CN113946932A - Method and device for evaluating reliability of space radiation environment - Google Patents
Method and device for evaluating reliability of space radiation environment Download PDFInfo
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Abstract
The embodiment of the invention provides a method and a device for evaluating the reliability of a space radiation environment, wherein the method comprises the following steps: obtaining a space radiation environment reliability evaluation input element, wherein the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM list, a system architecture and a protection design strategy; and based on the space radiation environment reliability evaluation input element, evaluating the reliability of an evaluation object of a specific application project by utilizing a pre-established space radiation environment reliability evaluation model group to obtain a reliability evaluation result. The embodiment of the invention can quantitatively and accurately guide the selection of key devices of the electronic system, the protection design of key functions and the reliability improvement of the key system, thereby ensuring the success of tasks.
Description
Technical Field
The invention relates to the technical field of reliability analysis, in particular to a method and a device for evaluating the reliability of a space radiation environment.
Background
Space radiation environment refers to all natural radiation ranging from the ground to extra-space. Natural radiation environments include the Galaxy cosmic rays, the solar cosmic rays, the earth's capture zone, and atmospheric neutron radiation. From the ground to 36000 km high altitude, is the daily working environment of electronic systems such as satellites, airplanes, ground network computers and the like. The outer space vehicles such as satellites working for more than 100 kilometers are mainly influenced by the cosmic rays of the silver river, the solar cosmic rays and the earth capture zone; the main radiation environment of the near space aircraft within the range of 20 kilometers to 100 kilometers is mainly neutrons, protons, electrons and the like; the aircraft is mainly influenced by neutron radiation in the atmosphere within the range of 3 kilometers to 20 kilometers; the radiation environment below 3 km and on the ground is mainly neutrons.
Radiation particles in a spatial radiation environment can have severe radiation damage effects on materials and radiation sensitive devices. The radiation damage effect can be classified into a Single Event Effect (SEE), a total ionization dose effect (TID), a displacement damage effect (DD), and the like according to the type of the radiation damage effect, so that the electronic device is caused to malfunction. Cumulative effects such as total dose effects, displacement damage effects, etc. can cause hard failures of semiconductor integrated circuits in electronic systems, while transient effects such as single event effects can cause hard and/or soft failures of semiconductor integrated circuits in electronic systems. Thus, the natural space radiation environmental hazard can affect the task success.
The existing method for evaluating the reliability of the space radiation environment is only a general method for electronic systems such as satellites, airplanes and ground network computers, and the reliability obtained by the method is not fine. A risk influence evaluation method for evaluating the space radiation environment harm to the task success is needed to quantitatively and accurately guide the selection of key devices of an electronic system, the protection design of key functions and the reliability improvement of a key system, so that over-design and under-design are effectively avoided, and the task success is ensured.
Disclosure of Invention
The embodiment of the invention provides a method and a device for evaluating reliability of a space radiation environment, which are used for solving the defects that the conventional method for evaluating reliability of a space radiation environment cannot quantitatively and accurately guide the selection of key devices of an electronic system, the protection design of key functions and the reliability improvement of the key system.
The embodiment of the invention provides a method for evaluating the reliability of a space radiation environment, which comprises the following steps:
obtaining a space radiation environment reliability evaluation input element, wherein the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM list, a system architecture and a protection design strategy;
and based on the space radiation environment reliability evaluation input element, evaluating the reliability of an evaluation object of a specific application project by utilizing a pre-established space radiation environment reliability evaluation model group to obtain a reliability evaluation result.
Optionally, before the obtaining the input element for evaluating the reliability of the spatial radiation environment, the method further includes:
acquiring a top-level system list corresponding to the evaluation object of the specific application project;
and based on the top system list, adopting a risk response decision-making method to obtain quantitative and qualitative relations among system top task requirements, system radiation resistance and multi-factor comprehensive radiation environment effect, and establishing a space radiation environment reliability evaluation model group.
Optionally, based on the top-level system list, a risk response decision method is adopted to obtain quantitative and qualitative relationships among system top-level task requirements, system radiation resistance and multi-factor comprehensive radiation environment effects, and a space radiation environment reliability evaluation model group is established, which specifically includes:
determining an objective function, a constraint condition and an assumed boundary by utilizing a risk response decision method based on the top system list;
establishing a space radiation environment reliability evaluation model group based on the objective function, the constraint condition and the assumed boundary;
the risk response decision method specifically comprises the following steps:
according to the task profile of the specific application project, determining the grouping state of planned interruption and unplanned interruption required to be designed by the top-level task, and determining the harm influence state of the reliability effect of the space radiation environment on each group required by the top-level task and a mitigation strategy thereof;
obtaining a space radiation environment SRE of planned interruption and unplanned interruption which affect the success of a top-level task and a mitigation strategy thereof;
calculating the SRE fault rate, and analyzing the SRE design margin when the top-level task is successful;
determining an SRE acceptable fault influence key control point based on the SRE design margin;
and carrying out BIST monitoring on the SRE acceptable fault influence key control points.
Optionally, the reliability of the evaluation object of the specific application item is evaluated by using a pre-established space radiation environment reliability evaluation model group based on the space radiation environment reliability evaluation input element to obtain a reliability evaluation result, specifically:
obtaining a test value of each space radiation environment reliability index of the evaluation object by using a space radiation environment reliability test method;
obtaining the predicted value of each space radiation environment reliability index of the evaluation object by using the space radiation environment reliability evaluation model group;
determining the space radiation environment reliability margin of the evaluation object according to the system top layer task requirement, the test value and the predicted value;
and if the reliability allowance of the space radiation environment meets a preset threshold, determining that the evaluation object meets the reliability design requirement.
The embodiment of the present invention further provides a device for evaluating reliability of a space radiation environment, including:
the system comprises an input element acquisition module, a protection design module and a protection design module, wherein the input element acquisition module is used for acquiring a space radiation environment reliability evaluation input element, and the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM (Bill of materials) list, a system architecture and a protection design strategy;
and the evaluation module is used for evaluating the reliability of the evaluation object of the specific application project by utilizing a pre-established space radiation environment reliability evaluation model group based on the space radiation environment reliability evaluation input element to obtain a reliability evaluation result.
Optionally, the method further comprises:
the top-level system list acquisition module is used for acquiring a top-level system list corresponding to the evaluation object of the specific application project;
and the evaluation model establishing module is used for acquiring quantitative and qualitative relations among the top task requirement of the system, the radiation resistance of the system and the multi-factor comprehensive radiation environment effect by adopting a risk response decision method based on the top system list, and establishing a space radiation environment reliability evaluation model group.
Optionally, the evaluation model building module is specifically configured to:
determining an objective function, a constraint condition and an assumed boundary by utilizing a risk response decision method based on the top system list;
establishing a space radiation environment reliability evaluation model group based on the objective function, the constraint condition and the assumed boundary;
the risk response decision method specifically comprises the following steps:
according to the task profile of the specific application project, determining the grouping state of planned interruption and unplanned interruption required to be designed by the top-level task, and determining the harm influence state of the reliability effect of the space radiation environment on each group required by the top-level task and a mitigation strategy thereof;
obtaining a space radiation environment SRE of planned interruption and unplanned interruption which affect the success of a top-level task and a mitigation strategy thereof;
calculating the SRE fault rate, and analyzing the SRE design margin when the top-level task is successful;
determining an SRE acceptable fault influence key control point based on the SRE design margin;
and carrying out BIST monitoring on the SRE acceptable fault influence key control points.
Optionally, the evaluation module is specifically configured to:
obtaining a test value of each space radiation environment reliability index of the evaluation object by using a space radiation environment reliability test method;
obtaining the predicted value of each space radiation environment reliability index of the evaluation object by using the space radiation environment reliability evaluation model group;
determining the space radiation environment reliability margin of the evaluation object according to the system top layer task requirement, the test value and the predicted value;
and if the reliability allowance of the space radiation environment meets a preset threshold, determining that the evaluation object meets the reliability design requirement.
The embodiment of the present invention further provides an electronic device, which includes a memory, a processor, and a computer program stored in the memory and executable on the processor, where the processor executes the computer program to implement any of the above steps of the method for evaluating reliability of a space radiation environment.
Embodiments of the present invention further provide a non-transitory computer-readable storage medium, on which a computer program is stored, where the computer program, when executed by a processor, implements the steps of the method for reliability assessment of space radiation environment as described in any one of the above.
The method and the device for evaluating the reliability of the space radiation environment provided by the embodiment of the invention can quantitatively and accurately guide the selection of key devices of an electronic system, the protection design of key functions and the reliability improvement of the key system, thereby ensuring the success of tasks.
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In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
Fig. 1 is a schematic flow chart of a method for evaluating reliability of a space radiation environment according to an embodiment of the present invention;
FIG. 2 is a schematic diagram of reliability evaluation of a space radiation environment according to an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a device for evaluating reliability of a space radiation environment according to an embodiment of the present invention;
fig. 4 is a schematic physical structure diagram of an electronic device according to an embodiment of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Fig. 1 is a schematic flow chart of a method for evaluating reliability of a space radiation environment according to an embodiment of the present invention, including:
100, obtaining a space radiation environment reliability evaluation input element, wherein the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM (Bill of materials) list, a system architecture and a protection design strategy;
specifically, in the embodiment of the present invention, the system task index requirement, the system task track environment, the system level BOM (Bill of Material) list, the system architecture, and the protection design policy are used as input elements for the reliability evaluation of the spatial radiation environment, that is, the reliability evaluation of the spatial radiation environment is performed by using the system task index requirement, the system task track environment, the system level BOM list, the system architecture, and the protection design policy.
And 101, evaluating the reliability of an evaluation object of a specific application project by utilizing a pre-established space radiation environment reliability evaluation model group based on the space radiation environment reliability evaluation input element to obtain a reliability evaluation result.
Specifically, the specific application item refers to an electronic information system such as a satellite, an airplane, a nuclear power plant, an aircraft, a ground computer network and the like. The evaluation object of the specific application project refers to a top-level system which can cause the damage of the electronic information system equipment such as satellites, airplanes, nuclear power stations, aircrafts, ground computer networks and the like to generate the multi-factor comprehensive space radiation environment influence such as total dose effect, displacement damage effect, single event effect and the like caused by the heavy ions of the rays of the silver river cosmic, the solar protons, the atmospheric neutrons and the like.
The space radiation environment reliability evaluation model group is established based on the radiation sensitivity intrinsic characteristics of a radiation sensitive device at the bottom layer of an electronic system on a Single Event Effect (SEE), a Total ionization Dose Effect (TID) and a Displacement Damage Effect (DD), and can reflect the quantitative and qualitative relation among the task requirement at the top layer of the system, the radiation resistance of the system and the multi-factor comprehensive radiation environment Effect. In the embodiment of the invention, a reliability evaluation result is obtained by utilizing a pre-established space radiation environment reliability evaluation model group.
The method for evaluating the reliability of the space radiation environment provided by the embodiment of the invention can quantitatively and accurately guide the selection of key devices of an electronic system, the protection design of key functions and the reliability improvement of the key system, thereby ensuring the success of tasks.
Based on the content of the foregoing embodiment, the method for evaluating reliability of a space radiation environment according to the embodiment of the present invention further includes, before step 100:
acquiring a top-level system list corresponding to the evaluation object of the specific application project;
and based on the top system list, adopting a risk response decision-making method to obtain quantitative and qualitative relations among system top task requirements, system radiation resistance and multi-factor comprehensive radiation environment effect, and establishing a space radiation environment reliability evaluation model group.
Specifically, according to the basic concept connotation of the reliability of the space radiation environment, the top-level system list can be listed, and the top-level system list corresponding to the evaluation object of the specific application item is obtained.
And then, based on the top system list, adopting a risk response decision-making method to obtain quantitative and qualitative relations among the top task requirement of the system, the radiation resistance of the system and the multi-factor comprehensive radiation environment effect, and establishing a space radiation environment reliability evaluation model group.
The Risk response Decision method is an RIDM (Risk-induced Decision Making) analysis method, and based on the top-level system list, the RIDM analysis method is adopted to obtain quantitative and qualitative relations among system top-level task requirements, system radiation resistance and multi-factor comprehensive radiation environment effects, mainly comprising an objective function, constraint conditions, a hypothesis boundary and the like, and establish a space radiation environment reliability evaluation model group.
Further, on the basis of the above embodiment, based on the top-level system list, a risk response decision method is adopted to obtain quantitative and qualitative relationships among system top-level task requirements, system radiation resistance and multi-factor comprehensive radiation environment effect, and a spatial radiation environment reliability evaluation model group is established, which specifically includes:
determining an objective function, a constraint condition and an assumed boundary by utilizing a risk response decision method based on the top system list;
establishing a space radiation environment reliability evaluation model group based on the objective function, the constraint condition and the assumed boundary;
the risk response decision method specifically comprises the following steps:
according to the task profile of the specific application project, determining the grouping state of planned interruption and unplanned interruption required to be designed by the top-level task, and determining the harm influence state of the reliability effect of the space radiation environment on each group required by the top-level task and a mitigation strategy thereof;
obtaining a space radiation environment SRE of planned interruption and unplanned interruption which affect the success of a top-level task and a mitigation strategy thereof;
calculating the SRE fault rate, and analyzing the SRE design margin when the top-level task is successful;
determining an SRE acceptable fault influence key control point based on the SRE design margin;
and carrying out BIST monitoring on the SRE acceptable fault influence key control points.
Specifically, step 1: and according to the task profile of the specific application project, determining the grouping state of planned interruption and unplanned interruption of the top-level task requirement design, and determining the harm influence state of the reliability effect of the space radiation environment on each group of the top-level task requirement and the mitigation strategy thereof. Table 1 shows protection and mitigation strategies for planned and unplanned interruptions.
TABLE 1 protection and mitigation strategies for planned and unplanned interrupts
Step 2: acquiring a Space Radiation Environment (SRE) (space radiation environment) which influences the success of the top-level task and the non-planned interruption and a relief strategy thereof, and defining the SRE which influences the success of the top-level task and the non-planned interruption and the relief strategy thereof in detail according to the content of 6 groups of the top-level task, thereby finally ensuring the seamless SRE deep defense strategy network list to fall to the ground. For example: planned interrupts require early warning, short term interrupts require redundancy strategies, safety critical equipment, require BIST, etc. In the SRE mitigation strategy, TID (Total ioning Dose effect) and DD (Displacement Damage effect) usually adopt radiation shielding, and common hard errors adopt current limitation, degradation and the like. Common soft errors are EDAC (Error Detection And Correction), ECC (Error Correction code), TMR (Triple Modular Redundancy), refresh mitigation, And the like.
And step 3: the SRE failure rate is calculated and the SRE design margins at the top level task success are analyzed, as are the planned and unplanned SRE hard failures in sets (1) - (4) in table 1, typically caused by TID, DD and destructive SEE, with the safety margins at the design stage being achieved by degradation or masking. The unplanned SRE failures in groups (5) - (6) obtain a safety margin through EDAC, ECC, TMR, refresh, etc. SRE fault rate calculation by adopting a space radiation environment reliability model is the basis of SRE design margin calculation. The top-level task is calculated according to the final seamless SRE deep defense strategy network list, and the success of the top-level task can be guaranteed only if a margin exists.
And 4, step 4: and determining the critical control points of the acceptable fault influence of the SRE based on the SRE design margin, wherein the critical control points specifically comprise space radiation environment sensitive devices and effects, and function boards, equipment, systems and the like comprising the sensitive devices. For example: the sensitive devices comprise an FPGA, a CPU, a DSP, a memory and the like, and the sensitive effects comprise: TID, and ELDRS (low dose rate enhancement effect). SEE HARD errors include SEL-HARD, SEB (Single Event Burnout), SEGR (Single Event Gate failure). SEE fixed errors include SEFI, SEL-under current limiting, etc. The SEE soft error includes an SEU (Single Event Upset), a SET (Single Event Transient), an MCU, and the like.
Typically, 100% of both SRE hard errors and SEE stuck-at errors may be propagated as SRE effects, while SEE soft errors are typically propagated in the circuit, with a transmission factor of approximately 0.1% -10%, resulting in device-level soft fault effects. Conservative calculations, SEE soft errors rarely translate to a SEE fault 100% as described in IEC 62396-1 annex B3. Equipment level experiments indicate that the SEE soft error rate may differ from the actual SEE impact rate by 1-3 orders of magnitude. Critical functions, such as the ADIRU (air data inertial reference unit) in an aircraft, soft errors may cause an ADIRU accident, while SEE is the only factor that cannot be excluded. Therefore, the definition of acceptable SRE impact in step 4 is the most important concept to systematically link the top-level closed-loop decision (steps 1, 2, 3) with the bottom-level closed-loop decision (steps 4, 5). Through quantitative calculation of allowance and balance, proper indexes of the SRE acceptable fault influence key control points are defined, and over-design and under-design can be avoided.
And 5: and carrying out BIST monitoring on the SRE acceptable fault influence key control points.
The BIST (Built-in Self Test) technique is a technique for implanting a relevant functional circuit in a circuit during design to provide a Self-Test function.
And determining an objective function, a constraint condition and an assumed boundary by using a risk response decision method based on the top system list, and then establishing a space radiation environment reliability evaluation model group based on the objective function, the constraint condition and the assumed boundary. As shown in table 2, different application projects may define the space radiation environment reliability evaluation model group through the 5 steps of the risk response decision method.
TABLE 2 evaluation principle and procedure based on RIDM space radiation environment reliability
According to the method for evaluating the reliability of the space radiation environment provided by the embodiment of the invention, from the analysis of source control elements influencing the success or failure of the task, based on the radiation sensitivity intrinsic characteristics of a radiation sensitive device at the bottom layer of an electronic system on a single event effect, a total dose effect and a displacement damage effect, the quantitative relation between the reliability of the space radiation environment and the radiation resistance performance of a system at the top layer of the task and the requirement of a final task success index is established in a targeted grouping manner, and a comparison table of an RIDM step and an SRE technical method is shown in a table 3.
TABLE 3 RIDM Steps vs. SRE technical methods comparison Table
To ensure the success of the task, the system needs to control planned and unplanned interruptions. The total unavailable time ratio DPM is generally grouped to realize the task risk control of planned interruption and unplanned interruption. The correspondence between planned interruptions, unplanned interruptions and spatial radiation environmental effects is shown in table 4.
TABLE 4 correspondence between planned and unplanned interruptions and spatial radiation environment effects
| Group of | Interruption of a memory | Interrupting SRE results | SRE effect |
| 1 | Plan for | Short term hard errors | TID/DD |
| 2 | Plan for | Long term hard error | TID/DD |
| 3 | Not plan for | Long term hard error | TID/DD/SEE |
| 4 | Not plan for | Short term hard errors | TID/DD/SEE |
| 5 | Not plan for | Short term soft errors (BIST) | SEE |
| 6 | Not plan for | Short term soft errors (non-BIST) | SEE |
Based on the physical characteristics of intrinsic failure, the influence effect of TID \ DD \ SEE in the final groups (1) to (6) is established in a targeted manner. Cumulative effects (total dose effect TID, displacement damage effect DD) if there is an alarm and repair replacement capability, groups (1) and (2) can be included, and if there is no alarm and repair replacement capability, groups (3) and (4) can be included; transient effect (single event effect SEE) hard failures may be incorporated in groups (3) and (4), and transient effect (single event effect SEE) soft failures may be incorporated in groups (5) and (6).
The quantitative influence relationship of the multi-factor space radiation environment reliability on the final task success index requirements, such as availability A, can be established through the following traditional reliability theoretical model to establish the relationship among 6 groups of task requirements:
DMP＝λi×ti×106……………………………(2)
in the formula (I), the compound is shown in the specification,
DPM: rate of million defects
A: reliability;
λ: the failure rate;
t: repairing time;
i: a method of fault packet classification.
Based on the content of the above embodiment, the evaluating the reliability of the evaluation object of the specific application item by using the pre-established space radiation environment reliability evaluation model group based on the space radiation environment reliability evaluation input element to obtain the reliability evaluation result, specifically:
obtaining a test value of each space radiation environment reliability index of the evaluation object by using a space radiation environment reliability test method;
obtaining the predicted value of each space radiation environment reliability index of the evaluation object by using the space radiation environment reliability evaluation model group;
determining the space radiation environment reliability margin of the evaluation object according to the system top layer task requirement, the test value and the predicted value;
and if the reliability allowance of the space radiation environment meets a preset threshold, determining that the evaluation object meets the reliability design requirement.
Specifically, based on the control principle and the control relationship between planned interruption and unplanned interruption in the top-level task index requirements, a new method for evaluating the reliability of the space radiation environment mainly includes the following 2 types of evaluation methods.
(1) Evaluating whether the predicted value of the reliability index of the space radiation environment meets the index requirement (Verification)
(2) Evaluating and verifying whether the reliability index of the space radiation environment meets the requirement (Validation) of the success of the real task
These 2 types of evaluation methods, in particular, require the following 3 types of calculation methods and corresponding data:
(1) and (3) index requirement formulation: formulating a space radiation environment reliability index requirement which meets the system task requirement;
(2) and (3) index prediction: under the service life profile of a specific grouping specific task space radiation environment working scene, through appropriate planned interruption or unplanned interruption fault grouping, whether the reliability of the system space radiation environment meets the grouping index requirement and the integral index requirement is predicted, if not, the protection slowing measures needing to be supplemented are calculated quantitatively and protection is applied;
(3) and (3) verifying the true value of the index: the system which meets the reliability index requirement of the system space radiation environment can complete specific grouping tasks and overall tasks under a real scene.
Fig. 2 is a schematic diagram of reliability evaluation of a space radiation environment according to an embodiment of the present invention. The specific evaluation procedure is shown in table 5. Obtaining a test value of each space radiation environment reliability index of the evaluation object by using a space radiation environment reliability test method; obtaining the predicted value of each space radiation environment reliability index of the evaluation object by using the space radiation environment reliability evaluation model group; and determining the space radiation environment reliability margin of the evaluation object according to the system top layer task requirement, the experimental value and the predicted value.
TABLE 5 evaluation of step elements
The method for evaluating the reliability of the space radiation environment provided by the embodiment of the invention can quantitatively, accurately and specifically guide key devices of an electronic system to select devices and protective measures which meet the requirements of specific tasks, are economical and reliable and have certain radiation resistance, so that the phenomenon that over-design and under-design exist simultaneously in a large range is avoided as much as possible, and the success of the tasks is ensured; the quantitative relation between the reliability of the space radiation environment and the radiation resistance of a task top-level system and the requirement of the final task success index is established in a targeted grouping mode, and the predicted result is more accurate than that in the past; multiple factors influencing the success of the task can be accurately identified, so that the optimal and feasible key device design and selection scheme can be selected in turn.
Fig. 3 is a schematic structural diagram of a device for evaluating reliability of a space radiation environment according to an embodiment of the present invention, including: an input element acquisition module 310 and an evaluation module 320, wherein,
an input element obtaining module 310, configured to obtain a space radiation environment reliability evaluation input element, where the space radiation environment reliability evaluation input element includes a system task index requirement, a system task orbital environment, a system-level BOM list, a system architecture, and a protection design policy;
and the evaluation module 320 is configured to evaluate the reliability of the evaluation object of the specific application item by using a pre-established space radiation environment reliability evaluation model group based on the space radiation environment reliability evaluation input element to obtain a reliability evaluation result.
The spatial radiation environment reliability assessment device provided in the embodiment of the present invention is configured to implement the method embodiment, and therefore the description in the method embodiment may be used to understand each functional module of the spatial radiation environment reliability assessment device in the embodiment of the present invention, and is not described herein again.
Based on the content of the above embodiment, the method further includes:
the top-level system list acquisition module is used for acquiring a top-level system list corresponding to the evaluation object of the specific application project;
and the evaluation model establishing module is used for acquiring quantitative and qualitative relations among the top task requirement of the system, the radiation resistance of the system and the multi-factor comprehensive radiation environment effect by adopting a risk response decision method based on the top system list, and establishing a space radiation environment reliability evaluation model group.
Based on the content of the foregoing embodiment, the evaluation model establishing module is specifically configured to:
determining an objective function, a constraint condition and an assumed boundary by utilizing a risk response decision method based on the top system list;
establishing a space radiation environment reliability evaluation model group based on the objective function, the constraint condition and the assumed boundary;
the risk response decision method specifically comprises the following steps:
according to the task profile of the specific application project, determining the grouping state of planned interruption and unplanned interruption required to be designed by the top-level task, and determining the harm influence state of the reliability effect of the space radiation environment on each group required by the top-level task and a mitigation strategy thereof;
obtaining a space radiation environment SRE of planned interruption and unplanned interruption which affect the success of a top-level task and a mitigation strategy thereof;
calculating the SRE fault rate, and analyzing the SRE design margin when the top-level task is successful;
determining an SRE acceptable fault influence key control point based on the SRE design margin;
and carrying out BIST monitoring on the SRE acceptable fault influence key control points.
Based on the content of the foregoing embodiment, the evaluation module is specifically configured to:
obtaining a test value of each space radiation environment reliability index of the evaluation object by using a space radiation environment reliability test method;
obtaining the predicted value of each space radiation environment reliability index of the evaluation object by using the space radiation environment reliability evaluation model group;
determining the space radiation environment reliability margin of the evaluation object according to the system top layer task requirement, the test value and the predicted value;
and if the reliability allowance of the space radiation environment meets a preset threshold, determining that the evaluation object meets the reliability design requirement.
The space radiation environment reliability evaluation device provided by the embodiment of the invention can quantitatively, accurately and specifically guide key devices of an electronic system to select devices and protective measures which meet the requirements of specific tasks, are economical and reliable and have certain radiation resistance in detail, so that the phenomenon that over-design and under-design exist simultaneously in a large range is avoided as much as possible, and the success of the tasks is ensured; the quantitative relation between the reliability of the space radiation environment and the radiation resistance of a task top-level system and the requirement of the final task success index is established in a targeted grouping mode, and the predicted result is more accurate than that in the past; multiple factors influencing the success of the task can be accurately identified, so that the optimal and feasible key device design and selection scheme can be selected in turn.
Fig. 4 illustrates a physical structure diagram of an electronic device, which may include, as shown in fig. 4: a processor (processor)410, a communication Interface 420, a memory (memory)430 and a communication bus 440, wherein the processor 410, the communication Interface 420 and the memory 430 are communicated with each other via the communication bus 440. The processor 410 may invoke logic instructions in the memory 430 to perform a method of spatial radiation environment reliability assessment, the method comprising: obtaining a space radiation environment reliability evaluation input element, wherein the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM list, a system architecture and a protection design strategy; and based on the space radiation environment reliability evaluation input element, evaluating the reliability of an evaluation object of a specific application project by utilizing a pre-established space radiation environment reliability evaluation model group to obtain a reliability evaluation result.
In addition, the logic instructions in the memory 430 may be implemented in the form of software functional units and stored in a computer readable storage medium when the software functional units are sold or used as independent products. Based on such understanding, the technical solution of the present invention may be embodied in the form of a software product, which is stored in a storage medium and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device) to execute 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), a magnetic disk or an optical disk, and other various media capable of storing program codes.
In another aspect, an embodiment of the present invention further provides a computer program product, where the computer program product includes a computer program stored on a non-transitory computer-readable storage medium, the computer program includes program instructions, and when the program instructions are executed by a computer, the computer can execute the method for evaluating reliability of a space radiation environment provided by the above-mentioned method embodiments, where the method includes: obtaining a space radiation environment reliability evaluation input element, wherein the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM list, a system architecture and a protection design strategy; and based on the space radiation environment reliability evaluation input element, evaluating the reliability of an evaluation object of a specific application project by utilizing a pre-established space radiation environment reliability evaluation model group to obtain a reliability evaluation result.
In still another aspect, an embodiment of the present invention further provides a non-transitory computer-readable storage medium, on which a computer program is stored, where the computer program is implemented by a processor to perform the method for evaluating reliability of a space radiation environment provided by the foregoing embodiments, where the method includes: obtaining a space radiation environment reliability evaluation input element, wherein the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM list, a system architecture and a protection design strategy; and based on the space radiation environment reliability evaluation input element, evaluating the reliability of an evaluation object of a specific application project by utilizing a pre-established space radiation environment reliability evaluation model group to obtain a reliability evaluation result.
The above-described embodiments of the apparatus are merely illustrative, and the units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the modules may be selected according to actual needs to achieve the purpose of the solution of the present embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
Through the above description of the embodiments, those skilled in the art will clearly understand that each embodiment can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware. With this understanding in mind, the above-described technical solutions may be embodied in the form of a software product, which can be stored in a computer-readable storage medium such as ROM/RAM, magnetic disk, optical disk, etc., and includes instructions for causing a computer device (which may be a personal computer, a server, or a network device, etc.) to execute the methods described in the embodiments or some parts of the embodiments.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present 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 solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. A method for evaluating reliability of a space radiation environment is characterized by comprising the following steps:
obtaining a space radiation environment reliability evaluation input element, wherein the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM list, a system architecture and a protection design strategy;
and based on the space radiation environment reliability evaluation input element, evaluating the reliability of an evaluation object of a specific application project by utilizing a pre-established space radiation environment reliability evaluation model group to obtain a reliability evaluation result.
2. The method for evaluating reliability of a spatial radiation environment according to claim 1, further comprising, before the obtaining the input elements for evaluating reliability of a spatial radiation environment:
acquiring a top-level system list corresponding to the evaluation object of the specific application project;
and based on the top system list, adopting a risk response decision-making method to obtain quantitative and qualitative relations among system top task requirements, system radiation resistance and multi-factor comprehensive radiation environment effect, and establishing a space radiation environment reliability evaluation model group.
3. The method for evaluating reliability of a space radiation environment according to claim 2, wherein a risk response decision method is adopted based on the top system list to obtain quantitative and qualitative relations among system top task requirements, system radiation resistance and multi-factor comprehensive radiation environment effect, and a space radiation environment reliability evaluation model group is established, specifically comprising:
determining an objective function, a constraint condition and an assumed boundary by utilizing a risk response decision method based on the top system list;
establishing a space radiation environment reliability evaluation model group based on the objective function, the constraint condition and the assumed boundary;
the risk response decision method specifically comprises the following steps:
according to the task profile of the specific application project, determining the grouping state of planned interruption and unplanned interruption required to be designed by the top-level task, and determining the harm influence state of the reliability effect of the space radiation environment on each group required by the top-level task and a mitigation strategy thereof;
obtaining a space radiation environment SRE of planned interruption and unplanned interruption which affect the success of a top-level task and a mitigation strategy thereof;
calculating the SRE fault rate, and analyzing the SRE design margin when the top-level task is successful;
determining an SRE acceptable fault influence key control point based on the SRE design margin;
and carrying out BIST monitoring on the SRE acceptable fault influence key control points.
4. The method according to claim 1, wherein the reliability of the evaluation object of the specific application item is evaluated based on the input element for evaluating the reliability of the space radiation environment by using a pre-established space radiation environment reliability evaluation model group, so as to obtain a reliability evaluation result, specifically:
obtaining a test value of each space radiation environment reliability index of the evaluation object by using a space radiation environment reliability test method;
obtaining the predicted value of each space radiation environment reliability index of the evaluation object by using the space radiation environment reliability evaluation model group;
determining the space radiation environment reliability margin of the evaluation object according to the system top layer task requirement, the test value and the predicted value;
and if the reliability allowance of the space radiation environment meets a preset threshold, determining that the evaluation object meets the reliability design requirement.
5. A spatial radiation environment reliability evaluation device is characterized by comprising:
the system comprises an input element acquisition module, a protection design module and a protection design module, wherein the input element acquisition module is used for acquiring a space radiation environment reliability evaluation input element, and the space radiation environment reliability evaluation input element comprises a system task index requirement, a system task orbit environment, a system level BOM (Bill of materials) list, a system architecture and a protection design strategy;
and the evaluation module is used for evaluating the reliability of the evaluation object of the specific application project by utilizing a pre-established space radiation environment reliability evaluation model group based on the space radiation environment reliability evaluation input element to obtain a reliability evaluation result.
6. The spatial radiation environment reliability evaluation device according to claim 5, further comprising:
the top-level system list acquisition module is used for acquiring a top-level system list corresponding to the evaluation object of the specific application project;
and the evaluation model establishing module is used for acquiring quantitative and qualitative relations among the top task requirement of the system, the radiation resistance of the system and the multi-factor comprehensive radiation environment effect by adopting a risk response decision method based on the top system list, and establishing a space radiation environment reliability evaluation model group.
7. The apparatus according to claim 6, wherein the evaluation model building module is specifically configured to:
determining an objective function, a constraint condition and an assumed boundary by utilizing a risk response decision method based on the top system list;
establishing a space radiation environment reliability evaluation model group based on the objective function, the constraint condition and the assumed boundary;
the risk response decision method specifically comprises the following steps:
according to the task profile of the specific application project, determining the grouping state of planned interruption and unplanned interruption required to be designed by the top-level task, and determining the harm influence state of the reliability effect of the space radiation environment on each group required by the top-level task and a mitigation strategy thereof;
obtaining a space radiation environment SRE of planned interruption and unplanned interruption which affect the success of a top-level task and a mitigation strategy thereof;
calculating the SRE fault rate, and analyzing the SRE design margin when the top-level task is successful;
determining an SRE acceptable fault influence key control point based on the SRE design margin;
and carrying out BIST monitoring on the SRE acceptable fault influence key control points.
8. The apparatus according to claim 5, wherein the evaluation module is specifically configured to:
obtaining a test value of each space radiation environment reliability index of the evaluation object by using a space radiation environment reliability test method;
obtaining the predicted value of each space radiation environment reliability index of the evaluation object by using the space radiation environment reliability evaluation model group;
determining the space radiation environment reliability margin of the evaluation object according to the system top layer task requirement, the test value and the predicted value;
and if the reliability allowance of the space radiation environment meets a preset threshold, determining that the evaluation object meets the reliability design requirement.
9. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor implements the steps of the method for reliability assessment of space radiation environment according to any of claims 1 to 4 when executing the program.
10. A non-transitory computer readable storage medium, on which a computer program is stored, wherein the computer program, when being executed by a processor, implements the steps of the method for reliability assessment of a spatial radiation environment according to any one of claims 1 to 4.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114925613A (en) * | 2022-05-27 | 2022-08-19 | 北京航空航天大学 | Software reliability equivalent evaluation method in space radiation environment based on deep learning |
| CN115097277A (en) * | 2022-06-20 | 2022-09-23 | 南方电网科学研究院有限责任公司 | Atmospheric neutron accelerated irradiation test method for flexible direct current converter valve power unit |
| CN116562630A (en) * | 2023-07-07 | 2023-08-08 | 数字太空(北京)智能技术研究院有限公司 | Risk assessment method and device for satellite influenced by space environment |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114925613A (en) * | 2022-05-27 | 2022-08-19 | 北京航空航天大学 | Software reliability equivalent evaluation method in space radiation environment based on deep learning |
| CN115097277A (en) * | 2022-06-20 | 2022-09-23 | 南方电网科学研究院有限责任公司 | Atmospheric neutron accelerated irradiation test method for flexible direct current converter valve power unit |
| CN115097277B (en) * | 2022-06-20 | 2024-04-12 | 南方电网科学研究院有限责任公司 | Atmospheric neutron acceleration irradiation test method for flexible direct current converter valve power unit |
| CN116562630A (en) * | 2023-07-07 | 2023-08-08 | 数字太空(北京)智能技术研究院有限公司 | Risk assessment method and device for satellite influenced by space environment |
| CN116562630B (en) * | 2023-07-07 | 2023-09-15 | 数字太空(北京)智能技术研究院有限公司 | Risk assessment method and device for satellite influenced by space environment |
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