CN113946532A - Satellite-borne 1553B control bus failure protection method - Google Patents
Satellite-borne 1553B control bus failure protection method Download PDFInfo
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- CN113946532A CN113946532A CN202110988293.9A CN202110988293A CN113946532A CN 113946532 A CN113946532 A CN 113946532A CN 202110988293 A CN202110988293 A CN 202110988293A CN 113946532 A CN113946532 A CN 113946532A
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/42—Bus transfer protocol, e.g. handshake; Synchronisation
- G06F13/4282—Bus transfer protocol, e.g. handshake; Synchronisation on a serial bus, e.g. I2C bus, SPI bus
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F1/00—Details not covered by groups G06F3/00 - G06F13/00 and G06F21/00
- G06F1/24—Resetting means
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F13/00—Interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F13/38—Information transfer, e.g. on bus
- G06F13/382—Information transfer, e.g. on bus using universal interface adapter
- G06F13/385—Information transfer, e.g. on bus using universal interface adapter for adaptation of a particular data processing system to different peripheral devices
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F2213/00—Indexing scheme relating to interconnection of, or transfer of information or other signals between, memories, input/output devices or central processing units
- G06F2213/0012—High speed serial bus, e.g. IEEE P1394
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Abstract
A satellite-borne 1553B control bus failure protection method is characterized in that a cold and hot reset identifier and an autonomous reset count are stored in a storage module of a satellite data transmission control unit; when the data transmission control unit is powered off and then powered on, the cold and hot reset mark is a cold reset mark, and the data transmission control unit enters a full-function mode; when the 1553B control bus is abnormal in function, the data transmission control unit cannot enter telemetering interruption, and at the moment, the cold and hot reset identifier is a hot reset identifier; the data transmission control unit carries out autonomous reset, the number of times of the autonomous reset is less than a set threshold value N, the data transmission control unit realizes the autonomous reset, and the number of times of the autonomous reset is reset; and if the continuous self-reset times are larger than or equal to the set threshold value N, the data transmission control unit enters a minimum system mode. The invention can intelligently judge the failure of the 1553B control bus, autonomously enter a minimum system mode without ground intervention, and ensure that the data transmission control unit can still execute the most basic operation under the condition of failure of the 1553B control bus.
Description
Technical Field
The invention belongs to the technical field of satellite-borne data transmission control, and relates to a satellite-borne 1553B control bus failure protection method.
Background
The 1553B control bus is a data transmission bus with high reliability and good real-time performance, is suitable for working in severe environments with strong vibration, high noise, much dust and large temperature change, is widely used in aerospace equipment and weaponry, and particularly has no chance of manual maintenance once a satellite computer control system on satellite-borne equipment such as a satellite, a rocket, an airship and the like fails, so that the reliability of the satellite-borne equipment needs to be improved to the maximum extent in the design process.
In the prior art, in order to improve the operation reliability of the data transmission control unit, the data transmission control unit is generally provided with two systems capable of working independently, wherein one system is a full-function mode system, the other system is a minimum-function mode system, the full-function mode system can support all functional requirements of the satellite borne equipment under the normal working condition, the minimum-function mode system can only realize the most basic and necessary functions of remote measurement and remote control, and the two systems are used in a matched manner, so that the reliability of the satellite borne equipment is greatly improved. However, in the on-orbit operation process of the satellite-borne equipment, the interface chip of the 1553B control bus is damaged, so that the data transmission control unit cannot receive the bus instruction, and the switching between the two systems in different modes cannot be realized in the modes of remote control and the like under necessary conditions, so that the data transmission control unit cannot work normally, and the task execution is influenced.
Disclosure of Invention
The technical problem solved by the invention is as follows: the satellite-borne 1553B control bus failure protection method overcomes the defects of the prior art, provides a satellite-borne 1553B control bus failure protection method, and solves the technical problem that the task execution is affected because a data transmission control unit cannot work normally under the condition that an interface chip of a 1553B control bus in the prior art is damaged.
The technical scheme of the invention is as follows:
a satellite-borne 1553B control bus failure protection method comprises the following steps:
a cold and hot reset identifier and an autonomous reset count are stored in a data transmission control unit storage module;
when the data transmission control unit is powered off and then powered on, the cold and hot reset mark is a cold reset mark, when the data transmission control unit identifies that the cold and hot reset mark is the cold reset mark, the data transmission control unit judges that the data transmission control unit is in cold start, and the data transmission control unit enters a full-function mode;
in a full-function mode, the data transmission control unit executes telemetering interruption periodically according to a signal of a 1553B control bus, when the 1553B control bus is abnormal in function, the data transmission control unit cannot enter telemetering interruption, and at the moment, the cold and hot reset identifier is a hot reset identifier;
when the data transmission control unit identifies that the cold and hot reset mark is the hot reset mark, performing autonomous reset, wherein the autonomous reset count is +1 every time the autonomous reset is performed, and if the continuous autonomous reset times are less than a set threshold value N, the data transmission control unit realizes the autonomous reset and simultaneously clears the autonomous reset count; and if the continuous self-reset times are larger than or equal to the set threshold value N, the data transmission control unit enters a minimum system mode.
And after the data transmission control unit enters a minimum system mode, executing a playback string instruction, and after the execution of the playback string instruction is finished, circularly feeding the dogs by the data transmission control unit to be in a standby state.
A timer is arranged in the data transmission control unit, and M second counting is stored in the storage module;
in the minimum system mode, when the data transmission control unit is in a standby state, judging the M second count through a timer, wherein the M second count is +1 when the timer counts M seconds, if the M second count is greater than a pre-designed count value P, the data transmission control unit enters a dog bite trap, and the data transmission control unit waits for the dog bite reset;
in the dog biting reset process, the data transmission control unit automatically resets once every time the timer counts M seconds, the data transmission control unit automatically resets once every time the data transmission control unit automatically resets, the number of times of the automatic reset is counted by +1, when the number of times of the automatic reset is larger than or equal to a set dog biting reset counting threshold value Q, the data transmission control unit enters a minimum system mode again to execute a playback string instruction, the M seconds is counted and reset, and the number of times of the automatic reset is counted and reset.
In the storage module, three variables of the cold and hot reset identification, the autonomous reset count and the M second count are stored in three parts respectively, the three parts are modified when modification is needed each time, and the three parts are read out by two when judgment is needed.
After the data transmission control unit enters a minimum system mode, when a ground sends a data transmission power-off command and a data transmission power-on command, the data transmission control unit is cold started, and when the data transmission control unit is cold started, the self-reset counting is cleared.
The data transmission control unit receives an instruction of a ground or upper computer through a 1553B control bus; under the full-function mode, the housekeeping computer sends corresponding instructions to the data transmission control unit according to the instructions of the ground or the upper computer to control the data transmission control unit to realize complete functions; the minimum system mode is an emergency state in which the data transmission control unit needs to realize basic functions.
The storage module is built in the digital control unit.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the satellite-borne 1553B control bus failure protection method, the cold and hot reset identification and the automatic reset count are stored in the storage module of the data transmission control unit, when the 1553B control bus is abnormal in function, the satellite-borne 1553B control bus failure protection method can autonomously control the data transmission control unit to enter a minimum system mode according to the cold and hot reset identification and the automatic reset count, and therefore the data transmission control unit can be guaranteed to achieve the most basic function. The satellite-borne 1553B control bus failure protection method is characterized in that the 1553B control bus failure is intelligently judged, a minimum system mode is automatically entered, ground intervention is not needed, the data transmission control unit can still execute the most basic operation under the condition that the 1553B control bus fails, and task execution is guaranteed.
2. Because the data transmission control unit can enter the minimum system mode after continuous self-reset for more than a plurality of times, the invention filters the recoverable fault of the data transmission control unit under the abnormal condition, avoids the 1553B control bus from entering the minimum system mode without real failure, and improves the reliability.
Drawings
FIG. 1 is a schematic diagram of the hardware connection principle of the present invention;
FIG. 2 is a schematic diagram of the data transfer control unit entering a minimum system mode;
FIG. 3 is a flow chart of minimum system mode action execution of the data transfer control unit;
fig. 4 is a flowchart of the standby state operation of the data transfer control unit in the minimum system mode.
Detailed Description
The invention is further elucidated with reference to the drawing.
Example 1:
a satellite-borne 1553B control bus failure protection method, please refer to fig. 1.
As shown in fig. 1, in this embodiment, the satellite-borne 1553B control bus failure protection method is implemented by a built-in storage module of a data transmission control unit, after the data transmission control unit is started, the data transmission control unit receives an instruction and sends telemetry through a 1553B control bus, and the 1553B control bus is used for transmitting the instruction of a satellite computer to the data transmission control unit and controlling the data transmission control unit through the instruction to implement a related function. Meanwhile, 1553B controls the bus to acquire the telemetering of the data transmission control unit and send the telemetering to the satellite computer.
The data transmission control unit is provided with a main control chip, for example, the main control chip can be an 80C32 single chip microcomputer, and the data transmission control unit is also provided with an interface chip of a 1553B control bus, for example, the interface chip can be a B65170 chip. The main control chip is internally provided with two sets of systems which are respectively in a full-function mode and a minimum system mode, and the data transmission control unit can receive the command of the 1553B control bus to realize the complete function in the full-function mode. The minimum system mode is a basic function which needs to be realized by the data transmission control unit in an emergency state.
The storage module can adopt a KW064 storage chip, a cold and hot reset identifier and an automatic reset count are stored in the storage module, the data transmission control unit is internally provided with the storage module, and according to the cold and hot reset identifier and the automatic reset count, the satellite-borne 1553B control bus failure protection method can realize the following functions:
when the data transmission control unit is powered off and then powered on, the data transmission control unit is cold started, for example, when the ground sends a data transmission power-off command and a data transmission power-on command, the data transmission control unit is restarted, the restarting process is cold starting, in the cold starting process, the cold and hot reset mark is a cold reset mark, the cold reset mark is a random number, after the main control chip in the data transmission control unit identifies the cold reset mark, the cold starting is judged, and the data transmission control unit enters a full-function mode.
In a full-function mode, the data transmission control unit executes telemetering interruption periodically according to a signal of a 1553B control bus, when the 1553B control bus is abnormal in function, the data transmission control unit cannot enter the telemetering interruption, at the moment, the cold and hot reset identifier is a hot reset identifier, the hot reset identifier in the embodiment is a code of 0 x 5555, when the main control chip identifies the hot reset identifier, the data transmission control unit performs autonomous reset, each autonomous reset is performed, the number of times of the autonomous reset in the storage unit is +1, in the process, if the number of times of the continuous autonomous reset is smaller than a set threshold value of 5, the data transmission control unit realizes the autonomous reset, and the autonomous reset count is cleared. And if the continuous self-reset times are more than or equal to the set threshold value 5, the data transmission control unit enters a minimum system mode. As shown in fig. 2.
Therefore, the satellite-borne 1553B control bus failure protection method can intelligently judge that the 1553B control bus fails, autonomously enters a minimum system mode, does not need ground intervention, and ensures that the data transmission control unit can still execute the most basic operation under the condition that the 1553B control bus fails. Because the data transmission control unit can enter the minimum system mode after more than 5 times of continuous autonomous reset, the fault which can be recovered by the data transmission control unit under the abnormal condition is filtered, and the 1553B control bus can be prevented from entering the minimum system mode without real failure.
Example 2:
a satellite-borne 1553B control bus failure protection method, please refer to fig. 2 to 4.
As shown in fig. 2, the satellite-borne 1553B control bus failure protection method includes: when the 1553B control bus is abnormal in function, the data transmission control unit cannot enter telemetry interrupt, at this time, the cold and hot reset identifier is a hot reset identifier, the hot reset identifier in the embodiment is a code of '0 x 5555', when the main control chip identifies the hot reset identifier, the data transmission control unit performs autonomous reset, and each autonomous reset count +1 is stored in the storage module, in the process, if the continuous autonomous reset frequency is less than a set threshold value 5, the data transmission control unit realizes autonomous reset, the autonomous reset count is cleared, and if the continuous autonomous reset frequency is more than or equal to the set threshold value 5, the data transmission control unit enters a minimum system mode.
As shown in fig. 3, when the data transmission control unit enters the minimum system mode, the playback string instruction is executed, where the playback string instruction is an instruction in the minimum system mode, and is an instruction for the data transmission control unit to execute the most basic function, a watchdog is arranged in the data transmission control unit, and after the playback string instruction is executed, the data transmission control unit feeds the watchdog in a circulating manner, and is in a standby state.
Further, a timer is further arranged in the data transmission control unit, and a 20-second count is further stored in the storage unit, so that the data transmission control unit in the standby state executes the playback string instruction again.
Specifically, as shown in fig. 4, in the minimum system mode, when the data transmission control unit is in the standby state, the timer is interrupted once every 50ms, in the interruption process of the timer, the main control chip judges the count of 20 seconds, when the timer counts 20 seconds and counts +1 every 20 seconds, if the count of 20 seconds is greater than 400, the data transmission control unit enters the dog bite trap, the data transmission control unit waits for the dog bite reset, in the reset process of the dog bite, the timer counts 20 seconds and the data transmission control unit resets autonomously, when the data transmission control unit resets autonomously once every 20 seconds, the data transmission control unit resets autonomously and counts +1, and when the autonomous reset count is greater than 3, the data transmission control unit enters the minimum system mode again to execute the playback string instruction, and the count of 20 seconds is cleared, and the autonomous reset count is cleared.
When the data transmission control unit is in the standby state again, the minimum system mode can be entered again according to the flow of fig. 4.
Furthermore, in the storage module, three variables of the cold and hot reset identification, the autonomous reset count and the 20-second count are stored in three parts respectively, the three parts are modified when modification is needed each time, and the three parts are read out by two when judgment is needed, so that the accuracy of the three variables of the cold and hot reset identification, the autonomous reset count and the 20-second count is ensured.
In addition, after the data transmission control unit enters the minimum system mode, a data transmission power-off command and a data transmission power-on command are sent on the ground, the data transmission control unit enters cold start after receiving the commands, and the self-reset counting is cleared when the cold start is carried out, so that the situation that the data transmission control unit is corrected and recovered to the full-function mode after the data transmission control unit enters the minimum system mode by mistake is prevented.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (7)
1. A satellite-borne 1553B control bus failure protection method is characterized by comprising the following steps:
a cold and hot reset identifier and an autonomous reset count are stored in a data transmission control unit storage module;
when the data transmission control unit is powered off and then powered on, the cold and hot reset mark is a cold reset mark, when the data transmission control unit identifies that the cold and hot reset mark is the cold reset mark, the data transmission control unit judges that the data transmission control unit is in cold start, and the data transmission control unit enters a full-function mode;
in a full-function mode, the data transmission control unit executes telemetering interruption periodically according to a signal of a 1553B control bus, when the 1553B control bus is abnormal in function, the data transmission control unit cannot enter telemetering interruption, and at the moment, the cold and hot reset identifier is a hot reset identifier;
when the data transmission control unit identifies that the cold and hot reset mark is the hot reset mark, performing autonomous reset, wherein the autonomous reset count is +1 every time the autonomous reset is performed, and if the continuous autonomous reset times are less than a set threshold value N, the data transmission control unit realizes the autonomous reset and simultaneously clears the autonomous reset count; and if the continuous self-reset times are larger than or equal to the set threshold value N, the data transmission control unit enters a minimum system mode.
2. The satellite-borne 1553B control bus failure protection method according to claim 1, wherein a replay string instruction is executed after a data transmission control unit enters a minimum system mode, and the data transmission control unit feeds a dog circularly and is in a standby state after the replay string instruction is executed.
3. The on-board 1553B control bus failure protection method of claim 2, wherein: a timer is arranged in the data transmission control unit, and M second counting is stored in the storage module;
in the minimum system mode, when the data transmission control unit is in a standby state, judging the M second count through a timer, wherein the M second count is +1 when the timer counts M seconds, if the M second count is greater than a pre-designed count value P, the data transmission control unit enters a dog bite trap, and the data transmission control unit waits for the dog bite reset;
in the dog biting reset process, the data transmission control unit automatically resets once every time the timer counts M seconds, the data transmission control unit automatically resets once every time the data transmission control unit automatically resets, the number of times of the automatic reset is counted by +1, when the number of times of the automatic reset is larger than or equal to a set dog biting reset counting threshold value Q, the data transmission control unit enters a minimum system mode again to execute a playback string instruction, the M seconds is counted and reset, and the number of times of the automatic reset is counted and reset.
4. The on-board 1553B control bus failure protection method of claim 3, wherein: in the storage module, three variables of the cold and hot reset identification, the autonomous reset count and the M second count are stored in three parts respectively, the three parts are modified when modification is needed each time, and the three parts are read out by two when judgment is needed.
5. The on-board 1553B control bus failure protection method of claim 3, wherein: after the data transmission control unit enters a minimum system mode, when a ground sends a data transmission power-off command and a data transmission power-on command, the data transmission control unit is cold started, and when the data transmission control unit is cold started, the self-reset counting is cleared.
6. The on-board 1553B control bus failure protection method of claim 1, wherein: the data transmission control unit receives an instruction of a ground or upper computer through a 1553B control bus; under the full-function mode, the housekeeping computer sends corresponding instructions to the data transmission control unit according to the instructions of the ground or the upper computer to control the data transmission control unit to realize complete functions; the minimum system mode is an emergency state in which the data transmission control unit needs to realize basic functions.
7. The on-board 1553B control bus failure protection method of claim 1, wherein: the storage module is built in the digital control unit.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03117253A (en) * | 1989-09-29 | 1991-05-20 | Toshiba Corp | Data transmission controller |
| US5528749A (en) * | 1994-08-05 | 1996-06-18 | Thomson Consumer Electronics, Inc. | Automatic instrument turn off/on for error correction |
| US6378021B1 (en) * | 1998-02-16 | 2002-04-23 | Hitachi, Ltd. | Switch control method and apparatus in a system having a plurality of processors |
| CN101968756A (en) * | 2010-09-29 | 2011-02-09 | 航天东方红卫星有限公司 | Satellite-borne computer autonomously computer switching system based on field programmable gata array (FPGA) |
| CN106649173A (en) * | 2016-10-10 | 2017-05-10 | 上海航天控制技术研究所 | High-reliability in-orbit self-correction system and method for on-board computer on the basis of 1553B bus |
| CN106647704A (en) * | 2016-12-19 | 2017-05-10 | 北京空间飞行器总体设计部 | Method for determining tracking precision of GEO orbital data transmission antenna |
| CN109491950A (en) * | 2018-09-26 | 2019-03-19 | 北京时代民芯科技有限公司 | A kind of simplified system interface 1553B remote terminal circuit |
-
2021
- 2021-08-26 CN CN202110988293.9A patent/CN113946532B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH03117253A (en) * | 1989-09-29 | 1991-05-20 | Toshiba Corp | Data transmission controller |
| US5528749A (en) * | 1994-08-05 | 1996-06-18 | Thomson Consumer Electronics, Inc. | Automatic instrument turn off/on for error correction |
| US6378021B1 (en) * | 1998-02-16 | 2002-04-23 | Hitachi, Ltd. | Switch control method and apparatus in a system having a plurality of processors |
| CN101968756A (en) * | 2010-09-29 | 2011-02-09 | 航天东方红卫星有限公司 | Satellite-borne computer autonomously computer switching system based on field programmable gata array (FPGA) |
| CN106649173A (en) * | 2016-10-10 | 2017-05-10 | 上海航天控制技术研究所 | High-reliability in-orbit self-correction system and method for on-board computer on the basis of 1553B bus |
| CN106647704A (en) * | 2016-12-19 | 2017-05-10 | 北京空间飞行器总体设计部 | Method for determining tracking precision of GEO orbital data transmission antenna |
| CN109491950A (en) * | 2018-09-26 | 2019-03-19 | 北京时代民芯科技有限公司 | A kind of simplified system interface 1553B remote terminal circuit |
Non-Patent Citations (2)
| Title |
|---|
| ARMAN UNCU等: ""Cyber Security Concerns Regarding Federated, Partly IMA and Full IMA Implementations"", 《2019 IEEE/AIAA 38TH DIGITAL AVIONICS SYSTEMS CONFERENCE》 * |
| 元勇等: ""一种复杂载荷任务的卫星数据信息链设计"", 《航天器工程》, pages 26 - 32 * |
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