SAR load and satellite platform radio frequency equipment electromagnetic compatibility whole satellite verification method and system

Abstract

The invention relates to a whole satellite verification method and system for electromagnetic compatibility of an SAR load and satellite platform radio frequency equipment. The method comprises the following steps: respectively carrying out power-on self-test on the satellite platform radio frequency equipment, load comprehensive electronics, the SAR load and a system consisting of the satellite platform radio frequency equipment and the load comprehensive electronics; a beam pointing angle of an SAR load and a beam scanning angle of satellite platform radio frequency equipment are set, receiving noise of the SAR load is recorded, the influence condition of the satellite platform radio frequency equipment on the SAR load can be determined according to a noise test result, and the influence of the satellite platform radio frequency equipment on the SAR load is quantitatively verified by replacing a full array with an SAR antenna sub-array, so that the influence of the satellite platform radio frequency equipment on the SAR load is verified. Therefore, the problem that the SAR load influence cannot be quantified during the whole-satellite test is solved, the verification of the whole-satellite radio frequency compatibility is ensured, the risk and cost of whole-satellite development are reduced, and meanwhile, the progress requirement is met.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite electromagnetic compatibility testing, and in particular to a whole-satellite verification method and system for electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device. Background Art

[0002] The main payload of a SAR satellite is the SAR payload. This payload is an active microwave remote sensing device that operates in the Ku band, has a large transmission power, and a high receiving sensitivity. Since the payload platform is a small satellite platform, the space on the satellite is limited, and the antenna gain of the payload equipment is high, resulting in a large antenna volume, the distance between the payload antenna and the platform antenna cannot be increased, and the coupling between the antennas is strong. Therefore, the electromagnetic compatibility test and verification between the SAR payload and the platform radio frequency equipment is an important task to ensure the performance of the satellite.

[0003] The electromagnetic compatibility test of the whole satellite is to verify the electromagnetic compatibility of the platform and payload equipment in the whole satellite environment. The design and verification process of the electromagnetic compatibility of the whole satellite is as follows: Figure 1 As shown, it mainly includes the scheme stage, the prototype stage, the whole star EMC test stage, and the prototype stage. In the scheme stage, the electromagnetic compatibility design specifications of the whole satellite are completed as the basic requirements for the electromagnetic compatibility design of each subsystem; in the prototype stage, the radiation model star (antenna isolation) test is completed, and the equipment-level (prototype product) EMC test required in the whole satellite design specifications is completed. After the overall product acceptance of the satellite is completed, the whole star EMC test is carried out, including the whole satellite electrical test and simulated flight test. The whole star EMC test can be divided into two types: conduction test and radiation test. Among them, the conduction test mainly verifies the electromagnetic compatibility conducted through the cable, including ripple, surge, etc. The radiation test mainly verifies the electromagnetic compatibility caused by unintentional radiation such as radiation from the antenna terminal, flange, equipment housing and cable.

[0004] At present, the traditional method for the whole satellite RF compatibility test verification in the prototype stage is: the equipment contractor develops the prototype product and participates in the whole satellite electromagnetic compatibility test. Although this method is relatively complete, the load data output by the load subsystem at this time is difficult to quantify the impact of the platform RF equipment on the load. Summary of the invention

[0005] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a whole-satellite verification method and system for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment, which can realize complete verification of the whole-satellite radio frequency compatibility of the prototype satellite.

[0006] To achieve the above-mentioned purpose of the invention, the present invention provides a whole-satellite verification method for electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device, comprising the following steps:

[0007] Step S1, completing a power-on self-test on the load integrated electronics, and determining and recording the working status of the load integrated electronics;

[0008] Step S2: Perform a power-on self-test on the satellite platform radio frequency device to determine and record the working status of the satellite platform radio frequency device;

[0009] Step S3, connecting the payload integrated electronics and the satellite platform radio frequency equipment to form a satellite platform radio frequency system;

[0010] Step S4, setting the beam pointing angle of the satellite platform radio frequency device according to the satellite platform radio frequency device self-test angle, performing a power-on self-test on the satellite platform radio frequency system, and determining and recording the working status of the satellite platform radio frequency system;

[0011] Step S5: setting the beam pointing angle of the SAR payload according to the SAR payload self-test angle, performing a power-on self-test on the SAR payload, and recording the working status of the SAR payload product;

[0012] Step S6: According to the whole satellite layout, the SAR payload, the payload integrated electronics and the satellite platform radio frequency equipment are installed on the simulated satellite board and connected to each other, and controlled to be in a normal working mode;

[0013] Step S7, setting the SAR payload beam pointing angle according to the SAR payload self-test angle, continuously observing the receiving noise floor of the SAR payload, testing and recording the SAR payload receiving noise data, and forming a first receiving noise data table;

[0014] Step S8, setting the beam pointing angle of the satellite platform radio frequency device according to the satellite platform radio frequency device self-test angle, testing and recording the receiving noise of the SAR payload, and forming a second receiving noise data table;

[0015] Step S9, repeating step S8 until all SAR payload beam pointing angles of the SAR payload are traversed;

[0016] Step S10: quantify the electromagnetic compatibility of the satellite platform radio frequency equipment and payload by comparing the first receiving noise data table with the second receiving noise data table.

[0017] According to a technical solution of the present invention, the satellite platform radio frequency equipment is a digital transmission phased array antenna.

[0018] According to a technical solution of the present invention, in step S4, the satellite platform radio frequency device self-test angle is set to:

[0019] The beam scanning angle of the digital transmission phased array antenna is set according to an azimuth angle of 0 to 360 degrees, an off-axis angle of 0 to 67.5 degrees, and a step of 5 degrees.

[0020] According to a technical solution of the present invention, in step S5, the SAR payload self-test angle is set to:

[0021] The beam pointing angle of the SAR payload is set to ±7.5 degrees in azimuth, -55 to 55 degrees in range, and 5 degrees in steps, and a self-check is performed.

[0022] According to a technical solution of the present invention, in step S7, it specifically includes:

[0023] The SAR payload is turned on, the SAR payload self-checks an angle to set the SAR payload beam pointing angle, maintains the state for t seconds at each angle, continuously observes the receiving background noise of the SAR payload, tests and records the SAR payload receiving noise data, and forms a first receiving noise data table.

[0024] According to a technical solution of the present invention, in step S8, it specifically includes:

[0025] The SAR payload is turned on, and the beam pointing angle of the SAR payload is set according to the SAR payload self-test angle. Under the beam pointing angle set by the SAR payload, the digital transmission phased array antenna sets its beam scanning angle according to the satellite platform radio frequency device self-test angle, and each beam pointing angle is maintained for t seconds. The noise data received by the SAR payload is tested and recorded to form a second receiving noise data table.

[0026] According to a technical solution of the present invention, the working status of the SAR payload product includes: working voltage, working current, antenna beam azimuth angle, antenna beam range angle;

[0027] The first receiving noise data table and the second receiving noise data table include: frequencies and their corresponding noise amplitudes.

[0028] According to a technical solution of the present invention, in the step S10, it specifically includes:

[0029] The frequencies in the first receiving noise data table are represented as f1, f2, ..., f K , and its corresponding noise amplitude is expressed as N1, N2, ···, N K ;

[0030] The frequencies in the second receiving noise data table are represented as f1, f2, ..., f K , and its corresponding noise amplitude is expressed as N'1, N'2, ..., N' K ;

[0031] The noise consistency factor is calculated according to the first receiving noise data table and the second receiving noise data table, and the calculation formula of the noise consistency factor is:

[0032]

[0033] Wherein, K represents the number of frequencies in the first receiving noise data table and the second receiving noise data table;

[0034] According to the calculated noise consistency factor not exceeding the noise consistency threshold, it is determined that the SAR payload is compatible with the satellite platform radio frequency device; otherwise, it is determined that the two are incompatible.

[0035] According to one aspect of the present invention, a system of the present invention is used to implement the above-mentioned whole-satellite verification method for electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device, comprising the satellite platform radio frequency device, the payload integrated electronics and the SAR payload, wherein the payload integrated electronics is electrically connected to the satellite platform radio frequency device, and further comprising:

[0036] A power supply unit, used to supply power to the payload integrated electronics, the satellite platform radio frequency equipment and the SAR payload;

[0037] A first ground detector, connected to the payload integrated electronics and the satellite platform radio frequency device, for controlling the payload integrated electronics and the satellite platform radio frequency device;

[0038] A second ground detector, electrically connected to the SAR payload, and used to control the SAR payload;

[0039] The simulated star board is used to install the payload integrated electronics, the satellite platform radio frequency equipment and the SAR payload, and to perform whole-satellite simulation; the satellite platform radio frequency equipment and the antenna of the SAR payload are arranged relative to each other on the simulated star board.

[0040] Compared with the prior art, the present invention has the following beneficial effects:

[0041] The present invention proposes a whole-satellite verification method and system for electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device. The method performs whole-satellite verification on electromagnetic compatibility of the payload integrated electronics, the satellite platform radio frequency device and the SAR payload, and records and compares noise data received by the SAR payload at different self-test angles to troubleshoot and locate interference, thereby solving the problem that the SAR influence of the whole-satellite radio frequency compatibility cannot be quantified during the whole-satellite test, reducing the risk and cost of the whole-satellite development while meeting the schedule requirements. Moreover, more data can be accumulated through testing and analysis to be applied to the development of subsequent models.

[0042] The present invention obtains the input noise on the radio frequency link of the SAR payload system after the SAR payload subarray by testing the electromagnetic noise emitted by the satellite platform radio frequency equipment. Compared with the inherent noise of the SAR payload system, the degree of noise deterioration, that is, the degree of influence, can be directly quantified, which not only makes the test method simpler, but also greatly shortens the test time. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0044] Figure 1 Schematic diagram of the flow chart for the design and verification of electromagnetic compatibility of the entire satellite;

[0045] Figure 2 A schematic diagram of the structure of the whole-satellite verification system for electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device provided according to the present invention is schematically shown;

[0046] Figure 3 The flowchart schematically shows the whole-satellite verification method for electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device provided by the present invention. DETAILED DESCRIPTION

[0047] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0048] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0049] like Figure 2As shown, the present invention provides a system for realizing a whole-satellite verification method of electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device, comprising a satellite platform radio frequency device, a payload integrated electronics 2 and a SAR payload 3, wherein the satellite platform radio frequency device is a digital transmission phased array antenna 1, and the payload integrated electronics 2 is electrically connected to the digital transmission phased array antenna 1, and further comprising:

[0050] A power supply unit 4 is used to supply power to the payload integrated electronics 2, the digital transmission phased array antenna 1 and the SAR payload 3;

[0051] The first ground detector 5 is connected to the payload integrated electronics 2 and the digital transmission phased array antenna 1, and is used to control the payload integrated electronics 2 and the digital transmission phased array antenna 1;

[0052] A second ground detector 6, electrically connected to the SAR payload 3, and used for controlling the SAR payload 3;

[0053] The simulated satellite board (not shown) is used to install the payload integrated electronics 2, the digital transmission phased array antenna 1 and the SAR payload 3, and to perform whole-satellite simulation; the digital transmission phased array antenna 1 and the antenna of the SAR payload 2 are arranged opposite to each other on the simulated satellite board.

[0054] like Figure 3 As shown, the present invention provides a whole-satellite verification method for electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device, comprising the following steps:

[0055] Step S1, completing a power-on self-test on the load integrated electronics, and determining and recording the working status of the load integrated electronics;

[0056] Connect the internal cables of the load integrated electronics 2, connect the cables between the load integrated electronics 2 and the first ground detection 5, complete the equipment power-on self-test, record the product working status of the load integrated electronics 2, and determine whether it is working normally.

[0057] Step S2: Perform a power-on self-test on the satellite platform radio frequency equipment, compare the measured value of the telemetry parameter with the designed value, and determine and record the working status of the satellite platform radio frequency equipment;

[0058] Connect the cable between the digital transmission phased array antenna 1 and the first ground detection 5, complete the equipment power-on self-test, record the product working status of the digital transmission phased array antenna 1, and determine whether it is working normally.

[0059] Step S3, connecting the payload integrated electronics and the satellite platform radio frequency equipment to form a satellite platform radio frequency system;

[0060] Step S4, setting the beam pointing angle of the satellite platform radio frequency device according to the self-test angle of the satellite platform radio frequency device, performing a power-on self-test on the satellite platform radio frequency system, and determining and recording the working status of the satellite platform radio frequency system;

[0061] The self-test angle of the satellite platform radio frequency equipment is set as follows: the beam scanning angle of the digital transmission phased array antenna 1 is set according to the azimuth angle of 0 degree to 360 degrees, the off-axis angle of 0 degree to 67.5 degrees, and the stepping angle of 5 degrees.

[0062] The payload integrated electronics 2 and the digital transmission phased array antenna 1 are powered on, and the system self-test is completed. The beam scanning angle of the digital transmission phased array antenna 1 is set according to the azimuth angle of 0 degrees to 360 degrees, the off-axis angle of 0 degrees to 67.5 degrees, and the stepping angle of 5 degrees. The telemetry is used to determine whether the working status of the equipment is normal.

[0063] Step S5: setting the beam pointing angle of the SAR payload according to the SAR payload self-test angle, performing a power-on self-test on the SAR payload, and recording the working status of the SAR payload product;

[0064] The product working status of the SAR payload includes working voltage (V), working current (A), antenna beam azimuth angle (degrees), and antenna beam range angle (degrees).

[0065] The SAR payload self-test angle is set as follows: the beam pointing angle of the SAR payload is set to ±7.5 degrees in azimuth, -55 to 55 degrees in range, and in steps of 5 degrees.

[0066] The SAR payload 3 is powered on, and the beam pointing angle of the SAR payload 3 is set to ±7.5 degrees in azimuth and -55 to 55 degrees (in 5-degree increments) in range. A self-check is performed, and the working status of the SAR payload product is recorded to determine whether it is working normally.

[0067] Step S6: According to the whole satellite layout, SAR payload, payload integrated electronics and satellite platform radio frequency equipment are installed on the simulated satellite board and connected to control it to be in normal working mode;

[0068] According to the whole satellite layout, the SAR payload 3 and the digital transmission phased array antenna 1 are installed on the simulated satellite board. The power supply and control cables of the SAR payload 3, the payload integrated electronics 2, and the digital transmission phased array antenna 1 are connected. The SAR payload 3, the payload integrated electronics 2, and the digital transmission phased array antenna 1 are controlled to be in normal working mode through the first ground detection 5 and the second ground detection 6.

[0069] Step S7, setting the SAR payload beam pointing angle according to the SAR payload self-test angle, continuously observing the receiving noise floor of the SAR payload, testing and recording the SAR payload receiving noise data, and forming a first receiving noise data table;

[0070] The SAR payload 3 is turned on and switched in sequence according to the self-test angles. The state is maintained for t seconds at each angle. The receiving noise floor of the SAR payload 3 is continuously observed, and the first noise data table is tested and recorded.

[0071] Step S8, setting the beam pointing angle of the satellite platform radio frequency device according to the self-test angle of the satellite platform radio frequency device, testing and recording the receiving noise of the SAR payload, and forming a second receiving noise data table;

[0072] The SAR payload 3 is turned on, and the SAR payload beam pointing angle is set according to the self-test angle. When the SAR payload is set to the pointing angle, the digital transmission phased array antenna 1 is set according to its own self-test beam pointing angle. Each beam pointing angle is maintained for t seconds (t seconds is the time it takes for the payload to complete one reception). The second noise data table is tested and recorded.

[0073] Step S9, repeating step S8 until all SAR payload beam pointing angles of the SAR payload are traversed;

[0074] Step S10: quantify the electromagnetic compatibility of the satellite platform radio frequency equipment and payload by comparing the first receiving noise data table with the second receiving noise data table.

[0075] Table 1 First receiving noise data table

[0076] Frequency (GHz) <![CDATA[f1]]> <![CDATA[f2]]> … <![CDATA[f K ]]> Noise Amplitude (dBm / Hz) <![CDATA[N1]]> <![CDATA[N2]]> … <![CDATA[N K ]]>

[0077] Table 2 Second receiving noise data table

[0078] Frequency (GHz) <![CDATA[f1]]> <![CDATA[f2]]> … <![CDATA[f K ]]> Noise Amplitude (dBm / Hz) <![CDATA[N′1]]> <![CDATA[N′2]]> … <![CDATA[N′ K ]]>

[0079] The noise consistency factor is calculated according to the first receiving noise data table and the second receiving noise data table. The calculation formula of the noise consistency factor is:

[0080]

[0081] Wherein, K represents the number of frequencies in the first receiving noise data table and the second receiving noise data table.

[0082] If C≤0.5, the noise consistency of the two tests is good, and the satellite platform RF equipment does not cause the noise deterioration of the payload, and it is determined that the two are electromagnetically compatible. Otherwise, it indicates that turning on the satellite platform RF equipment will cause the payload noise to deteriorate, and the two are determined to be incompatible.

[0083] Therefore, by comparing the first receiving noise data table and the second receiving noise data table, the influence of the satellite platform radio frequency equipment on the payload can be determined, and the quantitative analysis result of the payload performance can be obtained, thereby verifying the electromagnetic compatibility of the satellite platform radio frequency equipment and the payload.

[0084] Through the above method, the SAR payload and the digital transmission phased array antenna can be installed on the satellite simulation board according to the actual satellite installation position. The SAR payload and the digital transmission phased array antenna can be turned on at the same time, the direction of the digital transmission phased array antenna can be adjusted, and the noise received by the payload can be tested, thereby completing the complete verification of the RF compatibility of the entire prototype satellite.

[0085] It should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, once the basic creative concept of the present invention is known, a number of improvements and modifications can be made by a person skilled in the art without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A whole-satellite verification method for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment, characterized in that: The following steps are involved: Step S1, completing a power-on self-test on the load integrated electronics, and determining and recording the working status of the load integrated electronics; Step S2: Perform a power-on self-test on the satellite platform radio frequency device to determine and record the working status of the satellite platform radio frequency device; Step S3, connecting the payload integrated electronics and the satellite platform radio frequency equipment to form a satellite platform radio frequency system; Step S4, setting the beam pointing angle of the satellite platform radio frequency device according to the satellite platform radio frequency device self-test angle, performing a power-on self-test on the satellite platform radio frequency system, and determining and recording the working status of the satellite platform radio frequency system; Step S5: setting the beam pointing angle of the SAR payload according to the SAR payload self-test angle, performing a power-on self-test on the SAR payload, and recording the working status of the SAR payload product; Step S6: According to the whole satellite layout, the SAR payload, the payload integrated electronics and the satellite platform radio frequency equipment are installed on the simulated satellite board and connected to each other, and controlled to be in a normal working mode; Step S7, setting the SAR payload beam pointing angle according to the SAR payload self-test angle, continuously observing the receiving noise floor of the SAR payload, testing and recording the SAR payload receiving noise data, and forming a first receiving noise data table; Step S8, setting the beam pointing angle of the satellite platform radio frequency device according to the satellite platform radio frequency device self-test angle, testing and recording the receiving noise of the SAR payload, and forming a second receiving noise data table; Step S9, repeating step S8 until all SAR payload beam pointing angles of the SAR payload are traversed; Step S10: Perform a quantitative analysis on the electromagnetic compatibility of the satellite platform radio frequency equipment and the SAR payload by comparing the first receiving noise data table with the second receiving noise data table.

2. The whole-satellite verification method for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment according to claim 1 is characterized in that: The satellite platform radio frequency equipment is a digital transmission phased array antenna.

3. The whole-satellite verification method for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment according to claim 2 is characterized in that: In step S4, the satellite platform radio frequency device self-test angle is set to: The beam scanning angle of the digital transmission phased array antenna is set according to an azimuth angle of 0 to 360 degrees, an off-axis angle of 0 to 67.5 degrees, and a step of 5 degrees.

4. The whole-satellite verification method for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment according to claim 3 is characterized in that: In step S5, the SAR payload self-test angle is set to: The beam pointing angle of the SAR payload is set to ±7.5 degrees in azimuth, -55 to 55 degrees in range, and 5 degrees in steps, and a self-check is performed.

5. The whole-satellite verification method for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment according to claim 4 is characterized in that: In the step S7, it specifically includes: The SAR payload is turned on, the SAR payload self-checks an angle to set the SAR payload beam pointing angle, maintains the state for t seconds at each angle, continuously observes the receiving background noise of the SAR payload, tests and records the SAR payload receiving noise data, and forms a first receiving noise data table.

6. The whole-satellite verification method for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment according to claim 5 is characterized in that: In the step S8, it specifically includes: The SAR payload is turned on, and the beam pointing angle of the SAR payload is set according to the SAR payload self-test angle. Under the beam pointing angle set by the SAR payload, the digital transmission phased array antenna sets its beam scanning angle according to the satellite platform radio frequency device self-test angle, and each beam pointing angle is maintained for t seconds. The noise data received by the SAR payload is tested and recorded to form a second receiving noise data table.

7. The whole-satellite verification method for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment according to claim 1, characterized in that: The working status of the SAR payload product includes: working voltage, working current, antenna beam azimuth angle, antenna beam distance angle; The first receiving noise data table and the second receiving noise data table include frequencies and their corresponding noise amplitudes.

8. The whole-satellite verification method for electromagnetic compatibility between SAR payload and satellite platform radio frequency equipment according to claim 7 is characterized in that: In the step S10, it specifically includes: The frequencies in the first receiving noise data table are represented as f1, f2, ..., f K , and its corresponding noise amplitude is expressed as N1, N2, ···, N K ; The frequencies in the second receiving noise data table are represented as f1, f2, ..., f K , and its corresponding noise amplitude is expressed as N'1, N'2, ··· 、N' K ; A noise consistency factor is calculated according to the first receiving noise data table and the second receiving noise data table, and the calculation formula of the noise consistency factor is: Wherein, K represents the number of frequencies in the first receiving noise data table and the second receiving noise data table; According to the calculated noise consistency factor not exceeding the noise consistency threshold, it is determined that the SAR payload is compatible with the satellite platform radio frequency device; otherwise, it is determined that the two are incompatible.

9. A system for implementing the whole-satellite verification method for electromagnetic compatibility between a SAR payload and a satellite platform radio frequency device as claimed in any one of claims 1 to 8, characterized in that: The system comprises the satellite platform radio frequency device, the payload integrated electronics and the SAR payload, wherein the payload integrated electronics is electrically connected to the satellite platform radio frequency device, and further comprises: A power supply unit, used to supply power to the payload integrated electronics, the satellite platform radio frequency equipment and the SAR payload; A first ground detector, connected to the payload integrated electronics and the satellite platform radio frequency equipment, and used to control the payload integrated electronics and the satellite platform radio frequency equipment; A second ground detector, electrically connected to the SAR payload, and used to control the SAR payload; The simulated star board is used to install the payload integrated electronics, the satellite platform radio frequency equipment and the SAR payload, and to perform whole-satellite simulation; the satellite platform radio frequency equipment and the antenna of the SAR payload are arranged relative to each other on the simulated star board.

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