CN108563166B - FPGA-based small satellite on-orbit health comprehensive management terminal and management method - Google Patents

FPGA-based small satellite on-orbit health comprehensive management terminal and management method Download PDF

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CN108563166B
CN108563166B CN201810245046.8A CN201810245046A CN108563166B CN 108563166 B CN108563166 B CN 108563166B CN 201810245046 A CN201810245046 A CN 201810245046A CN 108563166 B CN108563166 B CN 108563166B
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CN108563166A (en
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刘源
吴生龙
程建华
赵琳
周俊峰
丁继成
李慧
李亮
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Harbin Engineering University
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    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
    • G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
    • G05B19/0423—Input/output
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B19/00—Programme-control systems
    • G05B19/02—Programme-control systems electric
    • G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
    • G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
    • G05B19/0428—Safety, monitoring
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B23/00—Testing or monitoring of control systems or parts thereof
    • G05B23/02—Electric testing or monitoring
    • G05B23/0205—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults
    • G05B23/0208—Electric testing or monitoring by means of a monitoring system capable of detecting and responding to faults characterized by the configuration of the monitoring system
    • G05B23/0213—Modular or universal configuration of the monitoring system, e.g. monitoring system having modules that may be combined to build monitoring program; monitoring system that can be applied to legacy systems; adaptable monitoring system; using different communication protocols
    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
    • G05B23/00—Testing or monitoring of control systems or parts thereof
    • G05B23/02—Electric testing or monitoring
    • 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
    • G05B23/0243—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 model based detection method, e.g. first-principles knowledge model

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Abstract

The invention provides a small satellite on-orbit health comprehensive management terminal and a management method based on an FPGA. The system comprises an on-orbit satellite monitoring information acquisition system (1), a satellite data analysis and processing system (2) based on an FPGA, an on-orbit satellite health data evaluation and management system (3), a system fault-tolerant control system (4), a satellite health data output system (5), a system communication bus (6), a backup NOR flash memory (7) and a PROM module (8). The satellite data analysis processing system based on the FPGA comprises a PROM and an SRAM, can process satellite health information, and has fault-tolerant processing capability; the on-orbit satellite health data evaluation management system comprises a satellite health management rule base and on-orbit satellite health evaluation prediction, and can store the health evaluation criterion and health condition of the satellite.

Description

FPGA-based small satellite on-orbit health comprehensive management terminal and management method
Technical Field
The invention relates to a health management device of an in-orbit satellite and also relates to a health management method of the in-orbit satellite.
Background
With the rapid development of a satellite electronic information system, a satellite can automatically plan a working process, in-orbit autonomous management is realized, and an effective satellite autonomous health comprehensive management terminal needs to be constructed. In recent years, a flight safety plan for comprehensive aircraft management is proposed abroad for safety reliability of aircraft, and the flight safety plan comprises functions of fault detection, fault diagnosis, influence evaluation, fault prediction and the like. However, to date, none of the health management systems with complete health management functions is put into practical engineering application. The research on satellite health management in China is at a primary stage at present, the health management of satellites is mainly based on ground diagnosis at present, and the on-orbit health management of the satellites mainly depends on a ground monitoring station and is managed by acquiring the actual running state of the satellites through manually distinguishing a large amount of satellite telemetering information. The method has the characteristics of large in-orbit satellite remote measurement, numerous parameter types, complexity and changeability, cannot meet the real-time requirement of satellite data monitoring, and also has the phenomenon of human misoperation and the like. The above series of problems greatly limit the development of satellite systems.
Disclosure of Invention
The invention aims to provide a small satellite in-orbit health comprehensive management terminal based on an FPGA (field programmable gate array) and capable of realizing automatic adjustment of satellite in-orbit parameters. The invention also aims to provide a comprehensive management method for the in-orbit health of the small satellite.
The invention relates to a small satellite on-orbit health comprehensive management terminal based on FPGA, which comprises a monitoring information acquisition system 1 of an on-orbit satellite, a satellite data analysis and processing system 2 based on FPGA, an on-orbit satellite health data evaluation and management system 3, a system fault-tolerant control system 4, a satellite health data output system 5, a system communication bus 6, a backup NOR flash Memory 7 and a PROM (Programmable Read-Only-Memory) module 8;
the monitoring information acquisition system 1 of the in-orbit satellite comprises information input 1-1 of a satellite thermal control subsystem, information input 1-2 of a satellite propulsion subsystem, information input 1-3 of a satellite radio frequency tracking system, information input 1-4 of a satellite energy subsystem, information input 1-5 of satellite attitude information and information acquisition parts 1-6 of each subsystem, wherein the information input of each subsystem is connected with the information acquisition parts 1-6 of each subsystem, and the information acquisition parts 1-6 of each subsystem are connected with a system communication bus 6;
the satellite data analysis processing system 2 based on the FPGA comprises a PROM module PROM2-1, an SRAM (Static Random Access Memory) module SRAM2-2, an FPGA processor 2-3, a PROM2-1, an SRAM2-2 and an FPGA2-3 which are connected with each other, an information input end of the FPGA2-3 is connected with a system communication bus 6, an information output end of the FPGA2-3 is also connected with the system communication bus 6, a heartbeat signal output end of the FPGA2-3 is connected with a WDG of a C8051 singlechip 4-3, an INT and a PROG input end of the FPGA2-3 are connected with the C8051 singlechip 4-3, and a satellite information health output of the FPGA2-3 is connected with a health management rule base 3-1 input and an on-orbit satellite health assessment prediction 3-2 input;
the on-orbit satellite health data evaluation management system 3 comprises a health management rule base 3-1 and an on-orbit satellite health evaluation prediction part 3-2, one end of the on-orbit satellite health evaluation prediction part 3-2 is connected with one input end of an FPGA2-3, the other end of the on-orbit satellite health evaluation prediction part is connected with a C805 single chip microcomputer 4-3, and the output end of the health management rule base 3-1 is connected with the input end of the on-orbit satellite health evaluation prediction part 3-2;
the system fault-tolerant control system 4 comprises a C8051 singlechip 4-3, wherein a plurality of output ports of the C8051 singlechip 4-3 are respectively connected with CE1, RST1, CE2 and RST2 of PROM18-1 and PROM 28-2;
the satellite health data output system 5 comprises a command 5-1 sent to a lower computer, an external information output 5-2, a subsystem parameter correction 5-3 and a satellite health condition prediction output 5-4, wherein the command 5-1 sent to the lower computer is input to be connected with a bus communication 6, the command 5-1 sent to the lower computer is output to be connected with an external information 5-2 input, and the external information 5-2 output is connected with the subsystem parameter correction 5-3 input and the satellite health condition prediction output 5-4 input;
the system communication bus 6 is a plurality of bus communication modes commonly used by satellites;
the backup NOR flash memory 7 is connected with a universal port of the FPGA;
the PROM module 8 comprises two PROMs, and the DATA output terminals DATA1 and DATA2 of PROM18-1 and PROM28-2 are connected with the FPGA 2-3.
The management method of the small satellite on-orbit health comprehensive management terminal based on the FPGA comprises the following steps:
the monitoring information acquisition system 1 of the on-orbit satellite collects thermal control subsystem information, propulsion subsystem information, radio frequency tracking subsystem information, energy subsystem information, attitude control subsystem information and the like collected by sensors loaded in various subsystems of the on-orbit satellite, and health information data of the satellite is sent to a satellite data analysis and processing system 2 based on FPGA through bus communication 6;
the FPGA2-3 processes the real-time health information of the on-orbit satellite sent by the bus communication, and stores the processed satellite health information into a satellite health management rule base 3-1, wherein the satellite health management rule base is used for counting and memorizing satellite health information data; the SRAM is used for refreshing and reading data generated in the running process of the FPGA2-3, and a system program starting code of the FPGA2-3 is stored in the PROM 2-1;
the on-orbit health assessment and prediction 3-2 collects satellite health data transmitted by the FPGA2-3 and health rules in a health management rule base and sends the collected data to the FPGA2-3 for analysis and processing to obtain the health condition of the satellite; after the satellite health information is obtained, a processing command is judged and obtained at the same time, the command is sent to a lower computer through bus communication, on one hand, the lower computer sends the processing command to each subsystem of the satellite to correct parameters of the real-time operation of the satellite, and on the other hand, the health condition of the satellite is output and displayed;
the FPGA2-3 outputs heartbeat signals, the heartbeat signals are connected with a WDG (wireless data generator) of a C8051 singlechip 4-1 and are used for monitoring whether the FPGA works in a normal state or not, if the heartbeat signals are normal, the FPGA2-3 is proved to work normally, if the health condition is monitored to be abnormal, the FPGA is proved not to be in a normal working state, at the moment, the C8051 can refresh the configuration file into the FPGA2-3 to repair the abnormal condition, in the running process of the FPGA, the C8051 reads back the configuration file of the FPGA in real time and compares the configuration file with an original configuration file, and if the configuration file is abnormal, the configuration file is refreshed back;
reading data needing protection in the FPGA2-3 into the backup NOR flash memory 7 through a memory access instruction before the FPGA2-3 has an error, and re-reading the stored important data from the backup NOR flash memory 7 after the FPGA2-3 is powered on again;
the monitoring information acquisition system 1 of the satellite and the satellite health data output system 5 have unpredictable faults in the operation process, so that when the data needing to be received or sent have errors, the data are stored in the PROM module, and when the faults occur, the data are reread from the PROM module.
The invention provides a health management terminal applied to a satellite, which can monitor and predict the health state of the satellite in real time and process partial faults of the satellite, and an implementation method thereof. The technical scheme is that the technical scheme is provided for solving the problem that a reasonable and effective means is lacked in the aspect of the current on-orbit satellite health management, and the on-orbit satellite health management is based on an FPGA (Field-Programmable Gate Array).
The invention has the advantages that: the invention takes the FPGA as a core, can receive the health information of the in-orbit satellite in real time for automatic processing, and feeds the processed information back to the satellite and the detection station, so that the satellite can realize the automatic adjustment of in-orbit parameters without manual interference processing, thereby saving a large amount of manpower and material resources, improving the processing and monitoring efficiency, and greatly improving the health management accuracy and the real-time performance of the satellite. Meanwhile, the fault-tolerant system has higher reliability and strong practicability due to the design of the fault-tolerant system. In addition, the components used in the invention are common commercial universal components in the market, so that the price is low, and the production cost is greatly reduced. The production process required by the invention is simple and convenient to manufacture.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic flow diagram of the present invention.
Detailed Description
With reference to fig. 1, the microsatellite in-orbit health comprehensive management terminal based on the FPGA of the present invention includes an in-orbit satellite monitoring information acquisition system 1, a satellite data analysis processing system 2 based on the FPGA, an in-orbit satellite health data evaluation management system 3, a C8051 single chip microcomputer 4-3, a satellite health data output system 5 and a system communication bus 6.
The monitoring information acquisition system 1 of the in-orbit satellite comprises information input 1-1 of a satellite thermal control subsystem, information input 1-2 of a satellite propulsion subsystem, information input 1-3 of a satellite radio frequency tracking system, information input 1-4 of a satellite energy subsystem, information input 1-5 of satellite attitude information and information acquisition parts 1-6 of all the subsystems. The information input of each subsystem is connected with the information acquisition parts 1-6, and the information acquisition is connected with the bus in communication.
The satellite data analysis processing system 2 based on the FPGA mainly comprises a PROM module PROM2-1, an SRAM module SRAM2-1 and an FPGA processor 2-3. The PROM2-1, the SRAM2-2 and the FPGA2-3 are mutually connected, an information input end of the FPGA2-3 is connected with a bus communication 6, an information output end of the FPGA2-3 is also connected with the bus communication, a heartbeat signal output end of the FPGA2-3 is connected with a WDG of a C8051 singlechip 4-3, an INT and PROG input end of the FPGA2-3 is connected with the C8051 singlechip 4-3, and a satellite information health output of the FPGA2-3 is connected with a health management rule base 3-1 input and an on-orbit satellite health assessment forecast 3-2 input.
The on-orbit satellite health data evaluation management system 3 comprises a health management rule base 3-1 and an on-orbit satellite health evaluation prediction 3-2. One end of the on-orbit satellite health assessment and prediction 3-2 is connected with one input end of the FPGA2-3, and the other end is connected with the C805 single chip microcomputer 4-3; the output end of the health management rule base 3-1 is connected with the input end of the on-orbit satellite health assessment prediction 3-2.
The system fault-tolerant control system 4 comprises a C8051 singlechip 4-3 system. Several output ports of the C8051 singlechip 4-3 are respectively connected with CE1, RST1, CE2 and RST2 of PROM18-1 and PROM 28-2.
The satellite health data output system 5 comprises a command 5-1 sent to a lower computer, external information output 5-2, subsystem parameter correction 5-3 and satellite health condition prediction output 5-4. The input of a command 5-1 sent to the lower computer is connected with the bus communication 6, the output of the command 5-1 sent to the lower computer is connected with the input of external information 5-2, and the output of the external information 5-2 is connected with the input of each subsystem parameter correction 5-3 and the input of satellite health condition prediction output 5-4.
The system communication bus 6 is mainly a plurality of bus communication modes commonly used by satellites.
The monitoring information acquisition system 1 of the on-orbit satellite collects thermal control subsystem information, propulsion subsystem information, radio frequency tracking subsystem information, energy subsystem information, attitude control subsystem information and the like collected by sensors mounted on various subsystems of the on-orbit satellite, and health information data of the satellite is sent to the satellite data analysis and processing system 2 based on the FPGA through bus communication 6.
The FPGA2-3 processes the real-time health information of the on-orbit satellite sent by the bus communication, on one hand, the processed satellite health information is stored in a satellite health management rule base 3-1, and the satellite health management rule base is used for counting and memorizing the satellite health information data. One SRAM is used for refreshing and reading data generated in the running process of the FPGA2-3, and a system program starting code of the FPGA2-3 is stored in the PROM2-1, so that the running efficiency and reliability of the FPGA are improved.
And (3) the on-orbit health assessment and prediction 3-2 collects the satellite health data transmitted by the FPGA2-3 and the health rules in the health management rule base and transmits the collected data and the health rules to the FPGA2-3 for analysis and processing, and finally the health condition of the satellite is obtained.
And after the satellite health information is obtained, judging to obtain a processing command, sending the command to the lower computer 5-1 through bus communication, on one hand, sending the processing command to each subsystem of the satellite to correct parameters of the real-time operation of the satellite, and on the other hand, outputting and displaying the health condition of the satellite.
The FPGA2-3 outputs a heartbeat signal, and the heartbeat signal is connected with a WDG of the C8051 singlechip 4-1 and is used for monitoring whether the FPGA works in a normal state. If the heartbeat signal is normal, the FPGA2-3 is proved to work normally, if the monitoring health condition is abnormal, the FPGA is proved not to be in a normal working state, and at the moment, the C8051 can brush the configuration file back into the FPGA2-3, so that the abnormal condition is repaired, and the reliability of the system is improved. In the running process of the FPGA, the C8051 reads back the configuration file of the FPGA in real time, compares the configuration file with the original configuration file, and if the configuration file is abnormal, the configuration file is refreshed back to ensure that the FPGA works normally.
The FPGA-based touch screen further comprises a backup NOR flash memory 7, wherein the input and output ends of the backup NOR flash memory 7 are connected with the data input and output ends of the FPGA 2-3.
Data is easy to lose after the system is powered down, and unnecessary troubles are brought. The problem is not solved, the data needing to be protected in the FPGA2-3 can be read into the backup NOR flash memory 7 through a certain memory access instruction before the FPGA2-3 has an error, and the saved important data can be read back from the backup NOR flash memory 7 after the FPGA2-3 is powered on again, so that the working reliability of the system is greatly improved.
A PROM module 8 is also included. The enabling and resetting ports CE1 and RST1 of the PROM1 and the PROM2, and CE2 and RST2 are all controlled by a C8051 singlechip 4-1, and the PROM1 and the PROM2 are used for storing satellite health information read by the FPGA2-3 and obtained satellite health prediction information.
Because unpredictable faults may occur in the operation process of the monitoring information acquisition system 1 and the satellite health data output system 5 of the satellite, errors occur in data which needs to be received or sent, in order to avoid the problems, the data can be stored in the PROM module, and when the faults occur, the data can be reread from the PROM module, so that the safety of the system is improved.
The health management algorithm of the on-orbit satellite health data evaluation management system is described as follows:
the method mainly adopts a fault diagnosis algorithm based on an analytic model, the algorithm is based on a mathematical model of a system, residual errors are generated by combining a certain number of methods such as observers, Kalman filters and the like, and finally, the generated residual errors are evaluated or decided according to a certain principle. The core idea of this algorithm is to replace hardware redundancy with analytical redundancy. The specific implementation steps are divided into the following 4 steps.
Step 1, establishing a fault model of a diagnosis object.
And 2, estimating the state of the diagnostic object at the next moment by adopting methods such as a Kalman filter, an observer and the like.
And 3, obtaining a filtering residual error by using the state obtained in the previous step.
And 4, setting a reasonable threshold value, and evaluating the obtained residual error. If the threshold value is exceeded, the fault is considered to occur, otherwise, the work is considered to be normal.
As shown in FIG. 2, the above 4 steps will be described by taking the thermal control subsystem as an example. And modeling the thermal control subsystem to obtain a mathematical model of the thermal control subsystem. In general, the controlled object can be represented by the following formulas (2) and (3).
x(t+Δt)＝(A+ΔA)x(t)+(B+ΔB)u(t)+E1n1(t) (1)
y(t)＝(C+ΔC)x(t)+(D+ΔD)u(t)+E2n2(t) (2)
Wherein Δ t is a time interval; x (t) is a controlled object state vector; u (t) input vector of bit system; y (t) is an output vector obtained by the sensor; A. b, C, D, a controlled object model coefficient matrix is represented; Δ A, Δ B, Δ C, Δ D represent uncertainty matrices of the controlled object; e1、E2Is a noise matrix.
The following fault model can be obtained by equations (1) and (2):
x(t+Δt)＝(A+ΔA+ΔAc)x(t)+(B+ΔB+ΔBc)u(t)+E1n1(t)+Bfa(t) (3)
y(t)＝(C+ΔC+ΔCc)x(t)+(D+ΔD+ΔDc)u(t)+E2n2(t)+fs(t) (4) wherein fa(t) is a fault vector of the actuator; f. ofs(t) is a fault vector of the sensor; delta Ac、ΔBc、ΔCc、ΔDcIs a model fault matrix of the controlled object. By fault vector fcIf (t) indicates uncertainty and various types of failures of the controlled object, equations (3) and (4) can be rewritten into equations (5) and (6) below:
x(t+Δt)＝Ax(t)+Bu(t)+E1n1(t)Bfa(t)+F1(t)fc(t) (5)
y(t)＝Cx(t)+Du(t)+E2n2(t)+fs(t)+F2(t)fc(t) (6)
let noise vector n (t) be [ n ]1(t)n2(2)]TFault vector f (t) ═ fa(t)fs(t)fc(t)]TThen the formulas (6) and (7) can be simplified to
y(t)＝G(z)x(t)+E(z)n(t)+F(z)f(t) (7)
In the formula: g (z) ═ C (zl-a)-1B+D；F(z)＝(zI-A)-1E1E2；E(z)＝(zIA)-1BI(zI-A)-1F1+F2(ii) a z is a variable matrix; and I is an identity matrix.
The residual r (t) can be written as
Figure BDA0001606295510000071
Wherein
Figure BDA0001606295510000072
Is the output vector obtained by the residual filter algorithm.
A threshold value S meeting the requirement is set in advance, the average value of the generated residual errors r (t) is detected, when the average value is larger than S, a fault is judged to occur, otherwise, no fault occurs.

Claims (2)

1. A microsatellite on-orbit health comprehensive management terminal based on FPGA comprises a monitoring information acquisition system (1) of an on-orbit satellite, a satellite data analysis and processing system (2) based on FPGA, an on-orbit satellite health data evaluation and management system (3), a system fault-tolerant control system (4), a satellite health data output system (5), bus communication (6), a backup NOR flash memory (7) and a PROM module (8);
the monitoring information acquisition system (1) of the in-orbit satellite comprises an information input (1-1) of a satellite thermal control subsystem, an information input (1-2) of a satellite propulsion subsystem, an information input (1-3) of a satellite radio frequency tracking system, an information input (1-4) of a satellite energy subsystem, an information input (1-5) of satellite attitude information and each subsystem information acquisition part (1-6), wherein each subsystem information input is connected with each subsystem information acquisition part (1-6), and each subsystem information acquisition part (1-6) is connected with a bus communication part (6);
the satellite data analysis and processing system (2) based on the FPGA comprises a PROM module PROM (2-1), an SRAM module SRAM (2-2) and an FPGA (2-3), the system comprises a PROM (2-1), an SRAM (2-2) and an FPGA (2-3), wherein the information input end of the FPGA (2-3) is connected with a bus communication (6), the information output end of the FPGA (2-3) is also connected with the bus communication (6), the heartbeat signal output end of the FPGA (2-3) is connected with a WDG (Wireless data group) of a C8051 singlechip (4-3), the INT and PROG input ends of the FPGA (2-3) are connected with the C8051 singlechip (4-3), and the satellite information health output of the FPGA (2-3) is connected with the input of a health management rule base (3-1) and the input of an on-orbit satellite health assessment and prediction (3-2);
the on-orbit satellite health data evaluation management system (3) comprises a health management rule base (3-1) and an on-orbit satellite health evaluation prediction part (3-2), one end of the on-orbit satellite health evaluation prediction part (3-2) is connected with one input end of an FPGA (2-3), the other end of the on-orbit satellite health evaluation prediction part is connected with a C805 single chip microcomputer (4-3), and the output end of the health management rule base (3-1) is connected with the input end of the on-orbit satellite health evaluation prediction part (3-2);
the system fault-tolerant control system (4) comprises a C8051 singlechip (4-3), wherein a plurality of output ports of the C8051 singlechip (4-3) are respectively connected with CE1, RST1, CE2 and RST2 of PROM1(8-1) and PROM2 (8-2);
the satellite health data output system (5) comprises a command (5-1) sent to the lower computer, an external information output (5-2), a subsystem parameter correction (5-3) and a satellite health condition prediction output (5-4), the input of the command (5-1) sent to the lower computer is connected with the bus communication (6), the output of the command (5-1) sent to the lower computer is connected with the input of the external information (5-2), and the output of the external information (5-2) is connected with the input of the subsystem parameter correction (5-3) and the input of the satellite health condition prediction output (5-4);
the backup NOR flash memory (7) is connected with a universal port of the FPGA;
the PROM module (8) comprises two PROMs, and the DATA output ends DATA1 and DATA2 of the PROM1(8-1) and PROM2(8-2) are connected with the FPGA (2-3).
2. The management method of the FPGA-based small satellite in-orbit health comprehensive management terminal based on claim 1 is characterized by comprising the following steps of:
the monitoring information acquisition system of the on-orbit satellite collects thermal control subsystem information, propulsion subsystem information, radio frequency tracking subsystem information, energy subsystem information and attitude control subsystem information which are collected by sensors loaded on all subsystems of the on-orbit satellite, and health information data of the satellite is sent to a satellite data analysis and processing system based on FPGA through bus communication;
the FPGA (2-3) processes the real-time health information of the on-orbit satellite sent by bus communication, and stores the processed satellite health information into a satellite health management rule base (3-1), wherein the satellite health management rule base is used for counting and memorizing satellite health information data; one SRAM is used for refreshing and reading data generated in the running process of the FPGA (2-3), and a system program starting code of the FPGA (2-3) is stored in the PROM (2-1);
the on-orbit health assessment and prediction (3-2) collects the satellite health data transmitted by the FPGA (2-3) and the health rules in the health management rule base and sends the data and the health rules to the FPGA (2-3) for analysis and processing to obtain the health condition of the satellite; after the satellite health information is obtained, a processing command is judged and obtained at the same time, the command is sent to a lower computer through bus communication, on one hand, the lower computer sends the processing command to each subsystem of the satellite to correct parameters of the real-time operation of the satellite, and on the other hand, the health condition of the satellite is output and displayed;
the FPGA (2-3) outputs heartbeat signals, the heartbeat signals are connected with a WDG (Wireless data gateway) of a C8051 singlechip and are used for monitoring whether the FPGA works in a normal state or not, if the heartbeat signals are normal, the FPGA (2-3) is proved to work normally, if the health condition is monitored to be abnormal, the FPGA is proved not to be in a normal working state, at the moment, the C8051 can refresh the configuration file into the FPGA (2-3) to realize the restoration of the abnormal condition, in the running process of the FPGA, the C8051 reads back the configuration file of the FPGA in real time and compares the configuration file with an original configuration file, and if the configuration file is abnormal, the configuration file is refreshed back;
reading data needing to be protected in the FPGA (2-3) into a backup NOR flash memory (7) through a memory access instruction before the FPGA (2-3) has an error, and re-reading the stored important data from the backup NOR flash memory (7) after the FPGA (2-3) is powered on again;
the monitoring information acquisition system (1) and the satellite health data output system (5) of the satellite have unpredictable faults in the operation process, so that when the data needing to be received or sent have errors, the data are stored in the PROM module, and when the faults occur, the data are reread from the PROM module.
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