CN113268368A - Flight task profile-based combined spacecraft safety critical data maintenance method - Google Patents
Flight task profile-based combined spacecraft safety critical data maintenance method Download PDFInfo
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- CN113268368A CN113268368A CN202110455131.9A CN202110455131A CN113268368A CN 113268368 A CN113268368 A CN 113268368A CN 202110455131 A CN202110455131 A CN 202110455131A CN 113268368 A CN113268368 A CN 113268368A
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Abstract
The method for maintaining the safety key data of the combined spacecraft based on the flight task profiles divides the whole flight task process of the combined spacecraft into a plurality of flight task profiles according to task characteristics, and each flight task profile has the safety key data and the data storage period which are concerned by the flight task profile. The method breaks through the traditional fixed format maintenance form of the safety key data, realizes the dynamic mapping of the safety key data format and the flight task profile, ensures that the safety key data format has task correlation, improves the utilization efficiency of safety key data resources, and improves the field recovery integrity after system failure occurs; by defining the safety key data self-analysis format and defining the respective safety key data format for each flight mission profile, the storage and recovery logic of the safety key data realizes the self-analysis operation of the safety key data content according to the header information, and the function maintenance workload and the code scale of the safety key data are effectively reduced.
Description
Technical Field
The invention relates to a flight task profile-based method for maintaining safety critical data of an assembled spacecraft, provides a system fault breakpoint recovery mechanism, can be used for system reliability design in the fields of aviation and aerospace, and belongs to the field of system reliability.
Background
The GNC subsystem is used as one of key subsystems of a spacecraft, the stable operation of the GNC subsystem is ensured by reliability design, the most common reliability design is a system fault breakpoint recovery mechanism, and the system recovery based on the periodic storage of safety key data is 'safety key data storage and recovery'. The safety key data mechanism provides the system with the capability of timely recovering system faults and continuing task operation when the system has faults such as power failure restart, tripping and the like. With the increasing complexity of a spacecraft system, the software maintenance data volume is larger and larger, and how to solve the contradiction between the limitation of safety key data storage resources and the overlarge and various flight task safety key data sets becomes a difficult problem for system design.
Disclosure of Invention
The technical problem solved by the invention is as follows: the method overcomes the defects of the prior art, provides a flight task profile-based method for maintaining safety key data of the combined spacecraft, and realizes dynamic mapping of a safety key data format and a flight task profile on the premise that the size of a safety key data storage space is fixed, so that the safety key data format has task relevance, the independent data of the current flight task profile is not listed as the safety key data format, the storage integrity of the safety key data related to all flight task profiles of the combined spacecraft is ensured, and the fault tolerance recovery design capability of a GNC subsystem of the spacecraft is improved.
The technical solution of the invention is as follows: the method for maintaining the safety critical data of the combined spacecraft based on the flight mission profile comprises the following steps:
step (1), determining the size L bytes of a safety key data storage space reserved by a spacecraft GNC subsystem, and entering step (2);
step (2), defining a safety key data self-analysis format model of the GNC subsystem of the spacecraft, designating the length of a header and the sum of the header in the self-analysis format model as M bytes and the length of effective data as N bytes, and entering step (3);
step (3), determining a spacecraft control Mode according to the preset system requirement, acquiring a control Mode set (Mode _ i: 1-m) designed by a spacecraft GNC subsystem, and entering step (4);
step (4), classifying all control modes in the control mode set according to events and environmental characteristics experienced by the spacecraft GNC subsystem to form an on-orbit flight task profile set < Section _ j: j ═ 1-n > of the spacecraft GNC subsystem, and entering step (5);
step (5), sequentially determining data items concerned by each flight task Section in a set < Section _ j: j ═ 1-N >, determining the data type of each data item according to the data characteristics, calculating the summary length dataLen _ j of the data items, if dataLen j > N, reselecting the data items of the current flight task Section, and repeating the step (5); if j is less than n, switching to the next flight mission profile, and repeating the step (5), otherwise, entering the step (6);
step (6), determining the data items of all flight mission profiles, summarizing to form a data item Table set < Table _ j: j ═ 1-n >, and entering step (7);
step (7), instantiating the self-analysis format model defined in the step (2) based on the data item Table set < Table _ j: j ═ 1-n > formed in the step (6), determining the self-analysis format header enumeration type definition, and entering the step (8);
step (8), determining a self-analysis format accumulation and calculation mode, and entering step (9);
step (9), based on the data item Table set < Table _ j: j ═ 1-n > formed in step (6), sequentially implementing the encoding and decoding function for each Table _ j, and entering step (10);
step (10), if the operation is the safety key data storage operation, finishing the data item table coding operation according to the self-analytic format mapping relation, filling a table header and an effective data area, and calculating the accumulated sum; if the data item is the safety key data recovery operation, extracting the header, the valid data and the accumulated sum, verifying the accumulated sum and the correctness, and finishing the data item table decoding operation according to the self-analytic format mapping relation; entering a step (11);
and (11) finishing maintenance of safety key data of the combined spacecraft based on the flight mission profile.
Further, in the step (1), the sizes of the safety critical data storage spaces reserved by different spacecraft GNC subsystems are different.
Further, in the step (2), the self-analytic format model header includes a flight mission profile identifier, which is used as a basis for mapping safety-critical data storage/recovery self-analytic operation.
Further, in the step (2), the length constraint relationship is that M + N is less than or equal to L.
Further, in the step (5), the data items concerned by each flight mission profile comprise a flag quantity, a state quantity and an algorithm calculation quantity; and (5) completing the rechecking of the data item and the total length of the data item.
Further, in the step (7), the enumeration type definition is mapped to a flight mission profile set < Section _ j: j ═ 1 to n > one to one.
Further, in the step (9), the data item Table _ j corresponding to each enumeration type has a set of saved content encoding operations and restored content decoding operations.
Further, in the step (10), the self-analytic format supports both the safety-critical data auto-save operation and the auto-restore operation.
A computer-readable storage medium, having stored thereon a computer program which, when being executed by a processor, carries out the steps of the method for maintaining safety-critical data of an assembled spacecraft based on a mission profile.
The flight mission profile-based combined spacecraft safety critical data maintenance device comprises a memory, a processor and a computer program which is stored in the memory and can run on the processor, wherein the processor realizes the steps of the flight mission profile-based combined spacecraft safety critical data maintenance method when executing the computer program.
Compared with the prior art, the invention has the advantages that:
(1) the method for maintaining the safety key data of the combined spacecraft based on the flight task profile breaks through the traditional fixed format maintenance form of the safety key data, realizes the dynamic mapping of the safety key data format and the flight task profile, enables the safety key data format to have task relevance, improves the utilization efficiency of safety key data resources, and improves the field recovery integrity after system failure;
(2) according to the method for maintaining the safety key data of the combined spacecraft based on the flight mission profiles, the safety key data self-analysis format is defined, the safety key data format is defined for each flight mission profile, the storage and recovery logic of the safety key data realizes the self-analysis operation of the safety key data content according to the header information, and the function maintenance workload and the code scale of the safety key data are effectively reduced.
Drawings
FIG. 1 is a flow chart of the present invention;
FIG. 2 is a safety critical data self-parsing format model.
FIG. 3 is a diagram illustrating a control mode, a flight mission profile, and a data item table mapping relationship.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
The method for maintaining the safety critical data of the combined spacecraft based on the flight mission profile provided by the embodiment of the application is further described in detail below with reference to the attached drawings of the specification, and specific implementation manners may include (as shown in fig. 1 to 3):
as shown in fig. 1, a method for maintaining safety critical data of an assembly spacecraft based on a flight mission profile includes the following steps:
(1) and (3) determining the size L bytes of a safety critical data storage space reserved by the GNC subsystem of the spacecraft, and entering the step (2). The size of the safety key data storage space is determined jointly according to the system resource condition and the system requirement, and the sizes of the safety key data storage spaces reserved by different spacecraft GNC subsystems are different.
(2) Defining a safety key data storage/recovery self-analysis format model of the GNC subsystem of the spacecraft, designating the length of a header and an accumulated sum in the self-analysis format model as M bytes and the length of effective data as N bytes, and entering the step (3). The safety-critical data self-parsing format model is shown in fig. 2. The ID and the SectionEnum jointly form a header, the ID and the Chksum serve as criteria of data effectiveness and integrity when safety critical data are recovered, and the SectionEnum is an enumeration type of a flight mission profile and safety critical data self-analytic format mapping.
(3) Determining a spacecraft control Mode according to preset system requirements, acquiring a control Mode set < Mode _ i: i ═ 1-m > designed by a spacecraft GNC subsystem, and entering step (4). The control mode is determined by the design of a spacecraft scheme, and in general, the control mode sets of different spacecrafts are different.
(4) And (5) according to the events and environmental characteristics experienced by the spacecraft GNC subsystem, inducing and classifying all control modes in the control mode set to form an on-orbit flight mission profile set < Section _ j: j ═ 1-n > of the spacecraft GNC subsystem, and entering the step (5). The flight task profile is used as a result of combining the same items of the control mode, and is suggested to be determined by a scheme design party, a total design party and a software design party.
(5) Sequentially determining data items concerned by each flight task Section in a set (Section _ j, j is 1-N), determining the data type of each data item according to the data characteristics, calculating the summary length dataLen _ j of the data items, reselecting the data items of the current flight task Section if the dataLen j is greater than N, and repeating the step (5); if j < n, switching to the next flight mission profile, and repeating the step (5), otherwise, entering the step (6). And (5) circularly traversing all flight task sections until the selection of the data items concerned by all the flight task sections and the rechecking of the total length of the data items are completed.
(6) All the data items of the flight mission profiles are determined, a data item Table set < Table _ j: j ═ 1-n > is formed in a summary mode, and the step (7) is carried out. The mapping relationship among the control mode set in step (3), the flight mission profile set in step (4), and the data item table set in step (6) is shown in fig. 3.
(7) And (3) instantiating the self-parsing format model defined in the step (2) based on the data item Table set < Table _ j: j ═ 1-n > formed in the step (6), determining the self-parsing format header enumeration type definition, and entering the step (8). Since there are n data item tables, n self-parsing formats are instantiated.
(8) And (4) determining a self-parsing format accumulation and calculation mode, and entering the step (9). The calculation mode of the accumulated sum generally selects four modes of accumulating according to bytes, accumulating according to bytes and then negating, accumulating according to 16-bit words and then negating.
(9) And (4) sequentially realizing the encoding and decoding function aiming at each Table _ j based on the data item Table set < Table _ j: j ═ 1-n > formed in the step (6), and entering the step (10). And designing storage encoding and recovery decoding for the content of each data item in the data item table.
(10) If the data is the safety key data storage operation, finishing the data item table coding operation according to the self-analytic format mapping relation, filling the table header and the effective data area, and calculating the accumulated sum; if the data item is the safety key data recovery operation, extracting the header, the valid data and the accumulated sum, verifying the accumulated sum and the correctness, and finishing the data item table decoding operation according to the self-analytic format mapping relation; step (11) is entered. And the automatic saving and recovery operation of safety critical data under different flight mission profiles is realized.
(11) And finishing the maintenance of safety key data of the combined spacecraft based on the flight mission profile. The dynamic mapping of the safety key data format and the flight task profile is realized, so that the safety key data format has task correlation, the utilization efficiency of safety key data resources is improved, and the field recovery integrity after system failure occurs is improved.
A computer-readable storage medium having stored thereon computer instructions which, when executed on a computer, cause the computer to perform the method of fig. 1.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. The method for maintaining the safety critical data of the combined spacecraft based on the flight mission profile is characterized by comprising the following steps of:
step (1), determining the size L bytes of a safety key data storage space reserved by a spacecraft GNC subsystem, and entering step (2);
step (2), defining a safety key data self-analysis format model of the GNC subsystem of the spacecraft, designating the length of a header and the sum of the header in the self-analysis format model as M bytes and the length of effective data as N bytes, and entering step (3);
step (3), determining a spacecraft control Mode according to the preset system requirement, acquiring a control Mode set (Mode _ i: 1-m) designed by a spacecraft GNC subsystem, and entering step (4);
step (4), classifying all control modes in the control mode set according to events and environmental characteristics experienced by the spacecraft GNC subsystem to form an on-orbit flight task profile set < Section _ j: j ═ 1-n > of the spacecraft GNC subsystem, and entering step (5);
step (5), sequentially determining data items concerned by each flight task Section in a set < Section _ j: j ═ 1-N >, determining the data type of each data item according to the data characteristics, calculating the summary length dataLen _ j of the data items, if dataLen j > N, reselecting the data items of the current flight task Section, and repeating the step (5); if j is less than n, switching to the next flight mission profile, and repeating the step (5), otherwise, entering the step (6);
step (6), determining the data items of all flight mission profiles, summarizing to form a data item Table set < Table _ j: j ═ 1-n >, and entering step (7);
step (7), instantiating the self-parsing format model defined in the step (2) based on the data item Table set < Table _ j: j ═ 1-n > formed in the step (6), determining the self-parsing format header enumeration type definition, filling effective data content, and entering the step (8);
step (8), determining a self-analysis format accumulation and calculation mode, and entering step (9);
step (9), based on the data item Table set < Table _ j: j ═ 1-n > formed in step (6), sequentially implementing the encoding and decoding function for each Table _ j, and entering step (10);
step (10), if the operation is the safety key data storage operation, finishing the data item table coding operation according to the self-analytic format mapping relation, calculating the accumulated sum, and filling the table header, the effective data and the accumulated sum; if the data item is the safety key data recovery operation, extracting the header, the valid data and the accumulated sum, verifying the accumulated sum and the correctness, and finishing the data item table decoding operation according to the self-analytic format mapping relation; entering a step (11);
and (11) finishing maintenance of safety key data of the combined spacecraft based on the flight mission profile.
2. The method for maintaining safety critical data of an assembled spacecraft based on mission profile as claimed in claim 1, wherein: in the step (1), the sizes of the safety key data storage spaces reserved by different spacecraft GNC subsystems are different.
3. The method for maintaining safety critical data of an assembled spacecraft based on mission profile as claimed in claim 1, wherein: in the step (2), the self-analytic format model header includes a flight mission profile identifier as a basis for mapping safety-critical data storage/recovery self-analytic operation.
4. The method for maintaining safety critical data of an assembled spacecraft based on mission profile as claimed in claim 1, wherein: in the step (2), the length constraint relation is that M + N is less than or equal to L.
5. The method for maintaining safety critical data of an assembled spacecraft based on mission profile as claimed in claim 1, wherein: in the step (5), the data items concerned by each flight task section comprise a flag quantity, a state quantity and an algorithm calculated quantity; and (5) completing the rechecking of the data item and the total length of the data item.
6. The method for maintaining safety critical data of an assembled spacecraft based on mission profile as claimed in claim 1, wherein: in the step (7), the enumeration type definition is mapped with a flight mission profile set < Section _ j: j ═ 1 to n > one by one.
7. The method for maintaining safety critical data of an assembled spacecraft based on mission profile as claimed in claim 1, wherein: in the step (9), the data item Table _ j corresponding to each enumeration type has a group of stored content encoding operations and restored content decoding operations.
8. The method for maintaining safety critical data of an assembled spacecraft based on mission profile as claimed in claim 1, wherein: in the step (10), the self-analytic format supports both the automatic saving operation and the automatic recovery operation of the safety-critical data.
9. A computer-readable storage medium, in which a computer program is stored which, when being executed by a processor, carries out the steps of the method according to any one of claims 1 to 8.
10. An assembly spacecraft safety critical data maintenance device based on mission profile, comprising a memory, a processor and a computer program stored in said memory and executable on said processor, characterized in that: the processor, when executing the computer program, performs the steps of the method according to any one of claims 1 to 8.
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