CN109213632A - A kind of satellite borne electronic system and reinforcement means of radiation tolerance design - Google Patents
A kind of satellite borne electronic system and reinforcement means of radiation tolerance design Download PDFInfo
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- CN109213632A CN109213632A CN201810965871.5A CN201810965871A CN109213632A CN 109213632 A CN109213632 A CN 109213632A CN 201810965871 A CN201810965871 A CN 201810965871A CN 109213632 A CN109213632 A CN 109213632A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F11/00—Error detection; Error correction; Monitoring
- G06F11/07—Responding to the occurrence of a fault, e.g. fault tolerance
- G06F11/14—Error detection or correction of the data by redundancy in operation
- G06F11/1479—Generic software techniques for error detection or fault masking
Abstract
The present invention proposes a kind of satellite borne electronic system of radiation tolerance design.The satellite borne electronic system includes system-monitoring module, nonvolatile storage, programmable gate array and OMAP, wherein system-monitoring module is responsible for monitoring programmable gate array and whether OMAP occurs single-particle inversion, programmable gate array is responsible for monitoring OMAP state and oneself state, the electrification reset to OMAP is guided, nonvolatile storage is responsible for the program and data that redundancy saves programmable gate array and OMAP.The satellite borne electronic system can restore in time after breaking down, and can update the program and data of programmable gate array configuration bit stream and OMAP, and the program and data of chip are stored in nonvolatile storage in system, and program and data have high reliability.By electrification reset and system monitoring, the single particle effect of electronic system generation can be repaired, the radiation resistance and reliability of entire satellite borne electronic system are promoted.
Description
Technical field
The present invention proposes a kind of satellite borne electronic system of radiation tolerance design, belongs to satellite reliability field, can be used for
The radiation tolerance design of satellite borne electronic system.
Background technique
Single particle effect mainly includes SEU (single-particle inversion single event upset), SET (single-ion transient state
Pulse single event transient), SEL (locking single particle single event latch) etc., it is wherein most main when SEU
The form of expression wanted.For SRAM type programmable gate array, due to the SRAM technique that it is used, easily generation single-particle effect
It answers, especially single-particle inversion.From the point of view of the ratio of single-particle inversion, specific gravity shared by configuration memory is maximum, is secondly LUT
RAM, bulk RAM and the trigger of type, other single particle effects ratio as shared by SET, SEFI is smaller, configuration memory
SEU is the main form of expression of programmable gate array single particle effect failure.
Satellite borne electronic system is responsible for Satellite operation management, signal transmitting and receiving, demodulation, operation packing, acquisition and tracking etc., is
Most crucial component on satellite.Mainly by FPGA (Field Programmable GateArray, programmable gate array),
The chips such as DSP, ADC, DAC are built for main components.And these LSI devices, especially SRAM (Static
RAM, Static RAM) type FPGA and DSP be easily by space S EE's (single event effect, single particle effect)
It influences.
The satellite borne electronic system of FPGA+DSP framework is a very classical framework on satellite using many years,
But as the new application demands such as Internet of Things, short data distribution occur, a kind of new framework is needed more preferably to realize to a large amount of
User terminal signal capture, tracking, processing, therefore it is TI (Dezhou instrument that a kind of new FPGA+OMAP system architecture, which is suggested .OMAP,
Device Texas Instruments) a heterogeneous dual-core processor newly released of company, it is integrated in ARM kernel and DSP in chip
Core.ARM kernel has powerful transaction management ability, is responsible for receiving trace demodulation, the task schedule, ARM system management of signal
And condition monitoring.DSP core realizes fast Acquisition algorithm, dsp system management and condition monitoring, passes through core Embedded between double-core
Sharing Memory Realization communication, without additional external circuit, simplifies the design of chip periphery circuit.The operation of OMAP needs journey
The program in sequence area, while being also required to the data of data field.The guidance of OMAP needs to draw the program and data of OMAP again
It leads.The ARM of OMAP is responsible for system administration and task schedule, and DSP is used for signal processing, and programmable gate array is responsible for system prison
Control, Some digital signal processing, communication function, whole system low-power consumption, low cost, high integration.But still due to the system
It operates among the severe space of radiation environment, and satellite borne electronic system has the single-particles Sensitive Apparatus such as FPGA, DSP, ARM,
Therefore it is directed to the satellite borne electronic system of this new construction, needs a kind of new method to carry out radiation hardening to system, to mention
Rise system reliability.Patent name is " the spaceborne processing platform with anti-single particle effect capability ", number of patent application are as follows:
The patent of invention of CN200910043422.6 discloses a kind of spaceborne processing platform with anti-single particle effect capability, it includes
By highly reliable monitoring unit, nonvolatile memory, field programmable gate array and more than one DSP, highly reliable prison
It controls unit and other each sections to interconnect using local bus, high-speed bus is used between field programmable gate array and DSP
Interconnection；The highly reliable monitoring unit is for detecting the single-particle inversion in field programmable gate array and DSP
And reparation.Although the present invention provides, a kind of structural principle is simple, spaceborne processing platform, the platform exist easily to operate
Such as the problem of stability difference etc..Due to being related to multiple functions and multiple-working mode, and satellite borne electronic system need to connect at any time
The data for carrying out user terminal are received, the reliability of satellite borne electronic system is related to the success or failure of whole satellite.How spaceborne electricity is monitored
The state of subsystem core device, and the failure of appearance is handled in time, it is the essential function of satellite borne electronic system.
Summary of the invention
The present invention proposes a kind of satellite borne electronic system of radiation tolerance design.The invention is directed to newest FPGA+OMAP
Satellite borne electronic system framework has carried out radiation hardening.Unified monitoring is carried out to satellite borne electronic system by system-monitoring module,
Load and condition monitoring are guided to OMAP using programmable gate array simultaneously, by monitoring and quickly repairing in time layer by layer,
System has anti-single particle effect capability, and system does not influence satellite borne electronic system to the reparation of single particle effect and works normally.
The technical solution of the present invention is to provide a kind of satellite borne electronic system based on radiation tolerance design, feature exists
In: it include: system-monitoring module, nonvolatile storage, field programmable gate array and more than one OMAP；Wherein:
System-monitoring module respectively with nonvolatile storage, field programmable gate array monitoring module,
OMAP loading module and OMAP are connected；For the configuration management of field programmable gate array and OMAP, realization scene can be compiled
The condition monitoring of journey logic gate array and OMAP, configuration bit stream refresh and OMAP resets；
Nonvolatile storage is for saving scene programmable gate array original configuration data and OMAP program and data；
Field programmable gate array includes OMAP loading module and monitoring module, wherein OMAP loading module
Connection system-monitoring module and OMAP, OMAP loading module are responsible for reading the OMAP journey of nonvolatile storage through system-monitoring module
The reconfiguration status that sequence and data guide load to OMAP, monitor programmable gate array；Monitoring module connection
OMAP and system-monitoring module, monitoring module are responsible for monitoring programmable gate array operating status and OMAP operation shape
State is then fed into system-monitoring module.
Nonvolatile storage can do three moulds to programmable gate array original configuration bit stream and OMAP program and data
Redundancy.
Further, nonvolatile storage is flash storage.
Further, field programmable gate array can be by HPI or EMIF interface to the program area sum number of OMAP
Load is guided according to area.
The present invention also provides a kind of anti-radiation adding methods of satellite borne electronic system, which comprises the following steps:
Step 1, system-monitoring module start to configure programmable gate array；
Step 2, system-monitoring module read the programmable gate array original configuration position that nonvolatile storage is saved
Stream, will test that the write-in of small group interface is programmable to patrol after the judgement of original configuration bit stream triplication redundancy by parallel bus or connection action
Collect gate array；
After step 3, configuration bit stream are completely written to programmable gate array, OMAP guiding module transmits a signal to system prison
It controls module confirmation programmable gate array configuration to complete, enters step 4；Continue if the not sent signal of OMAP guiding module
Step 2；
Step 4, system-monitoring module start to reset the OMAP of satellite borne electronic system；
After step 5, all OMAP of completion reset, satellite borne electronic system restarts to work normally.
Further, in step 4, resetted that specific step is as follows to the OMAP of one or more:
Step 4.1, system-monitoring module read the program and data of first OMAP of the storage in nonvolatile storage,
It is placed in the data/address bus of programmable gate array；
Step 4.2, the DSP program of first OMAP of programmable gate array reading and data simultaneously pass through HPI or EMIF
The DSP of first OMAP is written in bus；
Step 4.3, when system-monitoring module receive first OMAP DSP program and data write-in complete signal after,
Start to control the ARM configuration data of first OMAP of programmable gate array reading and is written first by HPI bus
The ARM of OMAP；Otherwise step 4.3 is repeated；
Step 4.4, when system-monitoring module receive first OMAP ARM configuration data write-in complete signal after, such as
Fruit OMAP quantity is 1, then the reset of OMAP is completed, then if OMAP quantity is greater than 1, enters step 4.5；
Step 4.5 repeats step 4.1~step 4.5, finishes until all OMAP all reset.
Further, the signal that the monitoring module of programmable gate array is monitored is the ARM's and DSP of OMAP
The state of watchdog signal and programmable gate array.
Beneficial effects of the present invention:
(1) system-monitoring module guidance whole system operation when powering on；
(2) satellite borne electronic system finds and restores in time after breaking down；
(3) program and data of programmable gate array configuration bit stream and OMAP can be updated；
(4) program and data of the chip (programmable gate array, OMAP) of satellite borne electronic system are stored in non-volatile
In memory, program and data have high reliability；
(5) radiation resistance and operational reliability of entire satellite borne electronic system are promoted.
Detailed description of the invention
Attached drawing 1 is the satellite borne electronic system structure and signal flow of a kind of radiation tolerance design；
Attached drawing 2 is that a kind of satellite borne electronic system of radiation tolerance design reboots configuration flow；
Attached drawing 3 is the process resetted to the OMAP of one or more.
Specific embodiment
The present invention is described in further details below with reference to Figure of description 1-2 and specific embodiment.
As shown in Fig. 1, this embodiment offers a kind of satellite borne electronic system based on radiation tolerance design, spaceborne electricity
Subsystem is after radiation tolerance design, comprising: system-monitoring module, nonvolatile storage, field programmable gate battle array
Column and more than one OMAP；Wherein:
System-monitoring module respectively with nonvolatile storage, field programmable gate array monitoring module,
OMAP loading module and OMAP are connected；For the configuration management of field programmable gate array and OMAP, realization scene can be compiled
The condition monitoring of journey logic gate array and OMAP, configuration bit stream refresh and OMAP resets；
Nonvolatile storage is for saving scene programmable gate array original configuration data and OMAP program and data；
Field programmable gate array includes OMAP loading module and monitoring module, wherein OMAP loading module
Connection system-monitoring module and OMAP, OMAP loading module are responsible for reading the OMAP journey of nonvolatile storage through system-monitoring module
The reconfiguration status that sequence and data guide load to OMAP, monitor programmable gate array；Monitoring module connection
OMAP and system-monitoring module, monitoring module are responsible for monitoring programmable gate array operating status and OMAP operation shape
State is then fed into system-monitoring module.
Nonvolatile storage can do three moulds to programmable gate array original configuration bit stream and OMAP program and data
Redundancy.
Nonvolatile storage is preferably flash storage.
Field programmable gate array can pass through HPI (hostport interface) or EMIF (external
Memory interface external memory expansion interface) interface guides load to the program area of OMAP and data field.
In the work of satellite borne electronic system, the work of programmable gate array and DSP, ARM of OMAP is constantly monitored
State, if it find that DSP the and ARM operation irregularity of programmable gate array and OMAP, then reboot matching to system
It sets, reboots the process that configuration is exactly radiation hardening.
The embodiment additionally provides a kind of anti-radiation adding method of satellite borne electronic system, specifically includes the following steps:
Step 1, system-monitoring module start to configure programmable gate array；
Step 2, system-monitoring module read the programmable gate array original configuration position that nonvolatile storage is saved
Stream will pass through SelectMap (parallel bus)/JTAG (connection action test group) after the judgement of original configuration bit stream triplication redundancy
Programmable gate array is written in interface；
After step 3, configuration bit stream are completely written to programmable gate array, OMAP guiding module transmits a signal to system prison
It controls module confirmation programmable gate array configuration to complete, enters step 4；Continue if the not sent signal of OMAP guiding module
Step 2；
Step 4, system-monitoring module start to reset the OMAP of satellite borne electronic system；
As shown in figure 3, being resetted in step 4 to the OMAP of one or more, specific step is as follows:
Step 4.1 system-monitoring module reads the program and data of first OMAP of the storage in nonvolatile storage,
It is placed in the data/address bus of programmable gate array；
Step 4.2, the DSP program of first OMAP of programmable gate array reading and data simultaneously pass through HPI or EMIF
The DSP of first OMAP is written in bus；
Step 4.3, when system-monitoring module receive first OMAP DSP program and data write-in complete signal after,
Start to control the ARM configuration data of first OMAP of programmable gate array reading and is written first by HPI bus
The ARM of OMAP；Otherwise step 4.3 is repeated；
Step 4.4, when system-monitoring module receive first OMAP ARM configuration data write-in complete signal after, such as
Fruit OMAP quantity is 1, then the reset of OMAP is completed.Then if OMAP quantity is greater than 1,4.5 are entered step；
Step 4.5 repeats step 4.1~step 4.5, finishes until all OMAP all reset.
After step 5, all OMAP of completion reset, satellite borne electronic system restarts to work normally.
Upon power-up of the system, first boot configuration also is carried out to system, i.e. execution step 1~step 5.
In this embodiment, the signal that the monitoring module of programmable gate array is monitored be OMAP ARM and
The watchdog signal of DSP and the state of programmable gate array.
Monitoring for monitoring module monitoring can compile logic gate array, once it notes abnormalities, programmable gate array
With regard to stopping sending watchdog signal, then system-monitoring module thinks system exception, i.e., carries out rebooting configuration to system.
The regular circling measurment ARM of the ARM and DSP of OMAP and DSP program executive condition stop house dog and feed if abnormal
Dog pulse, sends SEU status signal to system-monitoring module, and then system-monitoring module thinks system exception, i.e., to system into
Row reboots configuration.
The self-operating condition monitoring and restoration methods of OMAP be, every the set time and without OMAP do not communicate into
The program area of the inside of ARM and DSP program is carried out total check by journey, and the result and known results of calculating compare calculating,
If incorrect, stop ARM and DSP watchdog signal, then the monitoring module of programmable gate array does not receive
The watchdog signal to come to OMAP, is then interrupted to the watchdog signal of system-monitoring module, then system-monitoring module is recognized
For system exception, i.e., to being to carry out rebooting configuration.
System-monitoring module has a reset signal to OMAP, and OMAP loads mould by OMAP after receiving reset signal
Block reloads the program and data of ARM and DSP in OMAP, resets to itself.
Although the present invention has been described by way of example and in terms of the preferred embodiments, embodiment is not for the purpose of limiting the invention.Not
It is detached from the spirit and scope of the present invention, any equivalent change or retouch done also belongs to the protection scope of the present invention.Cause
This protection scope of the present invention should be based on the content defined in the claims of this application.
Claims (6)
1. a kind of satellite borne electronic system based on radiation tolerance design, it is characterised in that it is characterized by comprising: system monitoring
Module, nonvolatile storage, field programmable gate array and more than one OMAP；Wherein:
System-monitoring module adds with nonvolatile storage, the monitoring module of field programmable gate array, OMAP respectively
It carries module and OMAP is connected；For the configuration management of field programmable gate array and OMAP, field programmable logic is realized
The condition monitoring of gate array and OMAP, configuration bit stream refresh and OMAP resets；
Nonvolatile storage is for saving scene programmable gate array original configuration data and OMAP program and data；
Field programmable gate array includes OMAP loading module and monitoring module, wherein the connection of OMAP loading module
System-monitoring module and OMAP, OMAP loading module be responsible for through system-monitoring module read nonvolatile storage OMAP program and
The reconfiguration status that data guide load to OMAP, monitor programmable gate array；Monitoring module connects OMAP
And system-monitoring module, monitoring module are responsible for monitoring programmable gate array operating status and OMAP operating status, so
It is sent into system-monitoring module afterwards.
Nonvolatile storage can do triplication redundancy to programmable gate array original configuration bit stream and OMAP program and data.
2. the satellite borne electronic system according to claim 1 based on radiation tolerance design, it is characterised in that: non-volatile to deposit
Reservoir is flash storage.
3. the satellite borne electronic system according to claim 1 based on radiation tolerance design, it is characterised in that: scene can compile
Journey logic gate array can guide load to the program area of OMAP and data field by HPI or EMIF interface.
4. a kind of anti-radiation adding method of satellite borne electronic system, which comprises the following steps:
Step 1, system-monitoring module start to configure programmable gate array；
Step 2, system-monitoring module read the programmable gate array original configuration bit stream that nonvolatile storage is saved, will
Small group interface is tested by parallel bus or connection action after the judgement of original configuration bit stream triplication redundancy, programmable gate is written
Array；
After step 3, configuration bit stream are completely written to programmable gate array, OMAP guiding module transmits a signal to system monitoring mould
Block confirms that programmable gate array configuration is completed, and enters step 4；Continue step if the not sent signal of OMAP guiding module
2；
Step 4, system-monitoring module start to reset the OMAP of satellite borne electronic system；
After step 5, all OMAP of completion reset, satellite borne electronic system restarts to work normally.
5. the anti-radiation adding method of satellite borne electronic system according to claim 4, it is characterised in that: in step 4, to one or
Above OMAP is resetted, and specific step is as follows:
Step 4.1, system-monitoring module read the program and data of first OMAP of the storage in nonvolatile storage, place
In the data/address bus of programmable gate array；
Step 4.2, the DSP program of first OMAP of programmable gate array reading and data simultaneously pass through HPI or EMIF bus
The DSP of first OMAP is written；
Step 4.3, when system-monitoring module receive first OMAP DSP program and data write-in complete signal after, start
Programmable gate array is controlled to read the ARM configuration data of first OMAP and be written first OMAP's by HPI bus
ARM；Otherwise step 4.3 is repeated；
Step 4.4, when system-monitoring module receive first OMAP ARM configuration data write-in complete signal after, if
OMAP quantity is 1, then the reset of OMAP is completed, then if OMAP quantity is greater than 1, enters step 4.5；
Step 4.5 repeats step 4.1~step 4.5, finishes until all OMAP all reset.
6. the anti-radiation adding method of satellite borne electronic system according to claim 5, it is characterised in that: programmable gate array
The signal that is monitored of monitoring module be OMAP ARM and DSP watchdog signal and programmable gate array
State.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110427338A (en) * | 2019-07-05 | 2019-11-08 | 中国科学院电子学研究所 | Spaceborne field programmable gate array and its reliability reinforcement means |
| CN117687050A (en) * | 2024-02-01 | 2024-03-12 | 中国科学院国家空间科学中心 | Radiation-resistant method and device for commercial spot occultation detector |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101551762A (en) * | 2009-05-15 | 2009-10-07 | 中国人民解放军国防科学技术大学 | Spaceborne processing platform resisting single event effect |
| CN101551763A (en) * | 2009-05-15 | 2009-10-07 | 中国人民解放军国防科学技术大学 | Method and device for repairing single event upset in field programmable logic gate array |
| CN101561477A (en) * | 2009-05-15 | 2009-10-21 | 中国人民解放军国防科学技术大学 | Method and device for testing single event upset in in-field programmable logic gate array |
| CN103971732A (en) * | 2014-04-30 | 2014-08-06 | 浙江大学 | Method and system for monitoring single event upset effect of FPGA (field programmable gate array) and correcting reloading |
| US20160274816A1 (en) * | 2015-03-17 | 2016-09-22 | Gowin Semiconductor Corporation, Ltd. | Programmable Logic Device With On-Chip User Non-Volatile Memory |
| CN106557346A (en) * | 2016-11-24 | 2017-04-05 | 中国科学院国家空间科学中心 | A kind of primary particle inversion resistant star-carried data processing system and method |
-
2018
- 2018-08-23 CN CN201810965871.5A patent/CN109213632B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101551762A (en) * | 2009-05-15 | 2009-10-07 | 中国人民解放军国防科学技术大学 | Spaceborne processing platform resisting single event effect |
| CN101551763A (en) * | 2009-05-15 | 2009-10-07 | 中国人民解放军国防科学技术大学 | Method and device for repairing single event upset in field programmable logic gate array |
| CN101561477A (en) * | 2009-05-15 | 2009-10-21 | 中国人民解放军国防科学技术大学 | Method and device for testing single event upset in in-field programmable logic gate array |
| CN103971732A (en) * | 2014-04-30 | 2014-08-06 | 浙江大学 | Method and system for monitoring single event upset effect of FPGA (field programmable gate array) and correcting reloading |
| US20160274816A1 (en) * | 2015-03-17 | 2016-09-22 | Gowin Semiconductor Corporation, Ltd. | Programmable Logic Device With On-Chip User Non-Volatile Memory |
| CN106557346A (en) * | 2016-11-24 | 2017-04-05 | 中国科学院国家空间科学中心 | A kind of primary particle inversion resistant star-carried data processing system and method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110427338A (en) * | 2019-07-05 | 2019-11-08 | 中国科学院电子学研究所 | Spaceborne field programmable gate array and its reliability reinforcement means |
| CN117687050A (en) * | 2024-02-01 | 2024-03-12 | 中国科学院国家空间科学中心 | Radiation-resistant method and device for commercial spot occultation detector |
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