Commercial spaceflight COTS component irradiation database establishment method

Abstract

The invention relates to a commercial spaceflight COTS component irradiation database establishment method. The method comprises the following steps: calculating an anti-radiation index which needs to be met by a component under a current satellite demand; constructing a single-machine module based on a plurality of to-be-evaluated components; performing a total dose assessment test and a single particle assessment test on the single machine module in each working mode to obtain the total dose resistance and the single particle resistance of each component to be evaluated; performing failure protection design on the components with low total dose resistance and single particle resistance lower than the index to obtain corresponding failure protection strategies; obtaining the anti-radiation capability according to the total dose resistance and the single particle resistance of each component, and constructing a component radiation database according to the satellite operation environment parameters, the satellite demand information, the anti-radiation indexes of the components, the anti-radiation capability and the failure protection strategy. The method can reduce the research and development cost of satellites and shorten the research and development period.

Description

Technical Field

[0001] This application relates to the field of commercial space technology, and particularly to a method for establishing an irradiation database of commercial space COTS components. Background Art

[0002] With the rapid development of commercial space, space-grade COTS components with high costs and long supply cycles cannot meet the requirements of large quantities and low costs in commercial space. Instead, commercial off-the-shelf (COTS) components with large production batches and low procurement costs have become the preferred choice for the overall commercial space satellites and payload single-unit parties. COTS components are affected by space radiation particles in space, resulting in total dose effects, single-event effects, etc., causing performance degradation or even failure of COTS components, and ultimately leading to abnormal satellite functions or loss of contact.

[0003] When commercial space satellites select COTS components, they need to conduct anti-irradiation test assessments. The traditional assessment method is to first conduct anti-irradiation assessments on COTS components to determine the total dose resistance and single-event resistance capabilities of COTS components, establish an irradiation database of COTS components, and then import satellite tasks. According to the anti-irradiation indicators of the tasks, COTS components that meet the requirements are selected. If there are no COTS components that meet the requirements in the database, this method will require the re-development of COTS components and then re-assessment, resulting in a long supply cycle and affecting the delivery and use of satellites. Summary of the Invention

[0004] Based on this, it is necessary to provide a method for establishing an irradiation database of commercial space COTS components for the above technical problems.

[0005] A method for establishing an irradiation database of commercial space COTS components, the method comprising:

[0006] Simulating and calculating the anti-irradiation indicators that COTS components need to meet according to satellite operation environment parameters and satellite requirement information; the anti-irradiation indicators include total dose resistance indicators and single-event resistance indicators;

[0007] Obtaining a variety of COTS components to be evaluated, and constructing a single-unit module based on the variety of COTS components to be evaluated; the single-unit module includes multiple single-event test areas, and each single-event test area includes several COTS components to be evaluated;

[0008] Conducting total dose assessment tests on the single-unit module in each working mode to obtain the total dose resistance capabilities of each COTS component to be evaluated;

[0009] Decapsulate each COTS component to be evaluated in the single-unit module, and conduct single-event effect (SEE) qualification tests on each single-event test area in the decapsulated single-unit module under each working mode to obtain the single-event effect resistance of each COTS component to be evaluated.

[0010] Conduct failure protection design for COTS components with total ionizing dose (TID) resistance lower than the TID resistance index and COTS components with single-event effect resistance lower than the single-event effect resistance index respectively to obtain corresponding failure protection strategies.

[0011] Obtain the radiation resistance based on the TID resistance and single-event effect resistance of each COTS component, and construct a COTS component radiation database according to the satellite operating environment parameters, satellite requirement information, radiation resistance index, radiation resistance, and failure protection strategies of COTS components.

[0012] In one embodiment, it further includes: controlling the working mode of the single-unit module through a host computer, continuously applying a radiation dose to the single-unit module in the current working mode until the total dose standard of the total dose qualification test is reached; the total dose standard is obtained from the TID resistance index; during the total dose qualification test, remotely read the important parameter telemetry of the single-unit module in real time through the host computer, and conduct post-irradiation performance tests on the single-unit module at preset sampling points to obtain post-irradiation performance test results; if there are no abnormalities in the post-irradiation performance test results and important parameter telemetry at the current sampling point, continue the total dose qualification test; if abnormalities occur in the post-irradiation performance test and important parameter telemetry, pause the total dose qualification test, locate the failed COTS components in the single-unit module, conduct annealing tests on the failed COTS components, and then continue the total dose qualification test on the single-unit module. Conduct post-irradiation performance re-tests on the single-unit module at the current sampling point. If there are no abnormalities in the post-irradiation performance re-test results and important parameter telemetry, conduct an over-irradiation test, and conduct post-over-irradiation performance tests on the single-unit module after the over-irradiation test. If there are no abnormalities in the post-over-irradiation performance test results and important parameter telemetry, locate the failed COTS components in the single-unit module to obtain the radiation resistance of the failed COTS components; replace the failed COTS components and continue the total dose qualification test until all COTS components to be evaluated fail, then stop the total dose qualification test to obtain the TID resistance of each COTS component to be evaluated.

[0013] In one embodiment, it further includes: if there are no abnormalities in the post-over-irradiation performance test results and important parameter telemetry, conduct single-event effect qualification tests on the single-unit module.

[0014] In one embodiment, it further includes: if the performance retest result after irradiation and the remote measurement of important parameters are abnormal, locate the failed COTS components in the single-machine module to obtain the radiation resistance of the failed COTS components.

[0015] In one embodiment, it further includes: for COTS components with a total dose resistance lower than the total dose resistance index, calculate at least the required additional equivalent aluminum protection thickness based on the total dose resistance and the radiation design margin to obtain a protection and reinforcement plan; obtain the corresponding failure protection strategy based on the protection and reinforcement plan and the COTS component replacement plan.

[0016] In one embodiment, it further includes: for COTS components with a single-event effect resistance lower than the single-event effect threshold, perform protection and reinforcement design to obtain the corresponding protection and reinforcement plan; the protection and reinforcement design includes adding a current-limiting resistor, cold and hot backup, and triple modular redundancy protection design; obtain the corresponding failure protection strategy based on the protection and reinforcement plan and the COTS component replacement plan.

[0017] In one embodiment, it further includes: controlling the working mode of the single-machine module through the host computer, selecting the corresponding heavy ions according to the single-event effect index to irradiate each single-event test area in the de-packaged single-machine module in the current working mode, where the irradiation area of the particle beam corresponds to the single-event test area; during the single-event effect assessment test, read the remote measurement of important parameters of the single-machine module in real time through the host computer, monitor the output signals of each COTS component to be evaluated in real time through a flying wire external oscilloscope, judge whether the COTS component to be evaluated fails according to the output signals of each COTS component to be evaluated and the remote measurement of important parameters, if the COTS component to be evaluated fails, obtain the single-event effect resistance of the component according to the test situation, and continue to test other COTS components to be evaluated until all COTS components to be evaluated fail, so as to obtain the single-event effect resistance of each COTS component to be evaluated.

[0018] A system for establishing a radiation database of commercial aerospace COTS components, the system includes:

[0019] A single-machine module, host computer software, programmable power supply, flying wire external oscilloscope, performance test module, and handheld multimeter;

[0020] The single-machine module is respectively connected to the host computer, programmable power supply, flying wire external oscilloscope, and handheld multimeter. The single-machine module includes multiple single-event test areas, and each single-event test area includes several COTS components to be evaluated;

[0021] The host computer is used to control the working mode of the single-module, and respectively read back the important parameter telemetry of the single-module and the power supply voltage and current information of the programmable power supply to the single-module in real time during the total dose assessment test and the single particle assessment test, and is used to judge the abnormal operation state of the single-module and conduct failure analysis on the COTS components to be evaluated;

[0022] The programmable power supply is respectively connected to the single-module and the host computer, and is used to provide power supply for each COTS component in the single-module, and provide the output voltage and current data to the host computer;

[0023] The flying wire external oscilloscope is connected to the output end of the COTS component to be evaluated, and is used to monitor the output signal of the COTS component to be evaluated in real time and transmit it to the host computer during the single particle assessment test;

[0024] The performance test module is used to test the performance of the single-module and transmit the performance test results to the host computer; the performance includes spectrum, transmit power and receive power;

[0025] The handheld multimeter is used to test and monitor the electrical parameters of the COTS components during operation and transmit them to the host computer.

[0026] A device for establishing an irradiation database of commercial aerospace COTS components, the device includes:

[0027] The index calculation module is used to simulate and calculate the anti-irradiation indexes that the COTS components need to meet according to the satellite operation environment parameters and satellite requirement information; the anti-irradiation indexes include the total dose resistance index and the single particle resistance index;

[0028] The single-module construction module is used to obtain a variety of COTS components to be evaluated and construct a single-module based on the variety of COTS components to be evaluated; the single-module includes multiple single particle test areas, and each single particle test area includes several COTS components to be evaluated;

[0029] The total dose assessment module is used to conduct total dose assessment tests on the single-module in each working mode to obtain the total dose resistance capabilities of each COTS component to be evaluated;

[0030] The single particle assessment module is used to perform de-encapsulation processing on each COTS component to be evaluated in the single-module, and conduct single particle assessment tests on each single particle test area in the de-encapsulated single-module in each working mode to obtain the single particle resistance capabilities of each COTS component to be evaluated;

[0031] The failure protection module is used to perform failure protection design on COTS components with a total dose resistance lower than the total dose resistance index and COTS components with a single event effect resistance lower than the single event effect resistance index respectively, so as to obtain corresponding failure protection strategies;

[0032] The database construction module is used to obtain the radiation resistance according to the total dose resistance and single event effect resistance of each COTS component, and construct a COTS component radiation database according to the satellite operating environment parameters, satellite requirement information, radiation resistance index, radiation resistance and failure protection strategy of COTS components.

[0033] A computer device includes a memory and a processor. The memory stores a computer program. When the processor executes the computer program, the following steps are implemented:

[0034] Simulate and calculate the radiation resistance index that COTS components need to meet according to the satellite operating environment parameters and satellite requirement information; the radiation resistance index includes the total dose resistance index and the single event effect resistance index;

[0035] Obtain a variety of COTS components to be evaluated, and construct a single machine module based on the variety of COTS components to be evaluated; the single machine module includes multiple single event effect test areas, and each single event effect test area includes several COTS components to be evaluated;

[0036] Conduct a total dose assessment test on the single machine module in each working mode to obtain the total dose resistance of each COTS component to be evaluated;

[0037] Perform de-encapsulation processing on each COTS component to be evaluated in the single machine module, and conduct a single event effect assessment test on each single event effect test area in the de-encapsulated single machine module in each working mode to obtain the single event effect resistance of each COTS component to be evaluated;

[0038] Perform failure protection design on COTS components with a total dose resistance lower than the total dose resistance index and COTS components with a single event effect resistance lower than the single event effect resistance index respectively, so as to obtain corresponding failure protection strategies;

[0039] Obtain the radiation resistance according to the total dose resistance and single event effect resistance of each COTS component, and construct a COTS component radiation database according to the satellite operating environment parameters, satellite requirement information, radiation resistance index, radiation resistance and failure protection strategy of COTS components.

[0040] The above method for establishing an irradiation database of commercial space COTS components combines the satellite operating environment and mission requirements, determines in advance the anti-irradiation indicators that COTS components need to meet, and multiple components to be evaluated are tested simultaneously on a single-board module, such as total dose assessment tests and single-event assessment tests, avoiding the cumbersome process of individual testing, significantly shortening the testing time and reducing the R & D cost. For components with insufficient anti-irradiation capabilities found during testing, customized failure protection designs are carried out to improve their stability in the space environment. Finally, all evaluation data is integrated into a COTS component irradiation database, facilitating the subsequent rapid matching of component selection and mission requirements. The embodiments of the present invention not only ensure that COTS components meet the irradiation requirements, but also optimize the entire evaluation process, providing strong support for quickly responding to commercial space missions. BRIEF DESCRIPTION OF THE DRAWINGS

[0041] Figure 1 FIG. is a schematic flow chart of a method for establishing an irradiation database of commercial space COTS components in an embodiment;

[0042] Figure 2 FIG. is a schematic flow chart of a method for rapid evaluation of anti-irradiation of COTS components and establishment of a database in an embodiment;

[0043] Figure 3 FIG. is a schematic diagram showing the variation of cumulative dose with equivalent aluminum shielding layer thickness at different orbital altitudes in an embodiment;

[0044] Figure 4 FIG. is a schematic diagram of a single-event test circuit board in an embodiment;

[0045] Figure 5 FIG. is a block diagram of the structure of a system for establishing an irradiation database of commercial space COTS components in an embodiment;

[0046] Figure 6 FIG. is a block diagram of the structure of a device for establishing an irradiation database of commercial space COTS components in an embodiment;

[0047] Figure 7 FIG. is an internal structure diagram of a computer device in an embodiment. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0048] In order to make the objectives, technical solutions and advantages of the present application clearer, the present application will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present application and are not used to limit the present application.

[0049] In one embodiment, as Figure 1 shown, a method for establishing an irradiation database of commercial space COTS components is provided, including the following steps:

[0050] Step 102: Simulate and calculate the radiation resistance indexes that COTS components need to meet based on satellite operating environment parameters and satellite requirement information.

[0051] The satellite operating environment parameters include the satellite orbit altitude and orbit inclination, and the satellite requirement information includes the satellite service life. The radiation resistance indexes refer to the radiation dose that components can withstand in the space environment, including two indexes: total ionizing dose (TID) resistance and single event effect (SEE) resistance. The total ionizing dose (TID) refers to the total radiation dose that components can withstand when exposed to radiation for a long time, usually expressed in rad(Si). The single event effect (SEE) refers to the local failure that may occur when a high-energy particle impacts a component once.

[0052] By simulating and calculating the radiation resistance indexes, the radiation requirements of the satellite mission for components can be determined in advance, providing a clear goal for subsequent total dose assessment tests and single particle assessment tests.

[0053] Specifically, according to the overall satellite requirements, clarify information such as the satellite orbit altitude, orbit inclination, and service life, and use simulation software to calculate the radiation resistance indexes that components need to meet (including total ionizing dose resistance index and single particle resistance index). Among them, the radiation design margin (RDM) requirement for total ionizing dose resistance is greater than or equal to 2, and its formula is as follows:

[0054]

[0055] Among them, TID 元器件 refers to the total ionizing dose resistance ability of the component itself, with the unit of rad(Si), and TID 环境 refers to the cumulative dose of space radiation particles reaching the component after passing through the shielding material.

[0056] The requirements for single event effect resistance need to meet the following conditions according to aerospace standards:

[0057] 1. For devices with a LET threshold for single event latch-up (SEL) greater than or equal to 75 MeV·cm 2 / mg, they can be preferentially selected; for devices with a LET threshold for SEL greater than 37 MeV·cm 2 / mg, conduct a full system protection design, evaluate the protection effect, and if the protection effect evaluation is qualified, they can be selected.

[0058] 2. For devices with a LET threshold for single event upset (SEU) greater than or equal to 15 MeV·cm 2 / mg, they can be preferentially selected; for devices with a LET for SEU less than 15 MeV·cm 2 / mg devices can be selected after sufficient system protection design is carried out and the protection effect is evaluated and qualified.

[0059] 3. Power devices require a single event burnout (SEB) resistance LET threshold greater than 75 MeV cm 2 / mg, and the operating bias needs to be in the safe operating area (SOA).

[0060] Step 104 , obtaining a plurality of COTS components to be evaluated, and constructing a stand-alone module based on the plurality of COTS components to be evaluated.

[0061] The stand-alone module includes multiple single-particle test areas, each of which includes several COTS components to be evaluated.

[0062] The single-machine module contains multiple COTS components to be tested. This platform is used to simulate the actual satellite working environment and conduct irradiation tests. The size of the single-particle test area corresponds to the particle beam irradiation area in the single-particle assessment test. Through simulation calculation and modular testing, the radiation resistance of multiple components can be evaluated in a shorter time, which greatly accelerates the component evaluation process and shortens the R&D cycle.

[0063] Step 106 , performing a total dose assessment test on the stand-alone modules in each working mode to obtain the total dose resistance capability of each COTS component to be assessed.

[0064] The total dose assessment test (TID Test) is used to simulate the space radiation environment. By irradiating the components with a certain dose of radiation, the performance degradation of the components under different radiation doses is evaluated. The test results are usually used to judge the stability of components during long-term operation. The total dose resistance capability indicates the ability of the component to still work normally after being subjected to a certain radiation dose (TID). It is usually expressed in radiation dose (such as rad (Si)). The total dose assessment test is used to evaluate the tolerance of components to space radiation to ensure that the components can withstand long-term radiation exposure.

[0065] Step 108 , de-packaging each COTS component to be evaluated in the stand-alone module, and performing a single particle assessment test on each single particle test area in the de-packaging stand-alone module in each working mode to obtain the single particle resistance capability of each COTS component to be evaluated.

[0066] Remove the outer shell or package of the component to expose the internal core circuit part for more accurate single - particle evaluation tests. Single - particle evaluation tests are used to irradiate components with high - energy particles (such as heavy ions, protons, etc.) to evaluate their resistance to single - particle effects. Common single - particle effects include single - event upset (SEU), single - event latch - up (SEL), and single - event burnout (SEB). Decapsulating the component to expose its internal structure ensures that particles can directly act on the critical circuit and perform single - particle effect tests, thereby evaluating the component's tolerance to single - particle effects. The ability to resist single - particle effects refers to the ability of a component to maintain normal operation without failure when irradiated by high - energy particles. SEU, SEL, and SEB are common failure modes.

[0067] It can be understood that through rapid total - dose evaluation and single - particle evaluation, deficiencies in the radiation - resistance capabilities of components can be detected and supplemented in a timely manner, enabling rapid protective design or alternative design for problem components. This avoids the process of repeatedly developing new components in traditional methods, effectively reducing test time and costs.

[0068] Step 110: Conduct failure - protection designs for COTS components with total - dose - resistance capabilities lower than the total - dose - resistance index and COTS components with single - particle - resistance capabilities lower than the single - particle - resistance index respectively to obtain corresponding failure - protection strategies.

[0069] Failure - protection design refers to improving the radiation - resistance capabilities of components through redundancy design and hardening design means to ensure the stable operation of components in a high - radiation environment. Redundancy design means designing redundant backups for critical components so that when one component fails, the backup component can continue to work, preventing the overall failure of the system. Hardening design means enhancing the resistance of components to radiation through measures such as using radiation - resistant materials and improving fault - tolerance capabilities. For components with insufficient radiation - resistance capabilities, failure - protection design ensures that the components can adapt to the radiation conditions in the space environment.

[0070] Step 112: Obtain the radiation - resistance capabilities based on the total - dose - resistance capabilities and single - particle - resistance capabilities of each COTS component, and construct a COTS component radiation database according to the satellite operation environment parameters, satellite requirement information, radiation - resistance indexes, radiation - resistance capabilities, and failure - protection strategies of COTS components.

[0071] The COTS component radiation database can store the radiation resistance capabilities, failure protection designs, and other important parameters of different components in a database for convenient and quick querying and selection. According to the satellite mission requirements, suitable COTS components are selected from the database to ensure that they meet the radiation resistance requirements and can adapt to the satellite working environment. Specifically, the COTS component radiation database includes satellite requirement information, component name, manufacturer model, device specifications, process, test conditions, TID, SEL, SEU, and SEB.

[0072] It can be understood that by establishing a component radiation database, components that meet the mission requirements can be quickly queried, reducing the repeated testing of individual components in the traditional method and accelerating the mission delivery progress. At the same time, through database management, the changing requirements of satellite missions for components can be quickly responded to, reducing the development and delivery cycle.

[0073] In the above method for establishing a COTS component radiation database for commercial spaceflight, through simulation calculations, combined with the satellite operating environment and mission requirements, the radiation resistance indicators that COTS components need to meet are determined in advance. Multiple components to be evaluated are tested simultaneously on a single-module, such as total dose assessment tests and single-particle assessment tests, avoiding the cumbersome process of individual testing, significantly shortening the testing time and reducing the R & D cost. For components with insufficient radiation resistance capabilities found during testing, customized failure protection designs are carried out to improve their stability in the space environment. Finally, all evaluation data are integrated into a COTS component radiation database for convenient subsequent component selection and quick matching of mission requirements. The embodiments of the present invention not only ensure that COTS components meet the radiation requirements but also optimize the entire evaluation process, providing strong support for quickly responding to commercial spaceflight missions.

[0074] In one embodiment, as Figure 2As shown in the figure, a schematic flow chart of a method for rapid evaluation of radiation resistance of COTS components and database establishment is provided. The total dose assessment test is carried out on the single-machine module under each working mode to obtain the total dose resistance of each COTS component to be evaluated, including: controlling the working mode of the single-machine module through the host computer, continuously applying irradiation dose to the single-machine module under the current working mode until the total dose standard of the total dose assessment test is reached; the total dose standard is obtained through the total dose resistance index; during the total dose assessment test, the important parameter telemetry of the single-machine module is read back in real time through the host computer, and the post-irradiation performance test of the single-machine module is carried out at the preset sampling points to obtain the post-irradiation performance test results; if there is no abnormality in the post-irradiation performance test results and the important parameter telemetry at the current sampling point, the total dose assessment test is continued; if abnormalities occur in the post-irradiation performance test and the important parameter telemetry, the total dose assessment test is suspended, the failed COTS components in the single-machine module are located, annealing tests are carried out on the failed COTS components, and then the total dose assessment test is continued on the single-machine module. The post-irradiation performance retest of the single-machine module is carried out at the current sampling point. If there is no abnormality in the post-irradiation performance retest results and the important parameter telemetry, the over-irradiation test is carried out, and the post-over-irradiation performance test of the single-machine module after the over-irradiation test is carried out. If there is no abnormality in the post-over-irradiation performance test results and the important parameter telemetry, the failed COTS components in the single-machine module are located to obtain the radiation resistance of the failed COTS components; the failed COTS components are replaced, and the total dose assessment test is continued until all COTS components to be evaluated fail, and the total dose assessment test is stopped to obtain the total dose resistance of each COTS component to be evaluated.

[0075] In this embodiment, the post-irradiation performance test of the single-machine module at the preset sampling points means that for every 5 Krad(Si) of irradiation dose, the radiation source is lowered to stop irradiation, and the performance of the single machine is tested.

[0076] In one embodiment, the method further includes: if there is no abnormality in the post-over-irradiation performance test results and the important parameter telemetry, the single-particle assessment test is carried out on the single-machine module.

[0077] In one embodiment, the method further includes: if there is an abnormality in the post-irradiation performance retest results and the important parameter telemetry, the failed COTS components in the single-machine module are located to obtain the radiation resistance of the failed COTS components.

[0078] In one embodiment, failure protection design is carried out on COTS components with a total dose resistance ability lower than the total dose resistance index, and the corresponding failure protection strategies obtained include: for COTS components with a total dose resistance ability lower than the total dose resistance index, calculate at least the additional equivalent aluminum protection thickness required according to the total dose resistance ability and the radiation design margin to obtain a protection reinforcement plan; obtain the corresponding failure protection strategy according to the protection reinforcement plan and the COTS component replacement plan.

[0079] In one embodiment, failure protection design is carried out on COTS components with a single event effect resistance ability lower than the single event effect resistance index, and the corresponding failure protection strategies obtained include: for COTS components with a single event effect resistance ability lower than the single event effect threshold, carry out protection reinforcement design to obtain the corresponding protection reinforcement plan; the protection reinforcement design includes adding current limiting resistors, cold and hot backups, and two-out-of-three protection design; obtain the corresponding failure protection strategy according to the protection reinforcement plan and the COTS component replacement plan.

[0080] In one embodiment, single event effect assessment tests are carried out on each single event effect test area in the de-packaged single machine module in each working mode to obtain the single event effect resistance ability of each COTS component to be evaluated, including: controlling the working mode of the single machine module through the host computer, and irradiating each single event effect test area in the de-packaged single machine module in the current working mode with corresponding heavy ions according to the single event effect index, where the irradiation area of the particle beam corresponds to the single event effect test area; during the single event effect assessment test, the important parameter telemetry of the single machine module is read back in real time through the host computer, and the output signals of each COTS component to be evaluated are monitored in real time through an external oscilloscope connected by flying wires. Determine whether the COTS component to be evaluated fails according to the output signals of each COTS component to be evaluated and the important parameter telemetry. If the COTS component to be evaluated fails, obtain the single event effect resistance ability of the component according to the test situation, and continue to test other COTS components to be evaluated until all COTS components to be evaluated fail, so as to obtain the single event effect resistance ability of each COTS component to be evaluated.

[0081] In a specific embodiment, taking a satellite with an altitude of 500 km, an inclination of 98°, and a lifespan of 10 years as an example, the specific steps of the method of the present invention are described as follows:

[0082] Step 1, task import. Use simulation software to calculate the cumulative dose of components under this condition, such as Figure 3 the schematic diagram of the cumulative dose changing with the equivalent aluminum shielding layer thickness at different orbital heights shown. When the equivalent protective aluminum thickness is 2 mm, the TID 环境 is 10 krad(Si). According to the RDM of 2, the calculated TID 元器件The total dose test is at least 20 krad (Si). The single particle test selects LET = 37 or 75 MeV·cm 2 / mg of particles.

[0083] Step 2: Select components and application design. Choose components with radiation data from the component radiation database or literature research as much as possible. If not, choose components that meet the satellite performance indicators. Carry out stand-alone circuit design, and conduct radiation resistance tests after the hardware and software integration meets the overall performance indicators of the satellite.

[0084] At this point, the single machine has all the conditions for performance testing. The host computer software can read the remote measurement of important parameters of the single machine. At the same time, the output voltage, impedance, etc. of the single device can also be tested with a handheld multimeter to determine whether the component has failed.

[0085] Step 3, total dose assessment test, according to the calculation results of step 1, a total dose assessment test of 0.1rad (Si) / s and a total dose of at least 20krad (Si) is carried out. During the total dose test, the host computer software controls the single machine working mode, reads back the important parameter telemetry in real time (such as whether the instruction is sent normally, FPGA voltage, temperature, SEU flip number and important device voltage) and saves it. At the same time, the host computer software reads the voltage and current information of the programmable power supply to the single machine and saves it; according to the total dose test standard, every time the irradiation dose of 5Krad (Si) is carried out, the source is reduced and the irradiation is stopped, and the performance of the single machine is tested (such as spectrum, transmission power and receiving power, etc.) to ensure that the performance of the single machine meets the overall performance indicators, and record relevant important data.

[0086] Step 4: Retest after the total dose test. When the data is abnormal during the total dose test, the total dose irradiation test is suspended, and the failed components are located by testing the output voltage of the board components. After locating, a 168-hour annealing test (room temperature annealing or high temperature accelerated annealing) is performed. After annealing, retest is performed. After the test is qualified, a 50% over-irradiation test is performed. After the test, the performance is retested and the failure is located to obtain the component's radiation resistance TID. 元器件 Replace the failed components and continue the total dose irradiation test until all components fail, obtain the total dose resistance of all components, and improve the component information database.

[0087] Step 5: Single particle assessment test. De-encapsulate the components that need to be assessed in step 2. After the single device test is qualified, conduct the single particle assessment test. Select LET = 37 or 75 MeV·cm 2Conduct assessment tests using heavy ions with a dose of / mg. The beam spot area is a circle with a diameter of 4 cm, and multiple devices within the circle are assessed simultaneously (when applying the design in Step 2, after comprehensively considering other elements, try to layout the assessed devices as close as possible). For example, Figure 4 As shown in the schematic diagram of the single particle test circuit board, devices A, B, C, D, E, F, and G can be assessed simultaneously. The single particle assessment test of two identical types of devices can be carried out simultaneously to reduce the assessment time. The output terminals of the devices are externally connected to an oscilloscope through flying wires for monitoring. At the same time, the host computer software controls the single machine working mode, reads and saves the important parameter telemetry in real time, and reads and saves the supply voltage and current information of the programmable power supply to the single machine by the host computer software to determine whether the device fails.

[0088] Step 6: Based on the test results of Step 4 and Step 5, improve the component irradiation database. And carry out protection and reinforcement design and alternative design for components with poor radiation resistance.

[0089] Step 7: Protection and reinforcement design and alternative design. For devices with poor total dose resistance, according to the requirements of Step 1 and combined with the component radiation resistance TID obtained in Step 5 元器件 If TID 元器件 is 15 Krad, to meet the requirement that RDM is greater than or equal to 2, at least an additional equivalent aluminum protection thickness of 0.5 mm is required; for devices with poor single particle resistance, carry out protection designs such as adding current limiting resistors, cold and hot backups, and triple modular redundancy.

[0090] It should be understood that although Figure 1 the steps in the flowchart are shown in sequence according to the arrows, these steps are not necessarily executed in the order indicated by the arrows. Unless otherwise clearly stated in this article, there is no strict order restriction for the execution of these steps, and these steps can be executed in other orders. Moreover, Figure 1 at least a part of the steps in

[0091] In one embodiment, as Figure 5 shown, a system for establishing a radiation database of commercial aerospace COTS components is provided, including:

[0092] A single machine module, host computer software, programmable power supply, flying wire external oscilloscope, performance test module, and handheld multimeter;

[0093] The single - machine module is respectively connected to the host computer, the programmable power supply, the externally - connected oscilloscope with flying leads, and the handheld multimeter. The single - machine module includes multiple single - particle test areas, and each single - particle test area includes several COTS components to be evaluated;

[0094] The host computer is used to control the working mode of the single - machine module, read back in real - time the important parameter telemetry of the single - machine module, the power supply voltage and current information of the programmable power supply to the single - machine module respectively during the total - dose assessment test and the single - particle assessment test, and is used to perform abnormal judgment on the operating state of the single - machine module and failure analysis on the COTS components to be evaluated;

[0095] The programmable power supply is respectively connected to the single - machine module and the host computer, is used to provide power supply for each COTS component in the single - machine module, and provide the output voltage and current data to the host computer;

[0096] The externally - connected oscilloscope with flying leads is connected to the output end of the COTS component to be evaluated, and is used to monitor the output signal of the COTS component to be evaluated in real - time during the single - particle assessment test and transmit it to the host computer;

[0097] The performance test module is used to test the performance of the single - machine module and transmit the performance test results to the host computer; the performance includes spectrum, transmit power, and receive power;

[0098] The handheld multimeter is used to test and monitor the electrical parameters of the COTS components during operation and transmit them to the host computer.

[0099] In one embodiment, as Figure 6 shown, a device for establishing an irradiation database of commercial aerospace COTS components is provided, including:

[0100] The index calculation module 602 is used to simulate and calculate the anti - irradiation indexes that COTS components need to meet according to the satellite operation environment parameters and satellite requirement information; the anti - irradiation indexes include the total - dose resistance index and the single - particle resistance index;

[0101] The single - machine construction module 604 is used to obtain a variety of COTS components to be evaluated and construct a single - machine module based on the variety of COTS components to be evaluated; the single - machine module includes multiple single - particle test areas, and each single - particle test area includes several COTS components to be evaluated;

[0102] The total - dose assessment module 606 is used to perform total - dose assessment tests on the single - machine module in each working mode to obtain the total - dose resistance capabilities of each COTS component to be evaluated;

[0103] The single-particle evaluation module 608 is used to perform de-encapsulation processing on each COTS component to be evaluated in the single-machine module, and perform single-particle evaluation tests on each single-particle test area in the single-machine module after de-encapsulation processing in each working mode, so as to obtain the single-particle resistance ability of each COTS component to be evaluated;

[0104] The failure protection module 610 is used to perform failure protection design on COTS components with a total-dose resistance ability lower than the total-dose resistance index and COTS components with a single-particle resistance ability lower than the single-particle resistance ability index respectively, so as to obtain corresponding failure protection strategies;

[0105] The database construction module 612 is used to obtain the radiation resistance ability according to the total-dose resistance ability and single-particle resistance ability of each COTS component, and construct a COTS component radiation database according to the satellite operating environment parameters, satellite requirement information, radiation resistance index, radiation resistance ability and failure protection strategy of COTS components.

[0106] For the specific limitations of the commercial space COTS component radiation database establishment device, reference can be made to the limitations of the commercial space COTS component radiation database establishment method in the above text, which will not be elaborated here. Each module in the above commercial space COTS component radiation database establishment device can be implemented in whole or in part by software, hardware and their combination. The above modules can be embedded in the processor of the computer device in the form of hardware or independent of it, or stored in the memory of the computer device in the form of software, so that the processor can call and execute the operations corresponding to the above modules.

[0107] In one embodiment, a computer device is provided. The computer device can be a terminal, and its internal structure diagram can be as Figure 7 shown. The computer device includes a processor, a memory, a network interface, a display screen and an input device connected through a system bus. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system and a computer program. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, it realizes a commercial space COTS component radiation database establishment method. The display screen of the computer device can be a liquid crystal display screen or an electronic ink display screen. The input device of the computer device can be a touch layer covered on the display screen, or a button, a trackball or a touchpad set on the computer device shell, or an external keyboard, touchpad or mouse, etc.

[0108] Those skilled in the art can understand, Figure 7The structure shown is only a block diagram of some structures related to the solution of this application, and does not constitute a limitation on the computer device to which the solution of this application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine some components, or have different component arrangements.

[0109] In one embodiment, a computer device is provided, including a memory and a processor. The memory stores a computer program, and when the processor executes the computer program, the steps of the method in the above embodiment are implemented.

[0110] The technical features of the above embodiments can be combined arbitrarily. For the sake of concise description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope recorded in this specification.

[0111] The above-described embodiments only represent several implementation manners of this application. The description is relatively specific and detailed, but it should not be construed as a limitation on the scope of the invention. It should be noted that for those of ordinary skill in the art, without departing from the concept of this application, several deformations and improvements can still be made, and these all belong to the protection scope of this application. Therefore, the protection scope of this application should be subject to the appended claims.

Claims

1. A method for establishing a commercial aerospace COTS component irradiation database, characterized in that: The method comprises: Simulate and calculate the radiation resistance indicators that COTS components need to meet based on satellite operating environment parameters and satellite demand information; the radiation resistance indicators include total dose resistance indicators and single particle resistance indicators; Acquire multiple COTS components to be evaluated, and construct a stand-alone module based on the multiple COTS components to be evaluated; the stand-alone module includes multiple single particle test areas, each of which includes a number of COTS components to be evaluated; Conducting a total dose assessment test on the stand-alone module in each working mode to obtain the total dose resistance capability of each COTS component to be evaluated; De-packaging each COTS component to be evaluated in the stand-alone module, and performing a single particle assessment test on each single particle test area in the de-packaging stand-alone module in each working mode to obtain the single particle resistance capability of each COTS component to be evaluated; Failure protection designs are performed on COTS components whose total dose resistance capability is lower than the total dose resistance index and COTS components whose single particle resistance capability is lower than the single particle resistance capability index, respectively, to obtain corresponding failure protection strategies; The radiation resistance capability is obtained based on the total dose resistance capability and single particle resistance capability of each COTS component. The COTS component radiation database is constructed based on the satellite operating environment parameters, satellite demand information, COTS component radiation resistance indicators, radiation resistance capability and failure protection strategy.

2. The method according to claim 1, characterized in that The total dose assessment test is performed on the stand-alone module in each working mode to obtain the total dose resistance capability of each COTS component to be evaluated, including: Controlling the working mode of the stand-alone module through the host computer, continuously applying the irradiation dose to the stand-alone module in the current working mode until the total dose standard of the total dose assessment test is reached; the total dose standard is obtained through the total dose resistance index; During the total dose assessment test, the host computer reads back the important parameters of the stand-alone module remotely in real time, and performs a post-irradiation performance test on the stand-alone module at the preset sampling point to obtain the post-irradiation performance test results; If there is no abnormality in the post-irradiation performance test results and remote measurement of important parameters at the current sampling point, the total dose assessment test will continue; If the post-irradiation performance test and the remote measurement of important parameters are abnormal, the total dose assessment test is suspended, the failed COTS components in the stand-alone module are located, and the failed COTS components are subjected to annealing test. The total dose assessment test is then continued for the stand-alone module. The post-irradiation performance of the stand-alone module is retested at the current sampling point. If the post-irradiation performance retest results and the remote measurement of important parameters are normal, an over-irradiation test is performed. The post-irradiation performance test is performed on the stand-alone module after the irradiation test. If the post-irradiation performance test results and the remote measurement of important parameters are normal, the failed COTS components of the stand-alone module are located to obtain the radiation resistance of the failed COTS components. The failed COTS components are replaced, and the total dose assessment test is continued until all COTS components to be assessed fail, at which time the total dose assessment test is stopped to obtain the total dose resistance capability of each COTS component to be assessed.

3. The method according to claim 1, characterized in that: The method further comprises: If there are no abnormalities in the performance test results and remote measurement of important parameters after irradiation, a single particle assessment test will be carried out on the single module.

4. The method according to claim 1, characterized in that: The method further comprises: If the performance retest results after irradiation and the remote measurement of important parameters are abnormal, the failed COTS components of the single module are located to obtain the radiation resistance of the failed COTS components.

5. The method according to claim 1, characterized in that Failure protection design is performed on COTS components whose total dose resistance capability is lower than the total dose resistance index, and the corresponding failure protection strategies include: For COTS components whose total dose resistance capability is lower than the total dose resistance index, the minimum equivalent aluminum protection thickness that needs to be increased is calculated based on the total dose resistance capability and the radiation design margin to obtain a protection reinforcement plan; The corresponding failure protection strategy is obtained based on the protection reinforcement plan and COTS component replacement plan.

6. The method according to claim 1, characterized in that Failure protection design is performed on COTS components whose single-particle resistance is lower than the single-particle resistance index, and the corresponding failure protection strategies include: For COTS components whose single-particle resistance is lower than the single-particle resistance threshold, a protection reinforcement design is performed to obtain a corresponding protection reinforcement scheme; the protection reinforcement design includes adding current limiting resistors, hot and cold backups, and three-out-of-two protection designs; Obtain the corresponding failure protection strategy based on the protection reinforcement solution or COTS component replacement solution.

7. The method according to claim 1, characterized in that Single-particle assessment tests are performed on each single-particle test area in the stand-alone module after packaging in each working mode, and the single-particle resistance capabilities of each COTS component to be evaluated are obtained, including: The working mode of the stand-alone module is controlled by the host computer, and the corresponding heavy ions are selected according to the anti-single particle index to irradiate each single particle test area in the stand-alone module after the encapsulation process in the current working mode, wherein the irradiation area of ​​the particle beam corresponds to the single particle test area; During the single-particle assessment test, the host computer reads back the important parameter telemetry of the stand-alone module in real time, and the output signal of each COTS component to be evaluated is monitored in real time through a flying wire external oscilloscope. According to the output signal of each COTS component to be evaluated and the telemetry of important parameters, it is judged whether the COTS component to be evaluated has failed. If the COTS component to be evaluated has failed, the single-particle resistance capability of the component is obtained according to the test results, and other COTS components to be evaluated are tested until all COTS components to be evaluated fail, and the single-particle resistance capability of each COTS component to be evaluated is obtained.

8. A system for establishing a commercial aerospace COTS component irradiation database applied to the method according to any one of claims 1 to 7, characterized in that: The system includes a stand-alone module, host computer software, a program-controlled power supply, a flying lead external oscilloscope, a performance test module and a handheld multimeter; The stand-alone module is respectively connected to a host computer, a program-controlled power supply, a flying-wire external oscilloscope and a handheld multimeter. The stand-alone module includes a plurality of single-particle test areas, each of which includes a plurality of COTS components to be evaluated. The host computer is used to control the working mode of the stand-alone module, to read back the remote measurement of important parameters of the stand-alone module and the power supply voltage and current information of the program-controlled power supply to the stand-alone module in real time during the total dose assessment test and the single particle assessment test, and to judge the abnormality of the operating status of the stand-alone module and perform failure analysis on the COTS components to be evaluated; The programmable power supply is connected to the stand-alone module and the host computer respectively, and is used to provide power supply for each COTS component in the stand-alone module, and to provide output voltage and current data to the host computer; The flying wire external oscilloscope is connected to the output end of the COTS component to be evaluated, and is used to monitor the output signal of the COTS component to be evaluated in real time during the single particle assessment test and transmit it to the host computer; The performance test module is used to test the performance of the stand-alone module and transmit the performance test results to the host computer; the performance includes spectrum, transmission power and reception power; The handheld multimeter is used to test and monitor the electrical parameters of COTS components during operation and transmit the parameters to a host computer.

9. A device for establishing a commercial aerospace COTS component irradiation database, characterized in that: The device comprises: An index calculation module is used to simulate and calculate the radiation resistance index that COTS components need to meet based on satellite operating environment parameters and satellite demand information; the radiation resistance index includes a total dose resistance index and a single particle resistance index; A stand-alone construction module is used to obtain a plurality of COTS components to be evaluated, and to construct a stand-alone module based on the plurality of COTS components to be evaluated; the stand-alone module includes a plurality of single particle test areas, each of which includes a plurality of COTS components to be evaluated; A total dose assessment module is used to perform a total dose assessment test on the stand-alone module in each working mode to obtain the total dose resistance capability of each COTS component to be evaluated; A single particle assessment module is used to de-encapsulate each COTS component to be evaluated in the stand-alone module, and to perform a single particle assessment test on each single particle test area in the stand-alone module after de-encapsulation in each working mode, so as to obtain the single particle resistance capability of each COTS component to be evaluated; The failure protection module is used to perform failure protection design on COTS components whose total dose resistance capability is lower than the total dose resistance index and COTS components whose single particle resistance capability is lower than the single particle resistance capability index, and obtain corresponding failure protection strategies; The database construction module is used to obtain the radiation resistance capability based on the total dose resistance capability and single particle resistance capability of each COTS component, and to build a COTS component radiation database based on satellite operating environment parameters, satellite demand information, COTS component radiation resistance indicators, radiation resistance capability and failure protection strategy.

10. A computer device comprising a memory and a processor, wherein the memory stores a computer program, characterized in that: When the processor executes the computer program, the steps of the method according to any one of claims 1 to 7 are implemented.

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