CN111552584A - Test system, method and device for primary fault diagnosis isolation and recovery functions of satellite - Google Patents
Test system, method and device for primary fault diagnosis isolation and recovery functions of satellite Download PDFInfo
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- G06F11/0736—Error or fault processing not based on redundancy, i.e. by taking additional measures to deal with the error or fault not making use of redundancy in operation, in hardware, or in data representation the processing taking place on a specific hardware platform or in a specific software environment in functional embedded systems, i.e. in a data processing system designed as a combination of hardware and software dedicated to performing a certain function
- G06F11/0739—Error or fault processing not based on redundancy, i.e. by taking additional measures to deal with the error or fault not making use of redundancy in operation, in hardware, or in data representation the processing taking place on a specific hardware platform or in a specific software environment in functional embedded systems, i.e. in a data processing system designed as a combination of hardware and software dedicated to performing a certain function in a data processing system embedded in automotive or aircraft systems
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Abstract
The application discloses a test system, a method and a device for a primary fault diagnosis isolation and recovery function of a satellite, wherein the system comprises: the 1553B bus system comprises a bus control terminal on a satellite and at least one remote terminal, and is used for realizing data transmission between the bus control terminal and the at least one remote terminal through a 1553B bus; the bus terminal simulator is connected with the 1553B bus system and used for simulating fault excitation so as to inject fault information into the 1553B bus system; and the ground computer equipment is connected with the bus control terminal and used for carrying out data interaction with the bus control terminal and detecting the fault diagnosis isolation and recovery functions according to the interaction data. The method and the device solve the technical problem that the accuracy of the verification fault diagnosis and recovery function is poor in the prior art.
Description
Technical Field
The application relates to the technical field of spacecraft testing, in particular to a testing system with functions of primary fault diagnosis, isolation and recovery of a satellite.
Background
In order to automate and intelligentize satellite management, more and more satellites detect faults of the whole satellite in real time through fault diagnosis isolation and recovery functions, locate the faults and ensure safe and reliable operation of the satellite through measures such as reconstruction and the like, and the functions become indispensable contents of domestic and foreign spacecrafts. The fault diagnosis isolation and restoration function refers to a function of detecting a fault condition on a satellite, isolating the faulty subsystem or component, and restoring the faulty subsystem or component. There are various types of failures on the satellite, and the failures are classified according to the characteristics of the satellite failures, for example, the failures are classified into primary failures, secondary failures, tertiary failures, and the like. A brief description of the primary fault follows.
The primary satellite fault refers to a primary fault occurring in an internal module of a satellite component, but the autonomous recovery cannot be realized by the component level, and the detection and the recovery of the fault need to be realized by On-Board Controller (OBC) application software. In order to enable the satellite to operate normally, after a primary fault of the satellite occurs, the system performs autonomous fault isolation and Recovery according to a fault detection, isolation and Recovery (FDIR) strategy. In order to ensure that the satellite can be isolated and recovered from the autonomous fault when the satellite fails, the correctness of the logic function of the FDIR strategy needs to be verified. At present, when the FDIR policy logic function is verified, the detection of the fault isolation and recovery function may be performed when the satellite normally operates, that is, there is no fault, so that the result of verifying the FDIR processing logic is inaccurate.
Disclosure of Invention
The technical problem that this application was solved is: in the scheme provided by the embodiment of the application, fault equipment is injected into the whole satellite of the satellite, and logic or a method of fault detection and recovery functions is verified under the fault, so that the fault diagnosis and recovery functions are detected under the whole satellite; the fault diagnosis and recovery function can be detected under the condition that a fault exists, and the accuracy of a detection result is improved.
In a first aspect, an embodiment of the present application provides a test system for a satellite primary fault diagnosis isolation and recovery function, where the system includes:
the 1553B bus system comprises a bus control terminal on a satellite and at least one remote terminal, and is used for realizing data transmission between the bus control terminal and the at least one remote terminal through a 1553B bus;
the bus terminal simulator is connected with the 1553B bus system and used for simulating fault excitation so as to inject fault information into the 1553B bus system;
and the ground computer equipment is connected with the bus control terminal and used for carrying out data interaction with the bus control terminal and detecting the fault diagnosis isolation and recovery functions according to the interaction data.
According to the scheme provided by the embodiment of the application, a primary fault terminal on a satellite is simulated through a bus terminal simulator, the bus terminal simulator is connected to a 1553B bus system of the satellite, namely fault equipment is arranged in the satellite, then the bus control terminal operates the fault diagnosis and recovery function of the fault equipment according to fault information of the fault equipment, the bus control terminal sends data of the fault equipment to ground computer equipment, and the ground computer equipment detects the fault diagnosis isolation and recovery function according to the data sent by the bus control terminal. Therefore, in the scheme provided by the embodiment of the application, by injecting fault equipment into the whole satellite of the satellite and verifying the logic or method of fault detection and recovery function under the fault, the detection of the fault diagnosis and repair function under the whole satellite is realized; the fault diagnosis and recovery function can be detected under the condition that a fault exists, and the accuracy of a detection result is improved.
Optionally, the at least one remote terminal comprises: the system comprises a power supply control terminal, a load service terminal and a platform service terminal.
Optionally, the bus termination simulator is specifically configured to: and simulating a remote terminal with a fault in the 1553B bus system.
Optionally, the bus termination simulator is specifically configured to: and adjusting the module working zone bit of the bus terminal simulator to be a fault according to the received fault control instruction to obtain the remote terminal with the fault.
In a second aspect, the present application provides a method for testing a primary fault diagnosis isolation and recovery function of a satellite, including:
the bus control terminal sends a fault control instruction to a bus terminal simulator and receives fault information fed back by the bus terminal simulator according to the fault control instruction;
the bus control terminal carries out fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy, and determines data information after fault diagnosis and recovery;
and the bus control terminal sends the data information to the ground computer equipment so that the ground computer equipment tests the fault diagnosis isolation and recovery function based on the data information.
Optionally, the bus control terminal performs fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy, and the fault diagnosis and recovery method includes:
the bus control terminal determines corresponding fault diagnosis isolation and recovery information from the preset fault diagnosis isolation and recovery strategy according to the fault information, wherein the information comprises operation steps and the sequence of the operation steps;
and the bus control terminal carries out fault diagnosis and recovery according to the operation steps and the sequence of the operation steps.
Optionally, the fault information includes: the fault information of the power control terminal, the fault information of the load service terminal or the fault information of the platform service terminal.
In a third aspect, the present application provides a testing apparatus for a primary fault diagnosis isolation and recovery function of a satellite, the apparatus including:
the receiving unit is used for sending a fault control instruction to the bus terminal simulator and receiving fault information fed back by the bus terminal simulator according to the fault control instruction;
the fault diagnosis and recovery unit is used for carrying out fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy and determining data information after fault diagnosis and recovery;
and the sending unit is used for sending the data information to the ground computer equipment so that the ground computer equipment can test the fault diagnosis isolation and recovery function based on the data information.
Optionally, the failure diagnosis and recovery unit is specifically configured to:
determining corresponding fault diagnosis isolation and recovery information from the preset fault diagnosis isolation and recovery strategy according to the fault information, wherein the information comprises operation steps and the sequence of the operation steps;
and performing fault diagnosis and recovery according to the operation steps and the sequence of the operation steps.
Optionally, the fault information includes: the fault information of the power control terminal, the fault information of the load service terminal or the fault information of the platform service terminal.
In a fourth aspect, the present application provides a testing apparatus for a primary fault diagnosis isolation and recovery function of a satellite, the apparatus including:
a memory for storing instructions for execution by at least one processor;
a processor for executing instructions stored in the memory to perform the method of the second aspect.
In a fifth aspect, the present application provides a computer readable storage medium having stored thereon computer instructions which, when run on a computer, cause the computer to perform the method of the second aspect.
Drawings
Fig. 1 is a schematic structural diagram of a test system for satellite primary fault diagnosis isolation and recovery functions according to an embodiment of the present disclosure;
fig. 2 is a schematic flowchart of a method for testing a primary fault diagnosis isolation and recovery function of a satellite according to an embodiment of the present disclosure;
fig. 3 is a schematic structural diagram of a testing apparatus for satellite primary fault diagnosis isolation and recovery functions according to an embodiment of the present disclosure;
fig. 4 is a schematic structural diagram of a testing apparatus for satellite primary fault diagnosis isolation and recovery functions according to an embodiment of the present disclosure.
Detailed Description
In order to better understand the technical solutions, the technical solutions of the present application are described in detail below with reference to the drawings and specific embodiments, and it should be understood that the specific features in the embodiments and examples of the present application are detailed descriptions of the technical solutions of the present application, and are not limitations of the technical solutions of the present application, and the technical features in the embodiments and examples of the present application may be combined with each other without conflict.
Referring to fig. 1, the present application provides a test system for a primary fault diagnosis isolation and recovery function of a satellite, the test system comprising:
the 1553B bus system 1 comprises a bus control terminal 11 and at least one remote terminal 12 on a satellite, and is used for realizing data transmission between the bus control terminal 11 and the at least one remote terminal 12 through a 1553B bus;
the bus terminal simulator 2 is connected with the 1553B bus system 1 and used for simulating fault excitation so as to inject fault information into the 1553B bus system 1;
and the ground computer equipment 3 is connected with the bus control terminal 11 and is used for carrying out data interaction with the bus control terminal 11 and detecting the fault diagnosis isolation and recovery function according to the interaction data.
Specifically, in the solution provided in the embodiment of the present application, the 1553B bus system 1 is located on a satellite and is used for implementing data transmission between devices on the satellite, wherein the 1553B bus system 1 includes 3 parts: a Bus control terminal 11 (BC), at least one remote terminal 12(Real-Time, RT) and a Bus Monitor (BM). The bus control terminal 11 and the at least one remote terminal 12 realize data transmission through a 1553B bus, specifically, the bus control terminal 11 sends a data sending request or a data receiving request to the at least one remote terminal 12 through the 1553B bus, and after receiving the data sending request or the data receiving request, the at least one remote terminal 12 sends the data to the bus control terminal 11 through the 1553B bus. The bus terminal simulator 2 is arranged on the ground and used for simulating a remote terminal 12 with a fault in the 1553B bus system 1 and connecting the bus terminal simulator 2 with a 1553B bus in the 1553B bus system 1. The surface computer device 3 may comprise a distributed plurality of computer devices, for example, the surface computer device 3 comprises a remote control instruction transmitting computer, a telemetry display computer, a data processing computer, a dynamics simulation computer, or the like; a centralized, single-computer facility may also be included, and is not limited thereto. The ground computer equipment 3 can be directly connected with the bus control terminal 11, and also can be indirectly connected with the bus control terminal 11 through the ground telemetering control equipment 4 and the measurement and control subsystem 5, so as to realize data interaction with the bus control terminal 11, and further detect the fault diagnosis isolation and recovery function according to the interaction data.
Further, in the solution provided in the embodiment of the present application, there are various kinds of the at least one remote terminal 12. In one possible implementation, the at least one remote terminal 12 includes: a power control terminal 121, a load service terminal 122, and a platform service terminal 123.
In a possible implementation, the bus termination simulator 2 is specifically configured to: simulating a faulty remote terminal 21 in the 1553B bus system.
Specifically, the satellite primary fault comprises a comprehensive electronic primary fault, a power supply and distribution primary fault or a control primary fault. For different fault types, remote terminals with faults in the 1553B bus system 1 simulated by the bus terminal simulator 2 are different, for example, for a primary fault of integrated electronics, the bus terminal simulator 2 is used for simulating a load service terminal 122 or a platform service terminal 123 in the 1553B bus system 1; for the primary power supply and distribution fault, the bus terminal simulator 2 is used for simulating the power control terminal 121 in the 1553B bus system 1. In the solution provided in the embodiment of the present application, there are various ways for the bus termination simulator 2 to simulate the remote termination 21 with a fault, and a preferred way is taken as an example for the following description.
In a possible implementation manner, the bus termination simulator 2 is specifically configured to: and adjusting the module working zone bit of the bus terminal simulator to be a fault according to the received fault control instruction to obtain the remote terminal 21 with the fault.
Specifically, in the solution provided in the embodiment of the present application, the bus control terminal 11 is preset with a fault diagnosis and recovery policy. Each remote terminal 21 is provided with an operation flag bit for identifying an operation state of the remote terminal 21, for example, the operation state includes normal or failure.
In order to facilitate understanding of the process of the bus terminal simulator 2 simulating the remote terminals with different faults, the following description will be made for the integrated electronic primary fault or the power supply and distribution primary fault, respectively.
Aiming at the primary failure of the integrated electronics
Specifically, in the scheme provided in this embodiment of the present application, if the bus terminal simulator 2 simulates the load service terminal 122 or the platform service terminal 123 in the 1553B bus system 1, after the bus terminal simulator 2 is connected to the 1553B bus system 1, each system of the satellite is powered up, and the fault diagnosis and recovery strategy in the bus control terminal 11 is enabled, then the ground computer device 3 sends a remote control instruction to the bus control terminal 11, after receiving the remote control instruction, the bus control terminal 11 sends a fault control instruction to the bus terminal simulator 2 according to the remote control instruction, and the bus terminal simulator 2 adjusts the module working flag bit of the bus terminal simulator 2 into a fault according to the fault control instruction, so as to obtain the load service terminal 122 or the platform service terminal 123 with the fault.
Second, aiming at the first-level fault of power supply and distribution
Specifically, in the scheme provided in this embodiment of the present application, if the bus terminal simulator 2 simulates the power control terminal 121 in the 1553B bus system 1, after the bus terminal simulator 2 is connected to the 1553B bus system 1, each system of the satellite is powered up, and a fault diagnosis and recovery strategy in the bus control terminal 11 is enabled, then the ground computer device 3 sends a remote control instruction to the bus control terminal 11, after receiving the remote control instruction, the bus control terminal 11 sends a fault control instruction to the bus terminal simulator 2 according to the remote control instruction, and the bus terminal simulator 2 adjusts the module working flag bit of the bus terminal simulator 2 to a fault according to the fault control instruction, so as to obtain the power control terminal 121 with the fault.
Further, in the solution provided in the embodiment of the present application, the power supply and distribution primary fault includes a power control terminal fault, a charging fault, or a discharging fault, and a recovery process of the charging fault or the discharging fault is described below.
1) Charging failure
Specifically, after the bus terminal simulator 2 is connected to the satellite 1553B bus system 1, the bus terminal simulator 2 is set not to respond to an instruction, the backup parameter is in a discharge mode state, the energy autonomous management enable, the battery charging and discharging autonomous management enable, the charging regulation module fault switching enable and the bus terminal simulator 2 master parameter are set, so that the energy software is switched from a pause mode to a discharge mode; at this time, since the bus terminal simulator 2 does not respond to the command, that is, the command is not executed correctly for three consecutive times, the master fails to control the master charging adjustment module, and a fault is triggered.
2) Discharge failure
After the bus terminal simulator 2 is connected to a 1553B bus system 1 on the satellite, energy autonomous management enabling, battery charging and discharging autonomous management enabling, software long illumination period, discharging regulation module fault switching enabling, bus terminal simulator 2 master parameters and the like are set on the bus terminal simulator 2, so that discharging current is generated, and faults are triggered.
Further, after the bus terminal simulator 2 adjusts the working flag bit to be a fault to obtain the remote terminal 21 with the fault, the bus terminal simulator 2 sends the fault data to the bus control terminal 11 through a 1553B bus, after the bus control terminal 11 receives the fault data of the bus terminal simulator 2, the bus control terminal executes a fault diagnosis and recovery function according to the fault data and a preset fault diagnosis and recovery strategy, and after executing the fault diagnosis and recovery, sends the data received by the bus control terminal 11 to the ground computer device 3, and the ground computer device 3 detects whether the fault diagnosis isolation and recovery function is correct according to the received data, for example, the ground computer device 3 detects whether the 1553B bus system has the fault elimination according to the received data.
In the scheme provided by the embodiment of the application, a primary fault terminal on a satellite is simulated through a bus terminal simulator 2, the bus terminal simulator 2 is connected to a 1553B bus system 1 of the satellite, namely, fault equipment is arranged in the satellite, then, a bus control terminal 11 operates a fault diagnosis and recovery function according to fault information of the fault equipment, the bus control terminal 11 sends data of the fault equipment to a ground computer device 3, and the ground computer device 3 detects the fault diagnosis isolation and recovery function according to the data sent by the bus control terminal 11. Therefore, in the scheme provided by the embodiment of the application, by injecting fault equipment into the whole satellite of the satellite and verifying the logic or method of fault detection and recovery function under the fault, the detection of the fault diagnosis and repair function under the whole satellite is realized; the fault diagnosis and recovery function can be detected under the condition that a fault exists, and the accuracy of a detection result is improved.
The method for testing the satellite primary fault diagnosis isolation and recovery function provided by the embodiment of the present application is described in further detail below with reference to the accompanying drawings of the specification, and is applied to the system shown in fig. 1, and a specific implementation manner of the method may include the following steps (a method flow is shown in fig. 2):
step 201, a bus control terminal sends a fault control instruction to a bus terminal simulator, and receives fault information fed back by the bus terminal simulator according to the fault control instruction.
And 202, the bus control terminal carries out fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy, and determines data information after fault diagnosis and recovery.
Step 203, the bus control terminal sends the data information to a ground computer device, so that the ground computer device tests the fault diagnosis isolation and recovery function based on the data information.
Optionally, the bus control terminal performs fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy, and the fault diagnosis and recovery method includes:
the bus control terminal determines corresponding fault diagnosis isolation and recovery information from the preset fault diagnosis isolation and recovery strategy according to the fault information, wherein the information comprises operation steps and the sequence of the operation steps;
and the bus control terminal carries out fault diagnosis and recovery according to the operation steps and the sequence of the operation steps.
Optionally, the fault information includes: the fault information of the power control terminal, the fault information of the load service terminal or the fault information of the platform service terminal.
Specifically, the process of information interaction between the devices in the test method for testing the primary fault diagnosis isolation and recovery function of the satellite provided in fig. 2 is described in detail in the above description of the system shown in fig. 1, and is not described herein again.
Referring to fig. 3, the present application provides a testing apparatus for a primary fault diagnosis isolation and recovery function of a satellite, the apparatus comprising:
a receiving unit 301, configured to send a fault control instruction to a bus terminal simulator, and receive fault information fed back by the bus terminal simulator according to the fault control instruction;
a fault diagnosis and recovery unit 302, configured to perform fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy, and determine data information after fault diagnosis and recovery;
a sending unit 303, configured to send the data information to a ground computer device, so that the ground computer device tests the fault diagnosis isolation and recovery function based on the data information.
Optionally, the failure diagnosing and recovering unit 302 is specifically configured to:
determining corresponding fault diagnosis isolation and recovery information from the preset fault diagnosis isolation and recovery strategy according to the fault information, wherein the information comprises operation steps and the sequence of the operation steps;
and performing fault diagnosis and recovery according to the operation steps and the sequence of the operation steps.
Optionally, the fault information includes: the fault information of the power control terminal, the fault information of the load service terminal or the fault information of the platform service terminal.
Referring to fig. 4, the present application provides a testing apparatus for a primary fault diagnosis isolation and recovery function of a satellite, the apparatus comprising:
a memory 401 for storing instructions for execution by at least one processor;
a processor 402 for executing instructions stored in memory to perform the method described in fig. 2.
A computer-readable storage medium having stored thereon computer instructions which, when executed on a computer, cause the computer to perform the method of fig. 2.
As will be appreciated by one skilled in the art, embodiments of the present application may be provided as a method, system, or computer program product. Accordingly, the present application may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present application may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, optical storage, and the like) having computer-usable program code embodied therein.
The present application is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the application. It will be understood that each flow and/or block of the 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.
It will be apparent to those skilled in the art that various changes and modifications may be made in the present application without departing from the spirit and scope of the application. Thus, if such modifications and variations of the present application fall within the scope of the claims of the present application and their equivalents, the present application is intended to include such modifications and variations as well.
Claims (10)
1. A test system for a primary fault diagnosis isolation and recovery function of a satellite is characterized by comprising:
the 1553B bus system comprises a bus control terminal on a satellite and at least one remote terminal, and is used for realizing data transmission between the bus control terminal and the at least one remote terminal through a 1553B bus;
the bus terminal simulator is connected with the 1553B bus system and used for simulating fault excitation so as to inject fault information into the 1553B bus system;
and the ground computer equipment is connected with the bus control terminal and used for carrying out data interaction with the bus control terminal and detecting the fault diagnosis isolation and recovery functions according to the interaction data.
2. The system of claim 1, wherein the at least one remote terminal comprises: the system comprises a power supply control terminal, a load service terminal and a platform service terminal.
3. The system of claim 2, wherein the bus termination simulator is specifically configured to: and simulating a remote terminal with a fault in the 1553B bus system.
4. The system of claim 3, wherein the bus termination simulator is specifically configured to: and adjusting the module working zone bit of the bus terminal simulator to be a fault according to the received fault control instruction to obtain the remote terminal with the fault.
5. A test method for a primary fault diagnosis isolation and recovery function of a satellite is applied to the system as claimed in any one of claims 1 to 4, and is characterized by comprising the following steps:
the bus control terminal sends a fault control instruction to a bus terminal simulator and receives fault information fed back by the bus terminal simulator according to the fault control instruction;
the bus control terminal carries out fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy, and determines data information after fault diagnosis and recovery;
and the bus control terminal sends the data information to the ground computer equipment so that the ground computer equipment tests the fault diagnosis isolation and recovery function based on the data information.
6. The method of claim 5, wherein the bus control terminal performs fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy, and the method comprises:
the bus control terminal determines corresponding fault diagnosis isolation and recovery information from the preset fault diagnosis isolation and recovery strategy according to the fault information, wherein the information comprises operation steps and the sequence of the operation steps;
and the bus control terminal carries out fault diagnosis and recovery according to the operation steps and the sequence of the operation steps.
7. The method of claim 5 or 6, wherein the fault information comprises: the fault information of the power control terminal, the fault information of the load service terminal or the fault information of the platform service terminal.
8. A test device for a primary fault diagnosis isolation and recovery function of a satellite is characterized by comprising:
the receiving unit is used for sending a fault control instruction to the bus terminal simulator and receiving fault information fed back by the bus terminal simulator according to the fault control instruction;
the fault diagnosis and recovery unit is used for carrying out fault diagnosis and recovery according to the fault information and a preset fault diagnosis isolation and recovery strategy and determining data information after fault diagnosis and recovery;
and the sending unit is used for sending the data information to the ground computer equipment so that the ground computer equipment can test the fault diagnosis isolation and recovery function based on the data information.
9. The apparatus of claim 8, wherein the fault diagnosis and recovery unit is specifically configured to:
determining corresponding fault diagnosis isolation and recovery information from the preset fault diagnosis isolation and recovery strategy according to the fault information, wherein the information comprises operation steps and the sequence of the operation steps;
and performing fault diagnosis and recovery according to the operation steps and the sequence of the operation steps.
10. A test device for a primary fault diagnosis isolation and recovery function of a satellite is characterized by comprising:
a memory for storing instructions for execution by at least one processor;
a processor for executing instructions stored in a memory to perform the method of any of claims 5 to 7.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112255992A (en) * | 2020-09-10 | 2021-01-22 | 中国空间技术研究院 | Satellite FDIR task scheduling method |
| CN113722161A (en) * | 2021-08-09 | 2021-11-30 | 中国空间技术研究院 | Method and system for verifying FDIR scheduling strategy of whole satellite |
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