Spacecraft flight control process working condition rapid assessment system, method, equipment and medium

Abstract

The present invention discloses a system, method, device and medium for rapid evaluation of the working conditions of a spacecraft flight control process, and relates to the field of spacecraft evaluation technology, including: determining the behavior sequence corresponding to multiple key instructions corresponding to the flight control events corresponding to the flight control plan of the spacecraft to be evaluated, and establishing an instruction association set according to the evaluation parameters; real-time acquisition of telemetry data of the spacecraft to be evaluated in response to the current key instructions to generate an actual sequence; calculating the similarity between the actual sequence and the behavior sequence, determining the correlation between the change in the telemetry parameter in the actual sequence and the instruction association set, and generating fault information; determining the fault condition according to the fault information and the current key instructions. The method verifies the spacecraft to be evaluated through two schemes, thereby improving the accuracy of the verification results. The present invention studies the key technologies for rapid evaluation of the working conditions of a typical flight control process of a spacecraft, and explores technical routes and provides technical guidance for rapid evaluation of spacecraft working conditions.

Description

Background Art

[0002] At present, spacecraft condition assessment has the initial ability to identify the assessment object, but it requires manual real-time monitoring and post-analysis of the assessment object, which places extremely high demands on the ability and quality of the analysis staff, and the assessment standards are not unified. It is urgent to conduct research on the rapid assessment of typical flight control process conditions of spacecraft, establish assessment models and assessment methods before mission execution, get rid of the requirements for manual ability and energy during mission execution, and realize automatic rapid standardized assessment. Summary of the invention

[0003] The technical problem to be solved by the present invention is to address the deficiencies of the prior art, and specifically provide a system, method, device and medium for rapid evaluation of the working conditions of a spacecraft flight control process, as follows:

[0004] 1) In the first aspect, the present invention provides a system for rapid evaluation of the working conditions of a spacecraft flight control process, and the specific technical scheme is as follows:

[0005] Behavior prediction module, flight control important time design module, analysis module, acquisition module and fault diagnosis module;

[0006] The behavior prediction module is used to: determine, according to the flight control requirements of the spacecraft to be evaluated, a plurality of key instructions corresponding to the flight control events corresponding to the flight control plan of the spacecraft to be evaluated, sort the plurality of key instructions to obtain a behavior sequence of the spacecraft to be evaluated, and issue key instructions to the spacecraft to be evaluated in sequence according to the behavior sequence;

[0007] The flight control important time design module is used to: determine a plurality of evaluation parameters corresponding to the working condition event corresponding to the flight control file corresponding to the spacecraft to be evaluated according to the flight program of the spacecraft to be evaluated, and establish an instruction association set based on the plurality of evaluation parameters;

[0008] The acquisition module is used to: acquire telemetry data of the spacecraft to be evaluated in response to the current key instructions in real time to generate an actual sequence;

[0009] The analysis module is used to: calculate the similarity between the actual sequence and the behavior sequence by a fuzzy matching method, and determine whether the similarity is greater than a similarity threshold, and generate a first determination result;

[0010] Determine the correlation between the telemetry parameter change amount in the actual sequence and the instruction correlation set by using the fuzzy hierarchical analysis method, and judge whether the correlation is greater than a correlation threshold value, and generate a second judgment result;

[0011] When at least one of the first judgment result and the second judgment result is negative, generating fault information;

[0012] The fault diagnosis module is used to determine the fault condition according to the fault information and the current key instruction.

[0013] The beneficial effects of the rapid evaluation system for the working condition of a spacecraft flight control process provided by the present invention are as follows:

[0014] The two schemes are used to calibrate the spacecraft to be evaluated, thereby improving the accuracy of the verification results. The present invention studies the key technologies for rapid evaluation of the working conditions of a typical flight control process of a spacecraft, and explores technical routes and provides technical guidance for rapid evaluation of the working conditions of a spacecraft.

[0015] Based on the above solution, the present invention can also be improved as follows.

[0016] Furthermore, the actual sequence is determined by serializing and normalizing the telemetry parameters in sequence to obtain the actual sequence.

[0017] Furthermore, the analysis module is also used for:

[0018] When the first judgment result and the second judgment result are both yes, feedback information is sent to the behavior prediction module.

[0019] Furthermore, the behavior prediction module is also used for:

[0020] In response to the feedback information, new key instructions are issued to the spacecraft to be evaluated according to the behavior sequence.

[0021] 2) In the second aspect, the present invention also provides a method for rapid evaluation of the working conditions of a spacecraft flight control process, and the specific technical solution is as follows:

[0022] The behavior prediction module determines, according to the flight control requirements of the spacecraft to be evaluated, a plurality of key instructions corresponding to the flight control events corresponding to the flight control plan of the spacecraft to be evaluated, sorts the plurality of key instructions to obtain a behavior sequence of the spacecraft to be evaluated, and issues key instructions to the spacecraft to be evaluated in sequence according to the behavior sequence;

[0023] The flight control important time design module determines a plurality of evaluation parameters corresponding to the working condition events corresponding to the flight control file corresponding to the spacecraft to be evaluated according to the flight program of the spacecraft to be evaluated, and establishes an instruction association set based on the plurality of evaluation parameters;

[0024] The acquisition module collects the telemetry data of the spacecraft to be evaluated in response to the current key instructions in real time and generates the actual sequence;

[0025] The analysis module calculates the similarity between the actual sequence and the behavior sequence by a fuzzy matching method, and determines whether the similarity is greater than a similarity threshold, thereby generating a first determination result;

[0026] Determine the correlation between the telemetry parameter change amount in the actual sequence and the instruction correlation set by using the fuzzy hierarchical analysis method, and judge whether the correlation is greater than a correlation threshold value, and generate a second judgment result;

[0027] When at least one of the first judgment result and the second judgment result is negative, generating fault information;

[0028] The fault diagnosis module determines the fault condition according to the fault information and the current key instruction.

[0029] Based on the above solution, the present invention can also be improved as follows.

[0030] Furthermore, the actual sequence is determined by serializing and normalizing the telemetry parameters in sequence to obtain the actual sequence.

[0031] Furthermore, it also includes:

[0032] When the first judgment result and the second judgment result are both yes, feedback information is sent to the behavior prediction module.

[0033] Furthermore, it also includes:

[0034] In response to the feedback information, new key instructions are issued to the spacecraft to be evaluated according to the behavior sequence.

[0035] 3) In a third aspect, the present invention further provides a computer device, comprising a processor, wherein the processor is coupled to a memory, wherein the memory stores at least one computer program, and wherein the at least one computer program is loaded and executed by the processor so that the computer device implements any of the above methods.

[0036] 4) In a fourth aspect, the present invention further provides a computer-readable storage medium, wherein at least one computer program is stored in the computer-readable storage medium, and the at least one computer program is loaded and executed by a processor so that a computer implements any of the above methods.

[0037] It should be noted that the beneficial effects achieved by the technical solutions of the second to fourth aspects of the present invention and the corresponding possible implementation methods can be found in the above-mentioned technical effects of the first aspect and its corresponding possible implementation methods, and will not be repeated here. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0039] Figure 1A structural framework diagram of a system for rapid evaluation of working conditions of a spacecraft flight control process according to an embodiment of the present invention;

[0040] Figure 2 It is a schematic diagram of the computer equipment structure;

[0041] Figure 3 A schematic diagram of the technical architecture for rapid evaluation of typical flight control process conditions of spacecraft;

[0042] Figure 4 This is a schematic diagram of the behavior prediction technology based on the flight control instruction plan;

[0043] Figure 5 A schematic diagram of an automatic comparison method for injecting a dynamic comparison architecture;

[0044] Figure 6 It is one of the schematic diagrams of the theoretical attitude adjustment curve, the actual attitude adjustment curve and the abnormal attitude adjustment curve of the spacecraft;

[0045] Figure 7 This is the second schematic diagram of the spacecraft's theoretical attitude adjustment curve, actual attitude adjustment curve, and abnormal attitude adjustment curve;

[0046] Figure 8 This is the third schematic diagram of the spacecraft's theoretical attitude adjustment curve, actual attitude adjustment curve, and abnormal attitude adjustment curve;

[0047] Fig. 9 It is a comprehensive display of the whole system - a schematic diagram of the spacecraft status. DETAILED DESCRIPTION

[0048] In order to make the objectives, technical solutions and advantages of the present invention more clear, the embodiments of the present invention will be further described in detail below with reference to the accompanying drawings.

[0049] like Figure 1 As shown, a system 200 for quickly evaluating the working conditions of a spacecraft flight control process according to an embodiment of the present invention includes the following steps:

[0050] Behavior prediction module 210, flight control important time design module 220, analysis module 230, acquisition module 240 and fault diagnosis module 250;

[0051] The behavior prediction module 210 is used to: determine a plurality of key instructions corresponding to a flight control event corresponding to a flight control plan of the spacecraft to be evaluated according to a flight control requirement of the spacecraft to be evaluated, sort the plurality of key instructions to obtain a behavior sequence of the spacecraft to be evaluated, and issue key instructions to the spacecraft to be evaluated in sequence according to the behavior sequence;

[0052] The flight control important time design module 220 is used to: determine a plurality of evaluation parameters corresponding to the working condition events corresponding to the flight control file corresponding to the spacecraft to be evaluated according to the flight program of the spacecraft to be evaluated, and establish an instruction association set based on the plurality of evaluation parameters;

[0053] The acquisition module 240 is used to: acquire telemetry data of the spacecraft to be evaluated in response to the current key instructions in real time to generate an actual sequence;

[0054] The analysis module 230 is used to: calculate the similarity between the actual sequence and the behavior sequence by a fuzzy matching method, and determine whether the similarity is greater than a similarity threshold, and generate a first determination result;

[0055] Determine the correlation between the telemetry parameter change amount in the actual sequence and the instruction correlation set by using the fuzzy hierarchical analysis method, and judge whether the correlation is greater than a correlation threshold value, and generate a second judgment result;

[0056] When at least one of the first judgment result and the second judgment result is negative, generating fault information;

[0057] The fault diagnosis module 250 is used to determine the fault condition according to the fault information and the current key instruction.

[0058] The beneficial effects of the rapid evaluation system for the working condition of a spacecraft flight control process provided by the present invention are as follows:

[0059] The two schemes are used to calibrate the spacecraft to be evaluated, thereby improving the accuracy of the verification results. The present invention studies the key technologies for rapid evaluation of the working conditions of a typical flight control process of a spacecraft, and explores technical routes and provides technical guidance for rapid evaluation of the working conditions of a spacecraft.

[0060] like Figure 3 As shown, the behavior prediction module (i.e., the behavior prediction based on the flight control instruction plan during the process) is used to: determine multiple key instructions corresponding to the flight control events corresponding to the flight control plan of the spacecraft to be evaluated according to the flight control requirements of the spacecraft to be evaluated, sort the multiple key instructions to obtain the behavior sequence of the spacecraft to be evaluated, and issue key instructions to the spacecraft to be evaluated in sequence according to the behavior sequence. Among them:

[0061] like Figure 4 As shown, one flight control requirement corresponds to at least one flight control plan, one flight control plan corresponds to at least one flight control event, and one flight control event corresponds to at least one key instruction.

[0062] The behavior sequence is a sequence obtained by arranging all key instructions in time sequence according to flight control requirements. That is, the sequence consists of key instructions. The flight state reflected in the behavior sequence is transferred in the form of global state quantity. The global state quantity will affect the judgment threshold of the telemetry parameters transmitted by the spacecraft, realize the correlation relationship from the instruction plan to the judgment threshold of the specific parameter, and complete the behavior prediction of the spacecraft state.

[0063] According to the order of key instructions in the behavior sequence, key instructions are sent to the spacecraft to be evaluated in sequence.

[0064] The flight control important time design module (i.e., the flight control important time design based on hierarchical analysis in the figure) is used to: determine multiple evaluation parameters corresponding to the working condition events corresponding to the flight control file corresponding to the spacecraft to be evaluated according to the flight program of the spacecraft to be evaluated, and establish an instruction association set based on the multiple evaluation parameters.

[0065] The flight control file refers to: a parameter table corresponding to the flight procedure.

[0066] Evaluation parameters refer to parameters used to characterize or represent the completion of certain key instructions.

[0067] like Figures 5 to 8 As shown, in another embodiment, a verification module is also included: used to verify key instructions.

[0068] The acquisition module is used to: collect the telemetry data of the spacecraft to be evaluated in response to the current key instruction in real time to generate an actual sequence. The analysis module is used to: calculate the similarity between the actual sequence and the behavior sequence by fuzzy matching method, and determine whether the similarity is greater than the similarity threshold, and generate a first judgment result. Wherein:

[0069] The similarity threshold is a reference value formulated based on actual conditions and can be adaptively adjusted according to different environments and the performance of different spacecraft to be evaluated. No specific numerical value is limited here.

[0070] The correlation between the telemetry parameter change in the actual sequence and the instruction correlation set is determined by fuzzy hierarchical analysis method, and it is determined whether the correlation is greater than the correlation threshold value to generate a second judgment result.

[0071] The association threshold is the same as the similarity threshold, and no specific numerical value is limited here.

[0072] When at least one of the first judgment result and the second judgment result is negative, generating fault information;

[0073] The fault diagnosis module is used to determine the fault condition according to the fault information and the current key instruction.

[0074] like Fig. 9 As shown, based on the knowledge-based design and method of integrated display of flow, the operating information of each target and system of the spacecraft is comprehensively displayed to provide support for mission status monitoring and flight control decision-making, and multiple display methods such as multi-level, graphical, and three-dimensional digital (digital space station) are used to support the transformation of display from digital to knowledge-based.

[0075] The effects that can be achieved through this solution are:

[0076] 1) Expanding the previous flight control effect evaluation from point to line is conducive to grasping the entire flight control process from a detailed perspective.

[0077] 2) It can detect "wild values" or "mutations" that may exist in the actual sequence. Mission experience shows that these "wild values" and "mutations" usually indicate abnormal actions in the spacecraft's flight control process, and these abnormalities are often closely related to certain "hidden dangers" exposed in advance by the spacecraft. Using the theoretical flight control sequence as a filter can filter out the "wild values" in the actual flight control sequence, and by performing correlation analysis on the wild value parameters, it is possible to discover the "lesions" of the on-orbit spacecraft as early as possible. This will completely eliminate the hidden dangers of failure and effectively extend the life of the on-orbit spacecraft.

[0078] Furthermore, the actual sequence is determined by serializing and normalizing the telemetry parameters in sequence to obtain the actual sequence.

[0079] Furthermore, the analysis module is also used for:

[0080] When the first judgment result and the second judgment result are both yes, feedback information is sent to the behavior prediction module.

[0081] Furthermore, the behavior prediction module is also used for:

[0082] In response to the feedback information, new key instructions are issued to the spacecraft to be evaluated according to the behavior sequence.

[0083] The present invention also provides a method for quickly evaluating the working conditions of a spacecraft flight control process, and the specific technical solution is as follows:

[0084] The behavior prediction module determines, according to the flight control requirements of the spacecraft to be evaluated, a plurality of key instructions corresponding to the flight control events corresponding to the flight control plan of the spacecraft to be evaluated, sorts the plurality of key instructions to obtain a behavior sequence of the spacecraft to be evaluated, and issues key instructions to the spacecraft to be evaluated in sequence according to the behavior sequence;

[0085] The flight control important time design module determines a plurality of evaluation parameters corresponding to the working condition events corresponding to the flight control file corresponding to the spacecraft to be evaluated according to the flight program of the spacecraft to be evaluated, and establishes an instruction association set based on the plurality of evaluation parameters;

[0086] The acquisition module collects the telemetry data of the spacecraft to be evaluated in response to the current key instructions in real time and generates the actual sequence;

[0087] The analysis module calculates the similarity between the actual sequence and the behavior sequence by a fuzzy matching method, and determines whether the similarity is greater than a similarity threshold, thereby generating a first determination result;

[0088] Determine the correlation between the telemetry parameter change amount in the actual sequence and the instruction correlation set by using the fuzzy hierarchical analysis method, and judge whether the correlation is greater than a correlation threshold value, and generate a second judgment result;

[0089] When at least one of the first judgment result and the second judgment result is negative, generating fault information;

[0090] The fault diagnosis module determines the fault condition according to the fault information and the current key instruction.

[0091] Furthermore, the actual sequence is determined by serializing and normalizing the telemetry parameters in sequence to obtain the actual sequence.

[0092] Furthermore, it also includes:

[0093] When the first judgment result and the second judgment result are both yes, feedback information is sent to the behavior prediction module.

[0094] Furthermore, it also includes:

[0095] In response to the feedback information, new key instructions are issued to the spacecraft to be evaluated according to the behavior sequence.

[0096] In the above embodiments, although the steps are numbered S1, S2, etc., these are only specific embodiments given by the present invention. Those skilled in the art may adjust the execution order of S1, S2, etc. according to actual conditions, which is also within the protection scope of the present invention. It can be understood that in some embodiments, some or all of the above embodiments may be included.

[0097] It should be noted that the beneficial effects of the method for rapid evaluation of the working conditions of a spacecraft flight control process provided in the above embodiment are the same as the beneficial effects of the system for rapid evaluation of the working conditions of a spacecraft flight control process provided in the above embodiment, which will not be repeated here. In addition, when the system provided in the above embodiment realizes its functions, only the division of the above functional modules is used as an example. In actual applications, the above functions can be assigned to different functional modules as needed, that is, the system can be divided into different functional modules according to actual conditions to complete all or part of the functions described above. In addition, the system and method embodiments provided in the above embodiment belong to the same concept, and the specific implementation process is detailed in the method embodiment, which will not be repeated here.

[0098] like Figure 2 As shown, a computer device 300 according to an embodiment of the present invention includes a processor 320, the processor 320 is coupled to a memory 310, and the memory 310 stores at least one computer program 330, and the at least one computer program 330 is loaded and executed by the processor 320, so that the computer device 300 implements any of the above methods, specifically:

[0099] The computer device 300 may have relatively large differences due to different configurations or performances, and may include one or more processors 320 (Central Processing Units, CPU) and one or more memories 310, wherein the one or more memories 310 store at least one computer program 330, and the at least one computer program 330 is loaded and executed by the one or more processors 320, so that the computer device 300 implements a method for rapid evaluation of the working conditions of a spacecraft flight control process provided in the above embodiment. Of course, the computer device 300 may also have components such as a wired or wireless network interface, a keyboard, and an input and output interface for input and output, and the computer device 300 may also include other components for realizing the functions of the device, which will not be described in detail here.

[0100] A computer-readable storage medium according to an embodiment of the present invention stores at least one computer program, and the at least one computer program is loaded and executed by a processor so that a computer implements any one of the above methods.

[0101] Optionally, the computer-readable storage medium may be a read-only memory (ROM), a random access memory (RAM), a compact disc (CD-ROM), a magnetic tape, a floppy disk, an optical data storage device, and the like.

[0102] In an exemplary embodiment, a computer program product or a computer program is also provided, the computer program product or the computer program comprising computer instructions, the computer instructions being stored in a computer-readable storage medium. A processor of a computer device reads the computer instructions from the computer-readable storage medium, and the processor executes the computer instructions, so that the computer device performs any of the above methods.

[0103] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application are used to distinguish similar objects and represent the definition of a specific order or sequence. The order of use of similar objects can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than the order shown or described.

[0104] Those skilled in the art know that the present invention can be implemented as a system, method or computer program product. Therefore, the present disclosure can be specifically implemented in the following forms, namely: it can be complete hardware, it can be complete software (including firmware, resident software, microcode, etc.), or it can be a combination of hardware and software, which is generally referred to as "circuit", "module" or "system" herein. In addition, in some embodiments, the present invention can also be implemented in the form of a computer program product in one or more computer-readable media, and the computer-readable medium contains computer-readable program code.

[0105] Any combination of one or more computer-readable media may be used. A computer-readable medium may be a computer-readable signal medium or a computer-readable storage medium. A computer-readable storage medium may be, for example, but not limited to, an electrical, magnetic, optical, electromagnetic, infrared, or semiconductor system, device, or device, or any combination thereof. More specific examples (a non-exhaustive list) of computer-readable storage media include: an electrical connection with one or more wires, a portable computer disk, a hard disk, a random access memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disk read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination thereof. In this document, a computer-readable storage medium may be any tangible medium containing or storing a program that may be used by or in conjunction with an instruction execution system, device, or device.

[0106] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. A rapid evaluation system for the working conditions of a spacecraft flight control process, characterized in that: include: Behavior prediction module, flight control important time design module, analysis module, acquisition module and fault diagnosis module; The behavior prediction module is used to: determine, according to the flight control requirements of the spacecraft to be evaluated, a plurality of key instructions corresponding to the flight control events corresponding to the flight control plan of the spacecraft to be evaluated, sort the plurality of key instructions to obtain a behavior sequence of the spacecraft to be evaluated, and issue key instructions to the spacecraft to be evaluated in sequence according to the behavior sequence; The flight control important time design module is used to: determine a plurality of evaluation parameters corresponding to the working condition event corresponding to the flight control file corresponding to the spacecraft to be evaluated according to the flight program of the spacecraft to be evaluated, and establish an instruction association set based on the plurality of evaluation parameters; The acquisition module is used to: acquire telemetry data of the spacecraft to be evaluated in response to the current key instructions in real time to generate an actual sequence; The analysis module is used to: calculate the similarity between the actual sequence and the behavior sequence by a fuzzy matching method, and determine whether the similarity is greater than a similarity threshold, and generate a first determination result; Determine the correlation between the telemetry parameter change amount in the actual sequence and the instruction correlation set by using the fuzzy hierarchical analysis method, and judge whether the correlation is greater than a correlation threshold value, and generate a second judgment result; When at least one of the first judgment result and the second judgment result is negative, generating fault information; The fault diagnosis module is used to determine the fault condition according to the fault information and the current key instruction.

2. A rapid evaluation system for operating conditions of a spacecraft flight control process according to claim 1, characterized in that: The actual sequence is determined by serializing and normalizing the telemetry parameters in sequence to obtain the actual sequence.

3. A rapid evaluation system for operating conditions of a spacecraft flight control process according to claim 1, characterized in that: The analysis module is also used for: When the first judgment result and the second judgment result are both yes, feedback information is sent to the behavior prediction module.

4. A rapid evaluation system for operating conditions of a spacecraft flight control process according to claim 3, characterized in that: The behavior prediction module is also used for: In response to the feedback information, new key instructions are issued to the spacecraft to be evaluated according to the behavior sequence.

5. A method for rapid evaluation of the working conditions of a spacecraft flight control process, characterized in that: include: The behavior prediction module determines, according to the flight control requirements of the spacecraft to be evaluated, a plurality of key instructions corresponding to the flight control events corresponding to the flight control plan of the spacecraft to be evaluated, sorts the plurality of key instructions to obtain a behavior sequence of the spacecraft to be evaluated, and issues key instructions to the spacecraft to be evaluated in sequence according to the behavior sequence; The flight control important time design module determines a plurality of evaluation parameters corresponding to the working condition events corresponding to the flight control file corresponding to the spacecraft to be evaluated according to the flight program of the spacecraft to be evaluated, and establishes an instruction association set based on the plurality of evaluation parameters; The acquisition module collects the telemetry data of the spacecraft to be evaluated in response to the current key instructions in real time and generates the actual sequence; The analysis module calculates the similarity between the actual sequence and the behavior sequence by a fuzzy matching method, and determines whether the similarity is greater than a similarity threshold, thereby generating a first determination result; Determine the correlation between the telemetry parameter change amount in the actual sequence and the instruction correlation set by using the fuzzy hierarchical analysis method, and judge whether the correlation is greater than a correlation threshold value, and generate a second judgment result; When at least one of the first judgment result and the second judgment result is negative, generating fault information; The fault diagnosis module determines the fault condition according to the fault information and the current key instruction.

6. A method for rapid evaluation of working conditions of a spacecraft flight control process according to claim 5, characterized in that: The actual sequence is determined by serializing and normalizing the telemetry parameters in sequence to obtain the actual sequence.

7. The method for rapid evaluation of working conditions of a spacecraft flight control process according to claim 5, characterized in that: Also includes: When the first judgment result and the second judgment result are both yes, feedback information is sent to the behavior prediction module.

8. A method for rapid evaluation of working conditions of a spacecraft flight control process according to claim 7, characterized in that: Also includes: In response to the feedback information, new key instructions are issued to the spacecraft to be evaluated according to the behavior sequence.

9. A computer device, characterized in that: The computer device comprises a processor, the processor is coupled to a memory, at least one computer program is stored in the memory, and the at least one computer program is loaded and executed by the processor so that the computer device implements the method according to any one of claims 5 to 8.

10. A computer-readable storage medium, characterized in that: The computer-readable storage medium stores at least one computer program, and the at least one computer program is loaded and executed by a processor to enable a computer to implement the method according to any one of claims 5 to 8.

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