Semi-physical test method and device for satellite-borne phase interferometer positioning system

Abstract

The invention discloses a semi-physical testing method and device for a satellite-borne phase interferometer positioning system, and relates to the field of electronic reconnaissance. According to the invention, the problem that a phase interferometer positioning system cannot realize space-fed test in a microwave anechoic chamber is solved. Through the test of the device, the positioning test of the phase interferometer positioning system on various target scenes can be fully verified, and the coverage area dimension comprises the positioning test of targets in the coverage area, the coverage area boundary, even the area outside the coverage area and the like. The signal pattern dimension comprises but is not limited to positioning tests of PRI change, frequency agility, frequency group change, intra-pulse modulation and other patterns, and the signal parameter dimension comprises tests of frequency, PRI and pulse width change in a wide range. In addition, verification of the positioning precision of the phase interferometer positioning system under the condition that the radiation source signal and the calibration signal exist at the same time is supported.

Description

Technical Field

[0001] The present invention relates to the field of electronic reconnaissance, and in particular to a semi-physical testing method and device for a satellite-borne phase interferometer positioning system. Background Art

[0002] The statements in this section merely provide background information related to the present disclosure and may not constitute prior art.

[0003] In the field of passive positioning for electronic reconnaissance, the use of phase interferometer positioning systems to obtain target position information has been widely used in practical engineering. Phase interferometer positioning systems must undergo thorough ground-based functional performance testing and verification before delivery. Ground-based simulation testing and verification systems are particularly essential for spaceborne systems.

[0004] Regarding the ground test system of the phase interferometer positioning system, the document "Research on Semi-physical Simulation Test Method for Interferometer Passive Positioning Performance" [J]. Journal of Air Force Early Warning Academy, 2016, 30(2): 79-82, mainly addresses the shortcomings of the actual measurement method and electronic simulation method commonly used to test the passive positioning performance of the interferometer system, and proposes a semi-physical simulation test method. This method uses the darkroom, turntable, array control system, flight simulation system and other equipment in the Key Laboratory of Radio Frequency Integrated Simulation of Avionics Systems to simulate the outdoor test flight scene to conduct interferometer passive positioning simulation test experiments. However, the above test system needs to be carried out in a microwave darkroom, needs to transmit wireless signals, and requires the antenna of the phase interferometer positioning system to be fully deployed as designed. Considering the internal space of the actual microwave darkroom and the installation and deployment of the antenna, this test method is not suitable for the case where the interferometer baseline is long.

[0005] The paper "Design and Implementation of a Semi-Physical-in-the-Loop Test System for Onboard Real-Time Processing" [J]. Aerospace Electronic Countermeasures, 2022, 38(1): 31-35, addresses the need for onboard real-time processing of satellite payload subsystems. This paper constructs a test environment based on an onboard real-time processing semi-physical system for verification of onboard embedded software development. The system automatically compares and analyzes processing results, completes effect evaluation, and provides support for reliable on-orbit operation of satellites. However, this system simulates intermediate frequency signal output and can only test and verify the data processing capabilities of the digital end, but cannot verify the performance of the phase interferometer positioning system from the RF end. This system has certain limitations. Summary of the Invention

[0006] The purpose of the present invention is to address the problems existing in the prior art and provide a semi-physical testing method and device for a satellite-borne phase interferometer positioning system. The method can calculate the phase difference and amplitude difference of the signal arriving at the phase interferometer positioning system in real time based on the satellite's attitude and orbit. The method then uses a high-precision power adjustment matrix and phase shifter to perform high-precision amplitude and phase shifting on the signal, ensuring that the amplitude and phase relationship of the multi-path RF signals arriving at the RF front-end entrance of the interferometer positioning system are consistent with the actual on-orbit state. The present invention is suitable for desktop full-process testing and verification of phase interferometer positioning systems, and is particularly suitable for semi-physical verification of multi-beam large parabolic long-baseline interferometer arrays, which are difficult to implement in a microwave anechoic chamber for air-fed testing.

[0007] The technical solutions of the present invention are as follows:

[0008] A hardware-in-the-loop test device for a satellite-borne phase interferometer positioning system, comprising: host computer software, radio frequency amplitude and phase shifting network, and data receiving and interpretation software;

[0009] On the one hand, the host computer software simulates the satellite's real-time position and attitude and ground coverage area based on the satellite orbit parameters, and calculates the phase difference and amplitude difference of the interferometer channel based on the position of the ground target point and the tested phase interferometer positioning system simulation, and then generates amplitude and phase shift control instructions for the radio frequency amplitude and phase shift network; on the other hand, according to the task requirements, the phase interferometer positioning system is configured with task parameters and control instructions are generated;

[0010] The RF amplitude and phase shifting network is a hardware device that performs high-precision amplitude and phase shifting according to the amplitude and phase shifting control instructions generated by the host computer, so that the RF signal is consistent with the actual on-orbit state when it reaches the front-end entrance of the phase interferometer positioning system through the RF amplitude and phase shifting network;

[0011] The data receiving and interpretation software receives the result data of the phase interferometer positioning system under test and caches it locally to form a file, and then interprets more useful and interesting information according to needs;

[0012] The host computer software and data receiving and interpretation software run on a dedicated ground inspection computer.

[0013] Furthermore, the host computer software is composed of a track simulation software module, an amplitude and phase calculation software module, a radio frequency network control software module and an interferometer instruction issuing software module.

[0014] Furthermore, the orbit simulation software module is used to simulate the satellite orbit and, given the satellite position and attitude angle, simulate the beam coverage area on the ground according to the specific indicators of the satellite phase interferometer positioning system antenna array;

[0015] The amplitude and phase calculation software module first selects a specific location point in the beam coverage area, and then calculates the theoretical phase difference between the interferometer antenna signal phase detection channels and the theoretical amplitude difference between the multi-beam antenna signal detection channels based on the satellite's real-time orbital position and attitude and the geometric relationship between the selected location;

[0016] The radio frequency network control software module converts the above-calculated amplitude difference and phase difference into a control file for the radio frequency phase shift network;

[0017] The interferometer instruction issuing software module realizes the task parameter configuration and task instruction issuing operations of the phase interferometer positioning system.

[0018] Furthermore, the RF amplitude and phase shifting network is composed of an RF power division network, a phase shifter, and a power adjustment matrix, which realizes power division, phase shifting, and amplitude shifting of the signal, so that the RF signal reaching the front-end entrance of the tested phase interferometer positioning system is consistent with the actual on-orbit situation.

[0019] Furthermore, the RF power division network first performs multi-channel power division and attenuation control on the RF signal from the radar simulation source according to actual design requirements; a portion of the power-divided signal is output to the power adjustment matrix, and a portion is output to the phase shifter;

[0020] The power adjustment matrix performs power division, power adjustment, and group output on the input radio frequency signal. The power adjustment parameters are based on the theoretical value of the amplitude difference calculated by the amplitude and phase calculation software module, and the grouping is carried out according to the actual design requirements.

[0021] The phase shifter first performs power division on the input signal 1 as required, and then performs high-precision phase shifting on each power-divided signal according to the theoretical value of the phase difference calculated by the amplitude-phase calculation software module; at the same time, the input signal 2 is first power divided as required, and then performs high-precision phase shifting on each power-divided signal according to the theoretical value of the phase difference calculated by the amplitude-phase calculation software module; then the first signal of signal 1 after power division and phase shifting and the first signal of signal 1 after power division and phase shifting are combined and output, the second signal of signal 1 after power division and phase shifting and the second signal of signal 1 after power division and phase shifting are combined and output, and so on.

[0022] Furthermore, the data receiving and interpreting software includes: a data receiving and caching software module and a data interpreting software module;

[0023] The data receiving and caching software module completes the reception of the result data of the tested phase interferometer positioning system and caches it locally to form a file;

[0024] The data interpretation software module interprets the received result data of the tested phase interferometer positioning system to obtain more useful and interesting information according to needs.

[0025] The present invention also proposes a semi-physical testing method for a spaceborne phase interferometer positioning system, based on the above-mentioned semi-physical testing device for a spaceborne phase interferometer positioning system, comprising:

[0026] Step S1: Power on the ground inspection computer, power on the phase interferometer positioning system under test, open the host computer software, open the data receiving and interpretation software, and ensure that all equipment interfaces are correctly connected;

[0027] Step S2: In the satellite orbit simulation interface, input satellite orbit parameters, and output the satellite position, attitude angle, and beam coverage area of the satellite phase interferometer positioning system on the ground in real time. The simulated output satellite position, attitude angle, and beam coverage area all change over time.

[0028] Step S3: Select a target point of interest in the instantaneous coverage area of the beam as required and save it to a file containing the target's location information and signal parameters. The target parameters are then sent to the radar simulation source. Note that the target point of interest can be stationary or moving.

[0029] Step S4: In the amplitude and phase calculation interface, the phase difference between the interferometer channels and the amplitude difference between the initial direction finding channels are calculated in real time using the real-time position and attitude of the satellite and the position and frequency information of the target point in the coverage area;

[0030] Step S5: On the RF amplitude and phase shifting network control interface, the phase difference and amplitude difference generated in step S4 are first converted into control parameters for the phase shifter and the power adjustment matrix, respectively. Furthermore, the RF power division network control parameters are obtained by using the phase interferometer positioning system antenna array design and test parameters. The control parameters are then distributed separately.

[0031] Step S6: Start the radar simulation source output signal; in the interferometer command issuing interface, configure the task parameters according to the requirements and execute the phase interferometer positioning task;

[0032] Step S7: Use data receiving software to receive the interferometer positioning results in real time and generate files according to the task number; use interpretation software to complete detailed analysis of the received data, compare the measured positioning results with the target position during simulation, and calculate the positioning CEP value and related evaluation functions.

[0033] Furthermore, the step S1 further includes:

[0034] Synchronize the time of the hardware-in-the-loop test device with the phase interferometer positioning system under test to ensure that all software and hardware devices start working at the same time.

[0035] Furthermore, the step S2 further includes:

[0036] Start the satellite orbit simulation software function some time in advance.

[0037] Furthermore, the location information in step S3 includes: longitude and latitude;

[0038] The signal parameters in step S3 include frequency, repetition rate, pulse width, etc.

[0039] Compared with the existing technology, the beneficial effects of the present invention are:

[0040] 1. The present invention provides a semi-physical testing method and device for the satellite-borne phase interferometer positioning system, which solves the problem that the phase interferometer positioning system cannot realize air-feed testing in a microwave darkroom. Through the test of this device, the positioning test of the phase interferometer positioning system for various target scenes can be fully verified. The coverage area dimension includes positioning tests for targets within the coverage area, at the boundary of the coverage area, and even outside the coverage area. The signal pattern dimension includes but is not limited to positioning tests of PRI changes, frequency agility, frequency group changes, intra-pulse modulation and other styles. The signal parameter dimension includes tests of frequency, PRI, and pulse width changes within a wide range. In addition, it also supports verification of the positioning accuracy of the phase interferometer positioning system when the radiation source signal and the calibration signal exist at the same time.

[0041] 2. The method and device of the present invention are suitable for algorithm debugging, fault reproduction, performance evaluation and other tasks in the engineering development stage of phase interferometer positioning systems, and can be extended to the test and verification of phase interferometer positioning systems of other configurations. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 This is a diagram of a hardware-in-the-loop test setup for a spaceborne phase interferometer positioning system.

[0043] Figure 2 It is a block diagram of a radio frequency amplitude and phase shifting network;

[0044] Figure 3 A block diagram of a radio frequency power division network;

[0045] Figure 4 A block diagram of a power adjustment matrix is provided;

[0046] Figure 5 A block diagram of a phase shifter is provided;

[0047] Figure 6 This is a flow chart of a hardware-in-the-loop testing method for a spaceborne phase interferometer positioning system. DETAILED DESCRIPTION

[0048] It should be noted that relational terms such as "first" and "second" are used only to distinguish one entity or operation from another entity or operation, and do not necessarily require or imply any actual relationship or order between these entities or operations. Moreover, the terms "comprises," "comprising," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus comprising a series of elements includes not only those elements, but also other elements not explicitly listed, or elements inherent to such process, method, article, or apparatus. In the absence of further limitations, an element defined by the phrase "comprising a ..." does not exclude the presence of additional identical elements in the process, method, article, or apparatus comprising the element.

[0049] The features and performance of the present invention are further described in detail below with reference to the embodiments.

[0050] Example 1

[0051] See also Figure 1 , a semi-physical test device for a spaceborne phase interferometer positioning system, comprising:

[0052] Host computer software, RF amplitude and phase shifting network, and data receiving and interpretation software;

[0053] On the one hand, the host computer software simulates the satellite's real-time position and attitude and ground coverage area based on the satellite orbit parameters, and calculates the phase difference and amplitude difference of the interferometer channel based on the position of the ground target point and the tested phase interferometer positioning system simulation, and then generates amplitude and phase shift control instructions for the radio frequency amplitude and phase shift network; on the other hand, according to the task requirements, the phase interferometer positioning system is configured with task parameters and control instructions are generated;

[0054] The RF amplitude and phase shifting network is a hardware device that performs high-precision amplitude and phase shifting according to the amplitude and phase shifting control instructions generated by the host computer, so that the RF signal is consistent with the actual on-orbit state when it reaches the front-end entrance of the phase interferometer positioning system through the RF amplitude and phase shifting network;

[0055] The data receiving and interpretation software receives the result data of the phase interferometer positioning system under test and caches it locally to form a file, and then interprets more useful and interesting information according to needs;

[0056] The host computer software and data receiving and interpretation software run on a dedicated ground inspection computer.

[0057] In this embodiment, specifically, the host computer software is composed of a track simulation software module, an amplitude and phase calculation software module, a radio frequency network control software module and an interferometer instruction issuing software module.

[0058] In this embodiment, specifically, the orbit simulation software module is mainly used to simulate the satellite orbit. When the satellite position and attitude angle are known, the beam coverage area on the ground is simulated according to the specific indicators of the satellite phase interferometer positioning system antenna array;

[0059] The amplitude and phase calculation software module first selects a specific location point in the beam coverage area, and then calculates the theoretical phase difference between the interferometer antenna signal phase detection channels and the theoretical amplitude difference between the multi-beam antenna signal detection channels based on the satellite's real-time orbital position and attitude and the geometric relationship between the selected location;

[0060] The radio frequency network control software module converts the above-calculated amplitude difference and phase difference into a control file for the radio frequency phase shift network;

[0061] The interferometer instruction issuing software module realizes the operations such as task parameter configuration and task instruction issuing of the phase interferometer positioning system.

[0062] In this embodiment, specifically, the radio frequency amplitude and phase shifting network is composed of a radio frequency power division network, a phase shifter, and a power adjustment matrix, such as Figure 2 As shown, power division, phase shifting and amplitude shifting of the signal are realized, so that the RF signal reaching the front-end entrance of the phase interferometer positioning system under test is consistent with the actual on-orbit situation. It should be noted that the consistency is mainly manifested in two aspects: first, the phase characteristics of the RF signal reaching the interferometer channel must be consistent with the actual on-orbit state, and second, the amplitude characteristics reaching the initial direction finding channel must be consistent with the on-orbit state.

[0063] In this embodiment, it should also be noted that the RF amplitude and phase shifting network supports simultaneous power division, amplitude and phase shifting processing of two signals, such as Figure 2 Signal 1 and Signal 2, shown in the figure, each represent a single signal, corresponding to a practical scenario where a calibration source and a radiation source (or two radiation sources) coexist in a coverage area and need to be located. This RF amplitude and phase shifting network also supports scenarios where only a calibration source or radiation source is present. In this case, only Signal 1 or Signal 2 needs to be input, leaving the other segment empty.

[0064] Figure 2 The RF power division network simulates the power difference of the RF signal after passing through the initial direction finding antenna and the interferometer antenna; the power adjustment matrix simulates the impact of the initial direction finding antenna on the RF signal power, especially suitable for simulating the initial direction finding under the multi-beam reflector antenna system; the phase shifter simulates the phase difference characteristics caused by the same RF signal reaching the interferometer antenna, especially suitable for multi-baseline system interferometer.

[0065] In this embodiment, specifically, the RF power division network first performs multi-channel power division and attenuation control on the RF signal from the radar simulation source according to actual design requirements; a portion of the power-divided signal is output to the power adjustment matrix, and a portion is output to the phase shifter; the RF power division network composition block diagram is shown in FIG. Figure 3 As shown;

[0066] The power adjustment matrix performs power division, power adjustment, and group output on the input radio frequency signal. The power adjustment parameters are based on the amplitude difference theoretical value calculated by the amplitude and phase calculation software module, and the grouping is carried out according to the actual design requirements. A power adjustment matrix composition block diagram is shown as follows: Figure 4 As shown in ; It should be noted that the grouping design is intended to save hardware resources and reduce system hardware complexity. Because initial direction finding generally involves only a few antenna beams, the remaining antenna beams can be assumed to receive no signal. Therefore, when designing the test system, it is only necessary to ensure that only a few antenna beams have signal input at a time. The remaining antenna beams can "copy" these beams and simply turn off the signal from the back end of the antenna.

[0067] The phase shifter first performs power division on the input signal 1 as required, and then performs high-precision phase shifting on each power-divided signal according to the theoretical value of the phase difference calculated by the amplitude-phase calculation software module; at the same time, the input signal 2 is first power divided as required, and then performs high-precision phase shifting on each power-divided signal according to the theoretical value of the phase difference calculated by the amplitude-phase calculation software module; then the first signal of signal 1 after power division and phase shifting and the first signal of signal 1 after power division and phase shifting are combined and output, the second signal of signal 1 after power division and phase shifting and the second signal of signal 1 after power division and phase shifting are combined and output, and so on; a block diagram of the composition of a phase shifter is shown as follows: Figure 5 As shown in .

[0068] In this embodiment, the data receiving and interpretation software simulates satellite-to-ground data transmission reception, primarily implementing the reception and caching of high-speed result data. Furthermore, it performs data analysis, data statistics, graphical display, indicator compliance determination, and generation of determination files based on the generated task file copy according to a specific interface protocol. Specifically, it includes: a data receiving and caching software module and a data interpretation software module.

[0069] The data receiving and caching software module completes the reception of the result data of the tested phase interferometer positioning system and caches it locally to form a file;

[0070] The data interpretation software module interprets the received result data of the tested phase interferometer positioning system to obtain more useful and interesting information according to needs.

[0071] See also Figure 6This embodiment further proposes a semi-physical testing method for a spaceborne phase interferometer positioning system. The semi-physical testing device for a spaceborne phase interferometer positioning system described above includes:

[0072] Step S1: Power on the ground inspection computer and the phase interferometer positioning system under test, open the host computer software, open the data receiving and interpretation software, and ensure that all equipment interfaces are correctly connected; synchronize the time of the semi-physical test device and the phase interferometer positioning system under test to ensure that all software and hardware devices start working at the same time;

[0073] Step S2: In the satellite orbit simulation interface, input satellite orbit parameters (such as the number of orbital elements, satellite's viewing angle from the ground, and other parameters), and output the satellite's position, attitude angle, and the beam coverage area of the satellite's phase interferometer positioning system on the ground in real time. The simulated output of the satellite's position, attitude angle, and beam coverage area changes with time because the satellite is always in motion (actual GEO satellites actually make small-scale maneuvers relative to the earth). It should be noted that the output results of this simulation software require a convergence time, so it is recommended to start this satellite orbit simulation software function one hour in advance.

[0074] Step S3: Select a target point of interest in the instantaneous coverage area of the beam as required and save it to a file. The file contains the target's location information (latitude and longitude) and signal parameters (frequency, repetition rate, pulse width, etc.). At the same time, the target parameters are sent to the radar simulation source. It should be noted that the target point of interest can be stationary or moving.

[0075] Step S4: In the amplitude and phase calculation interface, the phase difference between the interferometer channels and the amplitude difference between the initial direction finding channels are calculated in real time using the real-time position and attitude of the satellite and the position and frequency information of the target point in the coverage area;

[0076] Step S5: On the RF amplitude and phase shifting network control interface, the phase difference and amplitude difference generated in step S4 are first converted into control parameters for the phase shifter and the power adjustment matrix, respectively. Furthermore, the RF power division network control parameters are obtained by using the phase interferometer positioning system antenna array design and test parameters. The control parameters are then distributed separately.

[0077] Step S6: Start the radar simulation source output signal; in the interferometer command issuing interface, configure the task parameters according to the requirements and execute the phase interferometer positioning task;

[0078] Step S7: Use data receiving software to receive the interferometer positioning results in real time and generate files according to the task number; use interpretation software to complete detailed analysis of the received data, compare the measured positioning results with the target position during simulation, and calculate the positioning CEP value and related evaluation functions.

[0079] Example 2

[0080] This embodiment is aimed at a certain satellite-borne project, and adopts the above method to design and develop a semi-physical testing device for a satellite-borne phase interferometer positioning system.

[0081] The initial direction finding channel of the device contains 5 beams, and the interferometer channel contains 9 beams. Figure 4 The middle power splitter is a 1-to-5 power splitter, and the combiner will use 5 2-input and 1-output combiners, and finally output 5 initial direction finding signals; the outputs of power splitters 1 to 4 are completely consistent, and each initial direction finding selects 1 from each of power splitters 1 to 4 according to a specific rule to form a 5-way signal input. Figure 5 The power splitter in the circuit is a 1-to-9 power splitter, and the combiner will use 9 of them, and finally output 9 interferometer signals.

[0082] Based on the mission requirements, the orbit simulation module and amplitude-phase calculation module in the host computer software were used to simulate a set of amplitude and phase difference calculation results, as shown in Table 1. In Table 1, 1-5 represents the phase difference between interferometer channel 1 and interferometer channel 5, 2-5 represents the phase difference between interferometer channel 2 and interferometer channel 5, and so on. The phase shifter settings are shown in Table 2. The phase value of channel 5 is set to 0° in Table 2 to facilitate setting the phase values of each interferometer channel according to the phase difference in Table 1. The final positioning results are shown in Table 3.

[0083] Table 1 Simulated target position and calculated phase difference

[0084]

[0085] Table 2 Phase shifter settings

[0086]

[0087] Table 3 Positioning result comparison

[0088]

[0089] The above-described embodiments merely represent specific implementation methods of the present application. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of protection of the present application. It should be noted that a person skilled in the art would be able to make numerous variations and improvements without departing from the technical concept of the present application, and all such variations and improvements fall within the scope of protection of the present application.

[0090] This background section is provided to generally present the context of the invention, and the work of the presently named inventors, the work to the extent described in this background section, and aspects of the description in this section that did not constitute prior art at the time of filing are neither explicitly nor implicitly admitted to be prior art to the present invention.

Claims

1. A semi-physical testing device for a spaceborne phase interferometer positioning system, characterized in that: include: Host computer software, RF amplitude and phase shifting network, and data receiving and interpretation software; On the one hand, the host computer software simulates the satellite's real-time position and attitude and ground coverage area based on the satellite orbit parameters, and calculates the phase difference and amplitude difference of the interferometer channel based on the position of the ground target point and the tested phase interferometer positioning system simulation, and then generates amplitude and phase shift control instructions for the radio frequency amplitude and phase shift network; on the other hand, according to the task requirements, the phase interferometer positioning system is configured with task parameters and control instructions are generated; The RF amplitude and phase shifting network is a hardware device that performs high-precision amplitude and phase shifting according to the amplitude and phase shifting control instructions generated by the host computer, so that the RF signal is consistent with the actual on-orbit state when it reaches the front-end entrance of the phase interferometer positioning system through the RF amplitude and phase shifting network; The data receiving and interpretation software receives the result data of the phase interferometer positioning system under test and caches it locally to form a file, and then interprets more useful and interesting information according to needs; The host computer software and data receiving and interpretation software run on a dedicated ground inspection computer.

2. A hardware-in-the-loop testing device for a spaceborne phase interferometer positioning system according to claim 1, characterized in that: The host computer software consists of a track simulation software module, an amplitude and phase calculation software module, a radio frequency network control software module and an interferometer instruction issuing software module.

3. The semi-physical testing device for a spaceborne phase interferometer positioning system according to claim 2, characterized in that: The orbit simulation software module is used to simulate the satellite orbit. When the satellite position and attitude angle are known, the beam coverage area on the ground is simulated according to the specific indicators of the satellite phase interferometer positioning system antenna array. The amplitude and phase calculation software module first selects a specific location point in the beam coverage area, and then calculates the theoretical phase difference between the interferometer antenna signal phase detection channels and the theoretical amplitude difference between the multi-beam antenna signal detection channels based on the satellite's real-time orbital position and attitude and the geometric relationship between the selected location; The radio frequency network control software module converts the above-calculated amplitude difference and phase difference into a control file for the radio frequency phase shift network; The interferometer instruction issuing software module realizes the task parameter configuration and task instruction issuing operations of the phase interferometer positioning system.

4. The semi-physical testing device for a spaceborne phase interferometer positioning system according to claim 1, characterized in that: The RF amplitude and phase shifting network consists of a RF power division network, a phase shifter, and a power adjustment matrix, which realizes power division, phase shifting, and amplitude shifting of the signal, so that the RF signal reaching the front-end entrance of the tested phase interferometer positioning system is consistent with the actual on-orbit situation.

5. The semi-physical testing device for a spaceborne phase interferometer positioning system according to claim 4, characterized in that: The RF power division network first performs multi-channel power division and attenuation control on the RF signal from the radar simulation source according to actual design requirements; a portion of the power-divided signal is output to the power adjustment matrix, and a portion is output to the phase shifter; The power adjustment matrix performs power division, power adjustment, and group output on the input radio frequency signal. The power adjustment parameters are based on the theoretical value of the amplitude difference calculated by the amplitude and phase calculation software module, and the grouping is carried out according to the actual design requirements. The phase shifter first performs power division on the input signal 1 as required, and then performs high-precision phase shifting on each power-divided signal according to the theoretical phase difference value calculated by the amplitude-phase calculation software module; at the same time, the input signal 2 first performs power division on the input signal 2 as required, and then performs high-precision phase shifting on each power-divided signal according to the theoretical phase difference value calculated by the amplitude-phase calculation software module; Then the first signal after power division and phase shift of signal 1 and the first signal after power division and phase shift of signal 1 are combined and output, the second signal after power division and phase shift of signal 1 and the second signal after power division and phase shift of signal 1 are combined and output, and so on.

6. The semi-physical testing device for a spaceborne phase interferometer positioning system according to claim 1, characterized in that: The data receiving and interpreting software includes: a data receiving and caching software module and a data interpreting software module; The data receiving and caching software module completes the reception of the result data of the tested phase interferometer positioning system and caches it locally to form a file; The data interpretation software module interprets the received result data of the tested phase interferometer positioning system to obtain more useful and interesting information according to needs.

7. A semi-physical testing method for a spaceborne phase interferometer positioning system, characterized in that: A hardware-in-the-loop testing device for a spaceborne phase interferometer positioning system according to any one of claims 1 to 6, comprising: Step S1: Power on the ground inspection computer, power on the phase interferometer positioning system under test, open the host computer software, open the data receiving and interpretation software, and ensure that all equipment interfaces are correctly connected; Step S2: In the satellite orbit simulation interface, input satellite orbit parameters, and output the satellite position, attitude angle, and beam coverage area of the satellite phase interferometer positioning system on the ground in real time. The simulated output satellite position, attitude angle, and beam coverage area all change over time. Step S3: Select a target point of interest in the instantaneous coverage area of the beam as required and save it to a file containing the target's location information and signal parameters. The target parameters are then sent to the radar simulation source. Note that the target point of interest can be stationary or moving. Step S4: In the amplitude and phase calculation interface, the phase difference between the interferometer channels and the amplitude difference between the initial direction finding channels are calculated in real time using the real-time position and attitude of the satellite and the position and frequency information of the target point in the coverage area; Step S5: On the RF amplitude and phase shifting network control interface, the phase difference and amplitude difference generated in step S4 are first converted into control parameters for the phase shifter and the power adjustment matrix, respectively. Furthermore, the RF power division network control parameters are obtained by using the phase interferometer positioning system antenna array design and test parameters. The control parameters are then distributed separately. Step S6: Start the radar simulation source output signal; in the interferometer command issuing interface, configure the task parameters according to the requirements and execute the phase interferometer positioning task; Step S7: Use data receiving software to receive the interferometer positioning results in real time and generate files according to the task number; use interpretation software to complete detailed analysis of the received data, compare the measured positioning results with the target position during simulation, and calculate the positioning CEP value and related evaluation functions.

8. The hardware-in-the-loop testing method for a spaceborne phase interferometer positioning system according to claim 7, characterized in that: The step S1 further includes: Synchronize the time of the hardware-in-the-loop test device with the phase interferometer positioning system under test to ensure that all software and hardware devices start working at the same time.

9. The method for hardware-in-the-loop testing of a spaceborne phase interferometer positioning system according to claim 7, wherein: The step S2 further includes: Start the satellite orbit simulation software function some time in advance.

10. The hardware-in-the-loop testing method for a spaceborne phase interferometer positioning system according to claim 7, characterized in that: The location information in step S3 includes: longitude and latitude; The signal parameters in step S3 include: frequency, repetition rate, and pulse width.

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