CN113268368B - Safety key data maintenance method for combined spacecraft based on flight mission profile - Google Patents
Safety key data maintenance method for combined spacecraft based on flight mission profile Download PDFInfo
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- CN113268368B CN113268368B CN202110455131.9A CN202110455131A CN113268368B CN 113268368 B CN113268368 B CN 113268368B CN 202110455131 A CN202110455131 A CN 202110455131A CN 113268368 B CN113268368 B CN 113268368B
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- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/07—Responding to the occurrence of a fault, e.g. fault tolerance
- G06F11/0703—Error or fault processing not based on redundancy, i.e. by taking additional measures to deal with the error or fault not making use of redundancy in operation, in hardware, or in data representation
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Abstract
The method for maintaining safety critical data of the combined spacecraft based on the flight mission section divides the whole flight mission process of the combined spacecraft into a plurality of flight mission sections according to the mission characteristics, and each flight mission section has safety critical data and data storage period which are concerned by each flight mission section. The traditional safety key data fixed format maintenance form is broken, 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 on-site recovery integrity after system faults occur is improved; by defining the self-analysis format of the safety key data, the respective safety key data format is defined for each flight task section, and the safety key data storage and recovery logic realizes the self-analysis operation of the safety key data content according to the header information, so that the maintenance workload of the safety key data function and the code scale are effectively reduced.
Description
Technical Field
The invention relates to a safety key data maintenance method of a combined spacecraft based on a flight mission profile, provides a system fault breakpoint recovery mechanism, can be used for system reliability design in the aviation and aerospace fields, and belongs to the field of system reliability.
Background
The GNC subsystem is used as one of key subsystems of a spacecraft, the reliability design ensures the stable operation of the GNC subsystem, 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 the safety key data storage and recovery. The safety key data mechanism provides the capability of timely recovering the system faults and continuing the task to run when the faults such as power failure restarting, switching off and the like occur to the system. Along with the continuous increase of the complexity of the spacecraft system, the software maintenance data volume is larger and larger, and how to solve the contradiction of limited safety critical data storage resources and overlarge and various flight mission safety critical data sets becomes a difficult problem faced by the system design.
Disclosure of Invention
The invention solves the technical problems that: the safety critical data maintenance method for the combined spacecraft based on the flight mission profile is provided, dynamic mapping of the safety critical data format and the flight mission profile is realized on the premise of fixed size of the safety critical data storage space, so that the safety critical data format has mission correlation, the irrelevant data of the current flight mission profile is not listed as the safety critical data format, the safety critical data storage integrity involved under all the flight mission profiles of the combined spacecraft is ensured, and the fault tolerance recovery design capability of the GNC subsystem of the spacecraft is improved.
The technical scheme of the invention is as follows: the safety key data maintenance method 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 GNC subsystem of the spacecraft, and entering step (2);
step (2), defining a self-analysis format model of safety key data of the GNC subsystem of the spacecraft, designating a header and an accumulated sum in the self-analysis format model as M bytes in length and N bytes in effective data length, and entering the step (3);
step (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);
step (4), classifying all control modes in the control mode set according to the event and environmental characteristics experienced by the GNC subsystem of the spacecraft to form an on-orbit flight task profile set < section_j: j=1-n > of the GNC subsystem of the spacecraft, and entering the step (5);
step (5), sequentially determining data items concerned by each flight mission profile in the 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 item from the current flight mission profile, and repeating the step (5); if j is less than n, turning to the next flight mission section, repeating the step (5), otherwise, entering the step (6);
step (6), all the data items of the flight mission profile are determined, and the data items are summarized to form a data item Table set < Table_j: j=1-n >, and the step (7) is entered;
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 the step (6), sequentially realizing the encoding and decoding function for each Table_j, and entering step (10);
step (10), if the safety key data is saved, completing the data item table coding operation according to the self-analysis format mapping relation, filling the table header and the effective data area, and calculating the accumulation sum; if the operation is the safety key data recovery operation, extracting the table header, the effective data and the accumulation sum, verifying the correctness of the accumulation sum, and completing the data item table decoding operation according to the self-analysis format mapping relation; step (11) is entered;
and (11) finishing the maintenance of safety critical data of the combined spacecraft based on the flight mission profile.
Further, in the step (1), the sizes of the safety key data storage spaces reserved by the GNC subsystems of different spacecrafts are different.
In the step (2), a flight mission profile identifier is included in the self-analysis format model header, which is used as a basis for storing/recovering the mapping safety key data from the analysis operation.
Further, in the step (2), the length constraint relationship is M+N.ltoreq.L.
Further, in the step (5), the data item concerned by each flight mission section includes a flag quantity, a state quantity and an algorithm calculation quantity; and (5) completing rechecking of the data item and the total length of the data item.
Further, in the step (7), the enumerated type definition is mapped to the flight task profile set < section_j:j=1 to n >.
Further, in the step (9), the data item Table table_j corresponding to each enumeration type has a set of save content encoding operation and restore content decoding operation.
Further, in the step (10), the self-parsing format supports both the automatic save operation and the automatic restore operation of the safety critical data.
A computer readable storage medium storing a computer program which when executed by a processor performs the steps of the method for maintaining safety critical data of an assembled spacecraft based on a flight mission profile.
The safety critical data maintenance equipment of the combined spacecraft based on the flight mission profile 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 safety critical data maintenance method of the combined spacecraft based on the flight mission profile when executing the computer program.
Compared with the prior art, the invention has the advantages that:
(1) The safety critical data maintenance method for the combined spacecraft based on the flight mission profile breaks through the traditional safety critical data fixed format maintenance form, realizes dynamic mapping of the safety critical data format and the flight mission profile, ensures that the safety critical data format has mission correlation, improves the utilization efficiency of safety critical data resources, and improves the site recovery integrity after system faults occur;
(2) According to the safety key data maintenance method for the combined spacecraft based on the flight task sections, the safety key data self-analysis format is defined, the respective safety key data format is defined for each flight task section, and safety key data storage and recovery logic realizes the safety key data content self-analysis operation according to the header information, so that the safety key data function maintenance workload and the code scale are effectively reduced.
Drawings
FIG. 1 is a flow chart of the present invention;
fig. 2 is a security critical data self-parsing format model.
FIG. 3 is a schematic diagram of a control mode, flight mission profile, and data item table mapping relationship.
Detailed Description
In order to better understand the technical solutions described above, the following detailed description of the technical solutions of the present application is provided through the accompanying drawings and specific embodiments, and it should be understood that the specific features of the embodiments and embodiments of the present application are detailed descriptions of the technical solutions of the present application, and not limit the technical solutions of the present application, and the technical features of the embodiments and embodiments of the present application may be combined with each other without conflict.
The following describes in further detail the method for maintaining safety critical data of an assembled spacecraft based on a flight mission profile according to the embodiments of the present application with reference to the accompanying drawings, and the specific implementation manner may include (as shown in fig. 1 to 3):
as shown in fig. 1, the method for maintaining safety critical data of the combined spacecraft based on the flight mission profile comprises the following implementation steps:
(1) And (3) determining the size L bytes of the safety key 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 together according to the system resource condition and the system requirement, and the sizes of the safety key data storage spaces reserved by different GNC subsystems of the spacecraft are different.
(2) Defining a safety key data save/restore self-analysis format model of the GNC subsystem of the spacecraft, designating the length occupied by a header and an accumulated sum in the self-analysis format model as M bytes and the effective data length as N bytes, and entering the step (3). The security key data self-parsing format model is shown in fig. 2. The ID and the SectionEnum are combined to form a table header, the ID and the Chksum are used as criteria for data validity and integrity during safety critical data recovery, and the SectionEnum is an enumeration type of a flight mission profile and safety critical data self-analysis format mapping.
(3) And (3) determining a spacecraft control Mode according to the preset system demand, acquiring a control Mode set < mode_i:i=1-m > designed by the spacecraft GNC subsystem, and entering the step (4). The control mode is determined by the spacecraft scheme design, and in general, the control mode sets of different spacecraft are different.
(4) According to the event and the environmental characteristics experienced by the spacecraft GNC subsystem, all control modes in the control mode set are generalized and classified to form an on-orbit flight task profile set < section_j:j=1-n > of the spacecraft GNC subsystem, and the step (5) is entered. The flight mission profile is taken as a result of merging the similar items of the control mode, and the proposal is determined by the three parties of scheme design, overall design and software design.
(5) Sequentially determining data items focused on each flight mission Section in the 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, and if dataLen j > N, reselecting the data item from the current flight mission Section, and repeating the step (5); if j < n, turning to the next flight mission section, repeating the step (5), otherwise, entering the step (6). And (5) circularly traversing all flight mission sections until the selection of the data item concerned by all flight mission sections and the rechecking of the total length of the data item are completed.
(6) All the data items of the flight mission profile are determined, and the data items are summarized to form a data item Table set < Table_j:j=1-n >, and the step (7) is carried out. The mapping relations among the control mode set in the step (3), the flight mission profile set in the step (4) and the data item table set in the step (6) are shown in fig. 3.
(7) Based on the data item Table set < Table_j:j=1-n > formed in the step (6), instantiating the self-analysis format model defined in the step (2), determining the self-analysis format header enumeration type definition, and entering the step (8). Since there are n data item tables, then n self-parsing formats are instantiated.
(8) Determining a self-analysis format accumulation and calculation mode, and entering a step (9). The calculation mode of the accumulation sum generally selects four modes of accumulation according to bytes, accumulation according to bytes and inversion, accumulation according to 16-bit words and inversion.
(9) Based on the data item Table set < table_j:j=1 to n > formed in step (6), the encoding and decoding functions for each table_j are sequentially implemented, and step (10) is entered. And (3) designing storage coding and recovery decoding for each data item content in the data item table.
(10) If the operation is safety key data storage operation, completing data item table coding operation according to the self-analysis format mapping relation, filling a table header and an effective data area, and calculating an accumulation sum; if the operation is the safety key data recovery operation, extracting the table header, the effective data and the accumulation sum, verifying the correctness of the accumulation sum, and completing the data item table decoding operation according to the self-analysis format mapping relation; step (11) is entered. The safety key data under different flight mission sections are automatically saved and restored.
(11) And (5) finishing safety critical data maintenance 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 on-site recovery integrity after the system fault occurs is improved.
The present application provides a computer readable storage medium storing computer instructions that, when run on a computer, cause the computer to perform the method described in fig. 1.
It will be appreciated by those skilled in the art that 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, magnetic 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 flowchart illustrations and/or block diagrams, and combinations of flows and/or blocks in the flowchart illustrations 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 modifications and variations can be made in the present application without departing from the spirit or scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims and the equivalents thereof, the present application is intended to cover such modifications and variations.
What is not described in detail in the present specification is a well known technology to those skilled in the art.
Claims (10)
1. The safety key data maintenance method 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 GNC subsystem of the spacecraft, and entering step (2);
step (2), defining a self-analysis format model of safety key data of the GNC subsystem of the spacecraft, designating a header and an accumulated sum in the self-analysis format model as M bytes in length and N bytes in effective data length, and entering the step (3);
step (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);
step (4), classifying all control modes in the control mode set according to the event and environmental characteristics experienced by the GNC subsystem of the spacecraft to form an on-orbit flight task profile set < section_j: j=1-n > of the GNC subsystem of the spacecraft, and entering the step (5);
step (5), sequentially determining data items concerned by each flight mission profile in the 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 item from the current flight mission profile, and repeating the step (5); if j is less than n, turning to the next flight mission section, repeating the step (5), otherwise, entering the step (6);
step (6), all the data items of the flight mission profile are determined, and the data items are summarized to form a data item Table set < Table_j: j=1-n >, and the step (7) is entered;
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, 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 the step (6), sequentially realizing the encoding and decoding function for each Table_j, and entering step (10);
step (10), if the safety key data is saved, completing the data item table coding operation according to the self-analysis format mapping relation, calculating an accumulation sum, and filling the header, the effective data and the accumulation sum; if the operation is the safety key data recovery operation, extracting the table header, the effective data and the accumulation sum, verifying the correctness of the accumulation sum, and completing the data item table decoding operation according to the self-analysis format mapping relation; step (11) is entered;
and (11) finishing the maintenance of safety critical 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 of claim 1, wherein the method comprises the steps of: in the step (1), the sizes of the safety key data storage spaces reserved by the GNC subsystems of different spacecrafts are different.
3. The method for maintaining safety-critical data of an assembled spacecraft based on mission profile of claim 1, wherein the method comprises the steps of: in the step (2), the self-analysis format model header includes a flight mission profile identifier as a basis for storing/recovering the self-analysis operation of the mapping safety key data.
4. The method for maintaining safety-critical data of an assembled spacecraft based on mission profile of claim 1, wherein the method comprises the steps of: in the step (2), the length constraint relation is M+N less than or equal to L.
5. The method for maintaining safety-critical data of an assembled spacecraft based on mission profile of claim 1, wherein the method comprises the steps of: in the step (5), the data item concerned by each flight mission section comprises a mark quantity, a state quantity and an algorithm calculated quantity; and (5) completing 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 of claim 1, wherein the method comprises the steps of: in the step (7), the enumerated type definition is mapped to the flight mission profile set < section_j: j=1 to n >.
7. The method for maintaining safety-critical data of an assembled spacecraft based on mission profile of claim 1, wherein the method comprises the steps of: in the step (9), the data item Table table_j corresponding to each enumeration type has a set of save content encoding operation and restore content decoding operation.
8. The method for maintaining safety-critical data of an assembled spacecraft based on mission profile of claim 1, wherein the method comprises the steps of: in the step (10), the self-analysis format supports the automatic save operation and the automatic recovery operation of the safety key data at the same time.
9. A computer readable storage medium storing a computer program, which when executed by a processor performs the steps of the method according to any one of claims 1 to 8.
10. An integrated spacecraft safety critical data maintenance device based on a flight 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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