CN106933740A - A kind of star sensor software on-line fault monitoring system and its monitoring method - Google Patents
A kind of star sensor software on-line fault monitoring system and its monitoring method Download PDFInfo
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- G06F11/00—Error detection; Error correction; Monitoring
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Abstract
A kind of star sensor software on-line fault monitoring system and its monitoring method, CPU module will need the star sensor software critical data of transmission to write FPGA module using the mode of address of cache, FPGA detect CPU module transmission handshake level state change after, star sensor software critical data is sent to ground receiving equipment, ground receiving equipment real time parsing simultaneously shows star sensor running software situation, online-monitoring software failure.The present invention realized to the real time on-line monitoring of star sensor software operation state, the failure problems that can occur in positioning software running in time, increased the visuality of star sensor software fault, is improve star sensor software fault and is investigated efficiency.
Description
Technical field
The present invention relates to a kind of star sensor software on-line fault monitoring system and its monitoring method.
Background technology
Satellite attitude measurement is the basis of satellite gravity anomaly.Star sensor is a kind of height using fixed star as observed object
Precision attitude sensor, be it is a kind of be completely independent with autonomous attitude measurement instrument, without being combined with other attitude sensors,
It is capable of achieving the capture of satellite three-axis attitude and tracks, quickly determines appearance and orbit maneuver.Star sensor is with pinpoint in celestial sphere
Star system by the observation to fixed star, identification, is calculated as absolute frame, obtains the attitude of satellite.Due to certainty of measurement
High, real-time, small volume, it is low in energy consumption the advantages of, star sensor is widely used in measuring system of satellite attitude in recent years.
Star sensor software is a kind of embedded from major software, and software size is big, and the function to be completed is more, and algorithm is complicated,
It is the core that star sensor realizes attitude measurement.Star sensor software is different from general common software, and it is quick that it resides in star
In sensor processor, at least more than the 2 years time of in-orbit uninterrupted operation is required after satellite launch, therefore software systems are necessary
High reliability with long-play.
Because the increase of star sensor software size and the increase of complexity, software there may be many defects, this needs logical
Ground long-time, the experiment and test of multi-state are crossed, potential problem in software is constantly found, by changing Software for Design, no
It is disconnected to improve software, failure Producing reason is eradicated, star sensor software reliability is stepped up, will with the design for reaching regulation
Ask.
But in a practical situation, many problems are needed under a certain specific operation, long period uninterrupted operation software
Could reappear, and after power-off restarting, software can recover normal again.Accordingly, it would be desirable to one kind being capable of high efficiency, effective sensitive to star
Device software issue is positioned, convenient that questions and prospect is investigated, and be capable of real-time monitoring software operation state method and
Means.
The content of the invention
The present invention provides a kind of star sensor software on-line fault monitoring system and its monitoring method, realizes to star sensor
The real time on-line monitoring of software operation state, the failure problems that can occur in positioning software running in time, increased star quick
The visuality of sensor software fault, improves star sensor software fault investigation efficiency.
In order to achieve the above object, the present invention provides a kind of star sensor software on-line fault monitoring system, comprising：CPU
Module, FPGA module and ground receiving equipment, FPGA module connect CPU module by data/address bus and address bus, and pass through
Interface connects ground receiving equipment；
Described CPU module will need the star sensor software critical data of transmission by data/address bus and address bus, utilize
The mode of address of cache writes FPGA module, and the level state that FPGA detects the handshake of CPU module transmission changes
Afterwards, star sensor software critical data is sent to ground receiving equipment, ground receiving equipment real time parsing simultaneously shows that star is sensitive
Device running software situation, online-monitoring software failure.
Described FPGA module is included：
Random access memory ram, it passes through data/address bus and address bus connection CPU module, the star for storing CPU module write-in
Sensor software critical data；
Data transmission blocks, its connection random access memory ram and CPU module, when the handshake for detecting CPU module transmission
After level state changes, star sensor software critical data is sent to interface module；
Interface module, its connection data transmission blocks and ground receiving equipment, star sensor software critical data is sent to ground
Face receiving device.
Described interface module includes multiple interface sub-modules.
The present invention also provides a kind of star sensor software on-line fault monitoring method, comprises the steps of：
Step S1, CPU module will need the star sensor software critical data packing of transmission, by data/address bus, address bus
And control signal, using address of cache mode by after packing star sensor software critical data write-in FPGA module in
Machine memory RAM, after CPU module completes the write-in of star sensor software critical data, changes the handshake with FPGA module
Level state；
The level state that data transmission blocks in step S2, FPGA module detect the handshake of CPU module transmission occurs
After change, star sensor software critical data is sent to interface module；
Step S3, interface module send to ground receiving equipment star sensor software critical data；
The star sensor software critical data that step S4, ground receiving equipment real time parsing are received, and show that star is sensitive in real time
Device running software situation, online-monitoring software failure.
In described step S2, data transmission blocks send to the method for interface module star sensor software critical data
Further include：
After step S2.1, upper electricity, data transmission blocks are in idle condition, wait the level state of handshake to change
Enable the arrival of signal；
Step S2.2, detect enable signal after, judge the type of interface sub-module；
Step S2.3, data transmission blocks send corresponding interface module and enable signal to interface according to the type of interface sub-module
Module, and data is activation to be sent to interface module is read from random access memory ram 201；
Step S2.4, data transmission blocks carry out continuous counter to the data amount check for having sent, if in random access memory ram 201
Data be not sent completely, then continue read Data Concurrent give, if being sent completely, into data is activation completion status, give
Go out to send complement mark signal, return to idle condition, wait next arrival for enabling signal.
In described step S3, interface module sends to the method for ground receiving equipment star sensor software critical data
Further include：
Step S3.1, interface module enable signal and decode to the interface module for receiving, and obtain interface for needing to enable
The type of module；
Interface sub-module needed for step S3.2, enable, is sent star sensor software critical data by the interface sub-module
To ground receiving equipment.
The present invention has advantages below and beneficial effect：
1st, caching, transmission, the interface configuration of software critical data are realized using FPGA；
2nd, interface can be configured to serial line interface, CAN interface or 1553B interfaces, flexibly and easily；
3rd, changed using the level of detection cpu signal, realize that what CPU interacted with FPGA data shakes hands, it is to avoid reading and writing data conflict
Generation, improve designed reliability；
4th, the star sensor software on-line fault monitoring system of design is general module, can be applied to all kinds of star sensor products.
Brief description of the drawings
Fig. 1 is a kind of structured flowchart of star sensor software on-line fault monitoring system that the present invention is provided.
Fig. 2 is the data is activation flow chart of data transmission blocks.
Fig. 3 is the interface selection schematic diagram of interface module.
Specific embodiment
Below according to Fig. 1~Fig. 3, presently preferred embodiments of the present invention is illustrated.
As shown in figure 1, the present invention provides a kind of star sensor software on-line fault monitoring system, comprising：CPU module 1,
FPGA module 2 and ground receiving equipment 3, FPGA module 2 connect CPU module 1 by data/address bus and address bus, and by connecing
Mouth connection ground receiving equipment 3.Described CPU module 1 will need the star sensor software critical data of transmission total by data
Line and address bus, FPGA module 2 is write using the mode of address of cache, and FPGA detects the handshake of the transmission of CPU module 1
Level state change after, star sensor software critical data is sent to ground receiving equipment 3, ground receiving equipment 3
Real time parsing simultaneously shows star sensor running software situation, online-monitoring software failure.
Described FPGA module 2 is included：
Random access memory ram 201, it passes through data/address bus and address bus connection CPU module 1, is write for storing CPU module 1
The star sensor software critical data for entering；
Data transmission blocks 202, its connection random access memory ram 201 and CPU module 1, when detect CPU module 1 transmission hold
After the level state of hand signal changes, star sensor software critical data is sent to interface module 203；
Interface module 203, its connection data transmission blocks 202 and ground receiving equipment 3, by star sensor software critical data hair
Deliver to ground receiving equipment 3.
Described interface module 203 includes multiple interface sub-modules, and described interface sub-module is that serial line interface or CAN are total
Line interface or 1553B EBIs or other interfaces.
The present invention also provides a kind of star sensor software on-line fault monitoring method, comprises the steps of：
Step S1, CPU module 1 will need the star sensor software critical data packing of transmission, by data/address bus, address bus
And control signal, using the mode of address of cache by the star sensor software critical data write-in FPGA module 2 after packing
Random access memory ram 201, after CPU module 1 completes the write-in of star sensor software critical data, change is held with FPGA module 2
The level state of hand signal；
Data transmission blocks 202 in step S2, FPGA module 2 detect the level state of the handshake of the transmission of CPU module 1
After changing, star sensor software critical data is sent to interface module 203；
Step S3, interface module 203 send to ground receiving equipment 3 star sensor software critical data；
The star sensor software critical data that step S4, the real time parsing of ground receiving equipment 3 are received, and show that star is sensitive in real time
Device running software situation, online-monitoring software failure.
As shown in Fig. 2 in described step S2, data transmission blocks send to interface star sensor software critical data
The method of module is further included：
After step S2.1, upper electricity, data transmission blocks 202 are in idle condition, wait the level state of handshake to become
The arrival of the enable signal of change；
Step S2.2, detect enable signal after, judge the type of interface sub-module, i.e. according to sign interface type interface
It is required that code is identified using the type of which kind of interface sub-module（Such as：Signal " 00 " characterizes serial line interface, signal " 01 " and characterizes
CAN interface, signal " 10 " characterizes 1553B EBIs）；
Step S2.3, data transmission blocks 202 according to the type of interface sub-module send corresponding interface module enable signal to
Interface module 203, and data is activation to be sent to interface module 203 is read from random access memory ram 201；
The data amount check that step S2.4, data transmission blocks 202 pairs have sent carries out continuous counter, if random access memory ram 201
In data be not sent completely, then continue read Data Concurrent give, if being sent completely, into data is activation completion status,
Be given and be sent completely marking signal, return to idle condition, wait next arrival for enabling signal.
As shown in figure 3, in described step S3, interface module sends to ground receiver star sensor software critical data
The method of equipment is further included：
The interface module that step S3.1, interface module 203 pairs are received enables signal and decodes, and obtains the interface for needing to enable
The type of submodule；
Interface sub-module needed for step S3.2, enable, is sent star sensor software critical data by the interface sub-module
To ground receiving equipment 3.
The present invention has advantages below and beneficial effect：
1st, caching, transmission, the interface configuration of software critical data are realized using FPGA, FPGA inside has RAM, is capable of achieving data
Caching；
2nd, interface can be configured to serial line interface, CAN interface or 1553B interfaces, flexibly and easily；
3rd, changed using the level of detection cpu signal, realize that what CPU interacted with FPGA data shakes hands, it is to avoid reading and writing data conflict
Generation, improve designed reliability；
4th, the star sensor software on-line fault monitoring system of design is general module, can be applied to all kinds of star sensor products.
Although present disclosure is discussed in detail by above preferred embodiment, but it should be appreciated that above-mentioned
Description is not considered as limitation of the present invention.After those skilled in the art have read the above, for of the invention
Various modifications and substitutions all will be apparent.Therefore, protection scope of the present invention should be limited to the appended claims.
Claims (6)
1. a kind of star sensor software on-line fault monitoring system, it is characterised in that include：CPU module（1）, FPGA module（2）
And ground receiving equipment（3）, FPGA module（2）CPU module is connected by data/address bus and address bus（1）, and by interface
Connection ground receiving equipment（3）；
Described CPU module（1）The star sensor software critical data of transmission will be needed by data/address bus and address bus, profit
FPGA module is write with the mode of address of cache（2）, FPGA detects CPU module（1）The level state of the handshake of transmission
After changing, star sensor software critical data is sent to ground receiving equipment（3）, ground receiving equipment（3）Solve in real time
Analyse and show star sensor running software situation, online-monitoring software failure.
2. star sensor software on-line fault monitoring system as claimed in claim 1, it is characterised in that described FPGA module
（2）Comprising：
Random access memory ram（201）, it passes through data/address bus and address bus connection CPU module（1）, for storing CPU module
（1）The star sensor software critical data of write-in；
Data transmission blocks（202）, its connection random access memory ram（201）And CPU module（1）, when detecting CPU module（1）
After the level state of the handshake of transmission changes, star sensor software critical data is sent to interface module（203）；
Interface module（203）, its connection data transmission blocks（202）And ground receiving equipment（3）, star sensor software is crucial
Data is activation is to ground receiving equipment（3）.
3. star sensor software on-line fault monitoring system as claimed in claim 2, it is characterised in that described interface module
（203）Comprising multiple interface sub-modules.
4. a kind of star sensor software on-line fault monitoring system using as described in any one in claim 1-3 enters planet
The method of sensor software on-line fault monitoring, it is characterised in that comprise the steps of：
Step S1, CPU module will need the star sensor software critical data packing of transmission, by data/address bus, address bus
And control signal, using address of cache mode by after packing star sensor software critical data write-in FPGA module in
Machine memory RAM, after CPU module completes the write-in of star sensor software critical data, changes the handshake with FPGA module
Level state；
The level state that data transmission blocks in step S2, FPGA module detect the handshake of CPU module transmission occurs
After change, star sensor software critical data is sent to interface module；
Step S3, interface module send to ground receiving equipment star sensor software critical data；
The star sensor software critical data that step S4, ground receiving equipment real time parsing are received, and show that star is sensitive in real time
Device running software situation, online-monitoring software failure.
5. star sensor software on-line fault monitoring method as claimed in claim 4, it is characterised in that described step S2
In, star sensor software critical data is sent to the method for interface module and further included by data transmission blocks：
After step S2.1, upper electricity, data transmission blocks are in idle condition, wait the level state of handshake to change
Enable the arrival of signal；
Step S2.2, detect enable signal after, judge the type of interface sub-module；
Step S2.3, data transmission blocks send corresponding interface module and enable signal to interface according to the type of interface sub-module
Module, and data is activation to be sent to interface module is read from random access memory ram 201；
Step S2.4, data transmission blocks carry out continuous counter to the data amount check for having sent, if in random access memory ram 201
Data be not sent completely, then continue read Data Concurrent give, if being sent completely, into data is activation completion status, give
Go out to send complement mark signal, return to idle condition, wait next arrival for enabling signal.
6. star sensor software on-line fault monitoring method as claimed in claim 5, it is characterised in that described step S3
In, star sensor software critical data is sent to the method for ground receiving equipment and further included by interface module：
Step S3.1, interface module enable signal and decode to the interface module for receiving, and obtain interface for needing to enable
The type of module；
Interface sub-module needed for step S3.2, enable, is sent star sensor software critical data by the interface sub-module
To ground receiving equipment.
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109141403A (en) * | 2018-08-01 | 2019-01-04 | 上海航天控制技术研究所 | A kind of image processing system and its method of the access of star sensor wicket |
| CN109212343A (en) * | 2018-08-08 | 2019-01-15 | 上海航天控制技术研究所 | A kind of star sensor digital signal detection circuit system |
| CN109240185A (en) * | 2018-11-23 | 2019-01-18 | 上海航天控制技术研究所 | A kind of in-orbit maintenance system of star sensor and method |
| CN109540128A (en) * | 2018-11-15 | 2019-03-29 | 上海航天控制技术研究所 | A kind of in-orbit autonomous configuration method of star sensor |
| CN109596122A (en) * | 2018-12-06 | 2019-04-09 | 上海航天控制技术研究所 | A kind of universal star sensor data test processor |
| CN110648524A (en) * | 2019-08-27 | 2020-01-03 | 上海航天控制技术研究所 | Multi-probe star sensor data transmission fault monitoring and autonomous recovery method |
| CN114665953A (en) * | 2022-04-15 | 2022-06-24 | 中国电子科技集团公司第五十四研究所 | Anomaly detection and reproduction method for satellite communication system |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101320524A (en) * | 2008-04-22 | 2008-12-10 | 北京航空航天大学 | Multiprocessor real-time simulation platform |
| CN101726319A (en) * | 2009-12-17 | 2010-06-09 | 哈尔滨工业大学 | Star sensor simulation method with function of injecting parameters |
| CN102735264A (en) * | 2012-06-18 | 2012-10-17 | 北京控制工程研究所 | Star sensor fault simulation system |
| CN106404003A (en) * | 2016-11-18 | 2017-02-15 | 上海航天控制技术研究所 | Test method and test system based on earth signal analog |
-
2017
- 2017-03-15 CN CN201710154428.5A patent/CN106933740B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101320524A (en) * | 2008-04-22 | 2008-12-10 | 北京航空航天大学 | Multiprocessor real-time simulation platform |
| CN101726319A (en) * | 2009-12-17 | 2010-06-09 | 哈尔滨工业大学 | Star sensor simulation method with function of injecting parameters |
| CN102735264A (en) * | 2012-06-18 | 2012-10-17 | 北京控制工程研究所 | Star sensor fault simulation system |
| CN106404003A (en) * | 2016-11-18 | 2017-02-15 | 上海航天控制技术研究所 | Test method and test system based on earth signal analog |
Non-Patent Citations (1)
| Title |
|---|
| 梁国龙 等: "星敏感器地基评测系统的设计研究", 《红外》 * |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109141403A (en) * | 2018-08-01 | 2019-01-04 | 上海航天控制技术研究所 | A kind of image processing system and its method of the access of star sensor wicket |
| CN109212343A (en) * | 2018-08-08 | 2019-01-15 | 上海航天控制技术研究所 | A kind of star sensor digital signal detection circuit system |
| CN109540128A (en) * | 2018-11-15 | 2019-03-29 | 上海航天控制技术研究所 | A kind of in-orbit autonomous configuration method of star sensor |
| CN109540128B (en) * | 2018-11-15 | 2020-04-14 | 上海航天控制技术研究所 | On-orbit autonomous configuration method of star sensor |
| CN109240185A (en) * | 2018-11-23 | 2019-01-18 | 上海航天控制技术研究所 | A kind of in-orbit maintenance system of star sensor and method |
| CN109240185B (en) * | 2018-11-23 | 2020-03-24 | 上海航天控制技术研究所 | Star sensor on-orbit maintenance system and method |
| CN109596122A (en) * | 2018-12-06 | 2019-04-09 | 上海航天控制技术研究所 | A kind of universal star sensor data test processor |
| CN110648524A (en) * | 2019-08-27 | 2020-01-03 | 上海航天控制技术研究所 | Multi-probe star sensor data transmission fault monitoring and autonomous recovery method |
| CN110648524B (en) * | 2019-08-27 | 2020-08-07 | 上海航天控制技术研究所 | Multi-probe star sensor data transmission fault monitoring and autonomous recovery method |
| CN114665953A (en) * | 2022-04-15 | 2022-06-24 | 中国电子科技集团公司第五十四研究所 | Anomaly detection and reproduction method for satellite communication system |
| CN114665953B (en) * | 2022-04-15 | 2024-01-26 | 中国电子科技集团公司第五十四研究所 | Anomaly detection and reproduction method for satellite communication system |
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