CN112650198B - Multi-spacecraft injection plan automatic generation and control method and device - Google Patents
Multi-spacecraft injection plan automatic generation and control method and device Download PDFInfo
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- CN112650198B CN112650198B CN202011516658.XA CN202011516658A CN112650198B CN 112650198 B CN112650198 B CN 112650198B CN 202011516658 A CN202011516658 A CN 202011516658A CN 112650198 B CN112650198 B CN 112650198B
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- G05B23/00—Testing or monitoring of control systems or parts thereof
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- G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
- G05B23/0218—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults
- G05B23/0256—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterised by the fault detection method dealing with either existing or incipient faults injecting test signals and analyzing monitored process response, e.g. injecting the test signal while interrupting the normal operation of the monitored system; superimposing the test signal onto a control signal during normal operation of the monitored system
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Abstract
A method and a device for automatically generating and controlling a multi-spacecraft injection plan are provided. The method comprises the following steps: obtaining a program control instruction to be sent according to the obtained program control instruction plan, and decomposing the program control instruction into injection data according to the maximum length of a data area of single-frame injection data and the length of a single program control instruction; generating an injection plan according to preset spacecraft control conditions; when the injection data generation time arrives, acquiring external parameters of the injection data, and generating a source code file and an injection data file; analyzing the source code file to obtain an external parameter value and an external parameter source, obtaining an original parameter value according to the external parameter source, and if the external parameter value is consistent with the original parameter value, sending the injection data file to the spacecraft when the injection data sending moment is reached. The invention eliminates the link of manual intervention, ensures that the control process of the injection data is more reliable, improves the generation efficiency of the injection data, ensures the correctness of the whole flow of the injection data, and further improves the control efficiency of the spacecraft.
Description
Technical Field
The invention relates to the technical field of spacecraft control, in particular to a method and a device for automatically generating and controlling a multi-spacecraft injection plan.
Background
The ground needs to control the spacecraft by sending injection data. In the multi-spacecraft control process, the injected data contains more instructions and has complex logic relation. Efficient generation of injection data, transmission timing determination, content inspection, and transmission control require a large amount of manpower.
In the control process of some spacecrafts, an instruction plan to be injected is generated on the ground, meanwhile, the name of injection data is arranged in a remote control instruction plan, injection data is generated through manual operation, the correctness of the injection data is checked manually, an injection data file contains multi-frame data, and the injection data is sent to the spacecrafts frame by frame. In the implementation process of the method, the command to be injected and the plan for transmitting injection data on the ground are independently arranged, and the consistency is difficult to ensure. Meanwhile, the method needs a large amount of manual operation and check rechecking work, and the implementation efficiency is low. Because the work of generating and checking the injection data is completed manually, the workload of manual operation is large, and the efficiency is low. Meanwhile, the real-time states of the measurement and control link and the spacecraft are not introduced into the control loop in the injection data sending process, so that the situation that the injection data of a certain frame fails to be sent cannot be adapted.
In addition, in some spacecraft control processes, injection data planning and generation are handled by an operation and management center, and injection data transmission and implementation are handled by a measurement and control center. In the mode, the injection data planning design and implementation processes are relatively independent, the implementation difficulty is low, and the implementation efficiency is also low. When the injection data is planned and adjusted, the transmission of related injection data and other unrelated instructions is suspended, the influence range is large, and the flexibility is low. In the scheme, two important links of injection data planning generation and transmission implementation are independent and disjointed, and the latter can carry out design and arrangement work only after the former is finished, so the implementation efficiency is low. Meanwhile, when the injected data control content is adjusted, other unrelated instructions in the instruction sending implementation stage also need to be paused, and the flexibility is low.
Disclosure of Invention
The embodiment of the invention mainly aims to provide a method and a device for automatically generating and controlling an injection plan of multiple spacecrafts, so as to realize the automatic generation and sending control of a large amount of injection data of the multiple spacecrafts.
In order to achieve the above object, an embodiment of the present invention provides a method for automatically generating and controlling a multi-spacecraft injection plan, where the method includes:
obtaining a program control instruction to be sent according to the obtained program control instruction plan, and decomposing the program control instruction into injection data according to the maximum length of a data area of single-frame injection data and the length of a single program control instruction;
generating an injection plan according to preset spacecraft control conditions; the injection plan comprises injection data generation time and injection data sending time;
when the injection data generation moment arrives, acquiring external parameters of injection data, and generating a source code file and an injection data file by using the injection data and the external parameters of the injection data;
analyzing the source code file to obtain an external parameter value and an external parameter source, obtaining an original parameter value according to the external parameter source, and if the external parameter value is consistent with the original parameter value, successfully checking the injected data;
and when the injection data sending time arrives, sending the injection data file with successful check to the spacecraft.
Optionally, in an embodiment of the present invention, decomposing the program control instruction into the injection data according to the maximum length of the injection data frame and the length of the single program control instruction includes: calculating the number of program control instructions which can be accommodated in the data area of the single-frame injection data according to the maximum length of the data area of the single-frame injection data and the length of a single program control instruction; and decomposing the program control command into injection data according to the number of the program control commands.
Optionally, in an embodiment of the present invention, the method further includes: naming the injection data according to the effect of the injection data to classify the injection data.
Optionally, in an embodiment of the present invention, the sending the injection data file successfully checked to the spacecraft includes: transmitting the injection data file with successful check to the spacecraft according to a frame-by-frame transmission mode; if the fact that the transmission of the injection data of the ith frame fails is known, repeated transmission is carried out for preset times; if the ith frame of injection data is successfully sent after repeated sending for the preset times, sending the (i + 1) th frame of injection data to the spacecraft; wherein i is a positive integer.
The embodiment of the invention also provides a device for automatically generating and controlling the injection plan of the multi-spacecraft, which comprises:
the instruction decomposition module is used for obtaining a program control instruction to be sent according to the obtained program control instruction plan and decomposing the program control instruction into injection data according to the maximum length of a data area of single-frame injection data and the length of a single program control instruction;
the plan generating module is used for generating an injection plan according to preset spacecraft control conditions; the injection plan comprises injection data generation time and injection data sending time;
the file generation module is used for acquiring external parameters of the injection data when the injection data generation moment arrives, and generating a source code file and an injection data file by using the injection data and the external parameters of the injection data;
the data checking module is used for analyzing the source code file to obtain an external parameter value and an external parameter source, obtaining an original parameter value according to the external parameter source, and if the external parameter value is consistent with the original parameter value, successfully checking the injected data;
and the data sending module is used for sending the injection data file with successful check to the spacecraft when the injection data sending time arrives.
Optionally, in an embodiment of the present invention, the instruction decomposition module includes: the instruction number unit is used for calculating the number of program control instructions which can be accommodated in the data area of the single-frame injection data according to the maximum length of the data area of the single-frame injection data and the length of a single program control instruction; and the instruction decomposition unit is used for decomposing the program control instructions into injection data according to the number of the program control instructions.
Optionally, in an embodiment of the present invention, the apparatus further includes: and the data naming module is used for naming the injection data according to the action of the injection data so as to classify the injection data.
Optionally, in an embodiment of the present invention, the data sending module is further configured to: transmitting the injection data file with successful check to the spacecraft according to a frame-by-frame transmission mode; if the fact that the transmission of the injection data of the ith frame fails is known, repeated transmission is carried out for preset times; if the ith frame of injection data is successfully sent after repeated sending for the preset times, sending the (i + 1) th frame of injection data to the spacecraft; wherein i is a positive integer.
The invention also provides an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor implements the method when executing the program.
The present invention also provides a computer-readable storage medium storing a computer program for executing the above method.
According to the invention, through the automatic generation of the injection plan and the injection data of the spacecraft and the automatic check and check, the link of manual intervention is eliminated, so that the control process of the injection data is more reliable, the consistency and correctness check of the whole processing process of the injection data are realized, the generation efficiency of the injection data is improved, the correctness of the whole flow of the injection data is ensured, and the control efficiency of the spacecraft is improved.
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 will be briefly introduced below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained based on these drawings without creative efforts.
FIG. 1 is a flow chart of a method for automatic generation and control of a multi-spacecraft injection plan in accordance with an embodiment of the present invention;
FIG. 2 is a flowchart illustrating program control instruction decomposition according to an embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a multi-spacecraft injection plan automatic generation and control system in accordance with an embodiment of the present invention;
fig. 4 is a schematic structural diagram of an apparatus for automatically generating and controlling a multi-spacecraft injection plan according to an embodiment of the present invention;
FIG. 5 is a block diagram of an instruction decomposition module according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of an electronic device according to an embodiment of the present invention.
Detailed Description
The embodiment of the invention provides a method and a device for automatically generating and controlling a multi-spacecraft injection plan.
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.
The execution subject of the multi-spacecraft injection plan automatic generation and control method provided by the embodiment of the invention comprises but is not limited to a computer. Fig. 1 is a flowchart of a method for automatically generating and controlling an injection plan of multiple spacecrafts according to an embodiment of the present invention, where the method includes:
and step S1, obtaining a program control instruction to be sent according to the obtained program control instruction plan, and decomposing the program control instruction into injection data according to the maximum length of the data area of the single-frame injection data and the length of the single program control instruction.
The program control command plan includes all program control commands to be injected and sent to the spacecraft and execution time of the commands. And extracting a required program control instruction list in the program control instruction plan, calculating the number of program control instructions which can be contained in the single-frame injection data according to the maximum length of the data area of the single-frame injection data and the length of the single program control instruction, and decomposing the program control instructions into the injection data. Specifically, after the number of the program control instructions exceeds the single-frame injection data accommodation capacity, an injection data file is newly created, and the program control instructions are continuously added.
Step S2, generating an injection plan according to preset spacecraft control conditions; the injection plan includes an injection data generation time and an injection data transmission time.
According to the requirements of spacecraft control conditions, namely the transmission time of the injection data is earlier than the earliest execution time of the frame program control instruction minus the transmission time cost, and the transmission time is later than the observation station double-capturing time. The injection data transmission time is defined as Ts, the program control command execution time is defined as T1, T2 and T3 … … Tn, the injection data transmission time takes Δ Ts, and the station double-capturing time Tb is defined as:
Ts<min(T1,T2,T3,…,Tn)-△Ts
Ts>Tb
before the injection data is sent, the generation, the inspection and the check of the injection data need to be completed, the time when the generation of the injection data is started is defined as Tc, the time length of the generation, the inspection and the check of the injection data is defined as Deltatc, namely:
Tc<Ts-△Tc。
after the framing, naming and time constraint calculation of the injection data are finished, the working time of the command sending test station is superposed, the generation of the injection data and the calculation of the sending time are finished, and an injection plan is automatically generated.
And step S3, when the injection data generation time arrives, acquiring external parameters of the injection data, and generating a source code file and an injection data file by using the injection data and the external parameters of the injection data.
After the injection plan is generated, execution is started according to the planned time. And when the injection data generation moment is reached, automatically collecting external parameter data such as control parameter files, form filling information, program control instruction plans and the like according to a preset parameter input list required by the injection data. Generating a source code file and an injection data file by using the injection data and external parameters thereof, and simultaneously storing external parameter values and external parameter sources corresponding to the source code file, wherein the external parameter sources comprise: control parameter file name, program control command plan file name and form filling source.
And step S4, analyzing the source code file to obtain an external parameter value and an external parameter source, obtaining an original parameter value according to the external parameter source, and if the external parameter value is consistent with the original parameter value, successfully checking the injected data.
After the injection data file is generated, the source code file of the injection data is subjected to inverse solution. The source code is analyzed into an injection instruction (program control instruction), an external parameter value and an external parameter source, and the correctness of the length, the structure and the checksum of the injected data source code is checked. After the source code inverse decoding is completed, according to the external parameter source, extracting the original control parameter file, the table filling information and the program control instruction plan file, and searching the most original external parameter and the external parameter in the source code inverse decoding result to compare one by one, namely comparing the original parameter value with the external parameter value, so as to check the consistency of the initial input of the injection data and the final result.
And step S5, when the injection data sending time arrives, sending the injection data file with successful check to the spacecraft.
After the injection data are generated and checked, the injection data are sent to the spacecraft in real time through the ground survey station according to the injection data sending time of the injection plan. Furthermore, in the automatic injection data sending process, the injection data transmission state and the spacecraft execution state are judged in real time.
As an embodiment of the present invention, as shown in fig. 2, decomposing the program control instruction into injection data according to the maximum length of the injection data frame and the length of a single program control instruction includes:
and step S21, calculating the number of program control instructions which can be accommodated in the data area of the single frame injection data according to the maximum length of the data area of the single frame injection data and the length of the single program control instruction.
The method comprises the steps of collecting frame structure components and length parameters of each program control command, accumulating the length parameters of the frame structures in real time, and calculating the data length of each program control command according to the program control command frame structure provided by a spacecraft development department and the frame structure components and length parameters of each program control command which are bound in advance. Binding the maximum length of a data area of an injection data structure of each spacecraft in advance according to the injection data structure provided by a spacecraft development department, and calculating the maximum length of the data area of single-frame injection data according to the spacecraft to which a program control instruction belongs. Sequencing all program control instructions according to the execution time of the program control instructions, then placing the program control instructions in a data area in sequence, and calculating the number of the program control instructions which can be contained in single-frame injection data according to the principle that the total length of the program control instructions contained in the data area injected into the data structure is less than or equal to the maximum length of the data area injected into the data structure.
And step S22, decomposing the program control command into injection data according to the number of the program control commands.
Specifically, after the number of the program control commands exceeds the single-frame injection data accommodation capacity, an injection data file is newly created, and the program control commands are continuously added.
As an embodiment of the invention, the method further comprises: naming the injection data according to the effect of the injection data to classify the injection data.
After the program control command is decomposed into the injection data, the injection data are automatically and uniquely named, and the naming needs to contain the injection data function, so that the injection data are classified. Each type of injected data adopts a special identifier word, such as: ZRGX, ZRSC, etc., the classification count sets a unique number.
As an embodiment of the present invention, the sending the injection data file successfully checked to the spacecraft includes: transmitting the injection data file with successful check to the spacecraft according to a frame-by-frame transmission mode; if the fact that the transmission of the injection data of the ith frame fails is known, repeated transmission is carried out for preset times; if the ith frame of injection data is successfully sent after repeated sending for the preset times, sending the (i + 1) th frame of injection data to the spacecraft; wherein i is a positive integer.
In the process of transmitting multi-frame injection data, recording the transmission frame number i as 1, setting the retransmission times as M, and judging the transmission execution condition of the injection data according to the feedback state of the measurement and control network and the telemetering state of the spacecraft. And if the i-th frame injection data is judged to be transmitted or failed, automatically retransmitting the current frame injection data, reducing the retransmission times m by one, stopping the injection data transmission flow when m is 0, and exiting the processing. And if the transmission of the injected data of the ith frame is judged to be successful, setting the transmission frame number i to be increased by one, setting the retransmission time number M to be M, and starting the transmission processing of the injected data of the next frame. And returning to the injection data sending success state until all the frames of the injection data are sent.
In a specific embodiment of the present invention, as shown in fig. 3, a schematic structural diagram of a multi-spacecraft injection plan automatic generation and control system applying the multi-spacecraft injection plan automatic generation and control method of the present invention is shown, and a work flow of the system shown in the drawing includes: the automatic generation of an injection plan, the automatic generation and checking of injection data driven by the injection plan and the automatic sending of multi-frame injection data are realized based on a program control instruction plan, and the feedback states of a measurement and control network and a spacecraft are realized.
As shown by the mark 1 in fig. 3, the program control instruction extraction module reads the program control instruction plan to obtain 300 program control instructions sent this time. The instruction length calculation decomposition module calculates the data length of each program control instruction to be L1 and L2 … … L300 respectively, and the calculation method comprises the following steps: and accumulating the length parameters of the frame structure in real time according to the frame structure of the program control instruction provided by the spacecraft development department and the frame structure composition and the length parameters of each program control instruction bound in advance. Calculating the maximum length Lmax of a data area of single frame injection data, wherein the calculation method comprises the following steps: binding the maximum length of a data area of an injection data structure of each spacecraft in advance according to the injection data structure provided by a spacecraft development department, and calculating the maximum length Lmax of the data area of single-frame injection data according to the spacecraft to which a program control instruction belongs. The program control command is decomposed according to the maximum length of the data area, and the data is injected into 16 frames to complete the injection of all the program control commands.
The external input conditions required by the injection data generation are combed by the injection generation condition creation module according to the data requirements required to be generated in the control processes of spacecraft platform switch control, orbit maneuver control, load test control and the like, and the external input conditions comprise: program-controlled command planning, track control parameter files F1, F2, F3, table filling parameters P1, P2 and P3; this injection data name ZRGX08 and ZRSC09 is defined by the injection file map naming module pair by the content classification of the injection data.
In this embodiment, the transmission time of the injected data is earlier than the earliest execution time of the frame of program control instruction minus the transmission time cost, and the transmission time is later than the two-station capturing time of the observation station, where the earliest execution time of the frame of program control instruction is the execution time of the first program control instruction in the frame of data; the sending time cost depends on the spacecraft equipment characteristics and is a pre-bound value; the double-capturing time of the measuring station comes from an externally input measurement and control network tracking plan. Injection data transmission time Ts, program control command execution time 2020-01-01T01:00:00.6000 and 2020-01-01T01:00:05.0000 … … respectively, injection data transmission time is 0.3s, station double-capturing time Tb is 2020-01-01T00:20:00.0000, namely:
Ts<2020-01-01T01:00:00.3000
Ts>2020-01-01T00:20:00.0000
before injection data is sent, injection data generation, check and check need to be completed, injection data generation starting time Tc is defined, and injection data generation, check and check time length is 1.6s, namely:
Tc<Ts-1.6s。
during the work time of the superposition transmission command survey station, the injection time calculation module calculates the injection data file generation time Tc of 2020-01-01T00:10:00.0000, the transmission start time Ts of 2020-01-01T00:20:05.0000, the injection plan generation module automatically generates an injection plan rpzr.
As shown in fig. 3, at time Tc, the injection generation condition preparation module starts to collect injection data conditions, including external parameter data such as various plans and inputs, and sends the data to the injection data framing generation module through the message interface for framing data, and records the parameter values Vs1, Vs2 and Vs3 … …, and identifies the sources as F1, F2, F3, P1, P2, P3, etc. The method comprises the steps that an injection data source code file is sent to an injection data back calculation module, and external parameter values and sources are sent to an injection data checking module; the data to be injected are reversely calculated by the data to be injected back to obtain external parameter values Vf1, Vf2 and Vf3 … …, and the external parameter values Vy1, y2 and Vy3 … … are submitted to the data to be injected checking module, the data to be injected checking module collects the original parameter values Vy1, y2 and Vy3 … … according to parameter sources, and the original parameter values are compared with the parameter values Vs1, Vs2 and Vs3 … … generated by the data to be injected file and the reversely solved external parameter values Vf1, Vf2 and Vf3 … …, so that the consistency of the parameter values of each link is ensured, and the correctness of the data to be injected generation processing process and the data content is ensured. And if the checking is successful, the data is sent to an injection data sending module of the injection generation condition preparation module, otherwise, the subsequent processing flow is interrupted, and the checking error information is output.
After the injection data is generated and checked, the injection data is transmitted to the spacecraft in real time by the injection data transmitting module according to the transmission starting time 2020-01-01T00:20:05.0000 through the ground survey station, as shown by the mark 6 in fig. 3. In the process of transmitting multi-frame injection data, the injection data transmitting module completes data transmission of a first frame, records that when a transmission frame number i is 1, the retransmission times are set to be m 3, and the transmission state judging module judges the injection data transmission execution condition according to the feedback state of the measurement and control network and the spacecraft telemetry state, as shown in an identifier 4 and an identifier 5 in fig. 3. And if the transmission or failure of the injection data of the ith frame is judged, automatically retransmitting the injection data of the current frame, wherein the retransmission time m is 2, stopping the injection data transmission flow when m is 0, and exiting the processing. If the 1 st frame injection data is judged to be successfully transmitted, the transmission frame number i is set to be 2, the retransmission time number m is set to be 3, and the transmission processing of the 2 nd frame injection data is started. And returning to the injection data sending success state when the injection data 16 frame is sent completely.
The invention can realize the automatic generation of the multi-spacecraft injection plan and eliminate the link of manual intervention. All the generation, checking and sending moments of the injection data can be determined in advance, so that the control process of the injection data is more reliable. The automation of the generation, the inspection and the check of the injection data is realized through the injection plan drive, the consistency and the correctness inspection of the whole process from the data source acquisition, the injection data framing, the injection data inverse solution to the final result output of the injection data are realized, the injection data generation efficiency is improved, and the correctness of the whole flow of the injection data is ensured. By adopting the state-based multi-frame injection data sending method, the automatic traversal sending of the multi-frame injection data is realized, and the efficiency of the implementation of the injection data sending is improved. Particularly, automatic complementary distribution of injection data under the abnormal conditions of data transmission and spacecraft execution is realized, and the integrity of injection data transmission under the emergency condition is improved.
Fig. 4 is a schematic structural diagram of an apparatus for automatically generating and controlling a multi-spacecraft injection plan according to an embodiment of the present invention, where the apparatus includes:
the instruction decomposition module 10 is configured to obtain a program control instruction to be sent according to the obtained program control instruction plan, and decompose the program control instruction into injection data according to the maximum length of the data area of single-frame injection data and the length of a single program control instruction;
a plan generating module 20, configured to generate an injection plan according to preset spacecraft control conditions; the injection plan comprises injection data generation time and injection data sending time;
the file generation module 30 is configured to acquire external parameters of the injection data when the injection data generation time arrives, and generate a source code file and an injection data file by using the injection data and the external parameters of the injection data;
the data checking module 40 is configured to analyze the source code file to obtain an external parameter value and an external parameter source, obtain an original parameter value according to the external parameter source, and if it is known that the external parameter value is consistent with the original parameter value, successfully check the injected data;
and the data sending module 50 is configured to send the injection data file with the successful verification to the spacecraft when the injection data sending time arrives.
As an embodiment of the present invention, as shown in fig. 5, the instruction decomposition module includes:
the instruction number unit is used for calculating the number of program control instructions which can be accommodated in the data area of the single-frame injection data according to the maximum length of the data area of the single-frame injection data and the length of a single program control instruction;
and the instruction decomposition unit is used for decomposing the program control instructions into injection data according to the number of the program control instructions.
As an embodiment of the present invention, the apparatus further comprises: and the data naming module is used for naming the injection data according to the action of the injection data so as to classify the injection data.
As an embodiment of the present invention, the data sending module is further configured to: transmitting the injection data file with successful check to the spacecraft according to a frame-by-frame transmission mode; if the fact that the transmission of the injection data of the ith frame fails is known, repeated transmission is carried out for preset times; if the ith frame of injection data is successfully sent after repeated sending for the preset times, sending the (i + 1) th frame of injection data to the spacecraft; wherein i is a positive integer.
Based on the same application concept as the multi-spacecraft injection plan automatic generation and control method, the invention also provides the multi-spacecraft injection plan automatic generation and control device. Because the principle of solving the problems of the multi-spacecraft injection plan automatic generation and control device is similar to the multi-spacecraft injection plan automatic generation and control method, the implementation of the multi-spacecraft injection plan automatic generation and control device can refer to the implementation of the multi-spacecraft injection plan automatic generation and control method, and repeated parts are not repeated.
According to the invention, through the automatic generation of the injection plan and the injection data of the spacecraft and the automatic check and check, the link of manual intervention is eliminated, so that the control process of the injection data is more reliable, the consistency and correctness check of the whole processing process of the injection data are realized, the generation efficiency of the injection data is improved, the correctness of the whole flow of the injection data is ensured, and the control efficiency of the spacecraft is improved.
The invention also provides an electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor implements the method when executing the program.
The present invention also provides a computer-readable storage medium storing a computer program for executing the above method.
As shown in fig. 6, the electronic device 600 may further include: communication module 110, input unit 120, audio processing unit 130, display 160, power supply 170. It is worthy to note that electronic device 600 also does not necessarily include all of the components shown in FIG. 6; furthermore, the electronic device 600 may also comprise components not shown in fig. 6, which may be referred to in the prior art.
As shown in fig. 6, the central processor 100, sometimes referred to as a controller or operational control, may include a microprocessor or other processor device and/or logic device, the central processor 100 receiving input and controlling the operation of the various components of the electronic device 600.
The memory 140 may be, for example, one or more of a buffer, a flash memory, a hard drive, a removable media, a volatile memory, a non-volatile memory, or other suitable device. The information relating to the failure may be stored, and a program for executing the information may be stored. And the cpu 100 may execute the program stored in the memory 140 to realize information storage or processing, etc.
The input unit 120 provides input to the cpu 100. The input unit 120 is, for example, a key or a touch input device. The power supply 170 is used to provide power to the electronic device 600. The display 160 is used for displaying display objects such as images and characters. The display may be, for example, an LCD display, but is not limited thereto.
The memory 140 may be a solid state memory such as Read Only Memory (ROM), Random Access Memory (RAM), a SIM card, or the like. There may also be a memory that holds information even when power is off, can be selectively erased, and is provided with more data, an example of which is sometimes called an EPROM or the like. The memory 140 may also be some other type of device. Memory 140 includes buffer memory 141 (sometimes referred to as a buffer). The memory 140 may include an application/function storage section 142, and the application/function storage section 142 is used to store application programs and function programs or a flow for executing the operation of the electronic device 600 by the central processing unit 100.
The memory 140 may also include a data store 143 for storing data, such as contacts, digital data, pictures, sounds, and/or any other data used by the electronic device. The driver storage portion 144 of the memory 140 may include various drivers of the electronic device for a communication function and/or for performing other functions of the electronic device (e.g., a messaging application, a directory application, etc.).
The communication module 110 is a transmitter/receiver 110 that transmits and receives signals via an antenna 111. The communication module (transmitter/receiver) 110 is coupled to the central processor 100 to provide an input signal and receive an output signal, which may be the same as in the case of a conventional mobile communication terminal.
Based on different communication technologies, a plurality of communication modules 110, such as a cellular network module, a bluetooth module, and/or a wireless local area network module, etc., may be provided in the same electronic device. The communication module (transmitter/receiver) 110 is also coupled to a speaker 131 and a microphone 132 via an audio processor 130 to provide audio output via the speaker 131 and receive audio input from the microphone 132 to implement general telecommunications functions. Audio processor 130 may include any suitable buffers, decoders, amplifiers and so forth. In addition, an audio processor 130 is also coupled to the central processor 100, so that recording on the local can be enabled through a microphone 132, and so that sound stored on the local can be played through a speaker 131.
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.
Claims (6)
1. A method for automatic generation and control of a multi-spacecraft injection plan, the method comprising:
obtaining a program control instruction to be sent according to the obtained program control instruction plan, and decomposing the program control instruction into injection data according to the maximum length of a data area of single-frame injection data and the length of a single program control instruction;
generating an injection plan according to preset spacecraft control conditions; the injection plan comprises injection data generation time and injection data sending time;
when the injection data generation moment arrives, acquiring external parameters of injection data, and generating a source code file and an injection data file by using the injection data and the external parameters of the injection data;
analyzing the source code file to obtain an external parameter value and an external parameter source, obtaining an original parameter value according to the external parameter source, and if the external parameter value is consistent with the original parameter value, successfully checking the injected data;
when the injection data sending time arrives, sending the injection data file with successful check to the spacecraft;
decomposing the program control instruction into the injection data according to the maximum length of the injection data frame and the length of the single program control instruction comprises:
determining the length of a single program control instruction according to a frame structure and length parameters corresponding to the program control instruction to be sent;
determining the maximum length of an injection data frame according to a spacecraft injection data structure corresponding to a program control instruction to be sent;
sequencing the program control instructions according to the execution time of the program control instructions, placing the program control instructions into a data area according to the sequencing of the program control instructions, and calculating the number of the program control instructions which can be accommodated in the data area of single-frame injection data according to the preset requirement that the total length of the program control instructions accommodated in the data area of the injection data structure is less than or equal to the maximum length of the data area of the injection data structure and the maximum length of a single program control instruction;
decomposing the program control command into injection data according to the number of the program control commands;
wherein, the step of sending the injection data file successfully checked to the spacecraft comprises the following steps: transmitting the injection data file with successful check to the spacecraft according to a frame-by-frame transmission mode; if the fact that the transmission of the injection data of the ith frame fails is known, repeated transmission is carried out for preset times; if the ith frame of injection data is successfully sent after repeated sending for the preset times, sending the (i + 1) th frame of injection data to the spacecraft; wherein i is a positive integer;
the preset spacecraft control conditions comprise that the injection data sending time is earlier than the earliest execution time of the frame program control instruction and minus the sending time cost, and the injection data sending time is later than the observation station double-capture time;
generating the injection plan according to the preset spacecraft control condition further comprises generating the injection plan according to the preset spacecraft control condition by using the following formula:
Ts<min(T1,T2,T3,…,Tn)-△Ts，Ts>Tb；
Tc<Ts-△Tc；
wherein Ts is injection data sending time, T1, T2 and T3 … … Tn are program control instruction execution time, Δ Ts is injection data sending time cost, Tb is station survey double-capturing time, Tc is injection data generation time, and Δ Tc is injection data generation, inspection and check time length.
2. The method of claim 1, further comprising: naming the injection data according to the effect of the injection data to classify the injection data.
3. A multi-spacecraft injection plan automatic generation and control apparatus, the apparatus comprising:
the instruction decomposition module is used for obtaining a program control instruction to be sent according to the obtained program control instruction plan and decomposing the program control instruction into injection data according to the maximum length of a data area of single-frame injection data and the length of a single program control instruction;
the plan generating module is used for generating an injection plan according to preset spacecraft control conditions; the injection plan comprises injection data generation time and injection data sending time;
the file generation module is used for acquiring external parameters of the injection data when the injection data generation moment arrives, and generating a source code file and an injection data file by using the injection data and the external parameters of the injection data;
the data checking module is used for analyzing the source code file to obtain an external parameter value and an external parameter source, obtaining an original parameter value according to the external parameter source, and if the external parameter value is consistent with the original parameter value, successfully checking the injected data;
the data sending module is used for sending the injection data file with successful check to the spacecraft when the injection data sending time arrives;
wherein the instruction decomposition module comprises:
the instruction number unit is used for determining the length of a single program control instruction according to a frame structure and length parameters corresponding to the program control instruction to be sent; determining the maximum length of an injection data frame according to a spacecraft injection data structure corresponding to a program control instruction to be sent; sequencing the program control instructions according to the execution time of the program control instructions, placing the program control instructions into a data area according to the sequencing of the program control instructions, and calculating the number of the program control instructions which can be accommodated in the data area of single-frame injection data according to the preset requirement that the total length of the program control instructions accommodated in the data area of the injection data structure is less than or equal to the maximum length of the data area of the injection data structure and the maximum length of a single program control instruction;
the instruction decomposition unit is used for decomposing the program control instructions into injection data according to the number of the program control instructions;
wherein the data sending module is further configured to: transmitting the injection data file with successful check to the spacecraft according to a frame-by-frame transmission mode; if the fact that the transmission of the injection data of the ith frame fails is known, repeated transmission is carried out for preset times; if the ith frame of injection data is successfully sent after repeated sending for the preset times, sending the (i + 1) th frame of injection data to the spacecraft; wherein i is a positive integer;
the preset spacecraft control conditions comprise that the injection data sending time is earlier than the earliest execution time of the frame program control instruction and minus the sending time cost, and the injection data sending time is later than the observation station double-capture time;
generating the injection plan according to the preset spacecraft control condition further comprises generating the injection plan according to the preset spacecraft control condition by using the following formula:
Ts<min(T1,T2,T3,…,Tn)-△Ts，Ts>Tb；
Tc<Ts-△Tc；
wherein Ts is injection data sending time, T1, T2 and T3 … … Tn are program control instruction execution time, Δ Ts is injection data sending time cost, Tb is station survey double-capturing time, Tc is injection data generation time, and Δ Tc is injection data generation, inspection and check time length.
4. The apparatus of claim 3, further comprising: and the data naming module is used for naming the injection data according to the action of the injection data so as to classify the injection data.
5. An electronic device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor implements the method of any of claims 1 to 2 when executing the program.
6. A computer-readable storage medium, characterized in that the computer-readable storage medium stores a computer program for executing the method of any one of claims 1 to 2.
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| CN114285916B (en) * | 2021-12-23 | 2023-09-01 | 北京航天飞行控制中心 | Method and device for generating delay injection data based on framing identification |
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