Satellite optical head integrated ground automation test system and full-link test method

Abstract

This invention discloses an integrated ground-based automated testing system and end-to-end testing method for satellite optical heads. The system includes a light source input module, a beam splitting and polarization module, a high-precision alignment optical path module, and an integrated coaxial fixture arranged sequentially along the same main optical axis, forming a shared main optical path for transmission, reception, calibration, and monitoring. The beam splitting and polarization module splits the beam into multiple monitoring branches for parallel monitoring. A fast-reflecting mirror and an imaging monitoring unit form a closed loop for optical axis calibration. The integrated coaxial fixture simultaneously interfaces with the optical head's transceiver end. A high-low temperature vacuum environment simulation unit achieves environmental and optical testing linkage through an optical transmission window. Implementing this invention allows for automated testing of all indicators on a single optical path, eliminating human error and improving accuracy, yield, and production capacity.

Description

Technical Field

[0001] This invention relates to the field of satellite laser communication, specifically to the field of optical inspection and automated testing, and particularly to an integrated ground-based automated testing system for satellite optical heads and a full-link testing method. Background Technology

[0002] With the large-scale construction of low-Earth orbit satellite constellations, inter-satellite laser communication has become a key technology for constellation networking. As the core payload of the inter-satellite link, the satellite optical head must undergo high-precision testing before leaving the factory, including testing for optical axis, modulation transfer function, wavefront, stray light, polarization, and communication bit error rate. The performance of the entire link must also be verified in extreme environments such as vacuum and high and low temperature cycling to ensure the reliability of on-orbit link establishment.

[0003] The existing ground testing of satellite optical heads suffers from the following drawbacks: First, the testing is fragmented, with transmission, reception, and communication indicators tested on separate platforms, requiring repeated disassembly and switching of products, resulting in low efficiency and introducing clamping errors. Second, it is highly dependent on manual labor, requiring 8 to 12 people to coordinate for a single test, with a cycle of 5 to 7 days and a monthly production capacity of only 20 to 50 units. Third, the accuracy and consistency are poor, with random errors introduced by manual optical path alignment, resulting in a yield rate of only 70% to 80%. Fourth, general-purpose testing platforms can only complete basic optical power and continuity tests, lacking dedicated test instructions for satellite optical heads, and cannot support specialized tests such as modulation transfer function, wavefront, and stray light, requiring manual calculation and interpretation of specialized indicators. Fifth, environmental testing and optical testing are disconnected, requiring manual re-adjustment and testing after changes in environmental conditions, resulting in large testing errors, low efficiency, and inaccurate correlation between test data and operating conditions. Sixth, test data is stored in a scattered manner, forming data silos and lacking unified analysis and quality traceability capabilities.

[0004] Therefore, how to provide an integrated, fully automated, high-precision, and environmentally compatible ground testing solution for satellite optical heads is an urgent problem to be solved. Summary of the Invention

[0005] This invention provides an integrated ground-based automated testing system and a full-link testing method for satellite optical heads. It can complete automated testing of all indicators of transmission, reception, communication and environment on a single optical path, eliminating human error and improving production capacity and yield.

[0006] On one hand, embodiments of the present invention provide an integrated ground-based automated testing system for satellite optical heads. The system includes: a light source input module, a beam splitting and polarization module, a multi-path parallel monitoring module, a high-precision alignment optical path module, an integrated coaxial fixture, and a high- and low-temperature vacuum environment simulation unit. The light source input module, the beam splitting and polarization module, the high-precision alignment optical path module, and the integrated coaxial fixture are sequentially arranged along the same main optical axis, forming a main optical path shared for transmission, reception, calibration, and monitoring. The light source input module includes a light source unit for generating a test light signal, which is transmitted along the main optical path. The beam splitting and polarization module splits the test light signal on the main optical path into multiple parallel monitoring branches. The multiple parallel monitoring module includes an imaging monitoring unit disposed on the monitoring branch for collecting the beam of the test light signal and the light returned by the satellite optical head under test. The high-precision alignment optical path module includes a beam adjustment component, which is used to adjust and collimate the test light signal incident along the main optical axis. The beam adjustment component and the imaging monitoring unit cooperate to form an optical axis calibration closed loop. The optical head of the satellite under test is located at the end of the main optical path. The integrated coaxial fixture is used to simultaneously connect the transmitting end and the receiving end of the optical head of the satellite under test, automatically complete the coaxial positioning, and make the receiving and receiving optical paths coaxial with the main optical path. The high and low temperature vacuum environment simulation unit includes a cabin with an optical transmission window. The optical head of the satellite under test is set in the cabin. The test light signal is incident on the receiving end of the optical head of the satellite under test through the optical transmission window. The beam returned from the transmitting end of the optical head of the satellite under test returns through the main optical path and is split by the beam splitting and polarization module to the multi-path parallel monitoring branch.

[0007] In one possible implementation, the beam splitting and polarization module includes a non-polarizing beam splitter prism and a polarizing beam splitter prism for splitting the test optical signal into multiple parallel monitoring branches.

[0008] In one possible implementation, the multi-channel parallel monitoring module further includes a power monitoring unit, a polarization monitoring unit, and a wavefront monitoring unit. The wavefront monitoring unit, together with the power monitoring unit, the polarization monitoring unit, and the imaging monitoring unit, constitutes four parallel monitoring branches. Therefore, this implementation enables parallel monitoring of power, polarization, light spot, and wavefront across multiple branches, avoiding the lag of single-channel monitoring, achieving real-time monitoring and multi-dimensional data calibration during the testing process, and improving the reliability and comprehensiveness of the test data.

[0009] In one possible implementation, the power monitoring unit includes an optical power meter, which is respectively arranged in the beam splitting branch and the return branch of the non-polarizing beam splitter; the polarization monitoring unit includes an ellipsometer, which is arranged in the beam splitting branch of the polarizing beam splitter; the wavefront monitoring unit includes a wavefront sensor; the imaging monitoring unit includes an area array CCD camera and an imaging lens group; and each monitoring branch is equipped with an electrically driven light-shielding baffle.

[0010] In one possible implementation, the system further includes a system control and processing module, which is used to schedule the various modules of the system to perform automated testing according to a preset testing procedure. Therefore, in this implementation, the system control and processing module uniformly schedules the various modules according to the preset testing procedure, achieving fully automated operation from installation and testing to reporting.

[0011] In one possible implementation, the system further includes a bit error rate tester and a telemetry and control bus. The bit error rate tester is coupled to the main optical path and is used to perform bit error rate testing on the communication optical signal transmitted back by the optical head of the satellite under test. The overall control and processing module is connected to the optical head of the satellite under test through the telemetry and control bus and is used to synchronously collect telemetry data from the optical head of the satellite under test during the test. Therefore, in this implementation, by combining the telemetry and control bus with the synchronous collection of telemetry data from the optical head, real-time monitoring and multi-dimensional data calibration of the test process are achieved.

[0012] In one possible implementation, the system further includes a dedicated test instruction library for satellite optical heads. This library contains standardized test scripts and algorithms adapted to inter-satellite laser communication optical heads, covering calibration, functionality, optics, and communication testing, along with preset pass / fail thresholds. The overall control and processing module calls this dedicated test instruction library to automatically complete parameter configuration, process execution, index calculation, and pass / fail determination. Therefore, this implementation solves the problem that general-purpose testing platforms cannot cover specialized optical testing, enabling fully automated operation of the entire optical head manufacturing process without manual intervention.

[0013] In one possible implementation, the light source input module further includes an electrically driven waveplate group for adjusting the polarization state of the incident light. For example, the electrically driven waveplate group may include a half-waveplate and a quarter-waveplate, whose rotation angle is automatically adjusted by optical path control to stably regulate the polarization state of the incident light and ensure polarization matching of the light receiving and receiving paths.

[0014] In one possible implementation, the light source unit includes a tunable laser and a visible light calibration light source. For example, the tunable laser has a wavelength range of 1529 nm to 1567 nm, 96 channels, a maximum output power of 20 mW, and can output a modulated light signal of a specified wavelength; the visible light calibration light source may have a wavelength of 638 nm.

[0015] In one possible implementation, the beam adjustment assembly includes a fast-reflecting mirror and a collimating lens. The fast-reflecting mirror is used to adjust the angle of the beam incident along the principal optical axis, and the collimating lens is used to convert the beam into parallel light. A folding mirror is also provided on the principal optical path, located between the beam splitting and polarization module and the fast-reflecting mirror, for realizing optical path folding and coaxial calibration of the principal optical path. The high-precision alignment optical path module also includes an electrically switched lens group, which is used to switch between different focal lengths to adapt to optical heads with different focal length specifications. For example, the folding mirror can be a 45° folding mirror, which can realize 90° optical path folding while completing coaxial calibration of the principal optical path, ensuring that the system's mechanical reference axis and optical axis are highly coincident. The collimating lens can have a focal length of 3 meters, converting the point light source into large-aperture parallel light, simulating the parallel light incident conditions of long-distance inter-satellite transmission, and ensuring that the light spot quality at the entrance pupil of the optical head of the satellite under test conforms to the real working conditions.

[0016] In one possible implementation, the integrated coaxial fixture has a positioning accuracy at the sub-micron level. The integrated coaxial fixture includes an electrically adjustable platform for automatically completing coaxial positioning. It should be noted that the sub-micron level positioning accuracy of the integrated coaxial fixture eliminates clamping errors caused by multi-station testing at the clamping level, allowing transmission testing, reception testing, and communication link testing to be carried out in parallel without switching fixtures.

[0017] In one possible implementation, the high and low temperature vacuum environment simulation unit integrates a high and low temperature environment control and vacuum simulation system to simulate extreme operating conditions of temperature cycling and vacuum degree. For example, it can achieve temperature cycling from -55℃ to +70℃ and 1×10⁻ 5 Extreme working condition simulation of vacuum degree Pa.

[0018] On the other hand, embodiments of the present invention also provide a satellite optical head testing system, the system comprising: a light source input module, a beam splitting and polarization module, and a multi-channel parallel monitoring module; the light source input module includes a light source unit for generating a test light signal; the beam splitting and polarization module includes a non-polarizing beam splitter prism and a polarizing beam splitter prism for splitting the test light signal into multiple parallel monitoring branches; the multi-channel parallel monitoring module includes a power monitoring unit, a polarization monitoring unit, a wavefront monitoring unit, and an imaging monitoring unit, each monitoring unit being respectively disposed on a corresponding monitoring branch for parallel monitoring of the test light signal and the beam transmitted back from the satellite optical head under test.

[0019] In one possible implementation, the power monitoring unit includes an optical power meter, which is respectively arranged in the beam splitting branch and the return branch of the non-polarizing beam splitter; the polarization monitoring unit includes an ellipsometer, which is arranged in the beam splitting branch of the polarizing beam splitter; the wavefront monitoring unit includes a wavefront sensor; the imaging monitoring unit includes a CCD camera and an imaging lens group; and each monitoring branch is equipped with an electrically driven light-shielding baffle. Therefore, in this implementation, the non-polarizing beam splitter and the polarizing beam splitter split the beam to each monitoring branch according to power and polarization. Power, polarization, beam spot, and wavefront parameters are acquired synchronously through multi-channel parallel monitoring, avoiding the lag of single-channel monitoring.

[0020] In another aspect, embodiments of the present invention provide a full-link testing method for satellite optical heads, applied to the aforementioned integrated ground-based automated testing system for satellite optical heads. The method includes: installing the satellite optical head under test onto the integrated coaxial fixture, wherein the integrated coaxial fixture simultaneously connects to both the transmitting and receiving ends of the satellite optical head under test, automatically completing coaxial positioning; performing a full-link self-test on the system, and entering the automated testing process after the self-test shows no abnormalities; and performing optical index testing, optoelectronic communication full-link verification, high and low temperature vacuum environment linked cyclic testing, and data fusion analysis and archiving according to a preset testing process.

[0021] In one possible implementation, the optical performance test includes an optical axis calibration test; the optical axis calibration test includes: performing an angle scan through the beam adjustment component, the imaging monitoring unit acquiring the position of the center of gravity of the light spot at different angles, fitting and calculating the angle between the optical axis and the mechanical axis of the optical head of the satellite under test based on the position of the center of gravity of the light spot, and driving the beam adjustment component to perform closed-loop correction based on the angle.

[0022] In one possible implementation, the optical performance testing further includes MTF testing, stray light testing, polarization testing, and wavefront testing. The MTF testing involves acquiring a light spot intensity distribution curve using the knife-edge method, and calculating the modulation transfer function based on the curve. The stray light testing involves controlling an electrically driven baffle to block the main light spot, allowing peripheral stray light to be incident on the imaging monitoring unit. Images are acquired in both the through-light and blocked light states, and the stray light coefficient is obtained by integrating the stray light energy to calculate the proportion of total energy. The polarization testing involves adjusting the angle of the electrically driven waveplate group, coordinating with the polarization monitoring unit to acquire transmission parameters under different polarization states, and calculating the polarization extinction ratio and polarization circularity based on these parameters. The wavefront testing involves acquiring wavefront distortion data of the beam split by an independent beam splitter using a wavefront sensor, and obtaining wavefront aberration test results based on this data. It should be noted that each specific test is automatically executed sequentially by the system under the same main optical path, and the performance indicators are automatically calculated by a built-in algorithm, eliminating the need for manual calculation and interpretation.

[0023] In one possible implementation, the end-to-end verification of optoelectronic communication includes: the light source unit outputting modulated optical signals at different powers and wavelengths, which are then incident on the receiving end of the optical head under test via the main optical path; the communication optical signal transmitted back from the transmitting end of the optical head under test is coupled to a bit error rate analyzer via the main optical path, and the communication bit error rate, receiving sensitivity, and packet loss rate are tested at different powers and wavelengths. It should be noted that by conducting tests at different powers and wavelengths one by one, the communication performance of the optical head across the entire operating condition range can be fully assessed.

[0024] In one possible implementation, the high and low temperature vacuum environment linked cycle test includes: establishing bidirectional communication with the high and low temperature vacuum environment simulation unit, which provides real-time feedback on the chamber temperature and vacuum level. Once the environmental parameters reach the target operating condition and remain stable, the corresponding test procedure is automatically triggered. During changes in environmental parameters, automatic optical path drift correction is performed synchronously, and the test data is stored with the current temperature and vacuum level timestamps. Therefore, in this implementation, a stable operating condition trigger signal is used as the test initiation condition, achieving precise timing matching between the environmental operating condition and the optical test.

[0025] In one possible implementation, the high and low temperature vacuum environment linkage cycle test includes a test parameter configuration stage, a vacuum establishment and room temperature test stage, a high and low temperature cycle test stage, and an environmental recovery stage. The test parameter configuration stage includes selecting an environmental test condition template, preset the target vacuum level, temperature range, temperature stabilization duration, number of cycles, and test items to be executed after each stabilization cycle. The vacuum establishment and room temperature test stage includes sending a vacuum start command to the high and low temperature vacuum environment simulation unit, with the vacuum sensor inside the chamber transmitting vacuum level values ​​in real time. When the vacuum level reaches the target vacuum level and remains stable for a preset duration, the full-item optical index test and optoelectronic communication full-link verification under a room temperature vacuum environment are automatically initiated. The high and low temperature cycle test stage includes sending a heating command, and the high and low temperature vacuum environment simulation unit... The ambient environment simulation unit linearly heats up to the target temperature at a set rate. During the heating and cooling process, the imaging monitoring unit collects the centroid of the light spot at a preset cycle and calculates the centroid drift. When the centroid drift exceeds a threshold, the beam adjustment component is automatically compensated. Once the cabin temperature reaches the target temperature, the temperature fluctuation stabilizes within a preset range, and remains stable for a preset duration, a full set of optical index tests is automatically executed. The environmental recovery phase includes sending a shutdown command after all cyclic tests are completed. The high and low temperature vacuum environment simulation unit then returns to room temperature at a preset rate and performs gradient vacuum breaking. After the cabin environment returns to room temperature and pressure, a room temperature and pressure retest is automatically performed. The baseline data before and after the test are compared to determine the environmental adaptability and stability of the satellite's optical head, and a special environmental test report is generated. Therefore, in this implementation, the environmental conditions and optical test timing are precisely matched, and automatic optical path drift correction is performed synchronously during heating and cooling. This eliminates the need for manual readjustment of the optical path and configuration of test parameters after changes in environmental conditions, improving the testing efficiency and data accuracy of environmental tests.

[0026] In one possible implementation, the data fusion analysis and archiving includes: real-time synchronous storage of raw data on optical power, polarization, spot size, wavefront, bit error rate, temperature, vacuum level, and optical head telemetry; automatic marking of abnormal indicators using built-in threshold judgment logic; generation of a standardized test report after all tests are completed, the standardized test report containing raw data, performance curves, and indicator comparison charts; and archiving of the full-cycle test data of a single optical head to a quality database by binding the product number, supporting full-process traceability and batch quality statistical analysis. It should be noted that unified storage and archiving of all test data by binding product numbers eliminates the data silo problem caused by scattered storage, supporting quality control and traceability in batch production.

[0027] In another aspect, embodiments of the present invention provide an electronic device, including: a processor adapted to implement one or more instructions; and a computer storage medium storing one or more instructions, the one or more instructions being adapted to be loaded by the processor and executed as follows: performing a full-link self-test on the system, and entering an automated testing process after the self-test shows no abnormalities; performing optical index testing according to a preset testing process, including angle scanning through a beam adjustment component, acquiring the position of the light spot centroid by an imaging monitoring unit, and fitting and calculating the angle between the optical axis and the mechanical axis to perform closed-loop correction; performing full-link verification of optoelectronic communication; performing a high-low temperature vacuum environment linkage cyclic test, and simultaneously performing automatic correction of optical path drift during changes in environmental parameters; and performing data fusion analysis and archiving.

[0028] In another aspect, embodiments of the present invention provide a computer storage medium storing one or more instructions, which are adapted to be loaded by a processor and executed as follows: performing a full-link self-test on the system, and entering an automated testing process after the self-test shows no abnormalities; performing optical index testing according to a preset testing process, including angle scanning through a beam adjustment component, acquiring the position of the light spot centroid by an imaging monitoring unit, and fitting and calculating the angle between the optical axis and the mechanical axis to perform closed-loop correction; performing full-link verification of optoelectronic communication; performing a high-low temperature vacuum environment linkage cyclic test, and simultaneously performing automatic correction of optical path drift during changes in environmental parameters; and performing data fusion analysis and archiving.

[0029] Therefore, this invention, through a shared main optical path for transmission, reception, calibration, and monitoring, an integrated coaxial fixture and a fast-reflection mirror optical axis calibration closed loop, and a time-series linkage closed loop control between optical testing hardware and the environmental simulation chamber, can achieve fully unattended testing from installation to reporting. The single-unit testing cycle is shortened from 5-7 days to 1-2 days, monthly production capacity increases from 20-50 units to 150-200 units, representing a 3-4 fold increase in capacity. The yield rate increases from 70%-80% to 95%-98%, and the testing manpower is reduced from 8-12 people to 1-2 people. Submicron-level alignment and nano-arc-level calibration improve testing accuracy by 90%. Implementing this invention allows for fully automated testing of all indicators on a single optical path, eliminating human error and improving accuracy, yield, and production capacity. Attached Figure Description

[0030] To more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings used in the following description of the embodiments will be briefly introduced. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0031] Figure 1 This is a scenario architecture diagram provided by an embodiment of the present invention; Figure 2 This is a schematic diagram of the structure of a ground-based automated testing system for an integrated satellite optical head provided in an embodiment of the present invention.

[0032] Figure 3 This is a schematic diagram of a multi-channel parallel monitoring architecture for a satellite optical head testing system provided in an embodiment of the present invention.

[0033] Figure 4 This is a flowchart illustrating a satellite optical head end-to-end testing method provided in an embodiment of the present invention; Figure 5 This is a schematic diagram of the stage timing of a high and low temperature vacuum environment linkage cycle test provided in an embodiment of the present invention; Figure 6 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention. Detailed Implementation

[0034] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention.

[0035] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of the embodiments of the present invention are used to distinguish different objects, rather than to describe a specific order.

[0036] like Figure 1 As shown, Figure 1 This is a scenario architecture diagram provided in an embodiment of the present invention. The integrated ground automated testing system for satellite optical heads provided in this embodiment of the present invention can be applied to, for example... Figure 1 The scenario architecture shown includes: a light source unit, including a tunable laser and a visible light calibration light source; an electric waveplate group, including 1 / 2 waveplates and 1 / 4 waveplates; a non-polarizing beam splitter; a polarizing beam splitter; a power monitoring unit, including an optical power meter; a polarization monitoring unit, including an ellipsometer; a 45° folding mirror; a fast-reflecting mirror; a collimating lens; an integrated coaxial fixture; the optical head of the satellite under test; an imaging monitoring unit, including a CCD camera and an imaging lens group; an electric switching lens group; a wavefront monitoring unit, including a wavefront sensor; a bit error rate meter; a telemetry and control bus; a high and low temperature vacuum environment simulation chamber; and a system control and processing module.

[0037] In this scenario architecture, the test light signal generated by the light source unit enters the main optical path after the polarization state is adjusted by the electric waveplate group, and then passes through the non-polarizing beam splitter and the polarizing beam splitter to the multi-path parallel detection module; the optional multi-path parallel detection module includes a power monitoring branch, a polarization monitoring branch and an imaging monitoring branch; the main beam is folded 90° by a 45° folding mirror and then incident on the fast-reflecting mirror, converted into large-aperture parallel light by the collimating lens, and then passed through the optical transmission window of the high and low temperature vacuum environment simulation chamber after the focal length is adapted by the electric switching lens group, and then acted on the optical head of the satellite under test installed on the integrated coaxial fixture; the optical head of the satellite under test and the integrated coaxial fixture are located inside the high and low temperature vacuum environment simulation chamber. The beam emitted by the optical head of the satellite under test is transmitted in reverse along the main optical path, passing sequentially through a collimating lens, a fast-reflecting mirror, and a 45° folding mirror, before entering a beam-splitting array composed of a non-polarizing beam-splitting prism and a polarizing beam-splitting prism. This array then couples to the power monitoring branch, polarization monitoring branch, and imaging monitoring branch, respectively, enabling simultaneous detection of emitted light power, polarization state, and beam characteristics. The receiving and transmitting light paths share the same main optical axis, with functional branch separation achieved only through the beam-splitting prism, eliminating the need to switch tooling and optical paths. The overall control and processing module establishes full-duplex communication with each instrument and the high-low temperature vacuum environment simulation chamber via an industrial bus, uniformly scheduling the entire testing process.

[0038] Please see Figure 2 , Figure 2 This is a schematic diagram of an integrated ground-based automated testing system for satellite optical heads provided in an embodiment of the present invention. The system includes a light source input module 101, a beam splitting and polarization module 102, a multi-channel parallel monitoring module 103, a high-precision alignment optical path module 104, an integrated coaxial fixture 105, a high-low temperature vacuum environment simulation unit 106, and a system control and processing module. The high-low temperature vacuum environment simulation unit 106 includes a cabin with an optical transmission window 108, and the satellite optical head 107 under test is disposed within the cabin. The light source input module 101 includes a light source unit for generating a test light signal. The test light signal is transmitted along the main optical path, sequentially passing through the beam splitting and polarization module 102 and the high-precision alignment optical path module 104, and then passes through the optical transmission window 108 to the receiving end of the satellite optical head 107 under test. The beam returned from the transmitting end of the satellite optical head 107 returns to the beam splitting and polarization module 102 via the main optical path, and is split by the beam splitting and polarization module 102 into multiple parallel monitoring branches. The multi-channel parallel monitoring module 103 includes an imaging monitoring unit set on the monitoring branch, used to acquire the beam of the test light signal and the spot image of the beam returned by the optical head 107 of the satellite under test; the high-precision alignment optical path module 104 includes a beam adjustment component, which is used to adjust the angle deflection and collimate the test light signal incident along the main optical axis, and cooperates with the imaging monitoring unit to form an optical axis calibration closed loop; the integrated coaxial fixture 105 simultaneously connects the transmitting end and the receiving end of the optical head 107 of the satellite under test, so that the receiving optical path is coaxial with the main optical path.

[0039] Based on the above-described scenario architecture, this invention proposes an integrated ground-based automated testing system for satellite optical heads. The system includes a light source input module, a beam splitting and polarization module, a multi-channel parallel monitoring module, a high-precision alignment optical path module, an integrated coaxial fixture, a high- and low-temperature vacuum environment simulation unit, and a system control and processing module. The system as a whole comprises five functional modules working in a two-way closed-loop collaborative manner: an integrated optical testing hardware platform, an instrument control and optical path scheduling module, a dedicated test command library for satellite optical heads, an environmental simulation and linkage control module, and a data acquisition, analysis, and report generation module. This forms an integrated closed-loop architecture encompassing hardware execution, scheduling control, algorithm-driven operation, environmental linkage, and data processing.

[0040] Specifically, the light source input module is used to generate test light signals and adjust the polarization state of the incident light. The light source unit includes a tunable laser and a 638nm visible light calibration light source. The tunable laser has a wavelength range of 1529nm to 1567nm, 96 channels, and a maximum output power of 20mW, and can output modulated light signals of a specified wavelength. The motorized waveplate group includes 1 / 2 waveplates and 1 / 4 waveplates, whose rotation angle is automatically adjusted by optical path scheduling to stably control the polarization state of the incident light and ensure polarization matching of the light receiving and receiving paths.

[0041] Specifically, the beam splitting and polarization module is composed of a combination of a non-polarizing beam splitter and a polarizing beam splitter. It splits the beam in the main optical path into two independent test optical paths according to power and polarization, and then splits the beam to the power monitoring branch, the polarization monitoring branch and the imaging monitoring branch to realize parallel monitoring of multiple branches. The 45° folding mirror realizes the 90° folding of the optical path and simultaneously completes the coaxial calibration of the main optical path to ensure that the mechanical reference axis and the optical axis of the system are highly coincident.

[0042] Specifically, the multi-path parallel monitoring module performs parallel monitoring of the incident beam and the beam returned by the optical head of the satellite under test. The power monitoring unit is equipped with a high-precision optical power meter, which is respectively arranged in the beam splitting branch of the non-polarizing beam splitter and the return branch of the optical head receiving optical path to monitor the incident light power and the emitted light power of the optical head in real time, and automatically calculate indicators such as emission efficiency and coupling efficiency; the polarization monitoring unit is equipped with an ellipsometer, which is placed in the beam splitting branch of the polarizing beam splitter to detect the polarization state, polarization circularity and other parameters of the incident light and the returned light in real time, supporting special polarization characteristic tests; the imaging monitoring unit is equipped with a high-resolution area array CCD camera and imaging lens group to acquire far-field spot images, automatically identify the spot centroid, divergence angle and spot shape, and use them for core tests such as optical axis calibration, stray light quantitative analysis and modulation transfer function calculation; each monitoring branch is independently equipped with an electric light shield, which can block the main spot as needed to realize the acquisition of stray light background baseline.

[0043] Specifically, the high-precision alignment optical path module includes a beam adjustment component, which comprises a fast-reflecting mirror and a collimating lens, used to adjust the angle deflection and collimate the test light signal incident along the principal optical axis. The high-precision alignment optical path module also includes an electrically switched lens group. The parallel light, after beam splitting, is incident on the fast-reflecting mirror, and the high-precision closed-loop adjustment of the incident optical axis is achieved through the nanoradian-level angle deflection of the fast-reflecting mirror. Subsequently, the beam enters the collimating lens with a focal length of 3 meters, converting the point source into large-aperture parallel light, simulating the parallel light incident conditions of long-distance inter-satellite transmission, ensuring that the light spot quality at the entrance pupil of the optical head of the satellite under test conforms to the real working conditions. The electrically switched lens group can switch between different focal lengths to adapt to the testing needs of optical heads with different focal length specifications.

[0044] Specifically, the integrated coaxial fixture uses a special fixture with submicron-level positioning accuracy, which can simultaneously align the transmitting and receiving ends of the satellite's optical head to ensure that the receiving and receiving optical paths are strictly coaxial with the system's main optical path. This allows for parallel transmission testing, receiving testing, and communication link testing without the need to switch fixtures. The fixture includes an electric fine-tuning platform, which automatically completes coaxial positioning.

[0045] Specifically, the high and low temperature vacuum environment simulation unit, also known as the high and low temperature vacuum environment simulation chamber, integrates high and low temperature environment control and vacuum simulation systems, and can achieve temperature cycling from -55℃ to +70℃, with a capacity of 1×10⁻ 5 Extreme working conditions simulation of vacuum level Pa; the cabin is equipped with a high-transmittance optical window to ensure that the test optical path can penetrate the cabin and act on the optical head of the satellite under test, so as to realize the linkage between environmental conditions and optical testing.

[0046] Specifically, the overall control and processing module communicates with the light source input module, the multi-channel parallel monitoring module, the fast-reflection mirror, and the high- and low-temperature vacuum environment simulation unit, respectively, to schedule and execute automated tests according to a preset test procedure. The overall control and processing module realizes instrument control and optical path scheduling, data acquisition and analysis, and report generation, and synchronously collects telemetry data from the optical head of the satellite under test via the telemetry and control bus. It should be noted that the telemetry and control bus is used for telemetry data collection between the overall control and processing module and the optical head of the satellite under test. It is separate from the industrial bus used for bidirectional timing-linked closed-loop control between the overall control and processing module and the high- and low-temperature vacuum environment simulation chamber; the two buses have different purposes and operate in parallel.

[0047] In one possible implementation, the multi-parallel monitoring module further includes a wavefront monitoring unit. This unit is equipped with a high-precision wavefront sensor, corresponding to an independent beam splitting branch. Together with the power monitoring unit, polarization monitoring unit, and imaging monitoring unit, it forms four parallel monitoring branches to acquire beam wavefront distortion data and complete wavefront aberration testing. The system also includes a bit error rate tester and a telemetry and control bus. The bit error rate tester is coupled to the main optical path and performs bit error rate testing on the communication optical signal transmitted back from the optical head of the satellite under test. The overall control and processing module is connected to the optical head of the satellite under test via the telemetry and control bus, synchronously acquiring telemetry data from the optical head during the test. Therefore, in this implementation, power, polarization, beam spot, and wavefront are monitored in parallel via a combination of non-polarizing and polarizing beam splitters. Combined with the tooling telemetry and control bus, the telemetry data from the optical head is synchronously acquired, avoiding the lag of single-path monitoring and achieving real-time monitoring and multi-dimensional data calibration during the testing process.

[0048] In one possible implementation, the system also includes a dedicated test instruction library for satellite optical heads. This library contains three categories of standardized test scripts and algorithms adapted to inter-satellite laser communication optical heads, covering calibration, functionality, optics, and communication testing, along with preset pass / fail thresholds. The overall control and processing module calls this dedicated test instruction library to automatically complete parameter configuration, process execution, index calculation, and pass / fail determination. Therefore, this implementation solves the problem that general-purpose testing platforms can only perform basic optical power and continuity tests and cannot cover specialized optical tests, enabling fully automated operation of the entire optical head manufacturing process and supporting unattended testing.

[0049] In one possible implementation, the light source includes a tunable laser with a wavelength range of 1529nm to 1567nm, 96 channels, and a maximum output power of 20mW, as well as a visible light calibration light source with a wavelength of 638nm; the motorized waveplate group includes 1 / 2 waveplates and 1 / 4 waveplates; a 45° folding mirror is also set in the main optical path, located between the beam splitting polarization module and the fast-reflecting mirror, for achieving 90° folding of the optical path and coaxial calibration with the main optical path; the collimating lens has a focal length of 3 meters; the high-precision alignment optical path module also includes a motorized switching lens group for switching different focal lengths to adapt to optical heads with different focal length specifications. It should be noted that the optical path switching can also be implemented using a motorized mirror or a fiber optic switcher. The motorized switching lens group used in this implementation has smaller aberrations and better long-term stability; in terms of acquisition equipment, the imaging monitoring unit can also use an infrared camera to adapt to the infrared optical head, but the cost is higher.

[0050] In one possible implementation, the integrated coaxial tooling achieves sub-micron positioning accuracy, including an electrically operated fine-tuning platform for automated coaxial positioning; the high and low temperature vacuum environment simulation unit integrates a high and low temperature environment control and vacuum simulation system to achieve temperature cycling from -55℃ to +70℃ and 1×10⁻ 5 Extreme operating condition simulation of vacuum level Pa. It should be noted that the system adopts a modular design, which can be adapted to multiple optical head models, reducing customization costs; in terms of architecture, the system can also be deployed in a distributed multi-station parallel manner to further improve productivity.

[0051] Please see Figure 3 Based on the above-described scenario architecture, this embodiment of the invention also provides a satellite optical head testing system. This system is a multi-channel parallel monitoring architecture, including a light source input module, a beam splitting and polarization module, and a multi-channel parallel monitoring module. Specifically, the light source input module includes a light source unit for generating a test light signal; the beam splitting and polarization module includes a non-polarizing beam splitter and a polarizing beam splitter for splitting the test light signal into multiple parallel monitoring branches; the multi-channel parallel monitoring module includes a power monitoring unit, a polarization monitoring unit, a wavefront monitoring unit, and an imaging monitoring unit, each monitoring unit being disposed on a corresponding monitoring branch for parallel monitoring of the test light signal and the beam transmitted back from the satellite optical head under test.

[0052] In one possible implementation, the power monitoring unit includes an optical power meter, which is respectively arranged in the beam splitting branch and the return branch of the non-polarizing beam splitter; the polarization monitoring unit includes an ellipsometer, which is arranged in the beam splitting branch of the polarizing beam splitter; the wavefront monitoring unit includes a wavefront sensor; the imaging monitoring unit includes an area array CCD camera and an imaging lens group; and each monitoring branch is equipped with an electrically driven light-shielding baffle. Therefore, this multi-path parallel monitoring architecture can be implemented independently of the coaxial fixture and environmental simulation unit, used as a monitoring subsystem in satellite optical head testing; it can also be combined with an integrated coaxial fixture, a high-precision alignment optical path module, and a high / low temperature vacuum environment simulation unit to form a... Figure 1 The integrated ground-based automated testing system shown.

[0053] Based on the description of the above system embodiments, this invention also discloses a full-link testing method for satellite optical heads, which can be executed by the overall control and processing module in the above system. Please refer to... Figure 4 The method includes the following steps: S201, the optical head of the satellite under test is installed onto the integrated coaxial fixture. The integrated coaxial fixture simultaneously aligns the transmitting end and the receiving end of the optical head of the satellite under test, and automatically completes coaxial positioning.

[0054] Specifically, after the optical head of the satellite under test is installed onto the integrated coaxial fixture, the fixture's electric fine-tuning platform automatically completes coaxial positioning with a positioning accuracy of sub-micron level. Since the fixture simultaneously connects to both the transmitter and receiver, and the receiver and receiver optical paths are strictly coaxial with the main optical path, subsequent transmission tests, receiver tests, and communication link tests can all be carried out in parallel without disassembling the product or switching fixtures, thus eliminating clamping errors caused by multi-station testing from a hardware perspective.

[0055] S202 performs a full-link self-check on the system. If no abnormalities are found during the self-check, the system enters the automated testing process.

[0056] Specifically, the system sequentially checks the communication status of the laser, the electric waveplate group, the fast-reflection mirror, each monitoring instrument, and the vacuum chamber sensor to confirm that the communication and working status of each device are normal. After the self-check is normal, the system enters the automated testing process, which requires no manual intervention throughout.

[0057] S203, perform optical index testing according to the preset test procedure, including optical axis calibration testing.

[0058] Specifically, the system calls upon a dedicated test instruction library for satellite optical heads, sequentially completing all optical performance tests according to a preset procedure. The optical axis calibration test utilizes a fast-reflecting mirror for minute-angle scanning, combined with an imaging monitoring unit to acquire the centroid position of the light spot at different angles. A built-in algorithm automatically fits and calculates the angle between the optical head's optical axis and the mechanical axis. Based on this angle, the fast-reflecting mirror performs closed-loop correction, achieving optical axis calibration with nanoradian-level accuracy, completely replacing manual alignment and eliminating human error. Compared to existing technologies relying on manual alignment using a six-dimensional platform, this implementation leverages the high-precision angle adjustment capability of the fast-reflecting mirror, combined with a light spot centroid recognition algorithm, to construct an optical axis calibration closed loop encompassing angle scanning, image acquisition, fitting calculation, and closed-loop correction. The optical axis calibration accuracy can stably reach the nanoradian level.

[0059] In one possible implementation, optical performance testing also includes MTF testing, stray light testing, polarization testing, and wavefront testing. MTF testing uses a knife-edge method, where the area array CCD camera of the imaging monitoring unit acquires the intensity distribution curve of the light spot, and a built-in algorithm automatically calculates the modulation transfer function to evaluate the imaging quality of the optical system. Stray light testing controls an electrically operated light-blocking baffle to block the main light spot, allowing only peripheral stray light to enter the CCD camera. Images are acquired in both the through-light and blocked light states, and the stray light coefficient is obtained by integrating the stray light energy to calculate the proportion of total energy. Polarization testing electrically adjusts the angles of the 1 / 2 waveplate and 1 / 4 waveplate, and, in conjunction with an ellipsometer, acquires transmission parameters under different polarization states, automatically calculating polarization extinction ratio, polarization circularity, and other indicators. Wavefront testing uses a wavefront sensor to acquire beam wavefront distortion data through an independent beam splitter branch, completing the wavefront aberration test. It should be noted that the above-mentioned special tests are all items that cannot be covered by existing general testing platforms and require manual calculation and interpretation. This implementation method incorporates them into the same main optical path and the same automated process for sequential execution. Each indicator is automatically calculated by the built-in algorithm of the instruction library and automatically judged according to the preset qualified criterion threshold.

[0060] S204, Perform full-link verification of optoelectronic communication.

[0061] Specifically, the tunable laser outputs a modulated optical signal of a specified wavelength, which is incident on the receiving end of the optical head of the satellite under test through the main optical path; the communication optical signal transmitted back from the transmitting end of the optical head of the satellite under test is coupled to the bit error rate tester through the system optical path, and the system automatically tests the communication bit error rate, receiving sensitivity, packet loss rate and other indicators to complete the full-link communication performance verification.

[0062] In one possible implementation, the light source unit outputs modulated optical signals at different powers and wavelengths, and the communication bit error rate, receiver sensitivity, and packet loss rate are tested at different powers and wavelengths. For example, multiple wavelength points can be selected within the wavelength range of 1529nm to 1567nm, and multiple injection power levels can be set at each wavelength point to conduct bit error rate tests one by one, thereby plotting the receiver sensitivity curve of the optical head in the full operating condition range, and comprehensively assessing the communication performance envelope.

[0063] S205 performs a high and low temperature vacuum environment linkage cycle test.

[0064] Specifically, this step utilizes the instrument control and optical path scheduling module to achieve bidirectional, time-series, closed-loop control between the optical testing hardware and the high- and low-temperature vacuum environment simulation chamber. The two establish full-duplex communication via an industrial bus, with the environmental chamber providing real-time feedback on its internal temperature and vacuum parameters. The scheduling module automatically triggers the corresponding test procedures based on the environmental conditions, and automatically corrects optical path drift during the heating and cooling process, all without requiring manual intervention. The test data is synchronously matched with the current temperature and vacuum timestamp for storage, ensuring accurate correspondence between the test data and the environmental conditions.

[0065] Please see Figure 5 In one possible implementation, the high and low temperature vacuum environment linkage cycle test includes the test parameter configuration stage, the vacuum establishment and room temperature test stage, the high and low temperature cycle test stage, and the environmental recovery stage.

[0066] Test parameter configuration stage: Before the test begins, select the environmental test condition template in the satellite optical head dedicated test instruction library. The preset parameters include target vacuum degree, temperature range (lower limit of low temperature, upper limit of high temperature), temperature stabilization duration, number of cycles, and test items to be executed after each round of stabilization.

[0067] Vacuum establishment and ambient temperature testing phase: The scheduling module sends a vacuum start command to the environmental chamber, which then starts the vacuum pump unit. The vacuum sensor inside the chamber transmits real-time values ​​back to the scheduling module every second. Once the vacuum level reaches the target value and remains stable for at least 30 minutes, the scheduling module automatically initiates full-item optical performance testing and end-to-end communication link verification under ambient temperature vacuum conditions. For example, the target vacuum level can be set to 3.6 × 10⁻³ Pa. Once the vacuum level inside the chamber reaches 3.6 × 10⁻³ Pa and remains stable for at least 30 minutes, the ambient temperature vacuum test is automatically triggered.

[0068] High and low temperature cycling test phase: The scheduling module sends a heating command, and the environmental chamber linearly rises to the target temperature at a set rate; during the heating and cooling process, the CCD camera of the imaging monitoring unit collects the centroid of the light spot every 2 minutes and calculates the drift. When the drift exceeds the threshold, the fast-reflecting mirror is driven to perform nanoradian-level automatic compensation to ensure coaxial accuracy under all working conditions; when the temperature inside the chamber reaches the target temperature and the temperature fluctuation is stable within ±0.3℃ and maintained for at least 30 minutes, a trigger signal is sent, and the scheduling module automatically executes a full set of optical index tests; all test data are synchronously matched with the current temperature and vacuum degree timestamps and stored.

[0069] Environmental recovery phase: After all cycle tests are completed, the scheduling module sends a shutdown command, and the environmental chamber slowly returns to room temperature at a preset rate and the vacuum is broken in a gradient. After the environment inside the chamber is completely restored to normal, the system automatically performs a room temperature and pressure retest, compares the baseline data before and after the test, and determines the environmental adaptability and stability of the product. Finally, an environmental special test report is automatically generated, which includes the change curve of indicators under all working conditions and the marking of abnormal items.

[0070] As can be seen, in this implementation, the stable operating condition trigger signal is used as the test start condition, the timing is precisely matched, no manual monitoring or switching is required, and the full index test under multiple environmental conditions is automatically completed. In the existing technology, environmental testing and optical testing are separated, and manual debugging is required after the environmental conditions change. However, this implementation does not require manual readjustment of the optical path and configuration of test parameters after the environmental conditions change, thus improving the testing efficiency and data accuracy of environmental testing.

[0071] S206, Perform data fusion analysis and archiving.

[0072] Specifically, during the testing process, the system synchronously stores all raw data in real time, including optical power, polarization, spot size, wavefront, bit error rate, temperature, vacuum level, and optical head telemetry; it has built-in threshold judgment logic to automatically mark abnormal indicators; and it automatically generates a standardized test report after all tests are completed, including raw data, performance curves, and indicator comparison charts.

[0073] In one possible implementation, the full-cycle test data of a single optical head is bound to the product number and archived in a quality database, supporting end-to-end traceability and batch quality statistical analysis. It should be noted that, compared to existing solutions that involve scattered storage of test data and lack unified analysis and quality traceability capabilities, this implementation achieves unified management and end-to-end traceability of test data, supporting quality control in mass production.

[0074] This invention also provides a computer storage medium (Memory), which is a memory device in an electronic device used to store programs and data. It is understood that the computer storage medium here can include both the built-in storage medium in the electronic device and extended storage media supported by the electronic device. The computer storage medium provides storage space, which stores the operating system of the electronic device. Furthermore, this storage space also stores one or more instructions suitable for loading and execution by the processor 301. When the processor 301 loads and executes these instructions, it implements the steps of the aforementioned satellite optical head end-to-end testing method. It should be noted that the computer storage medium here can be a high-speed RAM memory or a non-volatile memory, such as at least one disk storage device; optionally, it can also be at least one computer storage medium located remotely from the aforementioned processor.

[0075] like Figure 6 As shown, Figure 6 This is a schematic diagram of the structure of an electronic device provided in an embodiment of the present invention. The device includes: at least one processor 301, such as a central processing unit (CPU), at least one memory 302, and at least one bus 303. The memory 302 may store program instructions, and the processor 301 may be used to call the program instructions to execute the above-mentioned satellite optical head full-link test method.

[0076] Those skilled in the art will understand that all or part of the steps in the various methods of the above embodiments can be implemented by a program instructing related hardware. The program can be stored in a computer-readable storage medium, including read-only memory (ROM), random access memory (RAM), programmable read-only memory (PROM), erasable programmable read-only memory (EPROM), one-time programmable read-only memory (OTPROM), electrically-erasable programmable read-only memory (EEPROM), compactdisc read-only memory (CD-ROM), solid-state disk (SSD) or other optical disk storage, magnetic disk storage, magnetic tape storage, or any other computer-readable medium capable of carrying or storing data.

[0077] It should be noted that all steps in the embodiments of the present invention are performed under legal and compliant conditions, that is, all steps in the embodiments of the present invention are performed under authorized conditions.

[0078] The above description discloses only preferred embodiments of the present invention and should not be construed as limiting the scope of the present invention. Therefore, equivalent variations made in accordance with the claims of the present invention are still within the scope of the present invention.

Claims

1. A ground-based automated testing system integrating a satellite optical head, characterized in that, It includes a light source input module, a beam splitting and polarization module, a multi-channel parallel monitoring module, a high-precision alignment optical path module, an integrated coaxial tooling, and a high and low temperature vacuum environment simulation unit; The light source input module, the beam splitting and polarization module, the high-precision alignment optical path module, and the integrated coaxial tooling are arranged sequentially along the same main optical axis to form a main optical path shared by transmission, reception, calibration, and monitoring. The light source input module includes a light source unit, which is used to generate a test light signal; the test light signal is transmitted along the main optical path. The beam splitting and polarization module is used to split the test optical signal on the main optical path into multiple parallel monitoring branches; The multi-channel parallel monitoring module includes an imaging monitoring unit disposed on the multi-channel parallel monitoring branch, used to acquire the light spot image of the beam of the test light signal and the beam of the beam transmitted back by the optical head of the satellite under test; The high-precision alignment optical path module includes a beam adjustment component, which is used to adjust and collimate the test light signal incident along the main optical axis. The beam adjustment component and the imaging monitoring unit cooperate to form an optical axis calibration closed loop. The integrated coaxial fixture is used to simultaneously connect the transmitting end and the receiving end of the optical head of the satellite under test, so that the receiving optical path is coaxial with the main optical path; The high and low temperature vacuum environment simulation unit includes a cabin with an optical transmission window. The optical head of the satellite under test is disposed in the cabin. The test light signal is incident on the receiving end of the optical head of the satellite under test through the optical transmission window. The beam transmitted back from the transmitting end of the optical head of the satellite under test returns through the main optical path and is then split by the beam splitting polarization module to the multi-path parallel monitoring branch.

2. The system according to claim 1, characterized in that, The beam splitting polarization module includes a non-polarizing beam splitter prism and a polarizing beam splitter prism.

3. The system according to claim 1 or 2, characterized in that, The multi-channel parallel monitoring module also includes a power monitoring unit, a polarization monitoring unit, and a wavefront monitoring unit. The wavefront monitoring unit, together with the power monitoring unit, the polarization monitoring unit, and the imaging monitoring unit, constitutes four parallel monitoring branches.

4. The system according to claim 2, wherein the multi-channel parallel monitoring module further comprises a power monitoring unit, a polarization monitoring unit, and a wavefront monitoring unit, characterized in that, The power monitoring unit includes an optical power meter, which is respectively arranged in the beam splitting branch and the return branch of the non-polarizing beam splitter; the polarization monitoring unit includes an ellipsometer, which is arranged in the beam splitting branch of the polarizing beam splitter; the wavefront monitoring unit includes a wavefront sensor; the imaging monitoring unit includes an area array CCD camera and an imaging lens group; each monitoring branch is equipped with an electric light shield.

5. The system according to claim 1 or 2, characterized in that, It also includes a whole machine control and processing module, which is used to schedule the various modules of the system to perform automated tests according to a preset test process.

6. The system according to claim 5, characterized in that, The system also includes a bit error rate tester and a telemetry and control bus. The bit error rate tester is coupled to the main optical path and is used to perform bit error rate testing on the communication optical signal transmitted back by the optical head of the satellite under test. The whole machine control and processing module is connected to the optical head of the satellite under test through the telemetry and control bus and is used to synchronously collect the telemetry data of the optical head of the satellite under test during the test.

7. The system according to claim 5, characterized in that, The system also includes a dedicated test instruction library for satellite optical heads. This library contains standardized test scripts and algorithms adapted to inter-satellite laser communication optical heads, covering calibration, functionality, optics, and communication testing, and is equipped with preset pass / fail thresholds. The overall control and processing module calls the dedicated test instruction library for the satellite optical head to automatically complete parameter configuration, process execution, index calculation and qualification judgment.

8. The system according to claim 1 or 2, characterized in that, The light source input module also includes an electric waveplate group, which is used to adjust the polarization state of the incident light.

9. The system according to claim 1 or 2, characterized in that, The light source unit includes a tunable laser and a visible light calibration light source.

10. The system according to claim 1 or 2, characterized in that, The beam adjustment assembly includes a fast-reflecting mirror and a collimating lens. The fast-reflecting mirror is used to adjust the angle deflection of the test light signal incident along the main optical axis, and the collimating lens is used to convert the test light signal into parallel light. A folding mirror is also provided on the main optical path. The folding mirror is located between the beam splitting and polarization module and the fast-reflecting mirror, and is used to realize the optical path folding and coaxial calibration with the main optical path. The high-precision alignment optical path module also includes an electrically switched lens group, which is used to switch between different focal lengths to adapt to optical heads with different focal length specifications.

11. The system according to claim 1 or 2, characterized in that, The positioning accuracy of the integrated coaxial tooling is at the sub-micron level. The integrated coaxial tooling includes an electric fine-tuning platform, which is used to automatically complete coaxial positioning.

12. The system according to claim 1 or 2, characterized in that, The high and low temperature vacuum environment simulation unit integrates a high and low temperature environment control and vacuum simulation system to simulate extreme operating conditions of temperature cycling and vacuum degree.

13. A satellite optical head testing system, characterized in that, It includes a light source input module, a beam splitting and polarization module, and a multi-channel parallel monitoring module; The light source input module includes a light source unit, which is used to generate a test light signal; The beam splitting and polarization module includes a non-polarizing beam splitter and a polarizing beam splitter, used to split the test optical signal into multiple parallel monitoring branches. The multi-channel parallel monitoring module includes a power monitoring unit, a polarization monitoring unit, a wavefront monitoring unit, and an imaging monitoring unit. Each monitoring unit is set on a corresponding monitoring branch and is used to monitor the test optical signal and the beam transmitted back by the optical head of the satellite under test in parallel.

14. The system according to claim 13, characterized in that, The power monitoring unit includes an optical power meter, which is respectively arranged in the beam splitting branch and the return branch of the non-polarizing beam splitter; the polarization monitoring unit includes an ellipsometer, which is arranged in the beam splitting branch of the polarizing beam splitter; the wavefront monitoring unit includes a wavefront sensor; the imaging monitoring unit includes an area array CCD camera and an imaging lens group; each monitoring branch is equipped with an electric light shield.

15. A method for end-to-end testing of a satellite optical head, characterized in that, The method, applied to the integrated ground-based automated testing system for satellite optical heads according to any one of claims 1 to 12, comprises: The optical head of the satellite under test is installed onto the integrated coaxial fixture, which simultaneously connects the transmitting end and the receiving end of the optical head of the satellite under test, and automatically completes coaxial positioning. Perform a full-link self-test on the system. If no abnormalities are found during the self-test, proceed to the automated testing process. The optical index test, optoelectronic communication full-link verification, high and low temperature vacuum environment linkage cycle test, and data fusion analysis and archiving are performed according to the preset test procedure.

16. The method according to claim 15, characterized in that, The optical performance tests include optical axis calibration tests; The optical axis calibration test includes: performing an angle scan through the beam adjustment component; the imaging monitoring unit acquiring the position of the center of gravity of the light spot at different angles; calculating the angle between the optical axis and the mechanical axis of the optical head of the satellite under test based on the position of the center of gravity of the light spot; and driving the beam adjustment component to perform closed-loop correction based on the angle.

17. The method according to claim 15 or 16, characterized in that, The optical performance tests also include MTF testing, stray light testing, polarization testing, and wavefront testing. The MTF test includes: acquiring the light spot intensity distribution curve by the imaging monitoring unit using the knife-edge method, and calculating the modulation transfer function based on the light spot intensity distribution curve; The stray light test includes: controlling an electric light-shielding baffle to block the main light spot, so that the peripheral stray light is incident on the imaging monitoring unit, acquiring images in the light-through state and the light-blocking state respectively, and calculating the proportion of stray light energy to total energy by integration to obtain the stray light coefficient; The polarization test includes: adjusting the angle of the electric waveplate group, collecting transmission parameters under different polarization states in conjunction with the polarization monitoring unit, and calculating the polarization extinction ratio and polarization circularity based on the transmission parameters; The wavefront test includes: acquiring wavefront distortion data of the beam split by an independent beam splitter using a wavefront sensor, and obtaining wavefront aberration test results based on the wavefront distortion data.

18. The method according to claim 15, characterized in that, The full-link verification of optoelectronic communication includes: the light source unit outputs modulated optical signals at different powers and wavelengths, which are incident on the receiving end of the optical head of the satellite under test through the main optical path; the communication optical signal transmitted back from the transmitting end of the optical head of the satellite under test is coupled to the bit error rate tester through the main optical path, and the communication bit error rate, receiving sensitivity and packet loss rate are tested at different powers and wavelengths respectively.

19. The method according to claim 15, characterized in that, The high and low temperature vacuum environment linkage cycle test includes: establishing bidirectional communication with the high and low temperature vacuum environment simulation unit, the high and low temperature vacuum environment simulation unit providing real-time feedback on the chamber temperature and vacuum level, automatically triggering the corresponding test process when the environmental parameters reach the target working condition and remain stable, synchronously performing automatic optical path drift correction during the change of environmental parameters, and storing the test data synchronously matched with the current temperature and vacuum level timestamp.

20. The method according to claim 19, characterized in that, The high and low temperature vacuum environment linkage cycle test includes the test parameter configuration stage, the vacuum establishment and room temperature test stage, the high and low temperature cycle test stage, and the environmental recovery stage. The test parameter configuration stage includes: selecting an environmental test condition template, and presetting the target vacuum level, temperature range, temperature stability holding time, number of cycles, and test items to be executed after each round of stabilization; The vacuum establishment and room temperature testing phase includes: sending a vacuum start command to the high and low temperature vacuum environment simulation unit; the vacuum sensor inside the chamber transmitting the vacuum degree value in real time; and automatically starting the full-item optical index test and optoelectronic communication full-link verification under the room temperature vacuum environment after the vacuum degree reaches the target vacuum degree and remains stable for a preset time. The high and low temperature cycle test phase includes: sending a heating command, the high and low temperature vacuum environment simulation unit linearly heating to the target temperature at a set rate, during the heating and cooling process, the imaging monitoring unit collecting the spot centroid at a preset cycle and calculating the spot centroid drift, when the spot centroid drift exceeds a threshold, driving the beam adjustment component to perform automatic compensation, and when the chamber temperature reaches the target temperature, the temperature fluctuation stabilizes within a preset range and remains stable for a preset time, automatically executing a full set of optical index tests; The environmental recovery phase includes: after all cyclic tests are completed, a shutdown command is sent, the high and low temperature vacuum environment simulation unit recovers to room temperature at a preset rate and breaks the vacuum gradient, and after the cabin environment recovers to room temperature and pressure, the room temperature and pressure retest is automatically performed, the baseline data before and after the test are compared, the environmental adaptability and stability of the optical head of the satellite under test are determined, and a special environmental test report is generated.

21. The method according to claim 15, characterized in that, The execution data fusion analysis and archiving includes: real-time synchronous storage of raw data on optical power, polarization, spot size, wavefront, bit error rate, temperature, vacuum level, and optical head telemetry; automatic marking of abnormal indicators through built-in threshold judgment logic; generation of a standardized test report after all tests are completed, which includes raw data, performance curves, and indicator comparison charts; and archiving of the full-cycle test data of a single optical head to the quality database by binding the product number, supporting full-process traceability and batch quality statistical analysis.

Images