CN111337779A - Component on-orbit flight evaluation verification method - Google Patents
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Abstract
The on-orbit flight evaluation verification method for the components comprises the following steps: 1) determining the working state of the verified component in the on-orbit flight evaluation verification stage; 2) determining the functions and parameters of the tested components to be verified, which need to be tested for on-orbit flight evaluation verification; 3) developing and developing an on-orbit test system; 4) carrying out a ground calibration test on the on-orbit test system; 5) assembling the verified component and the on-orbit test system, and launching the component and the on-orbit test system into an orbit along with the spacecraft; during the on-orbit period, the verified component operates according to the working state determined in the step 1), and the on-orbit testing system tests the functions and parameters of the verified component in the outer space, wherein the functions and parameters are the functions and parameters which are determined in the step 2) and need to be tested and monitored; 6) downloading on-track test data; 7) and carrying out analysis and interpretation on the on-orbit test data of the verified component.
Description
Technical Field
The invention belongs to the technical field of quality reliability guarantee of electronic components for space navigation, and particularly relates to an on-orbit flight evaluation verification method for components.
Background
Microelectronics is the foundation of modern information industry and information society, is the core technology for reforming and improving the traditional industry, and relates to various fields of computers, household appliances, digital electronics, automation, electricity, communication, traffic, medical treatment, aerospace and the like. The development degree of the microelectronic industry is one of key indexes of the national science and technology development level, and is a fundamental and strategic industry related to national economy, national defense construction, people's life and information security.
The complication of the aerospace electronic information system and the rapid updating of the technology, the micro-electronics and the products thereof play an important role in building a novel aerospace industrial system, usually a generation of circuit, a generation of performance and a generation of equipment, and the novel aerospace model is not developed without the development of the micro-electronics technology. The rapid development of the aerospace technology puts requirements on high-performance components and parts, such as the need for a larger-capacity memory, a higher-speed and more-accurate analog-digital converter, more resources, a higher-speed and less-power-consumption processor and the like.
Due to the difference of basic industrial levels, the microelectronic research and development and production levels in China still have larger differences compared with developed countries in Europe and America at present, although some domestic components are qualified in the stages of identification, inspection, screening and acceptance, problems still occur in the using link, and designers still have worry about the reliability and adaptability of the domestic components, so that most of the core components of typical key single machines on aerospace equipment are still imported products, the domestic components lack application opportunities, and the development levels, the production scales and the application capabilities are slow. Due to the fact that demand traction is not tightly combined with technology promotion, the component development progress is not matched with the model development progress, the quality consistency of domestic components is poor, and necessary application verification is lacked, the model is difficult to independently bear the risks and responsibilities of increased workload, frequent quality problems, late development progress, rising development cost and the like caused by selection of newly developed domestic components, so that the engineering application difficulty of the domestic components is high, and the popularization and application effects of the domestic component engineering are not obvious.
The evaluation verification is a series of tests, evaluations and comprehensive evaluation works which are carried out on domestic components before the last application so as to determine maturity of component development and applicability of aerospace engineering application. In order to accelerate the mature application of domestic components in aerospace models and reduce the risk of using newly-developed components on a large scale, especially the last-day application of some complex and core components, comprehensive evaluation and verification work needs to be carried out. By developing the evaluation and verification work of components for aerospace, the research and combination are realized, the reliability of the domestic components is evaluated and assessed in an all-dimensional and multi-angle mode from a component level, a single-machine level and a system level, the weak links and the defects of the domestic components are found, the improvement and the promotion of the component development unit are assisted, the level of applying the domestic components by designers is improved, and the development of the high-end microelectronic industry and the aerospace industry in China is promoted.
The on-orbit flight evaluation and verification is a verification mode for examining whether components meet the use requirements or not by taking on-orbit actual flight as a means, and is an important component of component evaluation and verification. Particularly, for some novel complex domestic components adopting new materials, new technologies and new processes, on-orbit flight evaluation verification work needs to be carried out.
On the other hand, with the advent of the marketing era of the aerospace industry, the world has been vigorously pushing the convergence of military and civilian services and the industrial upgrading and transformation of "internet + aerospace" in recent years, and china has been progressing on the aspect of commercial satellites under the large background of a new round of global industrial revolution. The COTS device is advanced in technology, superior in performance, generally superior to an aerospace-grade device for 1-2 generations, and meanwhile has the advantages of being high in development speed, low in cost, small in packaging size, short in purchasing period, high in availability and the like. The COTS device is selected to reduce development costs to some extent for commercial satellites and microsatellites. In the long term, the highly reliable application of the COTS device is also an important measure advocated by the principle of "good, fast and province" in NASA practice, and is also the trend. However, the design and manufacture of COTS devices are oriented to the civil field where the devices are easy to repair and replace and used in a well-controlled environment, and are not the military field, especially the high-reliability application field of space flight and aviation, aiming at the harsh working environment, and the direct application of COTS devices to the space inevitably encounters many problems and risks. Before the high-performance COTS device is formally applied to a space system, the risk of the space application can be comprehensively identified through on-orbit flight evaluation verification, so that the bearable limit value, failure mode, weak link and the like of the high-performance COTS device under the environments of electricity, heat, force, EMC, particle radiation and the like can be obtained, the reliability and the adaptability of the space application can be reasonably evaluated, a designer can be effectively guided to use the high-performance COTS device to design a commercial satellite, and the effect of 'getting half the effort' is achieved.
Disclosure of Invention
The invention aims to provide a component on-orbit flight evaluation verification method, which is used for carrying out on-orbit flight evaluation verification work on domestic components.
In order to achieve the above object, the present invention provides a method for evaluating and verifying on-orbit flight of a component, comprising: 1) determining the working state of the verified component in the on-orbit flight evaluation verification stage; 2) determining functions and parameters required by on-orbit flight evaluation verification of a verified component; 3) developing and developing an on-orbit test system; 4) carrying out a ground calibration test on the on-orbit test system; 5) assembling the verified component and the on-orbit test system, and launching the component and the on-orbit test system into an orbit along with the spacecraft; during the on-orbit period, the verified component operates according to the on-orbit flight stage working state determined in the step 1), and the on-orbit testing system tests the functions and parameters of the verified component in the outer space, wherein the functions and parameters are the functions and parameters which are determined in the step 2) and need to be tested and monitored; 6) downloading on-track test data; 7) and carrying out analysis and interpretation on the on-orbit test data of the verified component.
The on-orbit flight evaluation verification method for the components comprises the steps that an on-orbit test system comprises a signal acquisition module, a power supply module, a data processing and transmission module, a data storage module and an interface module; the signal acquisition module is used for acquiring and monitoring on-orbit test parameters of the verified component; the power supply module is used for supplying voltage required by work to the verified device and other modules of the on-rail test system; the data storage module is used for temporarily storing the on-orbit test data acquired by the signal acquisition module; the data processing and transmitting module is used for carrying out primary processing on the on-orbit test data; the interface module comprises an interface module used for connecting a spacecraft star management unit and an interface module used for connecting spacecraft machinery and thermal control; the output data of the data processing and transmission module is transmitted to other single machines of the spacecraft through an interface module for connecting a spacecraft star management unit, and data downloading is carried out by using transmission channels of the other single machines; the interface module for connecting the spacecraft machinery and the thermal control realizes the connection between the on-orbit test system and the spacecraft temperature control, heat dissipation and heating device.
In the method for evaluating and verifying the on-orbit flight of the component, in the step 1), the working mode of the component to be verified in the on-orbit flight stage is determined according to the specific model specification, the basic functional performance and the typical application method of the component to be verified; the working mode at least comprises the following steps: the specific functions, power supply requirements, working time requirements and peripheral supporting circuit requirements of the verified component in the on-orbit flight verification stage are met.
In the method for evaluating and verifying the on-orbit flight of the component, in the step 2), the functions and parameters of the component to be verified, which need to be tested and monitored in the on-orbit flight stage, are determined according to the specific model specification, the functional performance and the application method of the component to be verified.
In the method for evaluating and verifying the on-orbit flight of the component, in the step 3), an on-orbit test system is developed according to the on-orbit test function and parameters determined in the step 2); the performance index of the on-orbit testing system needs to be comprehensively determined by combining the on-orbit testing function and parameters of the verified component, the energy, the emission weight, the volume and other factors which can be provided by the spacecraft during the on-orbit period.
In the method for evaluating and verifying the on-orbit flight of the component, in the step 4), the ground calibration test comprises testing the reliability of the on-orbit test system and testing the component to be verified on the ground by using the on-orbit test system.
The on-orbit flight evaluation verification method for the components comprises the following steps that the reliability of the on-orbit test system at least comprises an electrical characteristic test, a thermal environment adaptability test and a force environment adaptability test; the on-orbit testing system is used for testing the verified component on the ground, and comprises the steps of testing the verified component under different power supply voltages, testing the verified component at different temperatures, testing the verified component under a mechanical shock/vibration/centrifugal test, testing the verified component under a vacuum environment, and testing the verified component under long-time power-on work.
In the step 7), the in-orbit test data of the verified component is analyzed, the change conditions of the function and the parameter of the verified component along with the operation time, the environmental temperature, the environmental mechanical stress in the emission process and the space radiation stress suffered by the verified component in the space are obtained, and the in-orbit flight condition of the verified component is comprehensively evaluated by combining the in-orbit working mode and the realized function of the component.
Compared with the prior art, the invention has the beneficial technical effects that:
the flight verification work involves many links, and the working state of the components in the in-orbit flight process, how to realize parameter or function test on the orbit, how to develop and develop an in-orbit testing device, how to download in-orbit testing data, how to evaluate a testing result and the like need to be considered in detail.
Drawings
The on-orbit flight evaluation verification method of the component is given by the following embodiment and the attached drawings.
FIG. 1 is a schematic diagram of an on-track test system according to the present invention.
FIG. 2 is a schematic diagram of a voltage regulator in operation during an on-rail flight verification phase.
Fig. 3 is a schematic diagram of a test result of the on-rail test system testing a certain type of voltage regulator on the ground.
Fig. 4 is a flowchart of the on-orbit testing system performing parameter or function testing, data processing, and downloading on the verified device.
FIG. 5 is a graph of on-rail test data for a voltage regulator of one type.
Detailed Description
The on-orbit flight evaluation verification method for the components of the invention will be further described in detail with reference to fig. 1 to 5.
The on-orbit flight evaluation verification method for the components comprises the following steps:
1) determining the working state of the verified component in the on-orbit flight phase
Determining the specific working mode of the verified component in the on-orbit flight stage according to the specific model specification, the basic functional performance and the typical application method of the verified component;
the specific working mode at least comprises the following steps: the specific functions, power supply requirements, working time requirements and peripheral supporting circuit requirements of the verified component in the on-orbit flight verification stage are met;
2) determining on-orbit test functions and parameters of verified components
Determining functions and parameters of the verified component to be tested and monitored in the on-orbit flight phase according to the reliability evaluation criterion requirement of the verified component;
the determined parameters and functions are parameters which can truly reflect the functions and performance change conditions of the verified component in the on-orbit flight stage, are the core parameters and functions of the verified component, are parameters and functions which can realize testing on the basis of the current scientific and technological development level, and are parameters and functions which are very concerned by technicians applying the component;
3) on-orbit test system for development
Developing and developing an on-orbit test system according to the on-orbit test function and parameters determined in the step 2); the performance index of the on-orbit testing system needs to be comprehensively determined by combining the on-orbit testing function and parameters of the verified component, the energy, the emission weight, the volume and other factors which can be provided by the spacecraft during the on-orbit period;
the on-orbit testing system comprises a general on-orbit testing system and a special on-orbit testing system; for the functions and parameters of a plurality of verified components which need to be tested and monitored, a general on-orbit testing system can be developed, and for the specific functions and parameters of a certain verified component which needs to be tested and monitored, a special on-orbit testing system can be developed;
referring to fig. 1, the on-orbit testing system includes a signal acquisition module, a power supply module, a data processing and transmission module, a data storage module and an interface module;
the signal acquisition module is used for acquiring and monitoring on-orbit test parameters of the verified component;
the power supply module is used for providing voltage required by work for the verified device and other modules of the on-orbit test system, and the energy source of the power supply module can be a solar battery or other energy storage batteries of a spacecraft;
the data storage module is used for temporarily storing the on-orbit test data acquired by the signal acquisition module;
the data processing and transmitting module is used for carrying out primary processing on the on-orbit test data, such as interpretation, packaging and the like on the original data;
the interface module comprises an interface module used for connecting a spacecraft star management unit and an interface module used for connecting spacecraft machinery and thermal control; the output data of the data processing and transmission module is transmitted to other single machines of the spacecraft through an interface module for connecting a spacecraft star management unit, and data is downloaded by using transmission channels of the other single machines, namely the data is downloaded to a ground receiving station; the interface module for connecting the spacecraft machinery and the thermal control realizes the connection between the on-orbit test system and the spacecraft temperature control, heat dissipation and heating device;
the general on-orbit test system and the special on-orbit test system can adopt the system structure;
4) ground calibration test for on-orbit testing system
The step is used for calibrating and checking the performance and technical indexes of the on-orbit test system developed and researched;
the ground calibration test needs to fully test an on-orbit test system developed by research and development and at least comprises an electrical characteristic test, a thermal environment adaptability test and a force environment adaptability test;
the on-orbit testing system developed by the method is used for testing the verified component under various working conditions, and comprises the steps of testing the verified component under different power supply voltages (power supply voltage deviation), testing the verified component at different temperatures (environment temperature deviation), testing the verified component under a mechanical shock/vibration/constant acceleration test, testing the verified component under a vacuum environment, testing the verified component under a long-time power-on work (stability test), and comprehensively obtaining ground calibration test data according to the test results for analyzing and comparing the on-orbit test data subsequently;
5) to carry out on-orbit flight
Assembling the verified component and the in-orbit testing system, and launching the verified component and the in-orbit testing system into an orbit together with the spacecraft by the carrier rocket; during the on-orbit period, the verified component operates according to the on-orbit flight stage working state determined in the step 1), and the on-orbit testing system tests the functions and parameters of the verified component in the outer space, wherein the functions and parameters are the functions and parameters which are determined in the step 2) and need to be tested and monitored;
6) on-track test data download
A signal acquisition module of the on-orbit testing system acquires on-orbit testing parameters of the verified component; the collected on-orbit test data are temporarily stored by the data storage module and then are sent to the data processing and transmitting module, and the data processing and transmitting module performs primary processing to obtain packed on-orbit test data; the packed on-orbit test data is transmitted to a relevant single machine of the spacecraft through an interface module for connecting a spacecraft star management unit, and data is downloaded to a ground antenna receiving station by using a transmission channel of the relevant single machine;
7) on-orbit test analysis of verified component
The on-orbit test data of the verified component is analyzed, the change conditions of the function and the parameter of the verified component along with the operation time, the environment temperature, the environment mechanical stress in the emission process, the space radiation and other stresses of the verified component in the space are obtained, and the on-orbit flight condition of the verified component is comprehensively evaluated by combining the on-orbit specific working mode, the specifically realized function and the concerned content of technicians.
The on-orbit flight evaluation verification method of the component is described in detail by specific embodiments.
Taking a Low Dropout Regulator (LDO) as an example, the LDO is generally used to provide a supply voltage for other devices, such as a common fixed 1.8V, 2.5V, 3.3V, 5V output type voltage Regulator and an output voltage adjustable voltage Regulator.
Performance indexes of the voltage regulator, which are critical parameters, generally include accuracy of output voltage, capability of output current (with load capability), linear adjustment rate of output voltage (variation of output voltage with input voltage), load adjustment rate of output voltage (variation of output voltage with load), and the like, and these parameters are functions or parameters that are of particular interest to those who apply the voltage regulator.
In practical applications, the voltage regulator is generally in an operating state (i.e., providing a supply voltage to other devices) or an inactive state (i.e., the voltage regulator is temporarily inactive). The duration and switching frequency of the two operating states are determined according to the requirements of specific applications. For this purpose, the operating state of the voltage regulator can be set to the operating state or the non-operating state during the rail flight phase or can be switched between the operating state and the non-operating state for a certain time.
Fig. 2 shows a schematic diagram of the voltage regulator in operation during the on-rail flight verification phase. The on-rail test system provides power supply voltage required by normal work, such as 5V, 12V and the like, for the voltage regulator (namely, a verified component); the output end of the voltage regulator simulates an actual load by using a wire-wound resistor, so that the voltage regulator is under a corresponding load condition (such as 50% full load, full load and the like). And performing on-rail test and monitoring on the core parameter of the output voltage of the voltage regulator by using the on-rail test system. Similarly, for a device such as a memory (SRAM, FLASH, EEPROM, PROM, MRAM, etc.), it is a core function of the device to accurately store data and ensure that data is not lost and repaired, and the operating mode of the device in the in-orbit flight phase can be set to a data reading mode, that is, standard test data with a certain content is written in the memory in advance, and the data is read circularly in the in-orbit phase to determine whether the data is wrong. For programmable devices such as an FPGA, a section of universal test program can be programmed, such as standard FFT (fast Fourier transform) and the like, the FPGA circularly executes the standard FFT Fourier transform in the on-orbit flight phase, and whether the actual output result is wrong compared with the standard value or not is judged.
Table 1 shows the operating conditions of the voltage regulator during the rail flight phase, the functions and parameters to be tested and monitored. The typical supply voltage of the voltage regulator of the model is 5V, so that the on-rail test system is required to provide 5V supply voltage for the on-rail flight verification stage; the typical output voltage of the model is 3.3V, the maximum output current is 1.5A, the output current is 1.5A in the on-track flight verification stage according to 50% derating consideration, and the output current is converted into a wire-wound load resistance value of 2.2 omega; in the aspect of working state, one of three modes of long power-on, no power-on, power-on and no power-on cycle switching can be selected; in the aspect of on-rail test functions and parameters, the output voltage of the voltage regulator is collected and monitored by the on-rail test system.
TABLE 1 Voltage regulator operating conditions during the on-track flight phase, functions and parameters to be tested and monitored
For a voltage regulator, an on-orbit test system developed and developed utilizes an A/D converter meeting the requirement of precision sampling rate to circularly acquire the output voltage of the voltage regulator. For FPGA, the developed on-orbit test system can utilize DSP to collect and judge the result of FPGA after executing standard FFT Fourier transform. For the memory, an on-orbit test system is developed, and the DSP is used for circularly reading and comparing the stored data in the memory.
The performance index of the in-orbit testing system needs to be comprehensively determined by combining parameters or functions of verified components needing to be detected and monitored, energy, emission weight, volume and the like which can be provided by the spacecraft during the in-orbit period. Meanwhile, the on-orbit test system has to have enough stability, accuracy and power-on self-test capability to measure the on-orbit test function and parameters of the verified component.
After the on-orbit testing system is developed, a series of calibration tests are required to be carried out to evaluate the stability and accuracy of the system:
firstly, evaluating the reliability of an on-rail test system, wherein the reliability at least comprises an electrical characteristic test, a thermal environment adaptability test and a force environment adaptability test, and the on-rail test system is required to work normally under the condition of simulating an on-rail use environment and each index meets the requirement;
and secondly, testing the verified component on the ground by using an on-orbit testing system. Considering that the power supply voltage, the ambient temperature and the like of the verified component can change along with the increase of the running time, the influence of the sun movement and the influence of the temperature control system during the actual on-orbit period, the ground calibration needs to search out the actual measurement data of the tested component tested by the on-orbit testing system under different working conditions. The tests at least comprise that the verified component is tested under different power supply voltages (power supply voltage is biased), the verified component is tested under different temperatures (environment temperature is biased), the verified component is tested under a mechanical shock/vibration/constant acceleration test, the verified component is tested under a vacuum environment, the verified component is tested under long-time power-on work and the like.
Fig. 3 is a schematic diagram showing test results of an on-rail test system testing a certain type of voltage regulator on the ground. The on-orbit test system is utilized to respectively test the output voltage change condition of the voltage regulator under different environmental temperatures (-10 ℃ to +30 ℃) and the voltage regulation under different power supply voltages (4.5V to 5.5V)Output voltage variation of the device and different environmental vacuum degrees (1.3 × 10)-3Pa～1.3×10-2Pa) output voltage variation of the voltage regulator, and output voltage variation of the voltage regulator in a period of continuous operation (such as continuous 12 hours).
After all the ground calibration tests are completed, the on-orbit testing system provided with the measured voltage regulator is assembled and connected with the spacecraft according to specified electrical, thermal, gas and mechanical interfaces, and is launched into the orbit along with the spacecraft. After the transmission, the on-track test system performs startup, self-test, configuration of the required operating state of the voltage regulator (the verified component), parameter or function test, data processing, and downloading according to the requirements of the program control instruction, and the flow is as shown in fig. 4.
And analyzing the on-orbit test data to obtain the parameters and functions of the verified component along with the change conditions of the operation time, the environmental temperature, the environmental mechanical stress in the emission process, the suffered space radiation and other stresses of the verified component in the space. Fig. 5 is a schematic diagram of on-orbit test data of a voltage regulator of a certain model, and according to the on-orbit test data, the change condition of the output voltage of the voltage regulator along with the on-orbit working time is obtained, and meanwhile, the ambient temperatures around the verified component in different times are different, so that the parameter or function change condition of the voltage regulator in the comprehensive environment in space is obtained. The criterion selected in fig. 4 is that the upper and lower limits cannot exceed ± 10% of the ground calibration value, for example, the ground calibration value is 3.3V, the criterion is 2.97V to 3.63V, that is, if the output voltage of the voltage regulator is always within the range in the rail flight verification stage, the performance of the voltage regulator is considered to meet the application requirements, the evaluation conclusion of the rail flight verification is qualified, and the voltage regulator can be used in the day afterward.
Claims (8)
1. The on-orbit flight evaluation verification method for the components is characterized by comprising the following steps:
1) determining the working state of the verified component in the on-orbit flight evaluation verification stage;
2) determining the functions and parameters of the tested components to be verified, which need to be tested for on-orbit flight evaluation verification;
3) developing and developing an on-orbit test system;
4) carrying out a ground calibration test on the on-orbit test system;
5) assembling the verified component and the on-orbit test system, and launching the component and the on-orbit test system into an orbit along with the spacecraft; during the on-orbit period, the verified component operates according to the on-orbit flight stage working state determined in the step 1), and the on-orbit testing system tests the functions and parameters of the verified component in the outer space, wherein the functions and parameters are the functions and parameters which are determined in the step 2) and need to be tested and monitored;
6) downloading on-track test data;
7) and carrying out analysis and interpretation on the on-orbit test data of the verified component.
2. The on-orbit flight evaluation and verification method for the components as claimed in claim 1, wherein the on-orbit test system comprises a signal acquisition module, a power supply module, a data processing and transmission module, a data storage module and an interface module;
the signal acquisition module is used for acquiring and monitoring on-orbit test parameters of the verified component;
the power supply module is used for supplying voltage required by work to the verified device and other modules of the on-rail test system;
the data storage module is used for temporarily storing the on-orbit test data acquired by the signal acquisition module;
the data processing and transmitting module is used for carrying out primary processing on the on-orbit test data;
the interface module comprises an interface module used for connecting a spacecraft star management unit and an interface module used for connecting spacecraft machinery and thermal control; the output data of the data processing and transmission module is transmitted to other single machines of the spacecraft through an interface module for connecting a spacecraft star management unit, and data downloading is carried out by using transmission channels of the other single machines; the interface module for connecting the spacecraft machinery and the thermal control realizes the connection between the on-orbit test system and the spacecraft temperature control, heat dissipation and heating device.
3. The on-orbit flight evaluation and verification method for the component as claimed in claim 1, wherein in the step 1), the working mode of the verified component in the on-orbit flight stage is determined according to the specific model specification, the basic functional performance and the typical application method of the verified component; the working mode at least comprises the following steps: the specific functions, power supply requirements, working time requirements and peripheral supporting circuit requirements of the verified component in the on-orbit flight verification stage are met.
4. An on-orbit flight evaluation and verification method for components as claimed in claim 1, wherein in the step 2), functions and parameters required for testing and monitoring of the components to be verified in the on-orbit flight stage are determined according to specific model specifications, functional performances and application methods of the components to be verified.
5. The on-orbit flight evaluation and verification method for the component according to claim 1, wherein in the step 3), an on-orbit test system is developed according to the on-orbit test function and parameters determined in the step 2); the performance index of the on-orbit testing system needs to be comprehensively determined by combining the on-orbit testing function and parameters of the verified component, the energy, the emission weight, the volume and other factors which can be provided by the spacecraft during the on-orbit period.
6. The on-orbit flight evaluation and verification method for the components as claimed in claim 1, wherein in the step 4), the ground calibration test comprises testing the reliability of the on-orbit test system and testing the verified components on the ground by using the on-orbit test system.
7. The on-orbit flight evaluation and verification method for the component as claimed in claim 6, wherein the testing of the reliability of the on-orbit testing system at least comprises an electrical characteristic test, a thermal environment adaptability test and a force environment adaptability test; the on-orbit testing system is used for testing the verified component on the ground, and comprises the steps of testing the verified component under different power supply voltages, testing the verified component at different temperatures, testing the verified component under a mechanical shock/vibration/constant acceleration test, testing the verified component under a vacuum environment, and testing the verified component under long-time power-on work.
8. An on-orbit flight evaluation and verification method for components and parts as claimed in claim 1, wherein in the step 7), the on-orbit test data of the verified components and parts is analyzed, the change conditions of the functions and parameters of the verified components and parts along with the operation time, the environmental temperature, the environmental mechanical stress in the emission process and the space radiation stress suffered by the verified components and parts in the space are obtained, and the on-orbit flight conditions of the verified components and parts are comprehensively evaluated by combining the on-orbit working mode and the realized functions of the components and parts.
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