CN112441259A - Method and device for judging delay transmission control effect of multiple spacecrafts - Google Patents
Method and device for judging delay transmission control effect of multiple spacecrafts Download PDFInfo
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Abstract
The invention provides a method and a device for judging the delayed transmission control effect of multiple spacecrafts, wherein the method comprises the following steps: generating a command data source code block from the received command, and sending the command data source code block and the command sending time information to a transmission target; starting multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information to obtain a first processing result; starting multi-instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information to obtain a second processing result; and comparing the first processing result with the second processing result to obtain a delay transmission control result. The method comprises three links, namely a delayed transmission instruction sending and processing link, a delayed transmission data analysis and comparison starting link and a multi-spacecraft cooperation comparison link. The three links realize the effect of effectively judging whether the spacecraft can normally receive the instruction and execute the instruction, and the process does not need manual intervention, thereby avoiding the generation of human errors and improving the comparison and judgment efficiency.
Description
Technical Field
The application belongs to the technical field of deep space exploration, and particularly relates to a method and a device for judging the delayed transmission control effect of multiple spacecrafts.
Background
In the multi-spacecraft control process, one survey station is generally adopted to implement command control on one spacecraft, and the command control of a plurality of spacecrafts is relatively independent. However, when the deep space exploration task or the measurement and control resources are in shortage, in order to save the ground measurement and control resources, the ground center realizes the multi-spacecraft control by a transmission command mode, namely: the ground sends an instruction to a certain spacecraft A through a survey station, and the instruction of another spacecraft B is sent to the spacecraft A from the ground and forwarded to the spacecraft B by the spacecraft A. The generation transmission command is divided into real time transmission and delay generation transmission, wherein the real time transmission and the delay generation transmission are adopted, and the spacecraft A immediately transmits to the spacecraft B after receiving the command; after receiving the instruction, the spacecraft A is switched to the spacecraft B at regular time according to the delay time. For the multi-spacecraft delay transmission instruction, how to judge the execution condition of the multi-spacecraft instruction is a relatively complex problem, and a multi-spacecraft delay transmission control effect judging method needs to be designed to realize accurate and comprehensive judgment of the instruction transmission process and result.
In the existing multi-spacecraft control process, an instruction forwarding control mode of a relay communication satellite is mostly adopted. In this control mode, the relay communication satellite is only a forwarding path of the instruction, the execution condition of the instruction is not judged, and the ground center only judges whether the target spacecraft normally receives the instruction and the final execution condition of the instruction. The ground center does not judge the relay satellite forwarding process, so that the conditions of instruction forwarding and execution cannot be comprehensively judged.
Disclosure of Invention
The application provides a method and a device for judging the delay transmission control effect of multiple spacecrafts, which at least solve the problem that the monitoring and judgment on the execution condition of the delay transmission instruction of the spacecrafts is lacked at present.
According to one aspect of the application, a method for judging the effect of multi-spacecraft delay transmission control is provided, which comprises the following steps:
generating a command data source code block by the received command, and sending the command data source code block and the command sending time information to the generation target so that the generation target generates an injection data source code block and delayed generation time information according to the command data source code block and the command sending time information;
starting multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information to obtain a first processing result;
starting multi-instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information to obtain a second processing result;
and comparing the first processing result with the second processing result to obtain a delay transmission control result.
In an embodiment, the starting of the multiple-instruction comparison processing according to the instruction data source code block and the instruction sending time information to obtain a first processing result includes:
analyzing the instruction data source code block to obtain a plurality of control instructions;
acquiring an execution criterion of each control instruction and calculating a first judgment time according to instruction sending time information;
and carrying out multi-instruction-ratio judgment processing according to the execution criterion and the first judgment moment to obtain a first processing result.
In an embodiment, the starting the multi-instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information to obtain a second processing result includes:
analyzing the injected data source code block to obtain a plurality of execution criteria of injected data;
calculating a second judgment time according to the time-delay transmission time information;
and starting multi-instruction-ratio judgment processing of the generation target according to the execution criterion of the injected data and the second judgment moment so that the generation target obtains a second processing result after executing the processing and returns the second processing result.
In one embodiment, the performing the multiple instruction ratio processing according to the execution criterion and the first judgment time to obtain the first processing result includes:
collecting telemetering data from a first judgment moment and executing a control instruction;
and acquiring telemetering data before and after the execution time, and performing comparison analysis to obtain a first processing result.
From the perspective of a generation target, the method is taken as an execution main body, and a method for judging the delayed generation control effect of the multi-spacecraft is also provided, and comprises the following steps:
generating an injected data source code block according to an instruction data source code block sent by a receiving target and transmitting the injected data source code block back to the receiving target;
and finishing the execution condition ratio judgment processing of the injected data source code block according to the multi-instruction ratio judgment processing starting information sent by the receiving target to obtain a second processing result and sending the second processing result to the receiving target.
In one embodiment, generating an injection data source code block according to an instruction data source code block sent by a receiving target and transmitting the injection data source code block back to the receiving target comprises:
packaging an external data frame structure on the basis of the instruction data source code block to form an injection data source code block with an extended time propagation moment;
the injected data source code blocks are transmitted back to the receiving destination.
In an embodiment, the performing case ratio judgment processing on the injected data source code block according to the multiple instruction ratio judgment processing start information sent by the receiving target to obtain a second processing result, and sending the second processing result to the receiving target includes:
collecting the telemetering data from the second judgment moment and comparing the execution condition of the injection data in the injection data source code block to obtain a second processing result;
and sending the second processing result to a receiving target.
According to another aspect of the present application, there is also provided a multi-spacecraft delay transmission control effect determination apparatus that takes a reception target as an execution subject, including:
the instruction data source code block generating unit is used for generating an instruction data source code block from the received instruction, and transmitting the instruction data source code block and the instruction transmitting time information to the transmission target so that the transmission target generates an injection data source code block and delayed transmission time information according to the instruction data source code block and the instruction transmitting time information;
the first processing result acquisition unit is used for starting multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information to acquire a first processing result;
the second processing result acquisition unit is used for starting multi-instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information to acquire a second processing result;
and the control result acquisition unit is used for comparing the first processing result with the second processing result to obtain a delay transmission control result.
In one embodiment, the first processing result obtaining unit includes:
the first analysis module is used for analyzing the instruction data source code block to obtain a plurality of control instructions;
the first calculation module is used for acquiring the execution criterion of each control instruction and calculating a first judgment moment according to the instruction sending moment information;
and the first comparison module is used for carrying out multi-instruction-ratio judgment processing according to the execution criterion and the first judgment moment to obtain a first processing result.
In one embodiment, the second processing result obtaining unit includes:
the second analysis module is used for analyzing the injected data source code block to obtain a plurality of execution criteria of the injected data;
the second calculation module is used for calculating a second judgment time according to the time-delay transmission time information;
and the second comparison module is used for starting multi-instruction-ratio judgment processing of the transmission target according to the execution criterion of the injected data and the second judgment moment so as to enable the transmission target to obtain a second processing result after executing the processing and return the second processing result.
In one embodiment, the first comparing module comprises:
the execution module is used for collecting the telemetering data from the first judgment moment and executing the control instruction;
and the comparison and judgment module is used for acquiring the telemetering data before and after the execution time, and performing comparison and judgment analysis to obtain a first processing result.
With a generation target (spacecraft) as an execution main body, the application also provides a multi-spacecraft delay generation control effect judgment device, which comprises:
the injected data source code block generating unit is used for generating an injected data source code block according to the instruction data source code block sent by the receiving target and transmitting the injected data source code block back to the receiving target;
and the second processing result acquisition unit is used for finishing the execution condition ratio judgment processing of the injected data source code block according to the multi-instruction ratio judgment processing starting information sent by the receiving target to obtain a second processing result and sending the second processing result to the receiving target.
In one embodiment, the injected data source code block generating unit includes:
the packaging module is used for packaging an external data frame structure on the basis of the instruction data source code block to form an injection data source code block with an extended propagation time;
and the back transmission module is used for transmitting the injected data source code block back to the receiving target.
In one embodiment, the second processing result obtaining unit includes:
the execution module is used for acquiring the telemetering data from the second judgment moment and comparing the execution condition of the injection data in the injection data source code block to obtain a second processing result;
and the sending module is used for sending the second processing result to a receiving target.
The method comprises three links, namely a delayed transmission instruction sending and processing link, a delayed transmission data analysis and comparison starting link and a multi-spacecraft cooperation comparison link. The three links realize the effect of effectively judging whether the spacecraft can normally receive the instruction and execute the instruction, and the process does not need manual intervention, thereby avoiding the generation of human errors and improving the comparison efficiency.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.
Fig. 1 is a schematic diagram of a multi-spacecraft time-lapse instruction comparison control mode provided by the present application.
Fig. 2 is a flowchart of a method for determining a multi-spacecraft delay transmission control effect with a receiving target as an execution subject according to the present application.
Fig. 3 is a flowchart of obtaining a first processing result in the embodiment of the present application.
Fig. 4 is a flowchart of obtaining a second processing result in the embodiment of the present application.
Fig. 5 is a flowchart illustrating a first processing result obtained by performing multi-instruction-ratio processing according to an execution criterion and a first determination time in the embodiment of the present application.
Fig. 6 is a flowchart of a multi-spacecraft delay transmission control effect determination method with a transmission target as an execution subject according to the present application.
Fig. 7 is a flow chart of the present application for generating an injected data source code block according to an instruction data source code block for transmission back to a receiving destination.
Fig. 8 is a flowchart illustrating the execution ratio decision processing performed on the injected data source code blocks according to the multiple instruction ratio decision processing start information in the embodiment of the present application.
Fig. 9 is a block diagram of a multi-spacecraft delay transmission control effect determination device with a reception target as an execution subject.
Fig. 10 is a block diagram of the structure of the first processing result acquisition unit.
Fig. 11 is a block diagram of the structure of the second processing result acquisition unit.
Fig. 12 is a block diagram of a first comparison module.
Fig. 13 is a block diagram of a multi-spacecraft delay transmission control effect determination device with a transmission target as an execution subject.
Fig. 14 is a block diagram showing the structure of an injection data source code block generation unit.
Fig. 15 is a block diagram of the structure of the second processing result acquisition unit.
Fig. 16 is a schematic view of a working flow of the multi-spacecraft delay transmission control effect determination system.
Fig. 17 is a specific implementation of an electronic device in an embodiment of the present application.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Based on the defects in the prior art related to the background art, the method for judging the delay transmission control effect of the multiple spacecrafts is provided, and therefore the method for comparing the instruction forwarding and execution results can achieve the accurate delay transmission instruction control process without manual operation.
As shown in fig. 1, a schematic diagram of a multi-spacecraft time-delay transmission instruction comparison control mode is shown, in which a spacecraft a and ground control software corresponding to the spacecraft a are taken as a whole, the executed role of the spacecraft a is a transmission target, a spacecraft B and the ground control software thereof are taken as a receiving target, and the spacecraft a is responsible for time-delay transmission of instructions to the spacecraft B.
With a spacecraft B (i.e., a receiving target) as an execution subject, the method for determining a multi-spacecraft delay transmission control effect provided by the present application, as shown in fig. 2, includes:
s201: and generating an instruction data source code block by the received instruction, and sending the instruction data source code block and the instruction sending time information to the generation target so that the generation target generates an injection data source code block and delayed generation time information according to the instruction data source code block and the instruction sending time information.
The time-delay transmission instruction sending processing method adopts the principle that who generates and sends instructions: and the spacecraft B control software generates a plurality of instruction data source code blocks C which need to be transmitted, and the data source code blocks C are attached with ground control software which prolongs the time transmission moment and then are transmitted to the spacecraft A. And after analyzing the external data frame structure, the spacecraft B forwards the instruction source code block to the spacecraft B for execution according to the time delay moment.
S202: and starting multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information to obtain a first processing result.
S203: and starting multi-instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information to obtain a second processing result.
When the ground control software of the spacecraft B sends out the instruction data source code block C, the data analysis module of the spacecraft B analyzes the instruction data source code block in real time, reversely decodes a plurality of control instructions, obtains the execution criterion of each control instruction, calculates the judgment time according to the time delay transmission time, and starts the multi-instruction ratio judgment processing of the spacecraft B; when spacecraft A ground control software sends a source code DC of the transmission injection data, an instruction sending module of a spacecraft B obtains execution criteria of the DC injection data, calculates judgment time according to real-time sending time, and starts specific judgment processing of the spacecraft A injection data.
S204: and comparing the first processing result with the second processing result to obtain a delay transmission control result.
After the time-delay transmission instruction is sent out, the spacecraft B ground control software finishes the execution condition comparison of the plurality of instructions C, uses the telemetering data downloaded by the spacecraft B, starts to acquire the telemetering data from the time-delay transmission time to perform the instruction execution condition comparison, and outputs the single-spacecraft comparison result of the spacecraft B instruction; the spacecraft A ground control software completes the execution condition comparison of the time-delay transmission injection data source code block DC, telemetering data downloaded by the spacecraft A is used, the telemetering data is collected from the moment when the injection data source code block DC sends out, and a single-spacecraft comparison result of a spacecraft A instruction is output; and collecting the comparison and judgment results of the two single spacecrafts by the ground control software of the spacecraft B, matching and analyzing the comparison and judgment results of the two spacecrafts according to the ID number sent by the instruction, and outputting the comprehensive comparison and judgment result. The comprehensive comparison result reflects the condition of the spacecraft A forwarding instruction and the execution result of the spacecraft B instruction. And collecting the comparison and judgment results of the two single spacecrafts by the ground control software of the spacecraft B, matching and analyzing the comparison and judgment results of the two spacecrafts according to the ID number sent by the instruction, and outputting the comprehensive comparison and judgment result. The comprehensive comparison result reflects the condition of the spacecraft A forwarding instruction and the execution result of the spacecraft B instruction.
In a specific embodiment, a plurality of instruction data source code blocks C to be transmitted are generated by spacecraft B control software, and transmission time information of a spacecraft B instruction is added to the instruction code as a time standard for subsequent instruction comparison. And the spacecraft B ground control software sends the framed spacecraft B data source code blocks to ground control software which replaces the target A (because the instruction of the spacecraft B needs to be forwarded by the spacecraft A, the instruction of the framed spacecraft B needs to be sent to the control software of the spacecraft A, and the control software of the spacecraft A carries out subsequent processing). Generally, instruction formats of different spacecrafts are different, so that after receiving a data source code block C sent by control software of a spacecraft B, control software of the spacecraft a needs to package the data source code C according to a remote control instruction sending format of the spacecraft a, wherein a delayed transmission moment is attached, and an instruction sending module of the control software of the spacecraft a sends an instruction to the spacecraft a.
In an embodiment, starting the multiple instruction comparison processing according to the instruction data source code block and the instruction sending time information to obtain the first processing result, as shown in fig. 3, the method includes:
s301: and analyzing the code block of the instruction data source to obtain a plurality of control instructions.
S302: and acquiring an execution criterion of each control instruction and calculating a first judgment time according to the instruction sending time information.
S303: and carrying out multi-instruction-ratio judgment processing according to the execution criterion and the first judgment moment to obtain a first processing result.
And when the ground control software of the spacecraft B sends out the instruction data source code block C, the data analysis module of the spacecraft B analyzes the instruction data source code block in real time, reversely decodes a plurality of control instructions, obtains the execution criterion of each control instruction, calculates the judgment time according to the time delay transmission time, and starts the multi-instruction ratio judgment processing of the spacecraft B.
In a specific embodiment, the spacecraft B extracts the spacecraft control information contained in the command, and prepares for obtaining the telemetry data comparison after the spacecraft B command is executed.
In an embodiment, the starting the multiple instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information to obtain the second processing result, as shown in fig. 4, includes:
s401: and analyzing the injected data source code block to obtain a plurality of execution criteria of the injected data.
S402: and calculating a second judgment time according to the time-delay transmission time information.
S403: and starting multi-instruction-ratio judgment processing of the generation target according to the execution criterion of the injected data and the second judgment moment so that the generation target obtains a second processing result after executing the processing and returns the second processing result.
When the spacecraft A ground control software sends the injection data source code block DC, an instruction sending module of the spacecraft B obtains an execution criterion of the injection data source code block DC, calculates a judgment moment according to a real-time sending moment, and starts the ratio judgment processing of the injection data of the spacecraft A.
In an embodiment, performing the multiple instruction ratio processing according to the execution criterion and the first determination time to obtain the first processing result, as shown in fig. 5, includes:
s501: and collecting telemetering data from the first judgment moment and executing a control command.
S502: and acquiring telemetering data before and after the execution time, and performing comparison analysis to obtain a first processing result.
In a specific embodiment, starting from the time of delayed transmission, the comparison and judgment software of the spacecraft B starts to collect the telemetering data of the spacecraft B, simultaneously obtains the execution criterion contained in the data block C, and carries out judgment analysis on the telemetering data before and after the instruction execution time of the spacecraft B to obtain the instruction execution comparison and judgment result of the spacecraft B.
From the perspective of a generation target, a method for judging the effect of multi-spacecraft delay generation control is also provided by taking the generation target as an execution main body, as shown in fig. 6, and comprises the following steps:
s601: and generating an injected data source code block according to the instruction data source code block sent by the receiving target and transmitting the injected data source code block back to the receiving target.
S602: and finishing the execution condition ratio judgment processing of the injected data source code block according to the multi-instruction ratio judgment processing starting information sent by the receiving target to obtain a second processing result and sending the second processing result to the receiving target.
In an embodiment, generating an injection data source code block according to an instruction data source code block sent by a receiving target and transmitting the injection data source code block back to the receiving target, as shown in fig. 7, includes:
s701: and packaging an external data frame structure on the basis of the instruction data source code block to form an injection data source code block with an extended time propagation moment.
S702: the injected data source code blocks are transmitted back to the receiving destination.
In a specific embodiment, after the spacecraft a control software receives the data source code block C sent by the spacecraft B control software, the data source code C needs to be encapsulated according to the remote control instruction sending format of the spacecraft a to form an injected data source code block DC, which is accompanied by a delayed transmission time. The method comprises the steps that firstly, a ground control software of the spacecraft A sends an instruction to a ground measurement and control station, then the instruction is sent to the spacecraft A through a measurement station communication device of the measurement and control station, in the process, transmission delay from a control center to the measurement station, measurement station processing delay and three-section delay from the measurement station to the spacecraft are included, then, when comprehensive comparison time scale processing is carried out, the time delay is accurately calculated, the judgment starting time is obtained, and the spacecraft A sends an injection data source code block DC to a spacecraft B.
In an embodiment, the performing ratio judgment processing on the injected data source code block is completed according to the multiple instruction ratio judgment processing start information sent by the receiving target, so as to obtain a second processing result, and send the second processing result to the receiving target, as shown in fig. 8, includes:
s801: and acquiring telemetry data from the second judgment moment, and comparing the execution condition of the injection data in the injection data source code block to obtain a second processing result.
S802: and sending the second processing result to a receiving target.
In a specific embodiment, the ground control software of the spacecraft a acquires the telemetric data from the time when the injection data DC is sent out by using the telemetric data downloaded by the spacecraft a, and outputs a single-spacecraft comparison result of the spacecraft a instruction. After receiving the target instruction, the spacecraft a can cache and analyze the outer layer format of the instruction code of the spacecraft a, and forward the effective instruction to the spacecraft B, wherein the time delay of the uplink code rate and the space distance of the spacecraft a needs to be considered in the process. The following can be divided: the method comprises the steps that a spacecraft A processes time delay, a spacecraft A forwards time delay and space communication distance time delay between the spacecraft A and a spacecraft B.
After the spacecraft A and the spacecraft B obtain respective comparison and judgment results, the ground control software of the spacecraft B collects the comparison and judgment results of the two single spacecrafts (A and B), and sends ID numbers according to the instructions to match and analyze the comparison and judgment results of the two spacecrafts and output a comprehensive comparison and judgment result. The comprehensive comparison result reflects the condition of the spacecraft A forwarding instruction and the execution result of the spacecraft B instruction.
Based on the same inventive concept, the embodiment of the present application further provides a device for determining a multi-spacecraft delay transmission control effect, which can be used to implement the method described in the above embodiments, as described in the following embodiments. Because the principle of solving the problems of the multi-spacecraft delay transmission control effect judgment device is similar to the multi-spacecraft delay transmission control effect judgment method, the implementation of the multi-spacecraft delay transmission control effect judgment device can refer to the implementation of the multi-spacecraft delay transmission control effect judgment method, and repeated parts are not repeated. As used hereinafter, the term "unit" or "module" may be a combination of software and/or hardware that implements a predetermined function. While the system described in the embodiments below is preferably implemented in software, implementations in hardware, or a combination of software and hardware are also possible and contemplated.
As shown in fig. 9, with the received target as the execution subject, the present application further provides a multi-spacecraft delay transmission control effect determination apparatus, including:
an instruction data source code block generating unit 901, configured to generate an instruction data source code block from a received instruction, and send the instruction data source code block and the instruction sending time information to a proxy target, so that the proxy target generates an injection data source code block and delayed proxy time information according to the instruction data source code block and the instruction sending time information;
a first processing result obtaining unit 902, configured to start multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information, and obtain a first processing result;
a second processing result obtaining unit 903, configured to start multi-instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information, and obtain a second processing result;
and a control result obtaining unit 904, configured to compare the first processing result with the second processing result to obtain a delay transmission control result.
In one embodiment, as shown in fig. 10, the first processing result obtaining unit 902 includes:
a first parsing module 1001, configured to parse the instruction data source code block to obtain multiple control instructions;
the first calculating module 1002 is configured to obtain an execution criterion of each control instruction and calculate a first judgment time according to instruction sending time information;
the first comparing module 1003 is configured to perform multi-instruction-ratio judging processing according to the execution criterion and the first judging time to obtain a first processing result.
In an embodiment, as shown in fig. 11, the second processing result obtaining unit 903 includes:
a second parsing module 1101 for parsing the code block of the injection data source to obtain a plurality of execution criteria of the injection data;
the second calculating module 1102 is configured to calculate a second judgment time according to the time-delay transmission time information;
the second comparison module 1103 is configured to start multi-instruction-ratio processing on the generation target according to the execution criterion of the injection data and the second judgment time, so that the generation target obtains a second processing result after executing the processing and returns the second processing result.
In one embodiment, as shown in fig. 12, the first comparing module 1003 includes:
the execution module 1201 is used for collecting the telemetering data from the first judgment moment and executing the control instruction;
and the comparison module 1202 is used for obtaining the telemetering data before and after the execution time, and performing comparison analysis to obtain a first processing result.
With the generation target as the execution main body, the present application further provides a multi-spacecraft delay generation control effect determination device, as shown in fig. 13, including:
an injection data source code block generation unit 1301, configured to generate an injection data source code block according to an instruction data source code block sent by a receiving target, and transmit the injection data source code block back to the receiving target;
the second processing result obtaining unit 1302 is configured to complete execution condition ratio judgment on the injected data source code block according to the multiple instruction ratio judgment start information sent by the receiving target, obtain a second processing result, and send the second processing result to the receiving target.
In an embodiment, as shown in fig. 14, the injection data source code block generation unit 1301 includes:
an encapsulating module 1401, configured to encapsulate an external data frame structure on the basis of an instruction data source code block to form an injection data source code block with an extended propagation time;
a back-transmission module 1402 for transmitting the source code block of the injected data back to the receiving destination.
In an embodiment, as shown in fig. 15, the second processing result obtaining unit 1302 includes:
the execution module 1501 is configured to start to acquire telemetry data from the second judgment time and compare execution conditions of injection data injected into the data source code block to obtain a second processing result;
a sending module 1502 is configured to send the second processing result to a receiving destination.
A schematic working flow diagram (including a spacecraft a and a spacecraft B) of the multi-spacecraft delay transmission control effect determination system provided by the present application is shown in fig. 16.
The method and the device provided by the application solve the problem that the delay generation control effect of multiple spacecrafts is difficult to judge, and the automatic comparison method also reduces the consumption of human resources, so that the method and the device can be applied to the delay generation comparison work in the aerospace flight control task.
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention 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, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. 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.
The principle and the implementation mode of the invention are explained by applying specific embodiments in the invention, and the description of the embodiments is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
An embodiment of the present application further provides a specific implementation manner of an electronic device, which is capable of implementing all steps in the method in the foregoing embodiment, and referring to fig. 17, the electronic device specifically includes the following contents:
a processor (processor)1701, memory 1702, communication Interface 1703, bus 1704, and nonvolatile memory 1705;
the processor 1701, the memory 1702 and the communication interface 1703 complete mutual communication through the bus 1704;
the processor 1701 is configured to call the computer programs in the memory 1702 and the nonvolatile memory 1705, and the processor implements all the steps of the method in the foregoing embodiments when executing the computer programs, for example, the processor implements the following steps when executing the computer programs:
generating a command data source code block by the received command, and sending the command data source code block and the command sending time information to the generation target so that the generation target generates an injection data source code block and delayed generation time information according to the command data source code block and the command sending time information;
starting multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information to obtain a first processing result;
starting multi-instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information to obtain a second processing result;
and comparing the first processing result with the second processing result to obtain a delay transmission control result.
Or
Generating an injected data source code block according to an instruction data source code block sent by a receiving target and transmitting the injected data source code block back to the receiving target;
and finishing the execution condition ratio judgment processing of the injected data source code block according to the multi-instruction ratio judgment processing starting information sent by the receiving target to obtain a second processing result and sending the second processing result to the receiving target.
Embodiments of the present application also provide a computer-readable storage medium capable of implementing all the steps of the method in the above embodiments, where the computer-readable storage medium stores thereon a computer program, and the computer program when executed by a processor implements all the steps of the method in the above embodiments, for example, the processor implements the following steps when executing the computer program:
generating a command data source code block by the received command, and sending the command data source code block and the command sending time information to the generation target so that the generation target generates an injection data source code block and delayed generation time information according to the command data source code block and the command sending time information;
starting multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information to obtain a first processing result;
starting multi-instruction comparison processing of the generation target according to the injected data source code block and the delayed generation time information to obtain a second processing result;
and comparing the first processing result with the second processing result to obtain a delay transmission control result.
Or
Generating an injected data source code block according to an instruction data source code block sent by a receiving target and transmitting the injected data source code block back to the receiving target;
and finishing the execution condition ratio judgment processing of the injected data source code block according to the multi-instruction ratio judgment processing starting information sent by the receiving target to obtain a second processing result and sending the second processing result to the receiving target.
The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for the hardware + program class embodiment, since it is substantially similar to the method embodiment, the description is simple, and the relevant points can be referred to the partial description of the method embodiment. Although embodiments of the present description provide method steps as described in embodiments or flowcharts, more or fewer steps may be included based on conventional or non-inventive means. The order of steps recited in the embodiments is merely one manner of performing the steps in a multitude of orders and does not represent the only order of execution. When an actual apparatus or end product executes, it may execute sequentially or in parallel (e.g., parallel processors or multi-threaded environments, or even distributed data processing environments) according to the method shown in the embodiment or the figures. The terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, the presence of additional identical or equivalent elements in a process, method, article, or apparatus that comprises the recited elements is not excluded. For convenience of description, the above devices are described as being divided into various modules by functions, and are described separately. Of course, in implementing the embodiments of the present description, the functions of each module may be implemented in one or more software and/or hardware, or a module implementing the same function may be implemented by a combination of multiple sub-modules or sub-units, and the like. The above-described embodiments of the apparatus are merely illustrative, and for example, the division of the units is only one logical division, and other divisions may be realized in practice, for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection through some interfaces, devices or units, and may be in an electrical, mechanical or other form. The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. 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.
As will be appreciated by one skilled in the art, embodiments of the present description may be provided as a method, system, or computer program product. Accordingly, embodiments of the present description may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, embodiments of the present description 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, CD-ROM, optical storage, and so forth) having computer-usable program code embodied therein. The embodiments in the present specification are described in a progressive manner, and the same and similar parts among the embodiments are referred to each other, and each embodiment focuses on the differences from the other embodiments. In particular, for the system embodiment, since it is substantially similar to the method embodiment, the description is simple, and for the relevant points, reference may be made to the partial description of the method embodiment. In the description herein, references to the description of the term "one embodiment," "some embodiments," "an example," "a specific example," or "some examples," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of an embodiment of the specification.
In this specification, the schematic representations of the terms used above are not necessarily intended to refer to the same embodiment or example. Furthermore, various embodiments or examples and features of different embodiments or examples described in this specification can be combined and combined by one skilled in the art without contradiction. The above description is only an example of the embodiments of the present disclosure, and is not intended to limit the embodiments of the present disclosure. Various modifications and variations to the embodiments described herein will be apparent to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the embodiments of the present specification should be included in the scope of the claims of the embodiments of the present specification.
Claims (10)
1. A method for judging the delayed transmission control effect of multiple spacecrafts is characterized by comprising the following steps:
generating a command data source code block by using a received command, and sending the command data source code block and command sending time information to a generation target so that the generation target generates an injection data source code block and delayed generation time information according to the command data source code block and the command sending time information;
starting multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information to obtain a first processing result;
starting multi-instruction comparison processing of a generation target according to the injected data source code block and the time-delay transmission time information to obtain a second processing result;
and comparing the first processing result with the second processing result to obtain a delay transmission control result.
2. The method for judging the effect of multi-spacecraft delayed propagation control according to claim 1, wherein the starting of the multi-instruction comparison processing according to the instruction data source code block and the instruction transmission time information to obtain a first processing result includes:
analyzing the instruction data source code block to obtain a plurality of control instructions;
acquiring an execution criterion of each control instruction and calculating a first judgment time according to the instruction sending time information;
and carrying out multi-instruction-ratio judgment processing according to the execution criterion and the first judgment moment to obtain a first processing result.
3. The method for determining the effect of multi-spacecraft delayed propagation control according to claim 1, wherein the starting of the multi-instruction comparison processing of the propagation target according to the injected data source code block and the delayed propagation time information to obtain a second processing result includes:
analyzing the injected data source code block to obtain a plurality of execution criteria of injected data;
calculating a second judgment time according to the time-lapse transmission time information;
and starting multi-instruction-ratio judging processing of the generation target according to the execution criterion of the injected data and the second judgment moment so that the generation target obtains a second processing result after executing the processing and returns the second processing result.
4. The method for judging the effect of multi-spacecraft delayed flight control according to claim 2, wherein the performing the multi-instruction-ratio judging process according to the execution criterion and the first judgment time to obtain the first processing result comprises:
collecting telemetering data from the first judgment moment and executing a control instruction;
and acquiring telemetering data before and after the execution time, and performing comparison analysis to obtain a first processing result.
5. A method for judging the delayed transmission control effect of multiple spacecrafts is characterized by comprising the following steps:
generating an injected data source code block according to an instruction data source code block sent by a receiving target and transmitting the injected data source code block back to the receiving target;
and finishing the execution condition ratio judgment processing of the injected data source code block according to the multi-instruction ratio judgment processing starting information sent by the receiving target to obtain a second processing result and sending the second processing result to the receiving target.
6. The method for determining the effect of multi-spacecraft delay-triggered transmission control according to claim 5, wherein generating the injected data source code blocks according to the command data source code blocks sent by the receiving target and transmitting the injected data source code blocks back to the receiving target includes:
packaging an external data frame structure on the basis of the instruction data source code block to form the injection data source code block with an extended propagation time;
and transmitting the injected data source code blocks back to a receiving target.
7. The method for judging the effect of multi-spacecraft delay surrogate control according to claim 5, wherein the performing condition ratio judgment processing on the injected data source code block according to the multiple instruction ratio judgment processing start information sent by the receiving target to obtain a second processing result and send the second processing result to the receiving target includes:
collecting the telemetering data from the second judgment moment and comparing the execution condition of the injection data in the injection data source code block to obtain a second processing result;
and sending the second processing result to a receiving target.
8. A multi-spacecraft delay transmission control effect judgment device is characterized by comprising:
the instruction data source code block generating unit is used for generating an instruction data source code block from a received instruction, and sending the instruction data source code block and the instruction sending time information to a transmission target so that the transmission target generates an injection data source code block and delayed transmission time information according to the instruction data source code block and the instruction sending time information;
a first processing result obtaining unit, configured to start multi-instruction comparison processing according to the instruction data source code block and the instruction sending time information, and obtain a first processing result;
a second processing result obtaining unit, configured to start multi-instruction comparison processing of a generation target according to the injected data source code block and the time-lapse transmission time information, and obtain a second processing result;
and the control result acquisition unit is used for comparing the first processing result with the second processing result to obtain a delay transmission control result.
9. A multi-spacecraft delay transmission control effect judgment device is characterized by comprising:
the injected data source code block generating unit is used for generating an injected data source code block according to the instruction data source code block sent by the receiving target and transmitting the injected data source code block back to the receiving target;
and the second processing result acquisition unit is used for finishing the execution condition ratio judgment processing on the injected data source code block according to the multi-instruction ratio judgment processing starting information sent by the receiving target to obtain a second processing result and sending the second processing result to the receiving target.
10. An electronic device comprising a memory, a processor and a computer program stored in the memory and executable on the processor, wherein the processor executes the program to implement the method for determining the effect of delayed multi-spacecraft substitutive control according to any one of claims 1 to 4 and 5 to 7.
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