHz;
the channel insertion loss of the program control matrix switch is less than 3 dB;
the maximum bearing power of the program control matrix switch is 1W;
the standing wave of the port of the program control matrix switch is less than 1.4;
the inter-channel isolation of the programmable matrix switch is greater than 90 dB.
7. The navigation satellite EIRP and stability testing system of claim 1, wherein the testing and control system comprises:
the data analysis module is configured to receive a test case of a user and automatically generate a test item and a test sequence according to the test case;
a matrix switch control module configured to generate a gating control signal according to the test items and the test sequence;
the frequency spectrograph control module is configured to generate a test control signal according to the test items and the test sequence so as to set a measurement mode, a test frequency point, a measurement bandwidth and a frequency resolution of the frequency spectrograph and receive a test result and a frequency spectrogram of the frequency spectrograph;
a data analysis module further configured to analyze and store the test results and spectrogram;
and the human-computer interaction interface is configured to display the test result and the frequency spectrum, and allow a user to input the measurement mode, the test frequency point, the measurement bandwidth and the frequency resolution of the frequency spectrograph.
8. A method for testing EIRP and stability of navigation satellite is characterized in that,
the navigation payload provides a plurality of test signals;
the high-power attenuator is used for attenuating the test signal;
the test and control system provides gating control signals to the program control matrix switch;
the programmable matrix switch gates a test signal according to the gating control signal and transmits the test signal to the frequency spectrograph;
the test and control system provides gating control signals to the program control matrix switch;
the frequency spectrograph collects and measures the test signals gated by the program control matrix switch according to the test control signals to form a test result and a frequency spectrogram;
and the test and control system compares the test result with the measurement threshold in real time, gives an abnormal alarm if the test result exceeds the measurement threshold, and captures and stores the spectrogram at the moment.
9. The navigation satellite EIRP and stability testing method of claim 8, further comprising:
initializing an EIRP and a stability test system of a navigation satellite;
starting up and preheating a navigation load;
the data analysis module receives a test case of a user, and automatically generates a test item and a test sequence according to the test case;
the matrix switch control module generates gating control signals according to the test items and the test sequence;
the frequency spectrograph control module generates a test control signal according to the test items and the test sequence;
after the test signal of the navigation load is subjected to signal attenuation through the high-power attenuator, the test signal is sent to the program control matrix switch through the radio frequency cable;
the program control matrix switch is connected with an upper computer through a network cable, and the upper computer gates a certain path of the program control matrix switch through a test and control system, so that a gated test signal is provided to the frequency spectrograph;
after receiving the gated test signal, the frequency spectrograph utilizes the channel power measurement function to measure the in-band power and transmits the test result to a test and control system of an upper computer through a network cable;
the test and control system records and stores the test result in real time;
and the test and control system compares the test result with the measurement threshold, and if the test result exceeds the measurement threshold, the exceeding data on the screen of the frequency spectrograph is marked with red and the frequency spectrogram at the abnormal moment is stored.
10. The navigation satellite EIRP and stability testing method of claim 9, further comprising:
if the test result does not exceed the measurement threshold, storing the test result and judging whether the fixed screenshot time is reached, if so, automatically screenshot and storing the spectrogram and then carrying out the next step, otherwise, directly carrying out the next step;
and judging whether the test time meets the requirement, if so, ending, and otherwise, returning to the execution of the upper computer to gate a certain path of the program control matrix switch through the test and control system.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113791561A (en) * | 2021-09-15 | 2021-12-14 | 哈尔滨诺信工大测控技术有限公司 | Satellite electrical performance test signal source based on Ethernet and test signal generation method |
| CN115632696A (en) * | 2022-10-12 | 2023-01-20 | 中国科学院微小卫星创新研究院 | Automatic testing system and method for inter-satellite link to-be-tested equipment |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659935B (en) * | 2009-11-24 | 2013-02-27 | 北京空间飞行器总体设计部 | A kind of be applicable to remote sensing satellite data transmission subsystem whole star test macro |
| CN202797193U (en) * | 2012-08-07 | 2013-03-13 | 北京空间飞行器总体设计部 | Microwave switch matrix for testing radio-frequency signal |
| CN203840353U (en) * | 2014-05-21 | 2014-09-17 | 河北神舟卫星通信股份有限公司 | Dynamic satellite earth station carrier monitoring device |
| CN205484818U (en) * | 2016-02-18 | 2016-08-17 | 成都中森通信科技有限公司 | Detection apparatus for big dipper satellite receiving and dispatching radio frequency |
| CN111929710A (en) * | 2020-06-30 | 2020-11-13 | 中国科学院国家授时中心 | Delivery test method for Beidou satellite navigation signal quality assessment |
-
2021
- 2021-01-13 CN CN202110041069.9A patent/CN112882070A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105659935B (en) * | 2009-11-24 | 2013-02-27 | 北京空间飞行器总体设计部 | A kind of be applicable to remote sensing satellite data transmission subsystem whole star test macro |
| CN202797193U (en) * | 2012-08-07 | 2013-03-13 | 北京空间飞行器总体设计部 | Microwave switch matrix for testing radio-frequency signal |
| CN203840353U (en) * | 2014-05-21 | 2014-09-17 | 河北神舟卫星通信股份有限公司 | Dynamic satellite earth station carrier monitoring device |
| CN205484818U (en) * | 2016-02-18 | 2016-08-17 | 成都中森通信科技有限公司 | Detection apparatus for big dipper satellite receiving and dispatching radio frequency |
| CN111929710A (en) * | 2020-06-30 | 2020-11-13 | 中国科学院国家授时中心 | Delivery test method for Beidou satellite navigation signal quality assessment |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113791561A (en) * | 2021-09-15 | 2021-12-14 | 哈尔滨诺信工大测控技术有限公司 | Satellite electrical performance test signal source based on Ethernet and test signal generation method |
| CN115632696A (en) * | 2022-10-12 | 2023-01-20 | 中国科学院微小卫星创新研究院 | Automatic testing system and method for inter-satellite link to-be-tested equipment |
| CN115632696B (en) * | 2022-10-12 | 2023-08-29 | 中国科学院微小卫星创新研究院 | Automatic testing system and method for inter-satellite link to-be-tested equipment |
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