CN112800573B - Reliability analysis method and device - Google Patents
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Abstract
The embodiment of the invention provides a reliability analysis method and a device, wherein the method comprises the following steps: acquiring a space radiation environment corresponding to a task to be detected, wherein the task to be detected is an aviation/aerospace task; classifying the type of interruption that may occur in the aviation/aerospace task; acquiring a decision method of risk response in the space radiation environment, and calculating by combining the classified results to obtain calculation results of all steps of the decision method; substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result. The method can cover space radiation effect for reliability analysis.
Description
Technical Field
The invention relates to the field of reliability analysis of space radiation environments, in particular to a reliability analysis method and device.
Background
Under the influence of the space environment of the space task orbit, various effects such as charge-discharge effect, single event effect and the like can be generated by possible electronic components of the aviation/aerospace system, so that various faults of the electronic components can be caused, and the aviation/aerospace system is caused to be faulty.
At present, aiming at the reliability problem of an electronic component object, a traditional FIDES reliability model establishes a reliability analysis model based on failure physics and mainly considering multiple factors such as electricity-heat, temperature cycle, mechanical vibration and the like.
However, for aviation, aerospace and large-scale ground application systems, experiments and field applications have demonstrated that the spatial radiation effect SRE effect severely affects task success, whereas the above-described approach does not take into account the effect of the spatial radiation effect.
Disclosure of Invention
Aiming at the problems existing in the prior art, the embodiment of the invention provides a reliability analysis method for the radiation effect of a coverage space.
The embodiment of the invention provides a reliability analysis method, which comprises the following steps:
acquiring a space radiation environment corresponding to a task to be detected, wherein the task to be detected is an aviation/aerospace task;
classifying the type of interruption that may occur in the aviation/aerospace task;
acquiring a decision method of risk response in the space radiation environment, and calculating by combining the classified results to obtain calculation results of all steps of the decision method;
substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result.
In one embodiment, the method further comprises:
s1, acquiring a task unit of the task to be detected, judging whether the task unit is legal, and judging the interrupt type of the task unit by combining the classification result;
s2, acquiring a corresponding relieving strategy according to the interrupt type;
s3, acquiring the safety margin of the corresponding task unit after the implementation of the relief strategy;
s4, acquiring a device causing the interruption and the order of magnitude of the influence rate of the device;
s5, acquiring a key task unit in the task units, and detecting whether a device corresponding to the key task unit comprises a corresponding monitoring system.
In one embodiment, the method further comprises:
acquiring a task unit of the task to be detected, a task time period corresponding to the task unit, a task environment condition and a task purpose;
judging whether the task unit is legal or not according to the task time period, the task environment condition and the task purpose;
and acquiring an influence effect corresponding to the space radiation environment, and judging the type of interruption of the task unit according to the influence effect and the classification result.
In one embodiment, the method further comprises:
when the interrupt type is total dose effect TID, displacement damage effect DD, the mitigation strategy is radiation shielding;
when the interrupt type is a hard error, the mitigation strategy is to limit or degrade current;
when the interrupt type is soft error, the mitigation strategy adopts a EDAC, ECC, TMR, refreshing method.
In one embodiment, the method further comprises:
acquiring the incidence rate of the interruption after the implementation of the mitigation strategy and the standard incidence rate of the interruption;
and calculating the safety margin according to the incidence rate of the interruption and the incidence rate after the release strategy is implemented.
In one embodiment, the method further comprises:
the standard magnitude of the device is obtained, and the magnitude of the influence rate of the device is modified according to the standard magnitude.
In one embodiment, the method further comprises:
acquiring a key device corresponding to the key task unit, and detecting whether the key device comprises a corresponding monitoring system;
and when the key device does not contain the corresponding monitoring system, configuring the corresponding monitoring system for the key device.
An embodiment of the present invention provides a reliability analysis device, including:
the first acquisition module is used for acquiring a space radiation environment of a task to be detected, wherein the task to be detected is an aviation/aerospace task;
the classification module is used for classifying the types of the possible interruption in the aviation/aerospace task;
the second acquisition module is used for acquiring a decision method of risk response in the space radiation environment, and calculating calculation results of all steps of the decision method by combining the classification results;
and the calculation module is used for substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result.
The embodiment of the invention provides electronic equipment, which comprises a memory, a processor and a computer program stored on the memory and capable of running on the processor, wherein the processor realizes the steps of the reliability analysis method when executing the program.
An embodiment of the present invention provides a non-transitory computer readable storage medium having stored thereon a computer program which, when executed by a processor, implements the steps of the reliability analysis method described above.
The reliability analysis method and the reliability analysis device provided by the embodiment of the invention acquire the space radiation environment of the task to be detected; classifying interrupt types possibly occurring in a task, acquiring a decision method of risk response in a space radiation environment, and calculating by combining classification results to obtain calculation results of all steps of the decision method; substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result. The method acquires a corresponding reliability analysis model by combining a corresponding decision method of risk with a space radiation environment, and calculates a reliability analysis result of a coverage space radiation effect by the reliability analysis model.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions of the prior art, the following description will briefly explain the drawings used in the embodiments or the description of the prior art, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a flow chart of a reliability analysis method according to an embodiment of the present invention;
FIG. 2 is a block diagram of a reliability analysis device according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of an electronic device according to an embodiment of the invention.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
Fig. 1 is a schematic flow chart of a reliability analysis method provided by an embodiment of the present invention, and as shown in fig. 1, the embodiment of the present invention provides a reliability analysis method, including:
step S101, acquiring a space radiation environment of a task to be detected, wherein the task to be detected is an aviation/aerospace task.
Specifically, the space radiation environment may affect the electronic components of various aerospace systems in the space radiation environment to generate space radiation effects (SRE effects), including charge-discharge effects, single event effects, and the like, which affect the accuracy of the electronic components and the probability of errors, and the server acquires the space radiation environment, including radiation intensity, of the aerospace system corresponding to the aerospace task to be detected.
Step S102, classifying the types of interrupts that may occur in the aviation/aerospace task.
Specifically, the type of interruption that may occur in the space radiation environment for the aviation/aerospace task is classified, and the specific classification method of the interruption classification may be: the types of interruption which can occur are classified into 6 types, wherein the analyzable interruption is classified into two types, and the non-analyzable interruption is classified into four types, and the two types of analyzable interruption are respectively short-term hard faults and long-term hard faults; four types of non-analyzable interruption are long-term hard failure, short-term soft failure, long-term soft failure, respectively.
Step S103, a decision method of risk response under the space radiation environment is obtained, and calculation results of all steps of the decision method are obtained by combining the classification results.
Specifically, the server obtains a decision method corresponding to the Risk, wherein the decision method corresponding to the Risk is an analysis method based on an analysis framework of RIDM (Risk-Informed Decision Making), compared with a traditional method (such as a FIDES reliability prediction method, an MIL-HDBK-217 method and the like), the reliability influence factor considered by the space radiation environment reliability analysis method is more complete, the method is particularly suitable for space and aviation application scenes, the decision method of the RIDM can be divided into 5 steps under the space radiation environment where an aviation/aerospace task is located, and various interrupts in the aviation/aerospace system are calculated in a classified mode by combining the classified results, so that calculation results of the 5 steps can be obtained respectively.
And step S104, substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result.
Specifically, after calculation results of each step of the RIDM decision method are obtained, the calculation results are substituted into a preset reliability analysis model, wherein the reliability of a task refers to the probability that the task fully plays a specific role in a specific space radiation environment within a specific time, the reliability analysis model can comprise a preset functional relation among the calculation results of each step, the reliability analysis results of the aviation/aerospace system can be obtained through calculation according to the reliability analysis model, in addition, the process of obtaining the analysis results through the reliability analysis model by the calculation results can be the reliability prediction process of the space radiation environment, and the reliability prediction value of the aviation/aerospace system can be obtained through the analysis results.
The reliability analysis method provided by the embodiment of the invention obtains the space radiation environment of the task to be detected; classifying interrupt types possibly occurring in a task, acquiring a decision method of risk response in a space radiation environment, and calculating by combining classification results to obtain calculation results of all steps of the decision method; substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result. The method acquires a corresponding reliability analysis model by combining a corresponding decision method of risk with a space radiation environment, and calculates a reliability analysis result of a coverage space radiation effect by the reliability analysis model.
On the basis of the foregoing embodiment, the reliability analysis method further includes:
s1, acquiring a task unit of the task to be detected, judging whether the task unit is legal, and judging the interrupt type of the task unit by combining the classification result;
s2, acquiring a corresponding relieving strategy according to the interrupt type;
s3, acquiring the safety margin of the corresponding task unit after the implementation of the relief strategy;
s4, acquiring a device causing the interruption and the order of magnitude of the influence rate of the device;
s5, acquiring a key task unit in the task units, and detecting whether a device corresponding to the key task unit comprises a corresponding monitoring system
In the embodiment of the invention, the RIDM decision method can be divided into 5 steps in the space radiation environment where the aviation/aerospace task is located, wherein in the S1 step, a server acquires a task section according to the aviation/aerospace task, acquires each task unit of the task according to the task section, then acquires the preset requirement of the task to be detected, wherein the requirement can be legal or customer requirement, judges whether the task unit meets the preset requirement (whether legal) or not, and further judges the interrupt type of each task unit in the space radiation environment; in the step S2, various conventional protection strategies, and release strategies of the planned and unplanned interruption can be obtained according to different interrupt types of various task units; in the step S3, after the hidden danger of the interruption is solved in a targeted manner through the mitigation strategy, the analysis result after the solution can be obtained, for example, the error rate of interruption of a task unit after the task is solved is 10 -6 While the error rate of the task requirement is only 10 -4 The ratio of the actual error rate to the required error rate is the corresponding security of the task unitFull allowance; in the step S4, for the interruption in the steps S1 to S3, a specific device generating the interruption and an order of magnitude of an influence rate of the interruption of the specific device are obtained, wherein the order of magnitude of the influence rate may be a failure rate of the specific electronic component; in the S5 step, whether the electronic components of the task unit contain key electronic components or not is obtained, and the key task unit is detected to have a corresponding monitoring system, wherein the monitoring system is used for detecting the condition that the electronic component is influenced by the space radiation environment to generate negative effects. Generally, steps 1 to 3 are top closed loops of the aerospace system, while steps 4 and 5 are bottom closed loops of the aerospace system.
In addition, according to the RIDM decision method, 5 steps of calculation are performed step by step under the space radiation environment where the aviation/aerospace task is located, after the monitoring system is configured for the key electronic components in the step 5, the interruption occurrence rate (the ratio of the number of times of interruption to the total detection time) of the key electronic components after the monitoring system is configured is detected, according to the interruption occurrence rate, the relation between the interruption occurrence rate and the task to be detected in the reliability analysis model is combined, and the reliability analysis result of the task to be detected can be obtained, generally, the lower the interruption occurrence rate is, the higher the reliability of task completion is.
According to the embodiment of the invention, the influence condition of the space radiation environment on the aviation/aerospace task can be calculated in 5 steps under the space radiation environment of the aviation/aerospace task by the RIDM decision method, and the calculation result of the coverage space radiation effect is obtained.
On the basis of the foregoing embodiment, the reliability analysis method further includes:
acquiring a task unit of the task to be detected, a task time period corresponding to the task unit, a task environment condition and a task purpose;
judging whether the task unit is legal or not according to the task time period, the task environment condition and the task purpose;
and acquiring an influence effect corresponding to the space radiation environment, and judging the type of interruption of the task unit according to the influence effect and the classification result.
In the embodiment of the invention, a server acquires a task section according to an aviation/aerospace task, acquires each task unit of the task according to the task section, acquires a task time period, a task environment condition and a task purpose corresponding to each task unit, acquires preset requirements of the task to be detected, wherein the preset requirements also comprise the task time period, the task environment condition and the task purpose, the requirements can be legal requirements or customer requirements, judges whether the task time period, the task environment condition and the task purpose of the task unit meet the preset requirements (whether legal) or not, judges whether the task unit is legal or not according to the result, and further judges the type of successful interruption of each task unit to the task under the space radiation environment, wherein the effect types corresponding to the type of the interruption can comprise a device single event effect SEE, a total dose effect TID, a displacement damage effect DD and the like.
According to the embodiment of the invention, whether the space radiation environment is legal for the task unit in the aviation/aerospace task and the influence type of the task unit are calculated under the space radiation environment of the aviation/aerospace task by the RIDM decision method.
On the basis of the foregoing embodiment, the reliability analysis method further includes:
when the interrupt type is total dose effect TID, displacement damage effect DD, the mitigation strategy is radiation shielding;
when the interrupt type is a hard error, the mitigation strategy is to limit or degrade current;
when the interrupt type is soft error, the mitigation strategy adopts a EDAC, ECC, TMR, refreshing method.
In the embodiment of the invention, different mitigation strategies are configured for the types of negative influences of each task unit on task success, radiation shielding is generally adopted for TIDs and DDs, and current limitation, degradation and the like are adopted for common hard errors. Common soft errors take EDAC, ECC, TMR, refresh mitigation, etc
According to the embodiment of the invention, the type of negative influence of the inter-radiation environment on the task unit in the aviation/aerospace task is obtained under the space radiation environment of the aviation/aerospace task by the RIDM decision method, and the corresponding relief strategy is obtained.
On the basis of the foregoing embodiment, the reliability analysis method further includes:
acquiring the incidence rate of the interruption after the implementation of the mitigation strategy and the standard incidence rate of the interruption;
and calculating the safety margin according to the incidence rate of the interruption and the incidence rate after the release strategy is implemented.
In the embodiment of the invention, after the hidden danger of interruption is solved in a targeted manner through the mitigation strategy, the analysis result after the solution can be obtained, namely the occurrence rate of the interruption after the implementation of the mitigation strategy, the standard occurrence rate of the interruption is obtained, and the safety margin is calculated according to the occurrence rate and the occurrence rate of the interruption after the implementation of the mitigation strategy. For example, if a task unit is interrupted after the task is solved, the error rate of the interrupt is 10 -6 While the error rate of the task requirement is only 10 -4 The ratio of the actual error rate to the error rate required by the task is the safety margin corresponding to the task unit.
According to the embodiment of the invention, the safety margin of the space radiation environment to the task unit in the aviation/aerospace task is obtained by the RIDM decision method in the space radiation environment of the aviation/aerospace task, and different from the traditional FEMA analysis method, 1/10 of the analysis result can be taken for interrupt evaluation, so that more accurate safety margin can be obtained.
On the basis of the foregoing embodiment, the reliability analysis method further includes:
the standard magnitude of the device is obtained, and the magnitude of the influence rate of the device is modified according to the standard magnitude.
In the embodiment of the present invention, the device corresponding to the influence factor and the order of magnitude of the device are obtained, and generally, the device corresponding to the influence factor may include: hard errors include SEL-HARD, SEB, SEGR. Fixed errors include SEFI, SEL-under current limiting soft errors include SEU, SET, MCU, etc. Typically hard errors and stuck-at errors may be 100% transmitted as a radiation environment effect, whereas soft errors typically propagate in the circuit with a transmission factor of about 0.1% -10%, resulting in soft failure effects for devices at the equipment level. After the fault occurs, the standard magnitude order of the device is obtained, and the magnitude order corresponding to the device is modified according to the standard magnitude order.
According to the embodiment of the invention, the order of magnitude of the influence rate of the space radiation environment on the influence factors in the aviation/aerospace task is calculated under the space radiation environment of the aviation/aerospace task by the RIDM decision method.
On the basis of the foregoing embodiment, the reliability analysis method further includes:
acquiring a key device corresponding to the key task unit, and detecting whether the key device comprises a corresponding monitoring system;
and when the key device does not contain the corresponding monitoring system, configuring the corresponding monitoring system for the key device.
In the embodiment of the invention, for the key device corresponding to the task key task unit with possible influencing factors, a monitoring system (BIST) is necessary for monitoring the possibility of faults affecting the aviation/aerospace task, a server detects whether the task key device comprises the monitoring system, and when the key device does not comprise the corresponding monitoring system, the corresponding monitoring system is configured for the key device.
The embodiment of the invention provides a monitoring system for mission-critical devices in an aviation/aerospace mission under the space radiation environment where the aviation/aerospace mission is located by the RIDM decision method, and the monitoring capability is very useful for verifying and confirming the influence of the component, equipment or system level.
Fig. 2 is a reliability analysis device provided in an embodiment of the present invention, including: a first acquisition module 201, a classification module 202, a second acquisition module 203, a calculation module 204, wherein:
the first acquisition module is used for acquiring the space radiation environment of a task to be detected, wherein the task to be detected is an aviation/aerospace task.
And the classification module is used for classifying the types of the possible breaks in the aviation/aerospace task.
The second acquisition module is used for acquiring a decision method of the risk response under the space radiation environment, and calculating the calculation results of all steps of the decision method by combining the classification results.
And the calculation module is used for substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result.
In one embodiment, the apparatus may further include:
the risk response decision module is used for storing a decision method of risk response, and comprises the following steps: s1, acquiring task units of a task to be detected, judging whether the task units are legal, and judging the interrupt type of the task units by combining and classifying results; s2, acquiring a corresponding relieving strategy according to the type of the interrupt; s3, acquiring the safety margin of the corresponding task unit after the implementation of the relief strategy; s4, acquiring the order of magnitude of the influence rate of the device which causes the interruption; s5, acquiring a key task unit in the task units, and detecting whether a device corresponding to the key task unit comprises a corresponding monitoring system.
In one embodiment, the apparatus may further include:
the third acquisition module is used for acquiring task units of the task to be detected, task time periods corresponding to the task units, task environment conditions and task purposes.
And the judging module is used for judging whether the task unit is legal or not according to the task time period, the task environment condition and the task purpose.
And the fourth acquisition module acquires the influence effect corresponding to the space radiation environment, and judges the type of interruption of the task unit according to the influence effect and the classification result.
In one embodiment, the apparatus may further include:
the release strategy module is used for shielding radiation when the interrupt type is total dose effect TID and displacement damage effect DD; when the interrupt type is hard error, the mitigation strategy is to limit or degrade the current; when the interrupt type is soft error, the mitigation strategy adopts a EDAC, ECC, TMR and refreshing method.
In one embodiment, the apparatus may further include:
and the fifth acquisition module is used for acquiring the occurrence rate of interruption and the standard occurrence rate of interruption after the implementation of the release strategy.
And the second calculation module is used for calculating the safety margin according to the occurrence rate and the occurrence rate of interruption after the implementation of the relief strategy.
In one embodiment, the apparatus may further include:
and a sixth acquisition module, configured to acquire a standard order of magnitude of the device, and modify an order of magnitude of the influence rate of the device according to the standard order of magnitude.
In one embodiment, the apparatus may further include:
and the seventh acquisition module is used for the key device corresponding to the key task unit and detecting whether the key device comprises a corresponding monitoring system.
And the configuration module is used for configuring the corresponding monitoring system for the key device when the key device does not contain the corresponding monitoring system.
For specific limitations of the reliability analysis device, reference may be made to the above limitations of the reliability analysis method, and no further description is given here. The respective modules in the above-described reliability analysis apparatus may be implemented in whole or in part by software, hardware, or a combination thereof. The above modules may be embedded in hardware or may be independent of a processor in the computer device, or may be stored in software in a memory in the computer device, so that the processor may call and execute operations corresponding to the above modules.
Fig. 3 illustrates a physical schematic diagram of an electronic device, as shown in fig. 3, where the electronic device may include: a processor (processor) 301, a memory (memory) 302, a communication interface (Communications Interface) 303 and a communication bus 304, wherein the processor 301, the memory 302 and the communication interface 303 perform communication with each other through the communication bus 304. The processor 301 may call logic instructions in the memory 302 to perform the following method: acquiring a space radiation environment corresponding to a task to be detected, wherein the task to be detected is an aviation/aerospace task; classifying the type of interruption that may occur in the aviation/aerospace task; acquiring a decision method of risk response in the space radiation environment, and calculating by combining the classified results to obtain calculation results of all steps of the decision method; substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result.
Further, the logic instructions in memory 302 described above may be implemented in the form of software functional units and stored in a computer readable storage medium when sold or used as a stand alone product. Based on this understanding, the technical solution of the present invention may be embodied essentially or in a part contributing to the prior art or in a part of the technical solution, in the form of a software product stored in a storage medium, comprising several instructions for causing a computer device (which may be a personal computer, a server, a network device, etc.) to perform all or part of the steps of the method according to the embodiments of the present invention. And the aforementioned storage medium includes: a U-disk, a removable hard disk, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), a magnetic disk, or an optical disk, or other various media capable of storing program codes.
In another aspect, embodiments of the present invention further provide a non-transitory computer readable storage medium having stored thereon a computer program, which when executed by a processor is implemented to perform the transmission method provided in the above embodiments, for example, including: acquiring a space radiation environment corresponding to a task to be detected, wherein the task to be detected is an aviation/aerospace task; classifying the type of interruption that may occur in the aviation/aerospace task; acquiring a decision method of risk response in the space radiation environment, and calculating by combining the classified results to obtain calculation results of all steps of the decision method; substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result.
The apparatus embodiments described above are merely illustrative, wherein the elements illustrated as separate elements may or may not be physically separate, and the elements shown as elements may or may not be physical elements, may be located in one place, or may be distributed over a plurality of network elements. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of this embodiment. Those of ordinary skill in the art will understand and implement the present invention without undue burden.
From the above description of the embodiments, it will be apparent to those skilled in the art that the embodiments may be implemented by means of software plus necessary general hardware platforms, or of course may be implemented by means of hardware. Based on this understanding, the foregoing technical solution may be embodied essentially or in a part contributing to the prior art in the form of a software product, which may be stored in a computer readable storage medium, such as ROM/RAM, a magnetic disk, an optical disk, etc., including several instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the method described in the respective embodiments or some parts of the embodiments.
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and are not limiting; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (9)
1. A reliability analysis method, comprising:
acquiring a space radiation environment corresponding to a task to be detected, wherein the task to be detected is an aviation/aerospace task;
classifying the type of interruption that may occur in the aviation/aerospace task;
acquiring a decision method of risk response in the space radiation environment, and calculating by combining the classified results to obtain calculation results of all steps of the decision method;
substituting the calculation result into a preset reliability analysis model, and calculating according to the reliability analysis model to obtain a reliability analysis result;
the decision method of the risk response comprises the following steps:
s1, acquiring a task unit of the task to be detected, judging whether the task unit is legal, and judging the interrupt type of the task unit by combining the classification result;
s2, acquiring a corresponding relieving strategy according to the interrupt type;
s3, acquiring the safety margin of the corresponding task unit after the implementation of the relief strategy;
s4, acquiring a device causing the interruption and the order of magnitude of the influence rate of the device;
s5, acquiring a key task unit in the task units, and detecting whether a device corresponding to the key task unit comprises a corresponding monitoring system.
2. The reliability analysis method according to claim 1, wherein the step S1 includes:
acquiring a task unit of the task to be detected, a task time period corresponding to the task unit, a task environment condition and a task purpose;
judging whether the task unit is legal or not according to the task time period, the task environment condition and the task purpose;
and acquiring an influence effect corresponding to the space radiation environment, and judging the type of interruption of the task unit according to the influence effect and the classification result.
3. The reliability analysis method according to claim 1, wherein the obtaining the corresponding mitigation strategy according to the interrupt type includes:
when the interrupt type is total dose effect TID, displacement damage effect DD, the mitigation strategy is radiation shielding;
when the interrupt type is a hard error, the mitigation strategy is to limit or degrade current;
when the interrupt type is soft error, the mitigation strategy adopts a EDAC, ECC, TMR, refreshing method.
4. The reliability analysis method according to claim 1, wherein the obtaining the safety margin of the task unit corresponding to the implemented mitigation strategy includes:
acquiring the incidence rate of the interruption after the implementation of the mitigation strategy and the standard incidence rate of the interruption;
and calculating the safety margin according to the incidence rate of the interruption and the incidence rate after the release strategy is implemented.
5. The reliability analysis method according to claim 1, wherein the step S4 further comprises:
the standard magnitude of the device is obtained, and the magnitude of the influence rate of the device is modified according to the standard magnitude.
6. The reliability analysis method according to claim 5, wherein the step S5 further comprises:
acquiring a key device corresponding to the key task unit, and detecting whether the key device comprises a corresponding monitoring system;
and when the key device does not contain the corresponding monitoring system, configuring the corresponding monitoring system for the key device.
7. A reliability analysis apparatus, characterized in that the apparatus comprises:
the first acquisition module is used for acquiring a space radiation environment of a task to be detected, wherein the task to be detected is an aviation/aerospace task;
the classification module is used for classifying the types of the possible interruption in the aviation/aerospace task;
the second acquisition module is used for acquiring a decision method of risk response in the space radiation environment, and calculating calculation results of all steps of the decision method by combining the classification results;
the calculation module is used for substituting the calculation result into a preset reliability analysis model, and calculating to obtain a reliability analysis result according to the reliability analysis model;
wherein, the second acquisition module includes:
acquiring a task unit of the task to be detected, judging whether the task unit is legal or not, and judging the interrupt type of the task unit by combining the classification result;
acquiring a corresponding relieving strategy according to the interrupt type;
acquiring the safety margin of the corresponding task unit after the implementation of the relief strategy;
acquiring a device causing the interruption and the order of magnitude of the influence rate of the device;
and acquiring a key task unit in the task units, and detecting whether a device corresponding to the key task unit comprises a corresponding monitoring system.
8. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the processor implements the steps of the reliability analysis method according to any one of claims 1 to 6 when the program is executed by the processor.
9. A non-transitory computer readable storage medium, on which a computer program is stored, characterized in that the computer program, when being executed by a processor, implements the steps of the reliability analysis method according to any one of claims 1 to 6.
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