CN112597643B - Reliability modeling method and device for aerospace measurement and control system - Google Patents
Reliability modeling method and device for aerospace measurement and control system Download PDFInfo
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Abstract
The invention relates to the technical field of aerospace measurement and control, and provides a reliability modeling method and device of an aerospace measurement and control system, wherein the method comprises the following steps: acquiring inherent reliability indexes of a plurality of constituent units in the aerospace measurement and control system; determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the current measurement and control task requirement; determining a logic relationship between each component unit according to the judging basis and the working mode of the current aerospace measurement and control system; according to the logic relation, constructing a first layer of reliability model according to the overall scheme of the aerospace measurement and control system according to the time period; and in each period of the first layer reliability model, constructing a second layer reliability model according to the measurement and control service. The invention completely follows the actual condition of the system executing task, embodies the maintainability, the structural dynamics and the logic relationship complexity of the system, accurately reflects the characteristics of the system and provides a calculation basis for obtaining the reliable quantification result.
Description
Technical Field
The invention relates to the technical field of aerospace measurement and control, in particular to a reliability modeling method and device of an aerospace measurement and control system.
Background
The space mission is a typical system engineering, and has the advantages of multiple participation units, high engineering complexity and high reliability requirement. The aerospace measurement and control system is the only tie of the space craft in the space and earth connection during the in-orbit operation, is a necessary means for ensuring the reliable implementation of engineering, and is also of great importance in the reliable operation. Reliability technology has been studied for decades to form a complete theoretical system, including reliability analysis and evaluation, reliability distribution and other technical branches, and the aerospace measurement and control system in China has been developed for decades and has the characteristics of complex composition, powerful functions and the like.
High risk is a significant feature of the aerospace task, and high reliability is a fundamental requirement of the aerospace task. However, the reliability analysis of the large and complex system is still in a primary stage, and the reliability is generally improved in the system design by means of redundancy and backup construction. Therefore, because the aerospace measurement and control system has the characteristics of large scale, complex composition and dynamic change, the accurate establishment of a reliability model of the system for executing tasks is a primary solution.
Disclosure of Invention
Based on the above, the embodiment of the invention provides a reliability modeling method and device for an aerospace measurement and control system, which are used for solving the problem of low accuracy of a reliability model established in the prior art.
In a first aspect of the embodiment of the present invention, a reliability modeling method for an aerospace measurement and control system is provided, including:
Acquiring inherent reliability indexes of a plurality of constituent units in the aerospace measurement and control system;
Determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the current measurement and control task requirement;
Determining a logic relationship between each component unit according to the judging basis and the current working mode of the aerospace measurement and control system;
According to the logic relation, constructing a first layer of reliability model according to a time period by using the overall scheme of the aerospace measurement and control system;
And in each period of the first layer reliability model, constructing a second layer reliability model according to the measurement and control service.
Optionally, the constituent units of the aerospace measurement and control system include: the system comprises a command control center, communication network equipment and measurement and control equipment.
Optionally, the intrinsic reliability index includes: at least one of average no-fault operating time, average maintenance time, and availability.
Optionally, the determining, according to the current measurement and control task requirement, a judging basis of success or failure of the task executed by the aerospace measurement and control system includes:
Determining a task which the aerospace measurement and control system must complete currently according to the current measurement and control task requirement;
and determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the task which needs to be completed.
Optionally, determining the logical relationship between each of the constituent units according to the judgment basis and the current working mode of the aerospace measurement and control system includes:
according to the judging basis and any one of an orbit measurement mode, a remote control mode, a telemetry mode, a ground communication mode or an orbit calculation mode of the aerospace measurement and control system, determining the corresponding working component units of the aerospace measurement and control system when the aerospace measurement and control system is normal, and determining the corresponding fault component units of the aerospace measurement and control system when the aerospace measurement and control system is faulty.
Optionally, the constructing a first layer of reliability model according to the overall scheme of the aerospace measurement and control system according to the logic relationship includes:
Determining a task execution period according to the overall scheme of the aerospace measurement and control system;
according to the logic relation, according to the time of entering a task and the time of exiting the task during the execution of the task by each component unit, performing time cutting on the task execution time interval to obtain the aerospace measurement and control subsystem corresponding to each time interval; the constituent units of the aerospace measurement and control subsystems in any two time periods are different, and the logic relations of the aerospace measurement and control subsystems in adjacent time periods are in series connection.
Optionally, in each period of the first layer reliability model, a second layer reliability model is built according to measurement and control service, including:
in each time period of the first layer reliability model, a second layer reliability model is built according to a command control center structure, a communication network structure and a measurement and control station structure in sequence;
in each structure, if the components which are backup to each other exist, the components which are backup to each other form a parallel relation.
In a second aspect of the embodiment of the present invention, a reliability modeling apparatus for an aerospace measurement and control system is provided, including:
The index acquisition module is used for acquiring inherent reliability indexes of a plurality of constituent units in the aerospace measurement and control system;
the task criterion determining module is used for determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the current measurement and control task requirement;
the logic relation determining module is used for determining the logic relation between each component unit according to the judging basis and the current working mode of the aerospace measurement and control system;
the first layer model building module is used for building a first layer reliability model of the overall scheme of the aerospace measurement and control system according to the logic relation and the time period;
And the second layer model building module is used for building a second layer reliability model according to the measurement and control service in each period of the first layer reliability model.
In a third aspect of the embodiments of the present invention, a reliability modeling apparatus for an aerospace measurement and control system is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor, where the processor implements the steps of the reliability modeling method for an aerospace measurement and control system according to any one of the first aspects of the embodiments described above when the computer program is executed by the processor.
A fourth aspect of the embodiments of the present invention provides a computer readable storage medium storing a computer program which, when executed by a processor, implements the steps of the reliability modeling method of an aerospace measurement and control system according to any one of the first aspects of the embodiments.
Compared with the prior art, the reliability modeling method and device for the aerospace measurement and control system have the beneficial effects that:
The invention mainly aims at a large complex dynamic system, provides a detailed process of reliability modeling, firstly collects inherent reliability indexes of each component unit of the system, then determines the judging basis of success and failure of the system execution task, determines the reliability logic relation among each component unit, then builds a first layer of reliability model according to time segments, builds a second layer of model according to measurement and control service, completely follows the actual condition of the system execution task, reflects the maintainability, the structure dynamic property and the logic relation complexity of the system, accurately reflects the characteristics of the system, and provides a calculation basis for obtaining a reliable reliability quantification result.
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FIG. 1 is a schematic diagram of an implementation flow of a reliability modeling method for an aerospace measurement and control system provided by an embodiment of the invention;
FIG. 2 is a schematic diagram of an implementation flow of another reliability modeling method for an aerospace measurement and control system according to an embodiment of the present invention;
FIG. 3 is a schematic diagram of a reliability model constructed in time segments provided by an embodiment of the present invention;
FIG. 4 is a schematic diagram of a reliability model of a t1 period track measurement task provided by an embodiment of the present invention;
FIG. 5 is a schematic diagram of a reliability model of a t1 period engineering telemetry receiving task provided by an embodiment of the invention;
FIG. 6 is a schematic diagram of a reliability model of a t1 period remote control and data injection task provided by an embodiment of the present invention;
FIG. 7 is a schematic diagram of a reliability model of a t2 period track measurement task provided by an embodiment of the present invention;
FIG. 8 is a schematic diagram of a reliability model of a t2 period engineering telemetry receiving task provided by an embodiment of the invention;
FIG. 9 is a schematic diagram of a reliability model of a t2 period remote control and data injection task provided by an embodiment of the present invention;
FIG. 10 is a schematic diagram of a reliability model of a t3 period orbit measurement task provided by an embodiment of the present invention;
FIG. 11 is a schematic structural diagram of a reliability modeling device of an aerospace measurement and control system provided by an embodiment of the invention;
FIG. 12 is a schematic structural diagram of another reliability modeling apparatus for an aerospace measurement and control system according to an embodiment of the present invention.
Detailed Description
In the following description, for purposes of explanation and not limitation, specific details are set forth such as the particular system architecture, techniques, etc., in order to provide a thorough understanding of the embodiments of the present invention. It will be apparent, however, to one skilled in the art that the present invention may be practiced in other embodiments that depart from these specific details.
In order to illustrate the technical scheme of the invention, the following description is made by specific examples.
Referring to fig. 1, a schematic flow chart is implemented in one embodiment of a reliability modeling method of an aerospace measurement and control system provided in this embodiment, and is described in detail as follows:
step S101, acquiring inherent reliability indexes of a plurality of constituent units in the aerospace measurement and control system.
The reliability technology of the aerospace measurement and control system has been studied for decades, and a set of mature and complete theoretical system is formed, wherein the technical branches comprise reliability analysis and evaluation, reliability distribution and the like. The aerospace measurement and control system in China also has been developed for decades, has the characteristics of complex composition, powerful functions and the like, but the reliability quantitative accurate analysis aiming at a large-scale and complex system is still in a primary stage, and the reliability is generally improved in a redundancy and backup construction mode in system design due to the lack of accurate evaluation as a theoretical basis. Therefore, how to build an accurate model aiming at the characteristics of the system and how to obtain reliable reliability analysis results are both focused on the modeling method level in the traditional analysis method based on the combined model and the traditional analysis method based on the state space, and how to build the model by combining the characteristics of the system is further researched.
The space measurement and control system can internally comprise various constituent units and also can be various devices. Optionally, the constituent units of the aerospace measurement and control system of the embodiment may include: the command control center, the communication network equipment, the measurement and control equipment and the like are main equipment for spaceflight measurement and control, but the embodiment is not limited to the above-mentioned several constituent units.
The intrinsic reliability index of each constituent unit of the embodiment may include intrinsic reliability indexes of devices such as a command control center, a communication network device, and a measurement and control device. Alternatively, the intrinsic reliability index of the present embodiment may include: at least one or more of mean time between failure (Mean Time Between Failure, MTBF), mean time between maintenance (Mean Time To Repair, MTTR), and availability are used as a basis for computing system reliability, ensuring accuracy of the reliability model.
Step S102, determining the judging basis of success or failure of the execution task of the aerospace measurement and control system according to the current measurement and control task requirement.
Specifically, the task executed by the aerospace measurement and control system is determined according to the current measurement and control task requirement, and the reliability of the established model is guaranteed.
Optionally, the determining, according to the current measurement and control task requirement, a judging basis of success or failure of the task executed by the aerospace measurement and control system includes:
And determining the task which the aerospace measurement and control system must complete currently according to the current measurement and control task requirement.
And determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the task which needs to be completed.
In the actual process, the embodiment determines tasks which must be completed by the measurement and control system at a certain stage according to task requirements, such as track measurement, remote control instruction transmission, telemetry data reception and the like, takes success or failure of the tasks which must be completed as criteria for success or failure of the tasks executed by the system, and if the tasks which must be executed fail, the tasks of the system can be determined to be failed, namely the embodiment determines the reliability of the model according to the actual situation, and ensures the accuracy of reliability assessment.
Step S103, determining the logic relation between each component unit according to the judging basis and the current working mode of the aerospace measurement and control system.
In practical application, it is clear which tasks affect success or failure, that is, the judgment basis is determined, and the implementation flow of each task specifically described and the reliability logic relationship among units in the flow can be determined according to the working mode.
Optionally, determining the logical relationship between each of the constituent units according to the judgment basis and the current working mode of the aerospace measurement and control system includes:
according to the judging basis and any one of an orbit measurement mode, a remote control mode, a telemetry mode, a ground communication mode or an orbit calculation mode of the aerospace measurement and control system, determining the corresponding working component units of the aerospace measurement and control system when the aerospace measurement and control system is normal, and determining the corresponding fault component units of the aerospace measurement and control system when the aerospace measurement and control system is faulty.
Specifically, according to the embodiment of the invention, according to the system working mode, namely the specific implementation means of measurement and control services such as track measurement, remote control, remote measurement, ground communication, track calculation and the like, the system is determined to work normally when the equipment (unit) is normal, and the system is caused to fail when the unit fails, so that the logic relationship among the units in the system is determined.
Step S104, according to the logic relation, constructing a first layer of reliability model according to the overall scheme of the aerospace measurement and control system according to the time period.
Optionally, the constructing a first layer of reliability model according to the overall scheme of the aerospace measurement and control system according to the logic relationship includes:
And determining a task execution period according to the overall scheme of the aerospace measurement and control system.
According to the logic relation, according to the time of entering a task and the time of exiting the task during the execution of the task by each component unit, performing time cutting on the task execution time interval to obtain the aerospace measurement and control subsystem corresponding to each time interval; the constituent units of the aerospace measurement and control subsystems in any two time periods are different, and the logic relations of the aerospace measurement and control subsystems in adjacent time periods are in series connection.
The method comprises the steps of cutting a task time period into a plurality of time periods according to a measurement and control resource tracking time period which is clear in the overall scheme of a measurement and control system, and specifically, cutting and modeling according to time for entering and exiting a task during execution of the task by each component unit, ensuring that system components in each time period after cutting are fixed, ensuring that system components in any two time periods are different, establishing a reliability model for each time period after cutting, wherein elements in the model are aerospace measurement and control subsystems of each time period, and the logic relationship among each time period is generally a series relationship according to task requirements.
Step S105, in each period of the first layer reliability model, a second layer reliability model is built according to the measurement and control service.
Optionally, in each period of the first layer reliability model, a second layer reliability model is built according to measurement and control service, including:
in each time period of the first layer reliability model, a second layer reliability model is built according to a command control center structure, a communication network structure and a measurement and control station structure in sequence;
in each structure, if the components which are backup to each other exist, the components which are backup to each other form a parallel relation.
In the divided time periods, a reliability model is built according to the requirements of measurement and control tasks, namely, models are built for remote control, rail measurement, remote measurement, comprehensive tasks and the like, elements in the models are constituent units of measurement and control equipment, communication equipment, a task center and the like, and the logic relationship among the units is determined in the first step. That is, a reliability model can be built according to the structure of a command control center-a communication network-a measurement and control station for specific measurement and control means used by different services in each period, and if units (such as a double control center and a communication network double route) which are mutually backed up exist in each link in the structure, a parallel model relationship is formed.
For example, fig. 2 shows a schematic structural diagram of reliability modeling of the measurement and control system, taking a first-palace task scene of manned aerospace engineering as an example, a first-palace track-entering task is completed by a Beijing center, a western security center, a Qingdao station, a long-range ship No. three and a ground communication network. The reliability modeling method for the measurement and control system to execute the task of the track-in section is as follows:
1) The intrinsic reliability index of each constituent unit is given as shown in table 1:
Table 1 intrinsic reliability index of each constituent unit
2) Determining a criterion for success or failure of the execution task.
The task requirements of the track-in section include: if any requirement is not met, the system is considered to be not satisfactory to complete the task of the track entering section, and the system task is judged to be failed, but if one of the tasks is evaluated, such as evaluating track measurement, the project telemetry receiving task is assumed to be not completed, and the evaluation of the reliability of the track measuring task is not influenced.
3) Determining the reliability logic relationship among units of measurement and control service
As in fig. 2, for the track measurement task: the track measurement means is two kinds of measurement and control equipment external measurement tracks and navigation data orbit determination, wherein the navigation data is transmitted through a downlink telemetry channel and a data transmission channel of the measurement and control equipment. During ground transmission, external measurement data are simultaneously transmitted to the Beijing center and the western security center through double routes, and are respectively processed by the two centers to finish orbit determination calculation. Therefore, the telemetry channel and the data channel on the track measurement means form a parallel relation, the two routes on the communication transmission form a parallel relation, and the Beijing center and the western security center form a parallel relation in the aspect of track determination calculation.
For remote control and data injection tasks: the remote control data is generated by the Beijing center, transmitted to a measurement and control station (ship) through a ground route or a sanitary path, and sent to the Tiangong I through an uplink channel of measurement and control equipment. Thus, two routes on a communication transmission form a parallel relationship.
For engineering telemetry reception tasks: the first engineering telemetry data of the Tiangong is received through a telemetry channel and a data transmission channel of the measurement and control equipment, and is simultaneously transmitted to the Beijing center through a double-route, and the Beijing center finishes data processing and displaying. Therefore, the telemetry channel and the data channel on the engineering telemetry receiving means form a parallel connection relationship, and the two routes on the communication transmission form a parallel connection relationship.
4) Building a first layer reliability model
According to the time of entering and exiting tasks of the Qingdao station and the long-range ship III, the constructed first layer model is shown in figure 3, and time periods t 1-t 3 form a series relation.
5) Constructing a second level model according to the measurement and control service
According to the logical structure relation among the space-earth channel, the ground communication route and the task center of the measurement and control equipment provided in the step 3), the reliability model of each measurement and control task in the time period t1 is shown in figures 4 to 6; in the period t2, the long-range ship III is added to jointly execute tasks with the Qingdao station, the two stations form a parallel connection relationship, and the reliability model of each measurement and control task is shown in figures 7-9; when the ship with the long-range view No. three independently executes the task in the t3 period, other task model structures are identical to the t1 period except for the track measurement task reliability model, as shown in fig. 10.
In the reliability modeling method of the aerospace measurement and control system, a detailed process of reliability modeling is mainly provided for a large-scale complex dynamic system, firstly, the inherent reliability indexes of all the constituent units of the system are collected, then the judging basis of success and failure of the task executed by the system is determined, the reliability logic relation among all the constituent units is determined, then a first layer of reliability model is built according to time periods, a second layer of model is built according to measurement and control services, the actual condition of the task executed by the system is completely followed, the maintainability, the structural dynamics and the logic relation complexity of the system are reflected, the characteristics of the system are accurately reflected, and a calculation basis is provided for obtaining a reliable quantitative result.
It will be understood by those skilled in the art that the sequence number of each step in the above embodiment does not mean that the execution sequence of each process should be determined by the function and the internal logic, and should not limit the implementation process of the embodiment of the present invention.
Corresponding to the reliability modeling method of the aerospace measurement and control system described in the above embodiment, the embodiment provides a reliability modeling device of the aerospace measurement and control system. Referring specifically to fig. 11, a schematic structural diagram of a reliability modeling apparatus of the aerospace measurement and control system in this embodiment is shown. For convenience of explanation, only the portions related to the present embodiment are shown.
The reliability modeling device of the aerospace measurement and control system mainly comprises: an index acquisition module 110, a task criteria determination module 120, a logical relationship determination module 130, a first layer model building module 140, and a second layer model building module 150.
The index acquisition module 110 is configured to acquire intrinsic reliability indexes of a plurality of constituent units in the aerospace measurement and control system.
The task criterion determining module 120 is configured to determine a criterion for success or failure of the task executed by the aerospace measurement and control system according to a current measurement and control task requirement.
The logic relation determining module 130 is configured to determine a logic relation between each of the constituent units according to the judgment basis and a current working mode of the aerospace measurement and control system.
The first layer model building module 140 is configured to build a first layer reliability model of the overall scheme of the aerospace measurement and control system according to the logic relationship.
The second layer model building module 150 is configured to build a second layer reliability model according to the measurement and control service in each period of the first layer reliability model.
The reliability modeling device of the aerospace measurement and control system mainly aims at a large-scale complex dynamic system, provides a detailed process of reliability modeling, firstly collects inherent reliability indexes of all constituent units of the system, then determines judging basis of success or failure of a task executed by the system, determines reliability logic relation among all constituent units, then builds a first layer of reliability model according to time periods, builds a second layer of model according to measurement and control service, completely follows actual conditions of the task executed by the system, reflects maintainability, structural dynamics and logic relation complexity of the system, accurately reflects characteristics of the system, and provides a calculation basis for obtaining reliable quantitative results.
The embodiment also provides a schematic diagram of another reliability modeling apparatus 100 of the aerospace measurement and control system. As shown in fig. 12, the reliability modeling apparatus 100 of the aerospace measurement and control system of this embodiment includes: a processor 160, a memory 170, and a computer program 171 stored in the memory 170 and executable on the processor 160, such as a program for a reliability modeling method of an aerospace metrology system.
Wherein the processor 160, when executing the computer program 171 on the memory 170, implements the steps of the reliability modeling method embodiment of the aerospace measurement and control system described above, such as steps 101 to 105 shown in fig. 1. Or the processor 160, when executing the computer program 171, performs the functions of the modules/units of the apparatus embodiments described above, such as the functions of the modules 110 to 150 shown in fig. 11.
By way of example, the computer program 171 may be partitioned into one or more modules/units that are stored in the memory 170 and executed by the processor 160 to accomplish the present invention. The one or more modules/units may be a series of computer program instruction segments capable of performing a specific function for describing the execution of the computer program 171 in the reliability modeling apparatus 100 of the aerospace measurement and control system. For example, the computer program 171 may be divided into an index acquisition module 110, a task criterion determination module 120, a logical relationship determination module 130, a first layer model creation module 140, and a second layer model creation module 150, each of which functions as follows:
The index acquisition module 110 is configured to acquire intrinsic reliability indexes of a plurality of constituent units in the aerospace measurement and control system.
The task criterion determining module 120 is configured to determine a criterion for success or failure of the task executed by the aerospace measurement and control system according to a current measurement and control task requirement.
The logic relation determining module 130 is configured to determine a logic relation between each of the constituent units according to the judgment basis and a current working mode of the aerospace measurement and control system.
The first layer model building module 140 is configured to build a first layer reliability model of the overall scheme of the aerospace measurement and control system according to the logic relationship.
The second layer model building module 150 is configured to build a second layer reliability model according to the measurement and control service in each period of the first layer reliability model.
The reliability modeling apparatus 100 of the aerospace vehicle-to-test system may include, but is not limited to, a processor 160, a memory 170. It will be understood by those skilled in the art that fig. 12 is merely an example of the reliability modeling apparatus 100 of the aerospace measurement and control system, and does not constitute a limitation of the reliability modeling apparatus 100 of the aerospace measurement and control system, and may include more or less components than those illustrated, or may combine certain components, or different components, for example, the reliability modeling apparatus 100 of the aerospace measurement and control system may further include an input/output device, a network access device, a bus, and the like.
The Processor 160 may be a central processing unit (Central Processing Unit, CPU), but may also be other general purpose processors, digital signal processors (DIGITAL SIGNAL Processor, DSP), application SPECIFIC INTEGRATED Circuit (ASIC), off-the-shelf Programmable gate array (Field-Programmable GATE ARRAY, FPGA) or other Programmable logic devices, discrete gate or transistor logic devices, discrete hardware components, or the like. A general purpose processor may be a microprocessor or the processor may be any conventional processor or the like.
The memory 170 may be an internal storage unit of the reliability modeling apparatus 100 of the aerospace measurement and control system, for example, a hard disk or a memory of the reliability modeling apparatus 100 of the aerospace measurement and control system. The memory 170 may also be an external storage device of the reliability modeling apparatus 100 of the aerospace measurement and control system, for example, a plug-in hard disk, a smart memory card (SMART MEDIA CARD, SMC), a Secure Digital (SD) card, a flash memory card (FLASH CARD) or the like, which are provided on the reliability modeling apparatus 100 of the aerospace measurement and control system. Further, the memory 170 may also include both internal memory units and external memory devices of the reliability modeling apparatus 100 of the aerospace vehicle-mounted system. The memory 170 is used to store the computer program and other programs and data required by the reliability modeling apparatus 100 of the aerospace vehicle-mounted system. The memory 170 may also be used to temporarily store data that has been output or is to be output.
It will be apparent to those skilled in the art that, for convenience and brevity of description, only the above-described division of each functional unit and model is illustrated, and in practical application, the above-described function allocation may be performed by different functional units and modules according to needs, i.e. the internal structure of the apparatus is divided into different functional units or modules to perform all or part of the above-described functions. The functional units and modules in the embodiment may be integrated in one processing unit, or each unit may exist alone physically, or two or more units may be integrated in one unit, where the integrated units may be implemented in a form of hardware or a form of a software functional unit. In addition, the specific names of the functional units and modules are only for distinguishing from each other, and are not used for limiting the protection scope of the present application. The specific working process of the units and modules in the above system may refer to the corresponding process in the foregoing method embodiment, which is not described herein again.
In addition, each functional unit in the embodiments of the present invention may be integrated in one processing unit, or each unit may exist alone physically, or two or more units may be integrated in one unit. The integrated units may be implemented in hardware or in software functional units.
The integrated modules/units, if implemented in the form of software functional units and sold or used as stand-alone products, may be stored in a computer readable storage medium. Based on such understanding, the present invention may implement all or part of the flow of the method of the above embodiment, or may be implemented by a computer program to instruct related hardware, where the computer program may be stored in a computer readable storage medium, and when the computer program is executed by a processor, the computer program may implement the steps of each of the method embodiments described above. Wherein the computer program comprises computer program code which may be in source code form, object code form, executable file or some intermediate form etc. The computer readable medium may include: any entity or device capable of carrying the computer program code, a recording medium, a U disk, a removable hard disk, a magnetic disk, an optical disk, a computer Memory, a Read-Only Memory (ROM), a random access Memory (RAM, random Access Memory), an electrical carrier signal, a telecommunications signal, a software distribution medium, and so forth. It should be noted that the computer readable medium may include content that is subject to appropriate increases and decreases as required by jurisdictions in which such content is subject to legislation and patent practice, such as in certain jurisdictions in which such content is not included as electrical carrier signals and telecommunication signals.
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, and are intended to be included in the scope of the present invention.
Claims (8)
1. A reliability modeling method of an aerospace measurement and control system is characterized by comprising the following steps:
Acquiring inherent reliability indexes of a plurality of constituent units in the aerospace measurement and control system;
Determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the current measurement and control task requirement;
Determining a logic relationship between each component unit according to the judging basis and the current working mode of the aerospace measurement and control system;
according to the logic relationship, constructing a first layer of reliability model according to a time interval by the overall scheme of the aerospace measurement and control system, wherein the method comprises the following steps:
Determining a task execution period according to the overall scheme of the aerospace measurement and control system;
According to the logic relation, according to the time of entering the task and the time of exiting the task during the execution of the task by each component unit, performing time cutting on the task execution time period to obtain a space measurement and control subsystem corresponding to each time period, wherein the space measurement and control subsystem corresponding to each time period is an element in a first layer reliability model; the constituent units of the aerospace measurement and control subsystems in any two time periods are different, and the logic relations of the aerospace measurement and control subsystems in adjacent time periods are in series connection;
In each period of the first layer reliability model, constructing a second layer reliability model according to measurement and control service, including:
In each time period of the first layer reliability model, a second layer reliability model is built according to a command control center structure, a communication network structure and a measurement and control station structure in sequence; in each structure, if the components which are backup to each other exist, the components which are backup to each other form a parallel relation.
2. The method for modeling reliability of an aerospace measurement and control system of claim 1, wherein the constituent units of the aerospace measurement and control system comprise: the system comprises a command control center, communication network equipment and measurement and control equipment.
3. The method of modeling reliability of an aerospace measurement and control system of claim 1, wherein the intrinsic reliability index comprises: at least one of average no-fault operating time, average maintenance time, and availability.
4. The method for modeling the reliability of the aerospace measurement and control system according to claim 1, wherein the determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the current measurement and control task requirement comprises the following steps:
Determining a task which the aerospace measurement and control system must complete currently according to the current measurement and control task requirement;
and determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the task which needs to be completed.
5. The method for modeling reliability of a space measurement and control system according to claim 1, wherein determining the logical relationship between each of the constituent units according to the judgment basis and the current operation mode of the space measurement and control system comprises:
according to the judging basis and any one of an orbit measurement mode, a remote control mode, a telemetry mode, a ground communication mode or an orbit calculation mode of the aerospace measurement and control system, determining the corresponding working component units of the aerospace measurement and control system when the aerospace measurement and control system is normal, and determining the corresponding fault component units of the aerospace measurement and control system when the aerospace measurement and control system is faulty.
6. The reliability modeling device of the aerospace measurement and control system is characterized by comprising the following components:
The index acquisition module is used for acquiring inherent reliability indexes of a plurality of constituent units in the aerospace measurement and control system;
the task criterion determining module is used for determining the judging basis of success or failure of the task executed by the aerospace measurement and control system according to the current measurement and control task requirement;
the logic relation determining module is used for determining the logic relation between each component unit according to the judging basis and the current working mode of the aerospace measurement and control system;
The first layer model building module is used for building a first layer reliability model of the overall scheme of the aerospace measurement and control system according to the logic relation and the time period; the first layer model building module is specifically configured to: determining a task execution period according to the overall scheme of the aerospace measurement and control system; according to the logic relation, according to the time of entering the task and the time of exiting the task during the execution of the task by each component unit, performing time cutting on the task execution time period to obtain a space measurement and control subsystem corresponding to each time period, wherein the space measurement and control subsystem corresponding to each time period is an element in a first layer reliability model; the constituent units of the aerospace measurement and control subsystems in any two time periods are different, and the logic relations of the aerospace measurement and control subsystems in adjacent time periods are in series connection;
The second layer model building module is used for building a second layer reliability model according to measurement and control service in each period of the first layer reliability model; the second layer model building module is specifically configured to: in each time period of the first layer reliability model, a second layer reliability model is built according to a command control center structure, a communication network structure and a measurement and control station structure in sequence; in each structure, if the components which are backup to each other exist, the components which are backup to each other form a parallel relation.
7. A reliability modeling apparatus of an aerospace measurement and control system comprising a memory, a processor and a computer program stored in the memory and executable on the processor, characterized in that the processor, when executing the computer program, implements the steps of the reliability modeling method of an aerospace measurement and control system according to any one of claims 1 to 5.
8. A computer readable storage medium storing a computer program, characterized in that the computer program when executed by a processor implements the steps of the reliability modeling method of an aerospace measurement and control system according to any of claims 1 to 5.
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