CN112506527A - On-track reconstruction breakpoint continuous transmission implementation method based on antifuse Field Programmable Gate Array (FPGA) - Google Patents
On-track reconstruction breakpoint continuous transmission implementation method based on antifuse Field Programmable Gate Array (FPGA) Download PDFInfo
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Abstract
The invention provides an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse Field Programmable Gate Array (FPGA), which comprises the following steps of: during on-track reconstruction, after receiving a reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet; if the detection is correct, continuing to inject, and if the detection is incorrect, sending the discontinuous telemetering value or the error telemetering value of the check value of the reconstructed data packet back to the ground software; and the ground software stops the upper note, calculates to obtain the initial address of the breakpoint, and continues the upper note from the breakpoint until the on-track reconstruction is completed. The invention provides an on-orbit reconstruction breakpoint continuous transmission implementation method based on an anti-fuse FPGA (field programmable gate array). in order to solve the problem that a large amount of time is wasted when errors occur in the process of continuous transmission, ground software is utilized to combine the counting remote measurement values of reconstruction data packets, the number of reconstruction data contained in each reconstruction data packet is calculated, the initial address of continuous transmission is calculated, and then continuous transmission is performed from the address until the transmission of the whole reconstruction file is finished.
Description
Technical Field
The invention relates to the technical field of software engineering design, in particular to an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse Field Programmable Gate Array (FPGA).
Background
The particularity of the space application environment puts higher requirements on the reliability and safety of the on-orbit information processing platform. The reconfigurable technology can solve the problems that the on-orbit software upgrading can solve, such as the increase of software functions, the improvement of performance, the solution of faults and the like of the on-orbit information processing platform. The reconfigurable technology can control the SRAM type FPGA to load different configuration files through the antifuse FPGA or store the different configuration files to the FLASH chip through the satellite uplink channel. The configuration file of the SRAM type FPGA is large, the resources of the antifuse FPGA are limited, so the configuration file is required to be divided into a plurality of packets for uploading, if the reconstructed data packet is discontinuous or the check value is wrong in the uploading process, and if the storage FLASH chip is erased and the uploading is restarted, a large amount of time is wasted.
Disclosure of Invention
The invention provides an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse Field Programmable Gate Array (FPGA), which aims to solve the problem that a large amount of time is wasted when the on-track reconstruction breakpoint is reinjected from a first packet when an error occurs in the process of the on-track reconstruction breakpoint. And calculating the initial address of continuous uploading by combining the counting telemetry value of the reconstruction data packet and the number of reconstruction data contained in each reconstruction data packet by using ground software, and then continuously uploading from the address until the transmission of the whole reconstruction file is finished.
The invention provides an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse Field Programmable Gate Array (FPGA), which comprises the following steps of:
s1, burning: burning a configuration file of an SRAM type FPGA initial version in PROM of the satellite borne equipment;
s2, loading: loading an SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from a PROM on satellite-borne equipment;
s3, power-on: the anti-fuse FPGA controls the SRAM type FPGA to start from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, a reconstruction data packet is sent to a satellite containing satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote measurement value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measurement value or the check value error remote measurement value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting the discontinuous remote measurement value or the error remote measurement value of the check value of the reconstructed data packet, and calculates the initial address of the breakpoint according to the counting remote measurement value and the number of reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
and S6, completing the reconstruction on track after the transmission of the reconstruction data packet is finished.
The invention relates to an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse FPGA (field programmable gate array), which comprises the following steps as an optimal mode:
s1, burning: burning a configuration file of an SRAM type FPGA initial version in PROM of the satellite borne equipment;
s2, loading: loading an SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from a PROM on satellite-borne equipment;
s3, power-on: the anti-fuse FPGA controls the SRAM type FPGA to start from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, a reconstruction data packet is sent to a satellite containing satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote measurement value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measurement value or the check value error remote measurement value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting the discontinuous remote measurement value or the error remote measurement value of the check value of the reconstructed data packet, and calculates the initial address of the breakpoint according to the counting remote measurement value and the number of reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
s6, after the transmission of the reconstruction data packet is finished, the antifuse FPGA transmits a reconstruction data receiving finish remote measurement value and a reconstruction data packet counting remote measurement value to the ground software;
s7, checking: and the remote measurement value after the reconstruction data is received by the ground software is the same as the reconstructed data packet counting remote measurement value, the reconstructed data packet counting remote measurement value is the same as the total number of the reconstructed file data packets of the ground software, and the on-orbit reconstruction is completed.
The invention relates to an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse FPGA (field programmable gate array), which comprises the following steps as an optimal mode:
s1, burning: burning a configuration file of an SRAM type FPGA initial version in PROM of the satellite borne equipment;
s2, loading: loading an SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from a PROM on satellite-borne equipment;
s3, power-on: the anti-fuse FPGA controls the SRAM type FPGA to start from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, a reconstruction data packet is sent to a satellite containing satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote measurement value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measurement value or the check value error remote measurement value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting the discontinuous remote measurement value or the error remote measurement value of the check value of the reconstructed data packet, and calculates the initial address of the breakpoint according to the counting remote measurement value and the number of reconstructed data contained in each reconstructed data packet; if the reconstructed data counting remote measurement value is zero, calculating the starting address of a breakpoint according to the previous non-zero reconstructed data packet remote measurement value recorded by ground software and the number of reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
and S6, completing the reconstruction on track after the transmission of the reconstruction data packet is finished.
The invention discloses an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse FPGA (field programmable gate array). As an optimal mode, in step S5, a reconstructed file memory is a FLASH chip.
The invention relates to an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse FPGA (field programmable gate array), which comprises the following steps as an optimal mode:
s1, burning: burning a configuration file of an SRAM type FPGA initial version in PROM of the satellite borne equipment;
s2, loading: loading an SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from a PROM on satellite-borne equipment;
s3, power-on: the anti-fuse FPGA controls the SRAM type FPGA to start from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, a reconstruction data packet is sent to a satellite containing satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote measurement value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measurement value or the check value error remote measurement value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting the discontinuous remote measurement value or the error remote measurement value of the check value of the reconstructed data packet, and calculates the initial address of the breakpoint according to the counting remote measurement value and the number of reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
s6, completing the reconstruction on the track after the transmission of the reconstruction data packet is finished; and after the track reconstruction is finished, the anti-fuse FPGA controls the SRAM type FPGA to start from the FLASH.
The basic idea of the invention is as follows: in the track reconstruction process, the ground stops injecting when the ground receives a reconstruction data packet discontinuity or a check error remote measurement value, and the ground software calculates the starting address of continuous injection according to the reconstruction data packet counting remote measurement value and the number of reconstruction data contained in each reconstruction data packet. And then, the uploading is continued from the address until the transmission of the whole reconstructed file is finished. Avoiding a renewed wager from the first packet wastes a significant amount of time.
Compared with the prior art, the invention has the advantages that:
and when an error occurs in the uploading process, the ground software calculates the starting address for continuing uploading according to the counting remote measuring value of the reconstruction data packets and the number of reconstruction data contained in each reconstruction data packet. And then, the uploading is continued from the address until the transmission of the whole reconstructed file is finished. Avoiding a renewed wager from the first packet wastes a significant amount of time.
Drawings
FIG. 1 is a flowchart of an embodiment 1 of an on-track reconstruction breakpoint resume implementation method based on an antifuse FPGA;
FIG. 2 is a structural diagram of an embodiment 1-4 of an on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse FPGA;
fig. 3 is a flowchart of an embodiment 2-4 of an on-track reconstruction breakpoint resume implementation method based on an antifuse FPGA.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments.
Example 1
As shown in fig. 1-2, an on-rail reconstruction breakpoint resume implementation method based on an antifuse FPGA includes the following steps:
s1, burning: burning a configuration file of an SRAM type FPGA initial version in PROM of the satellite borne equipment;
s2, loading: loading an SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from a PROM on satellite-borne equipment;
s3, power-on: the anti-fuse FPGA controls the SRAM type FPGA to start from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, a reconstruction data packet is sent to a satellite containing satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote measurement value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measurement value or the check value error remote measurement value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting the discontinuous remote measurement value or the error remote measurement value of the check value of the reconstructed data packet, and calculates the initial address of the breakpoint according to the counting remote measurement value and the number of reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
s6, finishing sending: and completing the on-orbit reconstruction after the transmission of the reconstruction data packet is finished.
Example 2
As shown in fig. 2-3, an on-rail reconstruction breakpoint resume implementation method based on an antifuse FPGA includes the following steps:
s1, burning: burning a configuration file of an SRAM type FPGA initial version in the PROM of the satellite borne equipment;
s2, loading: loading an SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from a PROM on satellite-borne equipment;
s3, power-on: the anti-fuse FPGA controls the SRAM type FPGA to start from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, a reconstruction data packet is sent to a satellite containing satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory, namely a FLASH chip, of the SRAM type FPGA, adding 1 to the count remote value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measurement value or the check value error remote measurement value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting the discontinuous remote measurement value or the error remote measurement value of the check value of the reconstructed data packet, and calculates the initial address of the breakpoint according to the counting remote measurement value and the number of reconstructed data contained in each reconstructed data packet; if the reconstructed data counting remote measurement value is zero, calculating the starting address of a breakpoint according to the previous non-zero reconstructed data packet remote measurement value recorded by ground software and the number of reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
s6, finishing sending: after the transmission of the reconstruction data packet is finished, the antifuse Field Programmable Gate Array (FPGA) transmits a reconstruction data receiving finish remote measurement value and a reconstruction data packet counting remote measurement value to the ground software;
s7, checking: the remote measurement value of the reconstructed data after receiving is the same as the reconstructed data packet counting remote measurement value received by the ground software, the reconstructed data packet counting remote measurement value is the same as the total number of the reconstructed file data packets of the ground software, and the on-orbit reconstruction is completed; and after the track reconstruction is finished, the anti-fuse FPGA controls the SRAM type FPGA to start from the FLASH.
Example 3
As shown in fig. 2-3, in the track reconstruction process, when the ground receives a reconstructed data packet discontinuity or a check error telemetry value, the ground stops uploading, and the ground software calculates the starting address of the continuous uploading according to the reconstructed data packet counting telemetry value and the number of reconstructed data contained in each reconstructed data packet. And then, the uploading is continued from the address until the transmission of the whole reconstructed file is finished. Avoiding a renewed wager from the first packet wastes a significant amount of time.
The invention is described in further detail below with reference to the following figures and specific examples:
(1) as shown in fig. 2, the configuration file of the initial version of the SRAM type FPGA is burned in the PROM, and when the PROM is powered on and started, the antifuse FPGA controls the SRAM type FPGA to be started from the PROM.
(2) As shown in fig. 3, during the orbital reconstruction, the ground sends a reconstruction data packet to the satellite, and the antifuse FPGA performs continuity check and check value check on the reconstruction data packet after receiving the reconstruction data packet.
(3) If the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory FLASH, and adding 1 to the counting remote measurement value of the reconstructed data packet after successful writing; otherwise, the discontinuous telemetering value or the check value of the reconstructed data packet is sent back to the ground in error telemetering value.
(4) As shown in fig. 3, the above-mentioned note stops when the reconstructed data packet is received at the ground and the telemetry value is not continuous or wrong.
(5) And calculating the starting address of continuous injection by the ground software according to the counting remote measurement value of the reconstruction data packets and the number of reconstruction data contained in each reconstruction data packet.
(6) And continuing to annotate until the transmission of the reconstructed file is finished.
(7) And the remote measurement value after the reconstruction data is received on the ground and the reconstructed data packet counting remote measurement value are consistent with the total number of the data packets of the ground reconstruction file.
Example 4
As shown in fig. 2-3, a method for realizing on-track reconstruction breakpoint resume based on an antifuse FPGA is provided, in which a space information processing platform is configured as shown in fig. 2, a configuration file of an initial version of an SRAM-type FPGA is burned in a PROM, and when the PROM is powered on and started, the antifuse FPGA controls the SRAM-type FPGA to be started from the PROM; the FLASH is a configuration file memory for on-track reconstruction, and after the storage of the reconstruction file is finished, the anti-fuse FPGA can control the SRAM type FPGA to start from the FLASH. The invention provides a method for realizing that the remark is continuously performed from where the error occurs in the reconstruction process, and the waste of a large amount of time caused by the fact that the remark is performed again from the first packet when the error occurs in the remark process is avoided. For example, the size of a configuration file of an SRAM type FPGA chip is 2.7MB, under the limitation of antifuse FPGA resources, the configuration file is divided into 44352 reconstruction data packets, the size of each reconstruction data packet is 64Byte, and the sending time interval of the reconstruction data packets is 1 s. If 22176 reconstruction data packets are sent, error injection is stopped, and if the reconstruction data files are sent again after the reconstruction file memory is erased and reconstruction is completed successfully, the whole reconstruction process takes about 18 hours; if the point-of-break transmission is used, the reconstruction data packet is continuously filled from 22177 th data packet until the filling is successful, the whole reconstruction process takes about 12 hours, and the time is saved by about 6 hours compared with the filling from the beginning.
The above description is only for the preferred embodiment of the present invention, but the scope of the present invention is not limited thereto, and any person skilled in the art should be considered to be within the technical scope of the present invention, and the technical solutions and the inventive concepts thereof according to the present invention should be equivalent or changed within the scope of the present invention.
Claims (5)
1. An on-track reconstruction breakpoint continuous transmission implementation method based on an antifuse FPGA is characterized by comprising the following steps: the method comprises the following steps:
s1, burning: burning a configuration file of an SRAM type FPGA initial version in PROM of the satellite borne equipment;
s2, loading: loading the SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from the PROM on the satellite-borne equipment;
s3, power-on: the antifuse FPGA controls the SRAM type FPGA to be started from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, transmitting a reconstruction data packet to a satellite containing the satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measuring value or the check value error remote measuring value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting after receiving the discontinuous telemetering value of the reconstructed data packets or the error telemetering value of the check value, and calculates the initial address of the breakpoint according to the counting telemetering value and the number of the reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
s6, finishing sending: and finishing the on-orbit reconstruction after the reconstruction data packet is sent.
2. The on-rail reconstruction breakpoint resume implementation method based on the antifuse FPGA, according to claim 1, characterized in that: the method comprises the following steps:
s1, burning: burning a configuration file of the SRAM type FPGA initial version in the PROM of the satellite borne equipment;
s2, loading: loading the SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from the PROM on the satellite-borne equipment;
s3, power-on: the antifuse FPGA controls the SRAM type FPGA to be started from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, transmitting a reconstruction data packet to a satellite containing the satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measuring value or the check value error remote measuring value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting after receiving the discontinuous telemetering value of the reconstructed data packets or the error telemetering value of the check value, and calculates the initial address of the breakpoint according to the counting telemetering value and the number of the reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
s6, finishing sending: after the transmission of the reconstruction data packet is finished, the antifuse Field Programmable Gate Array (FPGA) transmits the reconstruction data receiving finish remote measurement value and the reconstruction data packet counting remote measurement value to the ground software;
s7, checking: and the ground software receives the reconstructed data receiving completion remote measuring value and the reconstructed data packet counting remote measuring value which are the same, the reconstructed data packet counting remote measuring value and the total number of the reconstructed file data packets of the ground software are the same, and the on-orbit reconstruction is completed.
3. The on-rail reconstruction breakpoint resume implementation method based on the antifuse FPGA, according to claim 1, characterized in that: the method comprises the following steps:
s1, burning: burning a configuration file of the SRAM type FPGA initial version in the PROM of the satellite borne equipment;
s2, loading: loading the SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from the PROM on the satellite-borne equipment;
s3, power-on: the antifuse FPGA controls the SRAM type FPGA to be started from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, transmitting a reconstruction data packet to a satellite containing the satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measuring value or the check value error remote measuring value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting after receiving the discontinuous telemetering value of the reconstructed data packets or the error telemetering value of the check value, and calculates the initial address of the breakpoint according to the counting telemetering value and the number of the reconstructed data contained in each reconstructed data packet; if the reconstructed data counting remote measurement value is zero, calculating the starting address of the breakpoint according to the previous non-zero reconstructed data packet remote measurement value recorded by the ground software and the number of the reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
s6, finishing sending: and finishing the on-orbit reconstruction after the reconstruction data packet is sent.
4. The on-rail reconstruction breakpoint resume implementation method based on the antifuse FPGA, according to claim 1, characterized in that: in step S5, the reconstructed file memory is a FLASH chip.
5. The on-rail reconstruction breakpoint resume implementation method based on the antifuse FPGA, according to claim 1, characterized in that: the method comprises the following steps:
s1, burning: burning a configuration file of the SRAM type FPGA initial version in the PROM of the satellite borne equipment;
s2, loading: loading the SRAM type FPGA and an anti-fuse FPGA for controlling the SRAM type FPGA to be started from the PROM on the satellite-borne equipment;
s3, power-on: the antifuse FPGA controls the SRAM type FPGA to be started from the PROM;
s4, sending a reconstruction data packet: during in-orbit reconstruction, transmitting a reconstruction data packet to a satellite containing the satellite-borne equipment on the ground;
s5, detection: after receiving the reconstruction data packet, the anti-fuse FPGA carries out continuity detection and check value detection on the reconstruction data packet;
when the continuity and check value detection is correct: if the reconstructed data packet is continuous and the check value is correct, writing the reconstructed data into a reconstructed file memory of the SRAM type FPGA, adding 1 to the count remote value of the reconstructed data packet after the writing is successful, and continuing to perform the step S4;
continuity and check value detection is incorrect: if the reconstructed data packet is discontinuous or the check value is incorrect, sending the discontinuous remote measuring value or the check value error remote measuring value of the reconstructed data packet back to the ground software;
stopping upper notes and breakpoint calculation: the ground software stops injecting after receiving the discontinuous telemetering value of the reconstructed data packets or the error telemetering value of the check value, and calculates the initial address of the breakpoint according to the counting telemetering value and the number of the reconstructed data contained in each reconstructed data packet;
and (4) breakpoint reinjection: the ground software continues to step S4 from the breakpoint;
s6, finishing sending: after the reconstruction data packet is sent, completing the on-orbit reconstruction; and after the on-track reconstruction is finished, the antifuse FPGA controls the SRAM type FPGA to start from the FLASH.
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| CN113098585A (en) * | 2021-03-30 | 2021-07-09 | 中国电子信息产业集团有限公司第六研究所 | Satellite on-orbit reconstruction system and method and satellite-ground link communication system |
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| 熊浩伦;闫国瑞;李国军;吕达;: "基于最小系统的小卫星在轨软件重构系统设计", 遥测遥控 * |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113098585A (en) * | 2021-03-30 | 2021-07-09 | 中国电子信息产业集团有限公司第六研究所 | Satellite on-orbit reconstruction system and method and satellite-ground link communication system |
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