CN107203399B - Satellite in-orbit program reinjection system - Google Patents
Satellite in-orbit program reinjection system Download PDFInfo
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- CN107203399B CN107203399B CN201710403506.0A CN201710403506A CN107203399B CN 107203399 B CN107203399 B CN 107203399B CN 201710403506 A CN201710403506 A CN 201710403506A CN 107203399 B CN107203399 B CN 107203399B
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- 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
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Abstract
The invention discloses a satellite on-orbit program reinjection system, which comprises a switching signal generation circuit, a main controller and a satellite on-orbit program reinjection circuit, wherein the switching signal generation circuit is used for outputting a corresponding guide identification signal to the main controller after receiving a switching program instruction sent by a ground control center; the main controller is used for controlling the system to perform reset operation after receiving the reset signal; after resetting, reading a bootstrap program in the original program memory for running, and guiding the remark program in the remark program memory or the original program in the original program memory to run in the memory by the bootstrap program according to the received bootstrap identification signal; and the reset circuit is used for generating a reset signal and sending the reset signal to the main controller after receiving a reset program instruction sent by the ground control center. The invention can avoid the influence on the system reset function and the program switching function caused by integrating a plurality of functions as much as possible, and has high reliability.
Description
Technical Field
The invention relates to the technical field of satellite program maintenance, in particular to an on-orbit program reinjection system for a satellite.
Background
The space payload of the satellite refers to instrument equipment (including a main controller, a memory for storing programs, a memory for executing programs and the like) for directly executing tasks of the satellite, because embedded software of the space payload is a working center, if part of functions of the embedded software fail due to changes of an on-orbit application environment, normal work of the space payload is influenced, and at the moment, the program of the embedded software needs to be updated or replaced by adopting an on-orbit program reinjection method, so that normal work of the space payload is recovered.
The method for re-injecting the in-orbit program comprises the steps of transmitting a re-injection program from a ground control center to a satellite platform through a space-ground link, transmitting the re-injection program to a space effective load through a satellite internal data bus by the satellite platform, receiving the re-injection program by the space effective load, storing the re-injection program after verification, enabling the re-injection program to cover an original program or independently store the re-injection program, transmitting a program switching instruction by the ground control center to enable the space effective load to be switched to a guide re-injection program, then performing system reset operation, and directly operating the re-injection program after reset.
At present, in a space payload, a part which receives a switching program instruction, converts the switching program instruction into a corresponding switching signal, sends the switching signal to a main controller for program switching is an FPGA, and meanwhile, the FPGA also has the function of receiving a reset instruction sent by a ground control center, generating a reset signal and sending the reset signal to the main controller, and other functions. Because the functions born by the FPGA are more, the programs are complex, and different programs may affect each other, that is, after a functional part in the FPGA fails, the functions of a program switching part or a reset part may be affected, so that switching failure or reset failure is caused, and a space payload cannot guide the operation of a reinjection program, that is, the FPGA with multiple functions is adopted as a functional component of the reset part and the program switching part, so that a great risk exists, and the reliability is low.
Therefore, how to provide a satellite on-orbit procedure re-injection system with high reliability is a problem that needs to be solved by those skilled in the art at present.
Disclosure of Invention
The invention aims to provide a satellite on-orbit program reinjection system which can avoid the influence on a system reset function and a program switching function caused by integrating a plurality of functions as far as possible and has high reliability.
In order to solve the technical problem, the invention provides a satellite on-orbit program reinjection system, which comprises a main controller, and a switching signal generation circuit, a memory, an original program memory, a reinjection program memory and a reset circuit which are respectively connected with the main controller;
an original program and a bootstrap program are stored in the original program memory;
the switching signal generating circuit is used for outputting a corresponding guiding identification signal to the main controller after receiving a switching program instruction sent by a ground control center;
the main controller is used for controlling the system to perform reset operation after receiving a reset signal; after resetting, reading a bootstrap program in the original program storage to run, wherein the bootstrap program guides the re-injection program in the re-injection program storage or the original program in the original program storage to run in the memory according to the received bootstrap identification signal;
and the reset circuit is used for generating the reset signal and sending the reset signal to the main controller after receiving a reset program instruction sent by the ground control center.
Preferably, the method further comprises the following steps:
the fault-tolerant circuit is used for filtering reset program instructions, the input end of the fault-tolerant circuit is used for receiving the reset program instructions sent by the ground control center, and the output end of the fault-tolerant circuit is connected with the input end of the reset circuit.
Preferably, the fault tolerant circuit is embodied as an RC circuit.
Preferably, the method further comprises the following steps:
and the shaping circuit is connected between the output end of the reset circuit and the reset input end of the main controller and is used for shaping the reset signal.
Preferably, the shaping circuit is embodied as a schmitt trigger.
Preferably, the method further comprises the following steps:
a watchdog circuit for generating a redundant reset signal;
logic circuitry for performing an OR operation;
the output end of the watchdog circuit and the output end of the shaping circuit are respectively connected with two input ends of the logic circuit, and the output end of the logic circuit is connected with the reset input end of the main controller.
Preferably, the switching signal generating circuit is embodied as a magnetic latching relay.
Preferably, the reset circuit is an electromagnetic relay.
Preferably, the memory specifically includes:
the operation module is used for operating the remark program or the original program;
and the reinjection module is used for receiving the reinjection program data packets which are sent by the ground control center and adopt the CCSDS codes for sequential verification and storage, integrating the programs in the data packets to obtain the reinjection program and verify the reinjection program after receiving the tail packet, and writing the reinjection program into the reinjection program storage after the verification is passed.
The invention provides a satellite on-orbit program reinjection system, which comprises a main controller, and a switching signal generation circuit, a memory, an original program memory, a reinjection program memory and a reset circuit which are respectively connected with the main controller; the switching signal generating circuit outputs a corresponding electric guide identification signal to the main controller after receiving a switching program instruction sent by the ground control center, the main controller reads a guide program to operate after resetting, and in the operation process of the guide program, the re-injection program in the re-injection program storage device or the original program in the original program storage device can be selectively guided to the memory to operate according to the guide identification carried by the received guide identification signal. Therefore, the system of the invention separates the reset circuit from the switching signal generating circuit, the reset signal and the switching signal are generated by different circuits, the reset circuit is only used for generating the reset signal, and the switching signal generating circuit is only used for generating the switching signal, thereby avoiding the mutual influence between the switching signal generating part and the reset part as much as possible, reducing the occurrence of faults caused by the influence of other functions due to the integration of the two functional parts and other functions, and improving the reliability of the satellite in-orbit program reinjection process.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed in the prior art and the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a satellite in-orbit procedure re-injection system provided in the present invention;
FIG. 2 is a schematic structural diagram of another satellite in-orbit procedure refill system according to the present invention;
fig. 3 is a schematic diagram of a data packet format of a CCSDS encoded re-injection program according to the present invention.
Detailed Description
The core of the invention is to provide a satellite on-orbit program reinjection system, which can avoid the influence on a system reset function and a program switching function caused by integrating a plurality of functions together as far as possible and has high reliability.
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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 some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The invention provides a satellite in-orbit procedure reinjection system, which is shown in fig. 1, wherein fig. 1 is a schematic structural diagram of the satellite in-orbit procedure reinjection system provided by the invention; the system comprises a main controller 1, and a switching signal generating circuit 5, a memory 4, an original program memory 3, a remarking program memory 2 and a reset circuit 6 which are respectively connected with the main controller 1;
the original program memory stores an original program and a bootstrap program;
the original program memory 3 and the reinjection program memory 2 are independent of each other, the two memories can be an EEPROM (the model can be 3DEE5M40VS5257), and different chip selection signals of the main controller 1 are adopted, so that the two memories have different address spaces. Of course, the present invention is not limited to a specific model of the two memories.
The switching signal generating circuit 5 is configured to output a corresponding guidance identifier signal to the main controller 1 after receiving a switching program instruction sent by a ground control center;
the switching signal generating circuit 5 may use the magnetic latching relay 2JB1-910, the pilot flag signal is a high/low level signal, different pilot flags are represented by different levels, for example, a high level indicates a pilot refill program, a low level indicates a pilot original program, and it is needless to say that which program the high level pilot is set by itself.
The main controller 1 is used for controlling the system to perform reset operation after receiving a reset signal; after resetting, reading a bootstrap program in the original program storage for running, wherein the bootstrap program guides the re-injection program in the re-injection program storage 2 or the original program in the original program storage 3 to run in the memory 4 according to the received bootstrap identification signal;
the main controller 1 may adopt a BM3803 processor, wherein a PI07 pin of the BM3803 processor is connected to an output terminal of the switching signal generating circuit 5 as an input of the switching signal (the first level signal and the second level signal). The memory 4 of the main controller 1 stores a bootstrap program, the bootstrap program automatically runs after being powered on, the function of the bootstrap program is to guide different application programs to be loaded to the memory 4 to run, after the main controller 1 is initialized, the data of a switching signal input by a pin PI07 is read, when the switching signal is a low level signal, the read data is 0, at the moment, the bootstrap program guides a reinjection program to the memory 4, when the switching signal is a high level signal, the read data is 1, at the moment, the bootstrap program guides an original program to the memory 4; of course, the present invention is not limited to a specific manner, which may be used to guide the re-injection procedure when the signal level is high, or to guide the original procedure when the signal level is low.
And the reset circuit 6 is used for generating a reset signal and sending the reset signal to the main controller 1 after receiving a reset program instruction sent by the ground control center.
Here, the reset circuit 6 may also adopt a magnetic latching relay 2JB1-910 for resetting when receiving a low level signal (80ms ± 10ms), and of course, a high level signal may be set to trigger the resetting, and the reset circuit 6 may also adopt other types of circuits, which is not particularly limited in the present invention.
The memory 4 here is an SRAM, and may specifically be a model 3DSR20M40VS6507, although the present invention is not limited to the model of the memory 4.
It should be noted that the boot program is located at 0 of PROM, and after each power-on or reset, the program is first run, and it decides to boot the original program or the re-injection program to the memory for running according to the received boot identifier. Since the re-note program may be overwritten many times, the boot program is stored in the original program memory in order to avoid the boot program being overwritten.
The invention provides a satellite on-orbit program reinjection system, which comprises a main controller, and a switching signal generation circuit, a memory, an original program memory, a reinjection program memory and a reset circuit which are respectively connected with the main controller; the switching signal generating circuit outputs a corresponding electric guide identification signal to the main controller after receiving a switching program instruction sent by the ground control center, the main controller reads a guide program to operate after resetting, and in the operation process of the guide program, the re-injection program in the re-injection program storage device or the original program in the original program storage device can be selectively guided to the memory to operate according to the guide identification carried by the received guide identification signal. Therefore, the system of the invention separates the reset circuit from the switching signal generating circuit, the reset signal and the switching signal are generated by different circuits, the reset circuit is only used for generating the reset signal, and the switching signal generating circuit is only used for generating the switching signal, thereby avoiding the mutual influence between the switching signal generating part and the reset part as much as possible, reducing the occurrence of faults caused by the influence of other functions due to the integration of the two functional parts and other functions, and improving the reliability of the satellite in-orbit program reinjection process.
For ease of understanding, the workflow of the above system is described as follows:
step s 101: the ground control center sends the re-injection program to the satellite platform through a space-ground link, and the satellite platform sends the re-injection program to a re-injection program memory 2 in the space payload through a 1553B bus or a CAN bus inside the satellite for verification and storage;
step s 102: after receiving a re-injection switching program instruction sent by a ground control center, a switching signal generating circuit 5 generates a first level signal to a main controller 1;
step s 103: after receiving a reset program instruction sent by a ground control center, the reset circuit 6 generates a reset signal and sends the reset signal to the main controller 1;
the boot is a copy operation.
Step s 104: after the memory 4 is initialized, the main controller 1 runs the read bootstrap program, and the bootstrap program guides the re-injection program in the re-injection program memory 2 to the memory 4 according to the received first level signal;
step s 105: and the re-injection program in the memory 4 automatically runs to complete the re-injection operation.
It is understood that the present invention can repeatedly switch the program source in the memory 4 and can realize multiple re-injection operations.
In a preferred embodiment, the memory 4 specifically includes:
the operation module is used for operating the reinjection program or the original program;
and the reinjection module is used for receiving the reinjection program data packets which are sent by the ground control center and adopt the CCSDS codes for sequential verification and storage, integrating the programs in the data packets to obtain and verify the reinjection program after receiving the tail packet, and writing the reinjection program into the reinjection program storage 2 after the verification is passed.
It will be appreciated that during the sending and storing of the refill program to the space payload in step s101, the refill program needs to be broken up into multiple refill program data packets.
Wherein, the size of the re-injection program data packet is 64 bytes per packet, the CCSDS code is a code based on the CCSDS standard, and fig. 3 is a schematic diagram of a format of the CCSDS code re-injection program data packet provided by the present invention.
Version number: binary 3 bits, fixed as b "000";
packet type: 1 bit binary system, fixed as b '0', representing the reinjection packet;
auxiliary guide head mark: 1 bit binary, b "0" represents no secondary leader; b '1' represents an auxiliary guide head;
application process ID: an 11-bit binary system for identifying each backend device;
sequence tag: 2-bit binary, label-annotating program
b "00" represents the middle packet of the upper note program;
b "01" represents the initial package of the superscript program;
b "10" represents the end package of the top note program;
b "11" represents a separate package for the superscript program.
Counting the packet sequence: a 14-bit binary, counting from 0, with a maximum of 16383(b "11111111111111"), for the order of the current packet in the overall sequence;
packet data length: a 16-bit binary value in bytes, having a value equal to the packet data length (including the sub-header and the valid data area) -1;
an effective data area: the hexadecimal data content is the sum of the upper note program and 2 bytes, and the data length is an even number;
CRC checking: 4 bytes, the check range includes the whole source packet, i.e. the leading header and the packet data area are checked.
It is further known that, in step s101, the process of sending and storing the space payload by the re-injection program is specifically as follows:
step s 201: the SRAM receives the transmitted re-injection program data packet through a 1553B bus or a CAN bus inside the satellite and carries out first verification, if the verification is qualified, the SRAM receives the re-injection program data packet, reads effective data in the re-injection program data packet and stores the effective data in the re-injection module according to the sequence number of the re-injection program data packet, if the verification fails, the SRAM discards the error information and returns the error information to the satellite platform to inform the satellite platform of retransmission;
step s 202: after detecting that the tail packet is received, the re-injection module integrates the effective data in each received data packet to obtain a complete re-injection program, performs second verification, and writes the re-injection program in the SRAM into a re-injection program memory 2 after the verification is qualified;
step s 203: and the re-injection program memory 2 performs third verification on the stored re-injection program, and after the stored re-injection program is qualified, the ground control center is informed that the re-injection program is received and completed, so that the subsequent switching guide operation of the re-injection program can be performed.
It can be understood that the first check is to check the transmitted data packet of the reinjection program, so as to judge the eligibility of the whole packet; the second check is to check the content of the remarking program, so as to judge whether an error occurs in the reading or integrating process of the valid data; the third check is to check the refilling program transferred into the refilling program memory 2 in order to determine whether an error occurs during the process of writing the refilling program from the SRAM into the refilling program memory 2. Through the three-time verification, the condition of transmission error of the re-injection program can be basically avoided, the condition of re-injection failure caused by the error of the re-injection program is reduced, and the reliability of re-injection operation is improved.
Preferably, the system further comprises:
and the input end of the fault-tolerant circuit is used for receiving the reset program instruction sent by the ground control center, and the output end of the fault-tolerant circuit is connected with the input end of the reset circuit 6.
It can be understood that the function of the fault-tolerant circuit is to filter the noise in the reset program instruction, prevent the false reset operation caused by the noise, and improve the reliability of the system.
Preferably, the fault tolerant circuit is embodied as an RC circuit, which is capable of filtering low level noise for less than 20 ms.
Preferably, the system further comprises:
and the shaping circuit is connected between the output end of the reset circuit 6 and the reset input end of the main controller 1 and is used for shaping the reset signal.
Specifically, the shaping circuit is specifically a schmitt trigger, and the model of the schmitt trigger may be SNJ54AHC14W, although the invention is not limited to the specific type of the shaping circuit.
Preferably, the system further comprises:
a watchdog circuit for generating a redundant reset signal;
logic circuitry for performing an OR operation;
the output end of the watchdog circuit and the output end of the shaping circuit are respectively connected with two input ends of the logic circuit, and the output end of the logic circuit is connected with the reset input end of the main controller 1.
It can be understood that the input terminal of the watchdog circuit also receives a reset program instruction sent by the ground control center, so as to control the watchdog circuit to generate a reset signal, and the input signal of the watchdog circuit is connected with the reset input terminal of the main controller 1 after being summed with the reset signal output by the reset circuit 6. The watchdog circuit is a redundant circuit and is used for generating a redundant reset signal, ensuring the successful execution of reset operation and improving the reliability of the system.
The embodiments in the present description are described in a progressive manner, each embodiment focuses on differences from other embodiments, and the same and similar parts among the embodiments are referred to each other. The device disclosed by the embodiment corresponds to the method disclosed by the embodiment, so that the description is simple, and the relevant points can be referred to the method part for description.
It is further noted that, in the present specification, relational terms such as first and second, and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other identical elements in a process, method, article, or apparatus that comprises the element.
The previous description of the disclosed embodiments is provided to enable any person skilled in the art to make or use the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (8)
1. A satellite on-orbit program reinjection system is characterized by comprising a main controller, a switching signal generation circuit, a memory, an original program memory, a reinjection program memory and a reset circuit, wherein the switching signal generation circuit, the memory, the original program memory, the reinjection program memory and the reset circuit are respectively connected with the main controller;
an original program and a bootstrap program are stored in the original program memory;
the switching signal generating circuit is used for outputting a corresponding guiding identification signal to the main controller after receiving a switching program instruction sent by a ground control center;
the main controller is used for controlling the system to perform reset operation after receiving a reset signal; after resetting, reading a bootstrap program in the original program storage to run, wherein the bootstrap program guides the re-injection program in the re-injection program storage or the original program in the original program storage to run in the memory according to the received bootstrap identification signal;
the reset circuit is used for generating the reset signal and sending the reset signal to the main controller after receiving a reset program instruction sent by the ground control center; wherein, the reset circuit is an electromagnetic relay.
2. The system of claim 1, further comprising:
the fault-tolerant circuit is used for filtering reset program instructions, the input end of the fault-tolerant circuit is used for receiving the reset program instructions sent by the ground control center, and the output end of the fault-tolerant circuit is connected with the input end of the reset circuit.
3. The system according to claim 2, characterized in that the fault tolerant circuit is embodied as an RC circuit.
4. The system of claim 2, further comprising:
and the shaping circuit is connected between the output end of the reset circuit and the reset input end of the main controller and is used for shaping the reset signal.
5. The system according to claim 4, characterized in that the shaping circuit is embodied as a Schmitt trigger.
6. The system of claim 4, further comprising:
a watchdog circuit for generating a redundant reset signal;
logic circuitry for performing an OR operation;
the output end of the watchdog circuit and the output end of the shaping circuit are respectively connected with two input ends of the logic circuit, and the output end of the logic circuit is connected with the reset input end of the main controller.
7. System according to any one of claims 1 to 6, characterized in that the switching signal generating circuit is embodied as a magnetic latching relay.
8. The system of claim 1, wherein the memory specifically comprises:
the operation module is used for operating the remark program or the original program;
and the reinjection module is used for receiving the reinjection program data packets which are sent by the ground control center and adopt the CCSDS codes for sequential verification and storage, integrating the programs in the data packets to obtain the reinjection program and verify the reinjection program after receiving the tail packet, and writing the reinjection program into the reinjection program storage after the verification is passed.
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| CN102207877A (en) * | 2011-04-15 | 2011-10-05 | 中国科学院长春光学精密机械与物理研究所 | Method and system for re-pouring on-track program of space camera |
| CN103955411A (en) * | 2014-05-21 | 2014-07-30 | 北京空间机电研究所 | On-orbit transmitting and configuring method for spaceborne high-capacity FPGA (Field Programmable Gate Array) program |
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| US8707370B2 (en) * | 2012-07-13 | 2014-04-22 | International Datacasting Corporation | Digital satellite broadcast program distribution over multicast IP broadband networks |
| CN103777983B (en) * | 2014-01-24 | 2016-09-21 | 航天东方红卫星有限公司 | A kind of On-board software is safeguarded and upgrade method in-orbit |
| CN105549464A (en) * | 2015-12-10 | 2016-05-04 | 中国电子科技集团公司第三十二研究所 | Management and control system for medium and high orbit satellite payload |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102207877A (en) * | 2011-04-15 | 2011-10-05 | 中国科学院长春光学精密机械与物理研究所 | Method and system for re-pouring on-track program of space camera |
| CN103955411A (en) * | 2014-05-21 | 2014-07-30 | 北京空间机电研究所 | On-orbit transmitting and configuring method for spaceborne high-capacity FPGA (Field Programmable Gate Array) program |
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