Method for verifying full-period reliability of long-life maintainable manned spacecraft

Abstract

The invention discloses a long-life maintainable manned spacecraft full-period reliability verification method, which comprises the steps of designing and optimizing product life and task reliability indexes based on an Ankov system; product life and reliability information is continuously collected and managed, and applicability analysis of life and reliability information of general products and similar products is carried out; according to product life and task reliability requirements, analyzing sufficiency of existing information, determining a life and reliability verification comprehensive scheme, and planning a life and reliability verification test; a multi-subsample part assembly is combined with a small subsample complete machine quantification verification test, and the test opportunity is moved forward; collecting on-orbit flight data, and identifying on-orbit life and reliability characteristics; and analyzing space-ground difference, and carrying out on-orbit service life and task reliability verification by integrating on-orbit flight data and reliability information in a development stage. According to the method, the problem of poor verification effectiveness caused by the fact that in-orbit flight data cannot be effectively fused is solved, the verification cost is remarkably controlled, and the verification opportunity is moved forward.

Description

Technical Field

[0001] The invention relates to the technical field of overall design of spacecraft, in particular to a full-cycle reliability verification method for a long-life maintainable manned spacecraft. Background Art

[0002] Reliability verification is an important means to discover reliability weaknesses and guide reliability improvement design. It is also a task that must be carried out during the development and long-term operation of spacecraft. However, the requirements of long life and high reliability have brought great challenges to the life and reliability verification of spacecraft products and systems. Reliability quantitative verification faces the difficulties of long test time, large sample demand, and high verification cost, especially for large and complex electromechanical products. The high-speed moving parts cannot shorten the test time by acceleration due to unclear acceleration mechanism. If the test is carried out according to the actual use conditions, the test cycle will exceed 15 years, making it almost impossible to obtain life test verification results before the model is launched; in addition, the reliability evaluation samples are accumulated on the basis of life verification, and the reliability index is evaluated using Weibull distribution. It is necessary to further extend the verification test time and add multiple samples. Products such as CMG and solar wings not only have a single unit price of more than 10 million yuan, but also have a long production cycle and limited production capacity. The feasibility of using multiple samples to carry out verification tests for evaluation engineering is poor and the cost is huge.

[0003] In addition, during the long-term operation of spacecraft in orbit, on-orbit flight data continues to accumulate, and the sample size is continuously expanded based on the life and reliability information in the development stage, which provides conditions for the reliability verification of spacecraft on-orbit missions. However, how to effectively integrate on-orbit flight data with the verification information in the development stage to improve the accuracy and effectiveness of verification is another difficulty faced by the long-term operation of manned spacecraft. Summary of the invention

[0004] The present invention provides a full-cycle reliability verification method for a long-life maintainable manned spacecraft, which solves the problem of poor verification effectiveness caused by the mismatch between the accumulated reliability verification time and the development / flight mission progress and the inability to effectively integrate the on-orbit flight data during the development and on-orbit operation of the spacecraft, and significantly controls the verification cost, thereby realizing an advance in the timing of verification.

[0005] In the first aspect, a full-cycle reliability verification method for a long-life maintainable manned spacecraft is provided, including:

[0006] Based on the Ankewei system design, optimize product life and mission reliability indicators;

[0007] Continuously collect and manage product life and reliability information, and conduct applicability analysis of life and reliability information of general products and similar products;

[0008] Compare product life and mission reliability requirements, analyze the adequacy of existing information, determine a comprehensive life and reliability verification plan, and plan life and reliability verification tests;

[0009] Adopt multiple sub-sample components combined with small sub-sample whole machine quantitative verification test to move the test timing forward;

[0010] Collect on-orbit flight data and identify on-orbit life and reliability characteristics;

[0011] Analyze the differences between space and earth, and integrate on-orbit flight data and reliability information from the development phase to carry out on-orbit service life and mission reliability verification.

[0012] In conjunction with the first aspect, in certain implementations of the first aspect, the design optimization of product life and mission reliability indicators includes:

[0013] Analyze the mission requirements and environmental profiles of long-life maintainable manned spacecraft, and determine the comprehensive design principles for maintainability based on the product's maturity, life and inherent reliability level, the support mode and constraints in the on-orbit flight environment, and the limited man-hours of astronauts, focusing on the life, reliability index requirements and maintenance support constraints of maintainable manned spacecraft. Analyze the maintainability quantitative and qualitative design requirements according to the integrated design principle, and optimize the product life and mission reliability indicators.

[0014] In conjunction with the first aspect, in certain implementations of the first aspect, the optimization principle is as follows:

[0015] The life requirements are comprehensively weighed against the safety, reliability, and maintainability design. The design life requirements of a single unit are determined by weighing the spare parts cost, replacement cycle, and uplink transportation requirements. For products that cannot be repaired on-orbit, the life index requirements of the spacecraft system are met through the product's own design and it has the ability to gradually extend the on-orbit service life through on-orbit use evaluation. The life margin is determined based on the model life extension requirements.

[0016] After analysis, stand-alone products whose lifespan does not meet the lifespan index of spacecraft systems are set to be repairable on-orbit; key items that affect the lifespan of spacecraft are set to be repairable on-orbit;

[0017] For single machines with sufficient redundant configuration, in-orbit repairability, and on-orbit spare parts, the mission reliability requirements of the single machine are reduced.

[0018] In conjunction with the first aspect, in certain implementations of the first aspect, the performing of the applicability analysis of the life and reliability information of general products and similar products includes:

[0019] First, the top-level planning is to carry out universal interchangeable design. For products with the same functions in the spacecraft, universal interchangeable design is used to increase the reliability evaluation samples. Second, a data validity evaluation mechanism for reliability evaluation is established, covering the tests in the ground development process and the on-orbit flight process. From the status, test conditions, test conditions of the participating products at all levels of development tests including single-machine development test, identification test, acceptance test, subsystem joint test, whole-device mechanical test, thermal test, single-cabin performance test, combination comprehensive test, life and reliability verification test, as well as the actual working conditions of the on-orbit flight products, effective data is screened as the evaluation matrix information. At the same time, a product life cycle reliability data collection system is constructed to comprehensively collect test and flight data of universal products and similar products of the combination, so as to realize the collection and management of the reliability information of the combination.

[0020] In conjunction with the first aspect, in certain implementations of the first aspect, the determining of a comprehensive life and reliability verification plan and planning of a life and reliability verification test include:

[0021] Compare the product life and mission reliability requirements, analyze the validity and sufficiency of existing information, and develop a comprehensive verification plan by combining comparative analysis verification, simulation verification, single-machine verification test, function and system-level test and experiment; continuously improve and optimize products through the "test-analysis-improvement" process to improve the inherent reliability of products, focusing on planning special quantitative verification tests for products with critical functions and insufficient quantitative verification data.

[0022] In conjunction with the first aspect, in certain implementations of the first aspect, the use of a multi-sub-sample component combined with a small-sub-sample whole machine quantitative verification test to move the test timing forward includes:

[0023] First, comprehensively analyze life, hazard, probability risk, failure mode and effect, and fault tree analysis to identify system risk points and product life and reliability characteristics, determine key components for life and reliability, and conduct failure and aging mechanism verification tests as early as possible; second, plan multi-sample statistical tests for components to verify the reliability of key reliability links and accumulate test samples; third, conduct whole machine tests to verify the compatibility of each component and the compliance of the overall functional performance indicators.

[0024] In conjunction with the first aspect, in certain implementations of the first aspect, the verification test implementation principles include:

[0025] Coordinate the goals of life verification and reliability verification, and conduct verification tests together; give priority to verifying the compliance of product design life indicators through tests;

[0026] Under the premise of not changing the failure mechanism, the accelerated test method can be considered; select the appropriate acceleration model according to the product life and reliability characteristics, and determine the test stress conditions, acceleration factors and test time; products whose life units are the number of switches, rotation cycles, cycles, and movements and do not have the characteristics of high-speed frequent continuous action and high-speed rotation, such as hatches, manual valves, working gimbals, etc., can be accelerated by increasing the working frequency or increasing the load;

[0027] Products with high-speed rotating parts, high life requirements and immature acceleration methods have the risk of not being able to complete verification before the launch of the spacecraft. It is advisable to carry out component life tests as early as possible, clarify the life assessment method and pass the review, use the accumulated test data, combine failure mechanism analysis and similar product data analogy to conduct life assessment to verify the product design life indicators, and supplement the actual flight data in orbit during the in-orbit operation phase to continuously conduct in-orbit service life assessment;

[0028] The failure mode, failure mechanism and life characteristics of the test piece are consistent with those of the original product; the test conditions and test conditions cover the conditions and modes of the product's ground assembly test, ground storage, and on-orbit operation to ensure the effectiveness of the test; the test is carried out using multiple sub-samples as much as possible to fully verify the consistency of product life and reliability.

[0029] In conjunction with the first aspect, in certain implementations of the first aspect, collecting on-orbit flight data and identifying on-orbit life and reliability characteristics include:

[0030] Continuously analyze on-orbit flight data, identify on-orbit life and reliability characteristics based on flight telemetry parameters, and determine on-orbit service life and reliability characteristic parameters.

[0031] In conjunction with the first aspect, in certain implementations of the first aspect, determining the on-orbit service life and reliability characteristic parameters includes:

[0032] Selecting a telemetry parameter that reflects the life characteristics of the product as the life characteristic parameter, or selecting other telemetry parameters that can be used to obtain the life characteristics of the product through conversion;

[0033] Monitor the current status of life characteristic parameters as the starting value for trend analysis; monitor the historical data of life characteristic parameters and combine them with ground test data as the basis for trend analysis;

[0034] When analyzing trends, the life characteristic parameter data of the product itself is compared vertically. If there are multiple products of the same type on orbit, the life characteristic parameter data of the same products is compared horizontally.

[0035] Trend analysis combines the performance degradation characteristics of the product and the flight status. The analysis method is approved by the relevant parties. The trend analysis results are the changes in product performance over time;

[0036] If it is impossible to obtain the product life characteristics by collecting telemetry parameters, consider using astronauts' on-orbit visual judgment and on-orbit measurement methods to assist; in addition, combine ground synchronous test data or previous flight test data as reference data; if necessary, the on-orbit faulty parts can be sent down to the ground to carry out fault mechanism analysis to support life characteristic analysis;

[0037] The weak links in life span can be identified based on the data analysis results of life span characteristic parameters;

[0038] Based on the product's on-orbit flight data, analyze the changing trends of the on-orbit service life characteristics, and manage the information on the cumulative working time in orbit, cumulative storage time, working conditions, working mode, on-orbit anomaly judgment criteria, anomaly records, on-orbit disposal status, on-orbit maintenance work content, and maintenance cycle according to the life and reliability information.

[0039] In conjunction with the first aspect, in certain implementations of the first aspect, analyzing the difference between the ground and the sky, and integrating the on-orbit flight data and the reliability information of the development stage to carry out on-orbit service life and mission reliability verification include:

[0040] Analyze the actual on-orbit environmental conditions, working modes, storage status and payload conditions of spacecraft products, review the factors affecting on-orbit life, compare with the ground verification situation, evaluate whether the ground verification project can cover the on-orbit working conditions, compare and analyze the current product on-orbit status parameters with the data of equivalent time points of ground tests, revise the performance degradation model and life assessment model, and carry out on-orbit life and mission reliability verification for various products.

[0041] Compared with the prior art, the solution provided by the present invention includes at least the following beneficial technical effects:

[0042] The solution provided by the present invention is a life and reliability verification method that runs through the entire cycle of long-life maintainable spacecraft development and on-orbit flight, which can achieve accurate verification of system life and mission reliability under the premise of moderate scale and controllable cost of verification test, and realize precise planning of quantitative verification tests to support model delivery and on-orbit life extension decision-making, comprehensively verify product functional performance indicators and realize early verification timing, thereby significantly controlling verification costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0043] Figure 1 The present invention is a flow chart of a full-cycle reliability verification method for a long-life maintainable manned spacecraft. DETAILED DESCRIPTION

[0044] The present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0045] Figure 1 The present invention is a flow chart of a full-cycle reliability verification method for a long-life maintainable manned spacecraft.

[0046] The first step is to optimize product life and mission reliability indicators based on the Ankewei system design.

[0047] Analyze the mission requirements and environmental profiles of long-life maintainable manned spacecraft, determine the integrated design principles of Ankewei based on the maturity, life and inherent reliability level of the product, the support mode and constraints in the on-orbit flight environment, and the limited man-hours of astronauts, and focus on the life, reliability index requirements and maintenance support constraints of maintainable manned spacecraft. Analyze the maintainable quantitative and qualitative design requirements according to the integrated design principle, and optimize the product life and mission reliability indicators. The optimization principles are as follows.

[0048] 1) Life requirements should be comprehensively weighed with safety, reliability, and maintainability design, and the design life requirements of a single unit should be determined by weighing aspects such as spare parts cost, replacement cycle, and uplink transportation requirements. Products that cannot be repaired on-orbit, such as sealed cabin structures, propulsion loop systems, etc., must meet the spacecraft system life index requirements through the product's own design and have the ability to gradually extend the on-orbit service life through on-orbit use evaluation. The life margin is determined based on the model extension requirements.

[0049] 2) Single-unit products whose life span (without maintenance) does not meet the life indicators of spacecraft systems after analysis must be repairable in orbit; key items that affect the life of the spacecraft should also be repairable in orbit in principle.

[0050] 3) For a single machine with sufficient redundant configuration, on-orbit maintenance, and on-orbit spare parts, the mission reliability requirements of the single machine can be appropriately reduced.

[0051] The second step is to continuously collect and manage product life and reliability information, and conduct applicability analysis of the life and reliability information of common products and similar products.

[0052] First, the top-level planning is to carry out universal interchangeable design. For products with the same functions in the spacecraft, the number of reliability evaluation samples can be significantly increased through universal interchangeable design. Secondly, a data validity evaluation mechanism for reliability evaluation is established, covering the tests in the ground development process and the on-orbit flight process. From the status, test conditions, and test conditions of the participating products at all levels of development tests including single-machine development test, identification test, acceptance test, subsystem joint test, whole-device mechanical test, thermal test, single-cabin performance test, combination comprehensive test, life and reliability verification test, as well as the actual working conditions of the on-orbit flight products, effective data is screened as the evaluation matrix information. At the same time, a product life cycle reliability data collection system is constructed to comprehensively collect test and flight data including universal products of the combination and other models of similar products, so as to realize the collection and management of combination reliability information.

[0053] Step three: Compare the product life and mission reliability requirements, analyze the adequacy of existing information, determine the comprehensive plan for life and reliability verification, and plan life and reliability verification tests.

[0054] Compare the product life and mission reliability requirements, analyze the validity and sufficiency of existing information, and formulate a comprehensive verification plan by combining comparative analysis verification, simulation verification, single-machine verification test, function and system-level test and test. Through the process of "test-analysis-improvement", we continuously improve and optimize products to improve the inherent reliability of products, and focus on planning special quantitative verification tests for products with key functions and insufficient quantitative verification data.

[0055] Step 4: Use multiple sub-sample components combined with small-sample whole-machine quantitative verification tests to move the test timing forward.

[0056] In view of the long verification test cycle of complex products and the problem that production capacity constraints prevent the investment of multiple whole machine samples, a strategy based on comprehensive evaluation of key reliability components is adopted to plan the key reliability component tests in combination with whole machine tests. First, comprehensive life analysis, hazard analysis, probabilistic risk analysis, failure mode impact analysis, and fault tree analysis are carried out to identify system risk points and product life and reliability characteristics, determine life and reliability key components, and carry out failure and aging mechanism verification tests as soon as possible; second, plan multiple sub-sample statistical tests for components to verify the reliability of key reliability links and accumulate test samples; third, carry out whole machine tests to verify the matching of the work of each component and the compliance of the overall functional performance indicators. The implementation principles of the verification test include:

[0057] 1) Coordinate the goals of life verification and reliability verification, and conduct verification tests together. Priority should be given to verifying the compliance of product design life indicators through tests;

[0058] 2) Under the premise of not changing the failure mechanism, accelerated test methods can be considered. The applicable acceleration model should be selected according to the product life and reliability characteristics, and the test stress conditions, acceleration factors and test time should be determined. Products whose life units are the number of switches, rotation cycles, cycles, and movements and do not have the characteristics of high-speed frequent continuous action and high-speed rotation, such as hatches, manual valves, working gimbals, etc., can be accelerated by increasing the working frequency or increasing the load;

[0059] 3) For products with high-speed rotating parts, high life requirements and immature acceleration methods, there is a risk that verification cannot be completed before the launch of the spacecraft. It is advisable to carry out component life tests as early as possible, clarify the life assessment method and pass the review, use the accumulated test data, combine failure mechanism analysis and similar product data analogy to conduct life assessment to verify the product design life indicators, and supplement the actual flight data in orbit during the in-orbit operation stage to continuously conduct in-orbit service life assessment;

[0060] 4) The failure mode, failure mechanism and life characteristics of the test piece should be consistent with those of the original product; the test conditions and test conditions should cover the conditions and modes of the product's ground assembly test, ground storage, and on-orbit operation to ensure the effectiveness of the test; the test should be carried out using multiple sub-samples as much as possible to fully verify the consistency of the product's life and reliability.

[0061] Step five: Collect on-orbit flight data and identify on-orbit life and reliability characteristics.

[0062] Continuously analyze on-orbit flight data, identify on-orbit life and reliability characteristics based on flight telemetry parameters, and determine the on-orbit service life and reliability characteristic parameters as follows:

[0063] 1) Telemetry parameters that reflect product life characteristics are preferably selected as life characteristic parameters, and other telemetry parameters that can be used to obtain product life characteristics through conversion may also be selected;

[0064] 2) Monitor the current state of the life characteristic parameters as the starting value for trend analysis; monitor the historical data of the life characteristic parameters and combine them with ground test data as the basis for trend analysis;

[0065] 3) When analyzing trends, a longitudinal comparison should be conducted with the product’s own life characteristic parameter data. If there are multiple products of the same type on orbit, a horizontal comparison should be conducted with the life characteristic parameter data of the same products;

[0066] 4) Trend analysis should be combined with the product's performance degradation characteristics and flight status. The analysis method should be approved by the relevant parties. The trend analysis results should be the changes in product performance over time;

[0067] 5) If it is impossible to obtain the product life characteristics by collecting telemetry parameters, consider using astronauts' on-orbit visual judgment and on-orbit measurement methods to assist. In addition, ground synchronous test data or previous flight test data should be used as reference data. If necessary, the on-orbit faulty parts can be brought down to the ground to carry out fault mechanism analysis and support life characteristic analysis;

[0068] 6) It should be possible to identify life weakness links based on the data analysis results of life characteristic parameters.

[0069] 7) Based on the product's on-orbit flight data, analyze the changing trends of the on-orbit service life characteristics, and manage the information such as the cumulative working time in orbit, cumulative storage time, working conditions, working mode, on-orbit abnormality judgment criteria, abnormality records, on-orbit disposal status, on-orbit maintenance work content, maintenance cycle, etc. according to the life and reliability information.

[0070] Step six: Analyze the differences between the sky and the earth, and integrate the on-orbit flight data and reliability information from the development phase to conduct on-orbit service life and mission reliability verification.

[0071] Analyze the actual on-orbit environmental conditions, working modes, storage status and payload conditions of spacecraft products, review the factors affecting on-orbit life, compare with the ground verification situation, evaluate whether the ground verification project can cover the on-orbit working conditions, compare and analyze the current product on-orbit status parameters with the data of equivalent time points of ground tests, revise the performance degradation model and life assessment model, and carry out on-orbit life and mission reliability verification for various products.

[0072] Although the present invention is disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications without departing from the spirit and scope of the present invention. Therefore, the scope of protection of the present invention shall be based on the scope defined by the claims of the present invention.

Claims

1. A full-cycle reliability verification method for a long-life maintainable manned spacecraft, characterized in that: include: Based on the Ankewei system design, optimize product life and mission reliability indicators; Continuously collect and manage product life and reliability information, and conduct applicability analysis of life and reliability information of general products and similar products; Compare product life and mission reliability requirements, analyze the adequacy of existing information, determine a comprehensive life and reliability verification plan, and plan life and reliability verification tests; Adopt multiple sub-sample components combined with small sub-sample whole machine quantitative verification test to move the test timing forward; Collect on-orbit flight data and identify on-orbit life and reliability characteristics; Analyze the differences between space and earth, and integrate on-orbit flight data and reliability information from the development phase to carry out on-orbit service life and mission reliability verification.

2. The method according to claim 1, characterized in that The design optimization product life and mission reliability indicators include: Analyze the mission requirements and environmental profiles of long-life maintainable manned spacecraft, and determine the comprehensive design principles for maintainability based on the product's maturity, life and inherent reliability level, the support mode and constraints in the on-orbit flight environment, and the limited man-hours of astronauts, focusing on the life, reliability index requirements and maintenance support constraints of maintainable manned spacecraft. Analyze the maintainability quantitative and qualitative design requirements according to the integrated design principle, and optimize the product life and mission reliability indicators.

3. The method according to claim 2, characterized in that The optimization principles are as follows: The life requirements are comprehensively weighed against the safety, reliability, and maintainability design. The design life requirements of a single unit are determined by weighing the spare parts cost, replacement cycle, and uplink transportation requirements. For products that cannot be repaired on-orbit, the life index requirements of the spacecraft system are met through the product's own design and it has the ability to gradually extend the on-orbit service life through on-orbit use evaluation. The life margin is determined based on the model life extension requirements. After analysis, stand-alone products whose lifespan does not meet the lifespan index of spacecraft systems are set to be repairable on-orbit; key items that affect the lifespan of spacecraft are set to be repairable on-orbit; For single machines with sufficient redundant configuration, in-orbit repairability, and on-orbit spare parts, the mission reliability requirements of the single machine are reduced.

4. The method according to claim 1, characterized in that: The analysis of the applicability of the life and reliability information of general products and similar products includes: First, the top-level planning is to carry out universal interchangeable design. For products with the same functions in the spacecraft, universal interchangeable design is used to increase the reliability evaluation samples. Second, a data validity evaluation mechanism for reliability evaluation is established, covering the tests in the ground development process and the on-orbit flight process. From the status, test conditions, test conditions of the participating products at all levels of development tests including single-machine development test, identification test, acceptance test, subsystem joint test, whole-device mechanical test, thermal test, single-cabin performance test, combination comprehensive test, life and reliability verification test, as well as the actual working conditions of the on-orbit flight products, effective data is screened as the evaluation matrix information. At the same time, a product life cycle reliability data collection system is constructed to comprehensively collect test and flight data of universal products and similar products of the combination, so as to realize the collection and management of the reliability information of the combination.

5. The method according to claim 1, characterized in that The comprehensive life and reliability verification plan is determined, and the life and reliability verification tests are planned, including: Compare the product life and mission reliability requirements, analyze the validity and sufficiency of existing information, and develop a comprehensive verification plan by combining comparative analysis verification, simulation verification, single-machine verification test, function and system-level test and experiment; continuously improve and optimize products through the "test-analysis-improvement" process to improve the inherent reliability of products, focus on planning special quantitative verification tests for products with critical functions and insufficient quantitative verification data.

6. The method according to claim 1, characterized in that The quantitative verification test using multiple sub-sample components combined with small sub-sample whole machine is used to move the test timing forward, including: First, comprehensively analyze life, hazard, probability risk, failure mode and effect, and fault tree analysis to identify system risk points and product life and reliability characteristics, determine key components for life and reliability, and conduct failure and aging mechanism verification tests as early as possible; second, plan multi-sample statistical tests for components to verify the reliability of key reliability links and accumulate test samples; third, conduct whole machine tests to verify the compatibility of each component and the compliance of the overall functional performance indicators.

7. The method according to claim 6, characterized in that The principles for implementing the validation test include: Coordinate the goals of life verification and reliability verification, and conduct verification tests together; give priority to verifying the compliance of product design life indicators through tests; Under the premise of not changing the failure mechanism, the accelerated test method can be considered; select the appropriate acceleration model according to the product life and reliability characteristics, and determine the test stress conditions, acceleration factors and test time; products whose life units are the number of switches, rotation cycles, cycles, and movements and do not have the characteristics of high-speed frequent continuous action and high-speed rotation, such as hatches, manual valves, working gimbals, etc., can be accelerated by increasing the working frequency or increasing the load; Products with high-speed rotating parts, high life requirements and immature acceleration methods have the risk of not being able to complete verification before the launch of the spacecraft. It is advisable to carry out component life tests as early as possible, clarify the life assessment method and pass the review, use the accumulated test data, combine failure mechanism analysis and similar product data analogy to conduct life assessment to verify the product design life indicators, and supplement the actual flight data in orbit during the in-orbit operation phase to continuously conduct in-orbit service life assessment; The failure mode, failure mechanism and life characteristics of the test piece are consistent with those of the original product; the test conditions and test conditions cover the conditions and modes of the product's ground assembly test, ground storage, and on-orbit operation to ensure the effectiveness of the test; the test is carried out using multiple sub-samples as much as possible to fully verify the consistency of product life and reliability.

8. The method according to claim 1, characterized in that The collection of on-orbit flight data and identification of on-orbit life and reliability characteristics include: Continuously analyze on-orbit flight data, identify on-orbit life and reliability characteristics based on flight telemetry parameters, and determine on-orbit service life and reliability characteristic parameters.

9. The method according to claim 8, characterized in that Determining the on-orbit service life and reliability characteristic parameters includes: Selecting a telemetry parameter that reflects the life characteristics of the product as the life characteristic parameter, or selecting other telemetry parameters that can be used to obtain the life characteristics of the product through conversion; Monitor the current status of life characteristic parameters as the starting value for trend analysis; monitor the historical data of life characteristic parameters and combine them with ground test data as the basis for trend analysis; When analyzing trends, the life characteristic parameter data of the product itself is compared vertically. If there are multiple products of the same type on orbit, the life characteristic parameter data of the same products is compared horizontally. Trend analysis combines the performance degradation characteristics of the product and the flight status. The analysis method is approved by the relevant parties. The trend analysis results are the changes in product performance over time; If it is impossible to obtain the product life characteristics by collecting telemetry parameters, consider using astronauts' on-orbit visual judgment and on-orbit measurement methods to assist; in addition, combine ground synchronous test data or previous flight test data as reference data; if necessary, the on-orbit faulty parts can be sent down to the ground to carry out fault mechanism analysis to support life characteristic analysis; The weak links in life span can be identified based on the data analysis results of life span characteristic parameters; Based on the product's on-orbit flight data, analyze the changing trends of the on-orbit service life characteristics, and manage the information on the cumulative working time in orbit, cumulative storage time, working conditions, working mode, on-orbit anomaly judgment criteria, anomaly records, on-orbit disposal status, on-orbit maintenance work content, and maintenance cycle according to the life and reliability information.

10. The method according to claim 1, characterized in that The above analysis of the differences between the sky and the ground, combined with the on-orbit flight data and the reliability information of the development stage, conducts on-orbit service life and mission reliability verification, including: Analyze the actual on-orbit environmental conditions, working modes, storage status and payload conditions of spacecraft products, review the factors affecting on-orbit life, compare with the ground verification situation, evaluate whether the ground verification project can cover the on-orbit working conditions, compare and analyze the current product on-orbit status parameters with the data of equivalent time points of ground tests, revise the performance degradation model and life assessment model, and carry out on-orbit life and mission reliability verification for various products.

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