CN117725461A - Spacecraft telemetry data fault autonomous processing method, device and storage medium - Google Patents
Spacecraft telemetry data fault autonomous processing method, device and storage medium Download PDFInfo
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Abstract
The invention relates to the field of spacecraft information design, in particular to a method and a device for autonomous processing of spacecraft telemetry data faults and a storage medium. After the method receives telemetry data, judging whether the current power-on state is normal or not, and executing a first fault processing strategy when the power-on state is abnormal; when the power-up state is normal, acquiring the type of the normal current power-up state and judging whether the current working state is normal, if so, not performing fault processing, and judging whether the power-up state is normal again, if not, executing a second fault processing strategy or a third fault processing strategy based on the type of the normal current power-up state; the three fault processing strategies comprise a power-on and power-off instruction sending and a measurement and control area judging and sending instruction. Compared with the prior art, the method has the advantages of improving the instantaneity, the accuracy and the processing efficiency of the on-orbit fault processing of the telemetry data of the spacecraft, ensuring that the real-time telemetry in the measurement and control area is continuous in downlink, preventing the telemetry from being lost for a long time when the measurement and control area is extended, and the like.
Description
Technical Field
The invention relates to the field of spacecraft information design, in particular to a method and a device for autonomous processing of spacecraft telemetry data faults and a storage medium.
Background
Telemetry data is a direct reflection of the on-orbit running state of the spacecraft and is mainly divided into two types, namely platform telemetry and load telemetry. The on-orbit management of the telemetry data is mainly realized by a central computer of the spacecraft and mainly comprises the functions of receiving, multiplexing and storing the telemetry data. When the spacecraft is in the measurement and control visible arc section, the computer transmits telemetry data to the downlink ground of the measurement and control subsystem; when the spacecraft observes and controls invisible arc segments, the computer stores telemetry data into the nonvolatile memory as time delay telemetry, and returns and downloads after entering the observation and control area. In the prior art, the monitoring and fault processing of the telemetry data can be realized manually by using the ground, but the instantaneity, the accuracy and the processing efficiency of the fault processing are all to be improved.
As shown in fig. 1, the central computer of the telemetry data processing system of the spacecraft mainly comprises a central processing unit (Central Processing Unit, CPU) module and a storage multiplexing module. The CPU module runs computer application software and system software, exchanges information with external bus terminal equipment through a 1553B bus, receives telemetry data of the bus terminal equipment and control instructions sent by the ground, and sends the telemetry data and the control instructions to the storage multiplexing module to control the operation of the storage multiplexing module; the storage multiplexing module adopts a dual-machine cold backup design, defaults to be in a main power-on state, runs storage multiplexing FPGA software on the storage multiplexing module, realizes the receiving, formatting and partition storage of multi-channel telemetry data according to an advanced on-orbit system (Advanced Orbiting Systems, AOS) protocol, completes data framing multiplexing according to a control instruction of the CPU module, and then stores the telemetry data into a nonvolatile memory or downloads the telemetry data to the ground in real time through an antenna-ground link of a measurement and control subsystem. It can be seen that the storage multiplexing module of the central computer is a key module for spacecraft telemetry data processing.
Because measurement and control resources are limited, if the operation of the storage multiplexing module is abnormal when the measurement and control are in the visible arc section during the task period, the real-time telemetry can not be carried out; if the storage multiplexing module works abnormally when the measurement and control is in the invisible arc section, the risk of losing the delay telemetry for a long time exists. Therefore, how to perform fault discovery and processing of telemetry data based on the working condition of the storage multiplexing module, so as to avoid that real-time telemetry data cannot be downlink or delay telemetry data is lost, and the problem to be solved in the field is solved.
Disclosure of Invention
The invention aims to overcome the defects of low instantaneity, low accuracy and low processing efficiency of telemetry data fault processing in the prior art, and provides a spacecraft telemetry data fault autonomous processing method, a spacecraft telemetry data fault autonomous processing device and a storage medium.
The aim of the invention can be achieved by the following technical scheme:
according to a first aspect of the present invention, there is provided a spacecraft telemetry data fault autonomous processing method comprising the steps of:
s1, receiving telemetry data, and judging whether the current power-on state is normal or not based on the telemetry data: if yes, acquiring the type of the current power-on state which is normal and executing S2, and if not, executing a first fault processing strategy;
s2, judging whether the current working state is normal or not: if yes, not performing fault processing, returning to the step S1, and if not, executing a second fault processing strategy or a third fault processing strategy based on the type of the current power-on state which is normal;
the first fault processing strategy, the second fault processing strategy and the third fault processing strategy all comprise a power-on and power-off instruction sending and a measurement and control area judging instruction sending.
As an optimal technical scheme, the judging and issuing condition of the command entering the measurement and control area is related to the state of the measurement and control arc section.
The process of judging whether the current working state is normal or not includes detecting and judging whether the task receiving count and the task sending count are equal or not, if yes, the working state is normal, and if no, the working state is abnormal.
As an optimal technical scheme, the normal power-on state type comprises single main power-on and single backup power-on, and the abnormal power-on state type is that the main backup power-on is all powered on.
As a preferable technical solution, executing the second fault handling policy or the third fault handling policy based on the type of the current normal power-up state includes executing the second fault handling policy when the power-up state is an independent power-up of the primary power-up; and executing a third fault handling strategy when the power-up state is independent backup power-up.
As an optimal technical scheme, the second fault processing strategy comprises the steps of judging whether the abnormal times of the current working state are smaller than or equal to two times, if so, sending second power-on and power-off instructions at intervals and judging to send measurement and control area instructions, otherwise, not performing fault processing.
As an preferable technical scheme, the third fault processing strategy includes judging whether the current working state is abnormal for the first time, if so, sending a third power-on and power-off instruction at intervals and judging to send a measurement and control area instruction, otherwise, not performing fault processing.
As a preferred technical solution, the first fault handling policy includes determining whether a current power-up state is a first exception: if yes, a first power-on and power-off instruction is sent at intervals, and the instruction of the measurement and control area is judged, otherwise, fault processing is not carried out.
According to a second aspect of the present invention, there is provided an autonomous processing device for telemetry data failure of a spacecraft, applied to a storage multiplexing module, said device comprising a data receiving and transmitting module, a power-on state and operating state judging module, and a failure handling policy executing module, said data receiving and transmitting module being in signal connection with said power-on state and operating state judging module, said power-on state and operating state judging module being in signal connection with said failure handling policy executing module,
the data receiving and transmitting module is used for receiving telemetry data and transmitting the telemetry data to the power-on state and working state judging module;
the power-on state and working state judging module is used for judging whether the current power-on state and the current working state of the storage multiplexing module are normal or not: when the current power-on state is abnormal, a first execution signal is sent; when the current power-up state is normal, acquiring the normal type of the current power-up state and judging whether the current working state is normal, if the current working state is normal, not performing fault processing, and judging whether the current power-up state of the storage multiplexing module is normal again, and if the current working state is abnormal, transmitting a second execution signal or a third execution signal based on the normal type of the current power-up state;
the fault processing strategy executing module is used for receiving the first executing signal, the second executing signal and the third executing signal and respectively controlling and executing a first fault processing strategy, a second fault processing strategy and a third fault processing strategy;
the first fault processing strategy, the second fault processing strategy and the third fault processing strategy all comprise a power-on and power-off instruction sending and a measurement and control area judging and sending instruction.
According to a third aspect of the present invention, there is provided a storage medium having stored thereon a program which when executed implements the method.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the method, whether the telemetry data of the storage multiplexing module have faults or not is judged according to the power-on state and the working state of the storage multiplexing module by establishing the connection between the power-on state and the working state of the storage multiplexing module;
2. the fault processing strategy adopted by the invention comprises the power-on and power-off instruction and the instruction entering the measurement and control area, and judges whether the instruction entering the measurement and control area is sent or not according to the state of the measurement and control arc section, on one hand, the real-time telemetry data in the measurement and control area can be ensured to be continuous in downlink, and meanwhile, the long-time loss caused by the overlong storage time of the delayed telemetry data outside the measurement and control area is avoided, on the other hand, unnecessary instructions are properly reduced, and the fault processing efficiency is further improved.
Drawings
FIG. 1 is a general structural schematic diagram of a spacecraft telemetry data processing system;
FIG. 2 is a schematic flow chart of the method of the present invention;
FIG. 3 is a schematic flow chart of the method of the present invention.
Detailed Description
The invention will now be described in detail with reference to the drawings and specific examples. The present embodiment is implemented on the premise of the technical scheme of the present invention, and a detailed implementation manner and a specific operation process are given, but the protection scope of the present invention is not limited to the following examples. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated.
Examples
As shown in fig. 2, the embodiment provides a method for autonomous processing of telemetry data faults of a spacecraft, which comprises the following steps:
step S1, telemetry data is received, and whether the current power-on state is normal or not is judged based on the telemetry data: if yes, acquiring the type of the current power-on state which is normal and executing S2, and if not, executing a first fault processing strategy;
step S2, judging whether the current working state is normal or not: if yes, the fault processing is not carried out, and the S1 is returned, if not, the second fault processing strategy or the third fault processing strategy is executed based on the type of the normal current power-on state.
As shown in fig. 3, the implementation flow of the method is as follows:
when step S1 is implemented, telemetry data is received, and it is determined, based on the telemetry data, what kind of power-on state the storage multiplexing module is in, that is, whether the power-on state is normal or abnormal. The method comprises the steps of powering up an independent main part and powering up an independent backup, wherein the type of abnormal power-up state is that the main backup is powered up. In practical applications, the single master power-up state is the most preferred power-up state for a spacecraft telemetry data processing system.
When step S2 is implemented, firstly, because the device or system applying the method of the embodiment and the FPGA of the storage multiplexing module will always perform data communication under normal conditions, whether the current working state of the storage multiplexing module is normal can be determined by detecting whether the task receiving count of the FPGA in the storage multiplexing module is equal to the task sending count of the software. When the task receiving count is not equal to the task sending count, the current working state of the storage multiplexing module is abnormal, and when the task receiving count is equal to the task sending count, the current working state of the storage multiplexing module is normal. Secondly, when the working state of the storage multiplexing module is normal, fault processing is not carried out, the step S1 is returned, and whether the power-on state is normal or not is judged again; and when the working state of the storage multiplexing module is abnormal, executing a second fault processing strategy or a third fault processing strategy based on the type of the normal current power-on state. Specifically, when the power-up state is the independent power-up of the master, executing a second fault handling policy; and executing a third fault handling strategy when the power-up state is independent backup power-up.
The first fault treatment strategy, the second fault treatment strategy and the third fault treatment strategy all comprise sending an on-off instruction and an on-measurement and control area instruction, the judging and issuing condition of the on-measurement and control area instruction is related to the state of the measurement and control arc section, and the state of the measurement and control arc section comprises the position in the measurement and control area and the position outside the measurement and control area. The reason is that in the fault processing process of the telemetry data of the spacecraft, the telemetry download function of the storage multiplexing module is closely related to the state of the measurement and control arc section of the spacecraft. If the storage multiplexing module is in the measurement and control area before abnormal operation, sending a command of entering the measurement and control area, and if the storage multiplexing module is out of the measurement and control area before abnormal operation, not sending the command.
Through the step S1 and the step S2, the connection between the power-on state and the working state of the storage multiplexing module is established, and through the detection and judgment of the two states, the step S1 and the step S2 can be repeatedly executed, so that the fault autonomous processing of the storage multiplexing module is realized according to a fixed period, and the processing strategies comprise three conditions, namely a first fault processing strategy, a second fault processing strategy and a third fault processing strategy.
The second fault handling strategy is a master fault autonomous handling strategy, and three specific handling modes exist in the strategy:
(1) When the working state of the master copy of the storage multiplexing module is judged to be abnormal for the 1 st time: sending second power-on and power-off instructions at intervals, namely sequentially sending instructions of powering off the main part of the storage multiplexing module and powering on the main part of the storage multiplexing module according to a certain time interval, and judging and sending an instruction of entering a measurement and control area after the instructions are executed normally;
(2) When the working state of the main part of the storage multiplexing module is abnormal in the 2 nd judgment: the second power-on and power-off instruction is sent at intervals, namely, the 'power-off of the main part of the storage multiplexing module' and the 'power-on and backup of the storage multiplexing module' instruction are sequentially sent at certain time intervals, and the 'measurement and control area entering' instruction is judged after the instruction is executed normally;
(3) If the failure of the master is judged to be more than 2 times, the failure autonomous processing is not performed.
The third failure handling policy is a backup failure autonomous handling policy, and there are two specific handling modes for this policy:
(1) When the 1 st time judges that the backup working state of the storage multiplexing module is abnormal: sending third power-on and power-off instructions at intervals, namely sequentially sending instructions of 'backup power-off of a storage multiplexing module' and 'backup power-on of the storage multiplexing module' according to a certain time interval, and judging to send an instruction of 'entering a measurement and control area' after the instructions are executed normally;
(2) If the backup fault is judged to be more than 1 time, the fault autonomous treatment is not carried out.
The first failure handling policy is a primary backup failure autonomous handling policy, and there are two specific handling modes for this policy:
(1) If the primary backup fault is detected for the 1 st time, namely the power-on state is abnormal, a first power-on and power-off instruction is sent at intervals, namely the instructions of powering off the primary part of the storage multiplexing module, powering off the backup of the storage multiplexing module and powering on the primary part of the storage multiplexing module are sequentially sent at certain time intervals, and after the instructions are executed normally, the instructions of entering a measurement and control area are judged;
(2) If the primary backup fault is detected to be more than 1 time, the software does not conduct fault autonomous treatment any more.
Further, when the number of times of judging various faults exceeds a certain threshold, the method can be combined with a ground manual detection and fault processing mode so as to further improve reliability of spacecraft telemetry data fault processing.
Further, the embodiment also provides a device for autonomous processing of remote measurement data faults of the spacecraft, which is applied to a storage multiplexing module, and comprises a data receiving and transmitting module, a power-on state and working state judging module and a fault processing strategy executing module, wherein the data receiving and transmitting module is in signal connection with the power-on state and working state judging module, and the power-on state and working state judging module is in signal connection with the fault processing strategy executing module.
The data receiving and transmitting module is used for receiving the telemetry data and transmitting the telemetry data to the power-on state and working state judging module; the power-on state and working state judging module is used for judging whether the current power-on state and the current working state of the storage multiplexing module are normal or not: when the current power-on state is abnormal, a first execution signal is sent; when the current power-up state is normal, acquiring the normal type of the current power-up state and judging whether the current working state is normal, if the current working state is normal, not performing fault processing, and judging whether the current power-up state of the storage multiplexing module is normal again, and if the current working state is abnormal, transmitting a second execution signal or a third execution signal based on the normal type of the current power-up state; the fault processing strategy executing module is used for receiving a first executing signal, a second executing signal and a third executing signal, wherein the first executing signal is used for controlling the execution of the first fault processing strategy, the second executing signal is used for controlling the execution of the second fault processing strategy, and the third executing signal is used for controlling the execution of the third fault processing strategy. The first fault handling policy, the second fault handling policy, and the third fault handling policy all include a power-on/power-off instruction and a measurement and control area judging instruction, and specific handling manners of the three fault handling policies may refer to the foregoing corresponding processes in the embodiment, which are not described herein again.
Further, the present embodiment also provides a storage medium having a program stored thereon, which when executed implements the foregoing method. Program code for carrying out methods of the present invention may be written in any combination of one or more programming languages. These program code may be provided to a processor or controller of a general purpose computer, special purpose computer, or other programmable data processing apparatus such that the program code, when executed by the processor or controller, causes the functions/operations specified in the flowchart and/or block diagram to be implemented. The program code may execute entirely on the machine, partly on the machine, as a stand-alone software package, partly on the machine and partly on a remote machine or entirely on the remote machine or server. In the context of the present invention, a computer-readable medium may be a tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device. The machine-readable medium may be a machine-readable signal medium or a machine-readable storage medium. The machine-readable medium may include, but is not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any suitable combination of the foregoing. More specific examples of a machine-readable storage medium would include an electrical connection based on one or more wires, a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing.
The foregoing describes in detail preferred embodiments of the present invention. It should be understood that numerous modifications and variations can be made in accordance with the concepts of the invention by one of ordinary skill in the art without undue burden. Therefore, all technical solutions which can be obtained by logic analysis, reasoning or limited experiments based on the prior art by the person skilled in the art according to the inventive concept shall be within the scope of protection defined by the claims.
Claims (10)
1. The autonomous processing method for the telemetry data faults of the spacecraft is characterized by comprising the following steps of:
s1, receiving telemetry data, and judging whether the current power-on state is normal or not based on the telemetry data: if yes, acquiring the type of the current power-on state which is normal and executing S2, and if not, executing a first fault processing strategy;
s2, judging whether the current working state is normal or not: if yes, not performing fault processing, returning to the step S1, and if not, executing a second fault processing strategy or a third fault processing strategy based on the type of the current power-on state which is normal;
the first fault processing strategy, the second fault processing strategy and the third fault processing strategy all comprise a power-on and power-off instruction sending and a measurement and control area judging instruction sending.
2. The autonomous processing method of spacecraft telemetry data faults according to claim 1, wherein the judging and issuing condition of the command entering the measurement and control area is related to the state of the measurement and control arc section.
3. The autonomous processing method for spacecraft telemetry data fault according to claim 1, wherein the process of judging whether the current working state is normal comprises detecting and judging whether a task receiving count and a task sending count are equal, if yes, the working state is normal, and if no, the working state is abnormal.
4. The spacecraft telemetry data fault autonomous processing method of claim 1, wherein the type of power-up state exception is a primary backup power-up, and wherein the type of power-up state exception is a primary backup power-up.
5. The method of claim 4, wherein executing the second or third fault handling policy based on the type of current normal power-up state comprises executing the second fault handling policy when the power-up state is an independent power-up of the master; and executing a third fault handling strategy when the power-up state is independent backup power-up.
6. The autonomous processing method of spacecraft telemetry data fault according to claim 1, wherein the second fault processing strategy comprises judging whether the current abnormal times of the working state are less than or equal to two times, if yes, sending second power-on and power-off instructions at intervals and judging to send the instructions into the measurement and control area, otherwise, not performing fault processing.
7. The autonomous processing method of spacecraft telemetry data fault according to claim 1, wherein the third fault processing strategy comprises determining whether the current working state is first abnormal, if so, sending third power-on and power-off instructions at intervals and determining to send the instructions into the measurement and control area, otherwise, not performing fault processing.
8. The spacecraft telemetry data fault autonomous processing method of claim 1, wherein said first fault handling strategy comprises determining if a current power-up state is a first anomaly: if yes, a first power-on and power-off instruction is sent at intervals, and the instruction of the measurement and control area is judged, otherwise, fault processing is not carried out.
9. The device is applied to a storage multiplexing module and is characterized by comprising a data receiving and transmitting module, a power-on state and working state judging module and a fault processing strategy executing module, wherein the data receiving and transmitting module is in signal connection with the power-on state and working state judging module, the power-on state and working state judging module is in signal connection with the fault processing strategy executing module,
the data receiving and transmitting module is used for receiving telemetry data and transmitting the telemetry data to the power-on state and working state judging module;
the power-on state and working state judging module is used for judging whether the current power-on state and the current working state of the storage multiplexing module are normal or not: when the current power-on state is abnormal, a first execution signal is sent; when the current power-up state is normal, acquiring the normal type of the current power-up state and judging whether the current working state is normal, if the current working state is normal, not performing fault processing, and judging whether the current power-up state of the storage multiplexing module is normal again, and if the current working state is abnormal, transmitting a second execution signal or a third execution signal based on the normal type of the current power-up state;
the fault processing strategy executing module is used for receiving the first executing signal, the second executing signal and the third executing signal and respectively controlling and executing a first fault processing strategy, a second fault processing strategy and a third fault processing strategy;
the first fault processing strategy, the second fault processing strategy and the third fault processing strategy all comprise a power-on and power-off instruction sending and a measurement and control area judging and sending instruction.
10. A storage medium having a program stored thereon, wherein the program, when executed, implements the method of any of claims 1-8.
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