System and method for automatically testing optical communication system for space navigation

Abstract

The invention relates to the technical field of optical fiber communication, in particular to an automatic test system and method for an optical communication system for space navigation, and the system comprises an FPGA (Field Programmable Gate Array) processing module, a channel switch module, a multi-channel analog quantity acquisition module, a signal interface matching module, a plurality of digital optical modules, a plurality of analog laser modules and a plurality of analog detector modules. According to the invention, data acquisition is carried out on FPGA processing modules in front-end equipment and rear-end equipment of an optical communication system through an interface matching module by a satellite platform network manager; parameters in the optical signal aspect and the electric signal aspect in the system are collected and analyzed through a plurality of circuit modules such as the channel switch module circuit and the multi-path analog quantity collection module circuit, channels are switched, and therefore working parameters of data channels of the optical communication system can be tested in an on-orbit and real-time mode, the method is simple and reliable, and the test efficiency is high. And the practicability is high. Therefore, the problem that the performance of the optical communication system cannot be monitored in real time in a complex space navigation environment is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of optical fiber communication, and in particular to a system and method for automatic testing of an aerospace optical communication system. Background Art

[0002] In optical communication systems for aerospace applications, users need to consider how to scientifically monitor the on-orbit performance of multiple data signals transmitted through the optical fiber communication system from the perspectives of application, testing and maintenance, and standardization. However, due to the complex aerospace working environment and the rated volume and weight, it is impossible to use various instruments to evaluate the post-transmission performance of the optical communication system as is done with ground-based equipment. Therefore, it is necessary to design a method for automatically testing the optical communication system on-orbit. Summary of the Invention

[0003] The purpose of the present invention is to provide a system and method for automatically testing an aerospace optical communication system, aiming to solve the problem that the performance of the optical communication system cannot be monitored in real time in a complex aerospace environment.

[0004] To achieve the above objectives, in a first aspect, the present invention provides a system for automatically testing aerospace optical communication systems, comprising an FPGA processing module, a channel switch module, a multi-channel analog quantity acquisition module, a signal interface matching module, multiple digital optical modules, multiple analog laser modules, and multiple analog detector modules;

[0005] The FPGA processing module is used to receive and process signals from the digital optical module, the analog laser module, and the analog detector module, and communicate with the satellite platform network management through the signal interface matching module;

[0006] The channel switch module is used to control the switch of the signal channel;

[0007] The multi-channel analog quantity acquisition module is used to sample the analog quantity parameters of the finalized analog laser module and multiple analog detector modules;

[0008] The signal interface matching module is used to convert the RS422 level signal into an LVTTL level signal that can be recognized by the FPGA processing module and the digital optical module;

[0009] The digital optical module is used to complete the conversion between digital electrical signals and optical signals and provide technical parameters of the digital optical signals in real time;

[0010] The analog laser module is used to convert the analog radio frequency electrical signal into an optical signal and output the analog quantity to the multi-channel analog quantity acquisition module;

[0011] The analog detector module is used to convert the optical signal into an analog radio frequency electrical signal and output the analog quantity to the multi-channel analog quantity acquisition module.

[0012] The channel switch module includes a MOS tube and an operational amplifier. The gate threshold voltage of the MOS tube is -2V to -4V, the turn-on delay time is 30ns, the turn-off delay time is 70ns, the static drain-source on-resistance is 0.29 ohms, the total dose resistance is ≥100Krad (Si), and the single particle resistance is ≥75MeV·cm 2 / mg.

[0013] The multi-channel analog acquisition module has an A / D acquisition resolution of 12 bits, a conversion time of 10 μs, 11 analog input channels, a maximum linear error of ±1.5 LSB, a total dose resistance of ≥60 krad (Si), and a single particle resistance of ≥75 MeV·cm 2 / mg.

[0014] Among them, the signal interface matching module circuit is DS26LV31QML, DS26LV32AW-QML, DS26LV31QML completes the transmission of 4-way LVTTL level to RS422 level, the package is W16A, and the operating voltage is 3~3.6V. DS26LV32AW-QML completes the reception of 4-way RS422 level to LVTTL level, the package is W16A, and the operating voltage is 3~3.6V.

[0015] The digital optical module circuit is HT850M10G4T4R-80mm-A, a 4-way parallel optical transceiver module in an airtight butterfly package. The module has a central wavelength of 850nm, a single 3.3VDC power supply, a transmission rate of 10.3125Gbps per channel, an operating temperature range of -40°C to +85°C, a total dose resistance of ≥30krad (Si), and a single particle resistance of ≥75MeV·cm 2 / mg, total dose of displacement damage ≥5×10 10 N / cm 2 , airtightness: no more than 5×10 -8 Pa*m 3 / s.

[0016] Among them, the analog laser module circuit is T-03-YYY-B-01#H, which is used to convert the input analog RF electrical signal into the optical signal required by the wavelength division multiplexer. It has an operating temperature of -55℃~+85℃, an output optical power of 8~10mW, a threshold current Ith≤20mA, a typical optical isolation value of 35dB, and is equipped with backlight detection and automatic temperature control unit, an SMP interface, and a pigtail.

[0017] Among them, the analog detector module circuit is R-12-MP-B-02#H, which is used to convert the optical signal input by the wavelength division multiplexer into an analog radio frequency electrical signal, has an operating temperature of -55℃~+85℃, an operating current ≤10mA, an SMP interface, and a pigtail.

[0018] In a second aspect, a method for automatically testing an aerospace optical communication system is provided, which is used in the system for automatically testing an aerospace optical communication system according to the first aspect, comprising the following steps:

[0019] The satellite platform network management starts an automatic test and reads the real-time reported data from the FPGA processing module in the optical communication system through the interface matching module;

[0020] The FPGA processing module reads the optical power, temperature, and voltage parameters of the digital optical module through the I2C bus and determines whether the digital optical module is working properly;

[0021] The FPGA processing module controls and enables the analog switch chip, and selects the analog quantity of the analog laser module or the analog detector module for sampling;

[0022] The FPGA processing module controls and enables the A / D chip, performs A / D conversion on the selected analog quantity, and stores the converted data;

[0023] After the FPGA processing module completes the sampling of all analog quantities, it forms the stored data into data frames and reports them to the satellite platform network management through the RS422 interface;

[0024] The satellite platform network administrator checks whether the parameters of the digital optical module and analog laser module detector are correct. If the result is incorrect, the corresponding channel switch is turned off, the data when it is turned off is measured, and then the channel switch is turned on and the data after it is turned on is measured again.

[0025] The satellite platform network manager compares the measured data and reports the working status of the aerospace optical communication system to the ground observation station.

[0026] A system for automatically testing a space optical communication system according to the present invention comprises an FPGA processing module, a channel switch module, a multi-channel analog quantity acquisition module, a signal interface matching module, multiple digital optical modules, multiple analog laser modules, and multiple analog detector modules; the FPGA processing module is used to receive and process signals from the digital optical module, the analog laser module, and the analog detector module, and to communicate with a satellite platform network management system through the signal interface matching module; the channel switch module is used to control the switching of the signal channel; the multi-channel analog quantity acquisition module is used to sample analog quantity parameters of the finalized analog laser module and the multiple analog detector modules; the signal interface matching module is used to convert RS422 level signals into LVTTL level signals recognizable by the FPGA processing module and the digital optical module; the digital optical module is used to complete the conversion between digital electrical signals and optical signals and provide technical parameters of the digital optical signals in real time; the analog laser module is used to convert analog radio frequency electrical signals into optical signals and output analog quantities to the multi-channel analog quantity acquisition module; and the analog detector module is used to convert optical signals into analog radio frequency electrical signals and output analog quantities to the multi-channel analog quantity acquisition module. The present invention uses an interface matching module to collect data from the FPGA processing modules within the front-end and back-end equipment of the optical communication system. Multiple circuit modules, such as a channel switch module circuit and a multi-channel analog acquisition module circuit, collect and analyze various parameters of the optical and electrical signals within the system. By switching each channel, the operating parameters of each data channel of the optical communication system can be tested in real time on orbit. This method is simple, reliable, and highly feasible. This solves the problem of being unable to monitor the performance of the optical communication system in real time in complex aerospace environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0028] Figure 1 The present invention is a schematic diagram of an automatic testing system for aerospace optical communication systems.

[0029] Figure 2 This is a connection diagram.

[0030] Figure 3 It is a workflow diagram.

[0031] Figure 4 The present invention provides a flow chart of a method for automatically testing an aerospace optical communication system.

[0032] In the figure: 1-FPGA processing module, 2-channel switch module, 3-multi-channel analog acquisition module, 4-signal interface matching module, 5-digital optical module, 6-multiple analog laser modules, 7-multiple analog detector modules, 8-oven-controlled crystal oscillator module, 9-A / D acquisition, 10-multi-channel analog switch. DETAILED DESCRIPTION

[0033] The following describes embodiments of the present invention in detail, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and are not to be construed as limiting the present invention.

[0034] See also Figures 1 to 3 In a first aspect, the present invention provides a system for automatically testing aerospace optical communication systems, comprising an FPGA processing module, a channel switch module, a multi-channel analog quantity acquisition module, a signal interface matching module, multiple digital optical modules, multiple analog laser modules, and multiple analog detector modules;

[0035] The FPGA processing module is used to receive and process signals from the digital optical module, the analog laser module, and the analog detector module, and communicate with the satellite platform network management through the signal interface matching module;

[0036] The channel switch module is used to control the switch of the signal channel;

[0037] The multi-channel analog quantity acquisition module is used to sample the analog quantity parameters of the finalized analog laser module and multiple analog detector modules;

[0038] The signal interface matching module is used to convert the RS422 level signal into an LVTTL level signal that can be recognized by the FPGA processing module and the digital optical module;

[0039] The digital optical module is used to complete the conversion between digital electrical signals and optical signals and provide technical parameters of the digital optical signals in real time;

[0040] The analog laser module is used to convert the analog radio frequency electrical signal into an optical signal and output the analog quantity to the multi-channel analog quantity acquisition module;

[0041] The analog detector module is used to convert the optical signal into an analog radio frequency electrical signal and output the analog quantity to the multi-channel analog quantity acquisition module.

[0042] Furthermore, the channel switch module includes a MOS tube and an operational amplifier. The gate threshold voltage of the MOS tube is -2V to -4V, the turn-on delay time is 30ns, the turn-off delay time is 70ns, the static drain-source on-resistance is 0.29 ohms, the total dose resistance is ≥100Krad (Si), and the single particle resistance is ≥75MeV·cm 2 / mg.

[0043] Furthermore, the A / D acquisition of the multi-channel analog acquisition module is 12-bit resolution, the conversion time is 10μs, it has 11 analog input channels, the maximum linear error is ±1.5LSB, the total dose resistance is ≥60krad(Si), and the single particle resistance is ≥75MeV·cm 2 / mg.

[0044] Furthermore, the signal interface matching module circuit is DS26LV31QML, DS26LV32AW-QML, DS26LV31QML completes the transmission of 4-way LVTTL level to RS422 level, is packaged as W16A, and has an operating voltage of 3~3.6V, DS26LV32AW-QML completes the reception of 4-way RS422 level to LVTTL level, is packaged as W16A, and has an operating voltage of 3~3.6V.

[0045] Furthermore, the digital optical module circuit is HT850M10G4T4R-80mm-A, a hermetically sealed butterfly package 4-way parallel optical transceiver module, the module center wavelength is 850nm, single power supply 3.3VDC power supply, each channel transmission rate is 10.3125Gbps, the operating temperature range is -40℃~+85℃, the total dose resistance is ≥30krad(Si), and the single particle resistance is ≥75MeV·cm 2 / mg, total dose of displacement damage ≥5×10 10 N / cm 2 , airtightness: no more than 5×10 -8 Pa*m 3 / s.

[0046] Furthermore, the analog laser module circuit is T-03-YYY-B-01#H, which is used to convert the input analog RF electrical signal into the optical signal required by the wavelength division multiplexer. The operating temperature is -55℃~+85℃, the output optical power is 8~10mW, the threshold current Ith≤20mA, the optical isolation typical value is 35dB, and it has backlight detection and automatic temperature control unit, interface SMP, and pigtail.

[0047] Furthermore, the analog detector module circuit is R-12-MP-B-02#H, which is used to convert the optical signal input by the wavelength division multiplexer into an analog radio frequency electrical signal, has an operating temperature of -55°C to +85°C, an operating current ≤10mA, an SMP interface, and a pigtail.

[0048] In this embodiment, the radiation-resistant FPGA processing module is connected to the oven-controlled crystal oscillator module, signal interface matching module, digital optical module, A / D acquisition module, and RS422 module, and receives switching control from the channel switch module. The radiation-resistant channel switch module is directly connected to the satellite platform network management on one side and to the FPGA processing module within the optical communication system on the other side. It is also connected to digital optical modules ①-⑤, analog laser modules ①-⑤, and analog detector modules ①-⑤, controlling the switching of corresponding signal channels according to the control of the satellite platform network management. The radiation-resistant multi-channel analog acquisition module includes A / D acquisition and multi-channel analog switching, both of which are connected to the FPGA processing module. The analog laser modules ①-⑤ and analog detector modules ①-⑤ each output two analog signals to the multi-channel analog switch module. The multi-channel analog switch outputs two analog signals to the A / D acquisition module according to the control of the FPGA processing module. The signal interface matching module is an RS422 level conversion interface, used to convert the input RS422 level signal to TTL level that can be recognized by the FPGA processing module and the digital optical module. The analog laser modules are connected to the wavelength division multiplexing module. Each module outputs two analog signals to a multi-channel analog switch. Simultaneously, they receive switch control from the satellite platform network management via the channel switch module. The analog detector modules are connected to the wavelength division multiplexing module. Each module outputs two analog signals to a multi-channel analog switch. Simultaneously, they receive switch control from the satellite platform network management via the channel switch module. The digital optical modules are connected to the interface matching module and FPGA, to the wavelength division multiplexing module, and to the FPGA processing module via the I2C bus. Simultaneously, they receive switch control from the satellite platform network management via the channel switch module.

[0049] The FPGA module's main chip is ACTEL's APA600-PQG208M, a Flash-based CMOS process with 600,000 system gates and a 0.22μm 4LM process. It operates at a maximum system clock of 150MHz and operates at +2.5V and +3.3V voltages. It can communicate with the satellite platform's network management system via an RS422 module, control multi-channel analog acquisition modules, and read analog values ​​acquired by A / D. It also accesses the DDM function of digital optical modules via the I2C data bus, providing real-time information on optical power, operating temperature, voltage, and other parameters.

[0050] The operating frequency of the constant temperature crystal oscillator module is 40MHZ, the output waveform is square wave, and the typical frequency stability is 5×10 in the temperature range of -55℃~+125℃. -6 / s, the overall dimensions are 7.2*5.2*1.8mm, the package is ceramic package, parallel sealing;

[0051] The radiation-resistant channel switch module is mainly composed of the radiation-resistant MOS tube RCS7382U3(P) and the operational amplifier OPA211AIDRGR. The MOS tube has a gate threshold voltage Vgs of -2V to -4V, a turn-on delay time of 30ns, a turn-off delay time of 70ns, a static drain-source on-resistance Rds of 0.29 ohms, a total dose resistance of ≥100Krad(Si), and a single particle resistance of ≥75MeV·cm 2 The main parameters of the OPA211AIDRGR op amp are total harmonic distortion + noise (THD+N): –136dB (G = 1, f = 1kHz), 16-bit settling time: 700ns, rail-to-rail output, output current: 30mA, and low supply current: 3.6mA / channel.

[0052] The radiation-resistant multi-channel analog acquisition module is mainly composed of the radiation-resistant AD chip B2543ARH and the radiation-resistant analog switch BM2720MQRH. The B2543ARH has 12-bit resolution, 10μs conversion time, 11 analog input channels, a maximum linear error of ±1.5LSB, programmable MSB or LSB priority output, and a total dose resistance of ≥60krad (Si) and a single particle resistance of ≥75MeV·cm 2 The BM2720MQRH analog switch chip is a 64-channel T-type analog switch implemented in two stages, consisting of four groups. Each group consists of a 16-to-1 analog switch unit and a transmission switch unit in a 4-to-1 analog switch unit, cascaded. A switch is grounded at the internal connection point to form a T-type switch junction. It has low power consumption of ≤1mA, a conduction time of ≤600ns, a total dose resistance of ≥100krad (Si), and a single-particle resistance of ≥80MeV·cm. 2 / mg.

[0053] The signal interface matching modules are DS26LV31QML and DS26LV32AW-QML, which comply with TIA / EIA-422 and ITU-TV.11 standards. The DS26LV31QML completes the transmission of 4-channel LVTTL level to RS422 level, is packaged in W16A, and has an operating voltage of 3 to 3.6V. The DS26LV32AW-QML completes the reception of 4-channel RS422 level to LVTTL level, is packaged in W16A, and has an operating voltage of 3 to 3.6V.

[0054] The digital optical module is the HT850M10G4T4R-80mm-A, a 4-way parallel optical transceiver module in an airtight butterfly package. The module has a central wavelength of 850nm and is powered by a single 3.3VDC power supply. The transmission rate per channel is 10.3125Gbps, and the operating temperature range is -40°C to +85°C. The total dose resistance is ≥30krad (Si) and the single particle resistance is ≥75MeV·cm 2 / mg, total dose of displacement damage ≥5×10 10 N / cm 2 , airtightness: no more than 5×10 -8 Pa*m 3 / s.

[0055] The analog laser module is T-03-YYY-B-01#H, which is used to convert the input analog RF electrical signal into the optical signal required by the wavelength division multiplexer. It has an operating temperature of -55℃ to +85℃, an output optical power of 8 to 10mW, a threshold current Ith ≤ 20mA, and a typical optical isolation of 35dB. It has backlight detection and an automatic temperature control unit, an SMP interface, and a pigtail.

[0056] The analog detector module is R-12-MP-B-02#H, which is used to convert the optical signal input by the wavelength division multiplexer into an analog RF electrical signal. It has an operating temperature of -55℃ to +85℃, an operating current of ≤10mA, an SMP interface, and a pigtail.

[0057] See also Figure 4 In a second aspect, a method for automatically testing an aerospace optical communication system is provided, which is used in the system for automatically testing an aerospace optical communication system according to the first aspect, and comprises the following steps:

[0058] S1: The satellite platform network management starts the automatic test and reads the real-time reported data from the FPGA processing module in the optical communication system through the interface matching module;

[0059] Specifically, the satellite platform network management starts the automatic test, first reading the real-time reported data of the FPGA processing module in the optical communication system through the interface matching module, with a reading interval of 1s.

[0060] S2: The FPGA processing module reads the optical power, temperature, and voltage parameters of the digital optical module through the I2C bus and determines whether the digital optical module is working properly.

[0061] Specifically, the FPGA processing module reads the optical power, temperature, and voltage parameters of the digital optical module through the I2C bus. If the output optical power is ≥-3dBm, the temperature is -40°C to +85°C, and the voltage is +2.8 to +3.5V, the digital optical module is working properly and stores the result.

[0062] S3: The FPGA processing module controls the analog switch chip to enable and select the analog quantity of the analog laser module or the analog detector module for sampling;

[0063] Specifically, the FPGA processing module controls the analog switch chip BM2720MQRH to enable, EN is high, and first selects the analog 1 working voltage of the analog laser module 1 according to the agreed address. After the analog 1 is selected, the analog 1 is connected to the analog input IN0 of the A / D chip.

[0064] S4: The FPGA processing module controls and enables the A / D chip, performs A / D conversion on the selected analog quantity, and stores the converted data;

[0065] Specifically, the FPGA processing module controls and enables the A / D chip, setting chip select CS high. First, over 12 clock cycles, the 8-bit control word 00000111 is written to the on-chip control register, selecting analog input IN0. The falling edge of the last clock cycle initiates the A / D conversion process. After a period of conversion time, data is read from the DATA OUT pin over the following 12 clock cycles. Then, CS transitions from high to low, enabling the I / OCLOCK and DATAINPUT terminals and initiating A / D conversion of analog quantity 1. After this conversion is complete, EOC transitions from high to low, completing the acquisition of analog quantity 1 from analog laser module 1. The acquisition of other analog quantities is then completed sequentially.

[0066] S5: After the FPGA processing module completes the sampling of all analog quantities, it assembles the stored data into data frames and reports them to the satellite platform network management through the RS422 interface;

[0067] Specifically, after completing analog acquisition of laser 1, the FPGA module stores the data and switches to the next channel. It then tests that channel according to steps S3 to S6. After the test is complete, it switches to the next channel again, and so on. After the test is complete, steps S3 and S4 are repeated 20 times. Once the FPGA completes AD acquisition of all analog quantities in the optical communication system, it organizes the stored data into data frames and reports them to the satellite platform network management at a data rate of 115.2 kbit / s.

[0068] S6: The satellite platform network manager checks whether the parameters of the digital optical module, analog laser module, and detector module are correct. If the result is incorrect, the corresponding channel switch is turned off, the data when it is turned off is measured, and then the channel switch is turned on again, and the data after it is turned on is measured again.

[0069] Specifically, the satellite platform network manager checks whether the parameters of the digital optical module and the analog laser detector are correct. If the result is incorrect, the corresponding channel switch is turned off, the data when it is turned off is measured, and then the channel switch is turned on and the data after it is turned on is measured again.

[0070] S7: The satellite platform network manager compares the measured data and reports the working status of the aerospace optical communication system to the ground observation station.

[0071] Specifically, the satellite platform network manager compares the measured data and reports the working status of the aerospace optical communication system to the ground observation station.

[0072] The above disclosure is merely a preferred embodiment of a system and method for automatic testing of aerospace optical communication systems of the present invention. It is of course not intended to limit the scope of the present invention. A person skilled in the art will understand that implementing all or part of the processes of the above embodiment and making equivalent changes in accordance with the claims of the present invention still fall within the scope of the invention.

Claims

1. A system for automatic testing of aerospace optical communication systems, characterized in that: It includes FPGA processing module, channel switch module, multi-channel analog acquisition module, signal interface matching module, multiple digital optical modules, multiple analog laser modules and multiple analog detector modules; The FPGA processing module is used to receive and process signals from the digital optical module, the analog laser module, and the analog detector module, and communicate with the satellite platform network management through the signal interface matching module; The channel switch module is used to control the switch of the signal channel; The multi-channel analog quantity acquisition module is used to sample the analog quantity parameters of the finalized analog laser module and multiple analog detector modules; The signal interface matching module is used to convert the RS422 level signal into an LVTTL level signal that can be recognized by the FPGA processing module and the digital optical module; The digital optical module is used to complete the conversion between digital electrical signals and optical signals and provide technical parameters of the digital optical signals in real time; The analog laser module is used to convert the analog radio frequency electrical signal into an optical signal and output the analog quantity to the multi-channel analog quantity acquisition module; The analog detector module is used to convert the optical signal into an analog radio frequency electrical signal and output the analog quantity to the multi-channel analog quantity acquisition module.

2. The system for automatic testing of aerospace optical communication systems according to claim 1, wherein: The channel switch module includes a MOS tube and an operational amplifier. The gate threshold voltage of the MOS tube is -2V to -4V, the turn-on delay time is 30ns, the turn-off delay time is 70ns, the static drain-source on-resistance is 0.29 ohms, the total dose resistance is ≥100Krad (Si), and the single particle resistance is ≥75MeV·cm 2 / mg.

3. The system for automatic testing of aerospace optical communication systems according to claim 1, wherein: The multi-channel analog acquisition module has an A / D acquisition resolution of 12 bits, a conversion time of 10 μs, 11 analog input channels, a maximum linear error of ±1.5 LSB, a total dose resistance of ≥60 krad (Si), and a single particle resistance of ≥75 MeV·cm 2 / mg.

4. The system for automatic testing of aerospace optical communication systems according to claim 1, wherein: The signal interface matching module circuit is DS26LV31QML and DS26LV32AW-QML. DS26LV31QML completes the transmission of 4-way LVTTL level to RS422 level, is packaged as W16A, and has an operating voltage of 3 to 3.6V. DS26LV32AW-QML completes the reception of 4-way RS422 level to LVTTL level, is packaged as W16A, and has an operating voltage of 3 to 3.6V.

5. The system for automatic testing of aerospace optical communication systems according to claim 1, wherein: The digital optical module circuit is HT850M10G4T4R-80mm-A, a four-way parallel optical transceiver module in an airtight butterfly package. The module has a central wavelength of 850nm, a single 3.3VDC power supply, a transmission rate of 10.3125Gbps per channel, an operating temperature range of -40°C to +85°C, a total dose resistance of ≥30krad (Si), and a single particle resistance of ≥75MeV·cm 2 / mg, total dose of displacement damage ≥5×10 10 N / cm 2 , airtightness: no more than 5×10 -8 Pa*m 3 / s.

6. The system for automatic testing of aerospace optical communication systems according to claim 1, wherein: The analog laser module circuit is T-03-YYY-B-01#H, which is used to convert the input analog RF electrical signal into the optical signal required by the wavelength division multiplexer. It has an operating temperature of -55°C to +85°C, an output optical power of 8 to 10mW, a threshold current Ith ≤ 20mA, a typical optical isolation value of 35dB, and is equipped with backlight detection and automatic temperature control units, an SMP interface, and a pigtail.

7. The system for automatic testing of aerospace optical communication systems according to claim 1, wherein: The analog detector module circuit is R-12-MP-B-02#H, which is used to convert the optical signal input by the wavelength division multiplexer into an analog radio frequency electrical signal. It has an operating temperature of -55°C to +85°C, an operating current of ≤10mA, an SMP interface, and a pigtail.

8. A method for automatic testing of an aerospace optical communication system, used in the system for automatic testing of an aerospace optical communication system according to any one of claims 1 to 7, characterized in that: The following steps are involved: The satellite platform network management starts an automatic test and reads the real-time reported data from the FPGA processing module in the optical communication system through the interface matching module; The FPGA processing module reads the optical power, temperature, and voltage parameters of the digital optical module through the I2C bus and determines whether the digital optical module is working properly; The FPGA processing module controls and enables the analog switch chip, and selects the analog quantity of the analog laser module or the analog detector module for sampling; The FPGA processing module controls and enables the A / D chip, performs A / D conversion on the selected analog quantity, and stores the converted data; After the FPGA processing module completes the sampling of all analog quantities, it forms the stored data into data frames and reports them to the satellite platform network management through the RS422 interface; The satellite platform network administrator checks whether the parameters of the digital optical module and analog laser module detector are correct. If the result is incorrect, the corresponding channel switch is turned off, the data when it is turned off is measured, and then the channel switch is turned on and the data after it is turned on is measured again. The satellite platform network manager compares the measured data and reports the working status of the aerospace optical communication system to the ground observation station.

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