In-orbit satellite ID number changing method and system

Abstract

The invention provides an in-orbit satellite ID number changing method and system. The method comprises the steps that a satellite identification word is newly added to a ground uplink remote control frame to change a remote control frame; the on-satellite CPU module sends a channel gateway remote control packet and a new satellite identification word change remote control packet; the satellite channel gateway FPGA module adds satellite identification word change remote control packet analysis and satellite identification word two-out-of-three self-refreshing storage; a downlink telemetry frame is newly added to the downlink telemetry frame of the channel gateway module; after the satellite ID number in-orbit change is completed, the latest ID is synchronously returned to the ground for confirmation; the problem that an identifier of a traditional satellite cannot be changed is solved. A satellite identifier is uploaded and changed through an uplink remote control channel of a satellite, the latest satellite identifier is stored, the urgent requirement of satellite networking application can be met, and in-orbit satellite ID maintenance and management functions of large-scale constellations are achieved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of on-orbit satellite management, in particular to an on-orbit satellite ID number changing method and system. BACKGROUND

[0002] The ID number of the on-orbit satellite is one of the important features of the satellite, which is responsible for providing a unique identity for the satellite, facilitating the tracking and long-term satellite management of the on-orbit satellite by the ground. The satellite ID number setting involves many factors such as satellite telemetry and remote control interpretation, task management, on-orbit monitoring, etc., and is an important index.

[0003] At present, the identifier of the traditional satellite is generally not changeable, and the corresponding identifier is often artificially allocated at the beginning of the design, which is deeply involved in the design of the whole satellite, involving multiple subsystems and subsystems. Therefore, after the satellite is launched into orbit, it is difficult to achieve high reliability of global change of the ID number. The initiator of the on-board data stream is the remote control uplink interface, and the satellite ID number is changed in orbit by innovatively changing the current remote control uplink data stream.

[0004] In the face of the development trend of increasing number of on-orbit satellites, multi-satellite networking, whole-satellite replacement, and large-scale on-orbit maintenance, a convenient and reliable on-orbit satellite ID number changing scheme is set, and the latest satellite identifier is stored by changing the satellite identifier through the satellite uplink remote control channel. It can meet the urgent needs of satellite networking applications and has the function of on-orbit satellite ID maintenance and management of large-scale constellation. SUMMARY

[0005] In view of the defects in the prior art, the purpose of the present application is to provide an on-orbit satellite ID number changing method and system.

[0006] According to the on-orbit satellite ID number changing method provided by the present application, the following steps are included: Step S1: adding a satellite identifier changing remote control frame on the ground uplink remote control frame; Step S2: adding a satellite identifier changing remote control package on the channel gateway remote control package sent by the on-board CPU module; Step S3: adding a satellite identifier changing remote control package analysis on the on-board channel gateway FPGA module, and performing three-to-two self-refresh storage on the satellite identifier; Step S4: adding a downlink telemetry frame to the downlink telemetry frame of the channel gateway module; Step S5: after completing the on-orbit change of the satellite ID number, the latest ID is returned to the ground for confirmation.

[0007] Preferably, in the step S1: The content of the uplink remote control frame is determined by the CPU software, the designer and the user.

[0008] Preferably, in the step S2: The CPU module can maintain the initial state of the satellite identification word, and be consistent with the initial jumper satellite word of the channel gateway; at the same time, the CPU module can change the satellite identification word, and parse the remote control frame; the satellite identification word is refreshed by three-to-two self-refresh storage; the CPU module can prevent the loss of the satellite identification word due to power failure; The CPU module can compare the satellite identification word state in real time through the channel gateway module on-board telemetry; when the satellite identification word comparison of three consecutive telemetry packets is inconsistent, the satellite identification word of the channel gateway is refreshed through a remote control packet; if the channel gateway module on-board telemetry cannot be received, the satellite identification word of the channel gateway is refreshed by using a timing sending remote control packet; All other application occasions involving the satellite identification word in the program of the CPU module need to be adaptively modified; The format of the channel gateway remote control packet is: synchronization header+byte 1+byte 2, a total of 4 bytes, wherein the spacecraft identifier is 12 bits; The synchronization header is fixed at 2 bytes, byte 1 is the high 8 bits of the satellite identification word, and byte 2 is the low 4 bits of the satellite identification word+0000.

[0009] Preferably, in the step S3: The channel gateway FPGA parses the satellite identification word change remote control packet and extracts the updated satellite identification word; the channel gateway FPGA displays the currently executed satellite identification word through telemetry; The channel gateway FPGA cancels part of the telemetry information according to the resource condition, and cancels the remote control frame count of the VCID number of the last received remote control frame.

[0010] Preferably, the satellite word related information in the channel gateway on-board telemetry is transmitted to the ground in real-time telemetry, and the remote control frame is controlled remotely according to the telemetry satellite word information in an abnormal state; The satellite word is restored to the power-on default jumper state through the instantaneous power-off instruction, and the channel gateway remote control output right is switched to a normally working machine before the instantaneous power-off, and then the master instantaneous power-off and the standby instantaneous power-off are sequentially sent.

[0011] According to the on-orbit satellite ID number change system provided by the application, the following steps are performed: Module M1: The satellite identification word change remote control frame is added to the uplink remote control frame of the ground; Module M2: The satellite identification word change remote control packet is added to the channel gateway remote control packet sent by the on-board CPU module of the satellite; Module M3: The satellite identification word change remote control packet parsing and the satellite identification word three-to-two self-refresh storage are added to the on-board channel gateway FPGA module of the satellite; Module M4: The downlink telemetry frame is added to the downlink telemetry frame of the channel gateway module; Module M5: After completing the on-orbit change of the satellite ID number, the latest ID will be synchronously returned to the ground for confirmation.

[0012] Preferably, in module M1: The content written to the uplink remote control frame is determined by the CPU software, designers, and users.

[0013] Preferably, in module M2: The CPU module can maintain the initial state of the satellite identification word, ensuring it matches the initial jumper satellite word at the channel gateway; it can also parse remote control frames that modify the satellite identification word, and perform self-refreshing storage of the satellite identification word (two out of three); the CPU module can prevent the satellite identification word from being lost due to power failure. The CPU module can perform real-time comparison of satellite identification word status through the telemetry of the channel gateway module itself; if the satellite identification word comparison of three consecutive telemetry packets is inconsistent, the channel gateway satellite identification word is refreshed through remote control packets; if the telemetry of the channel gateway module itself cannot be received, the method of periodically sending remote control packets to refresh the channel gateway satellite identification word is adopted. All other applications involving satellite identification characters in the CPU module's program need to be adapted accordingly; The format of the remote control packet sent to the channel gateway is: synchronization header + byte 1 + byte 2, totaling 4 bytes, of which the spacecraft identifier is 12 bits; The synchronization header is a fixed 2 bytes, with byte 1 being the satellite identification word (high 8 bits) and byte 2 being the satellite identification word (low 4 bits) + 0000.

[0014] Preferably, in module M3: The channel gateway FPGA parses the satellite identification word, changes the remote control packet, and extracts the updated satellite identification word. The channel gateway FPGA displays the currently executed satellite identification word through telemetry. The channel gateway FPGA cancels some telemetry information based on resource availability and cancels the remote frame count for the most recently received remote frame VCID number.

[0015] Preferably, satellite word-related information from the telemetry of the channel gateway board is transmitted to the ground in real-time telemetry, and remote control is performed by generating remote control frames based on the telemetry satellite word information in case of anomalies. The satellite signal is restored to the default jumper state by a momentary power failure command. Before the momentary power failure, the remote control output right of the channel gateway is switched to the working machine, and then the momentary power failure of the main machine and the momentary power failure of the backup machine are sent in sequence.

[0016] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention solves the problem of the unchangeable identifiers of traditional satellites. By uploading and changing satellite identifiers through the satellite's uplink remote control channel and storing the latest satellite identifiers, it can meet the urgent needs of satellite networking applications and has the function of maintaining and managing on-orbit satellite IDs for large-scale constellations.

[0017] 2. The newly added CPU module's function of real-time comparison of telemetry satellite identification words with channel gateway modules can not only achieve the purpose of real-time maintenance of channel gateway satellite identification words, but also achieve the function of quickly restoring the latest satellite identification words through the CPU module when the channel gateway is momentarily powered off and the latest satellite identification words are lost.

[0018] 3. This invention, in conjunction with the timed maintenance function in case of telemetry channel anomalies, ensures that the satellite identification word is known and maintainable by both the channel gateway and the CPU module under various operating conditions currently considered, further improving the reliability of satellite identification word annotation changes. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a flowchart of an on-orbit satellite ID number change method as described in an embodiment of the present invention; Figure 2 This is a schematic diagram of the traditional satellite remote control uplink data stream involved in an embodiment of the present invention; Figure 3 This is a schematic diagram of the remote control uplink data stream for changing the on-orbit ID number in an embodiment of the present invention; Detailed Implementation The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0020] Example 1: This invention provides a method for changing the on-orbit satellite ID (satellite identifier), comprising: after receiving a ground-based data entry command, the onboard CPU stores the latest satellite identifier and sends a remote control packet for changing the satellite identifier to the channel gateway module via a telemetry group acquisition command interface (asynchronous serial port); upon receiving the remote control packet, the channel gateway module updates and stores the latest satellite identifier; after completing the on-orbit change of the satellite ID, the channel gateway module adds a downlink telemetry frame to the downlink telemetry frame, synchronously returning the latest ID to the ground for confirmation. This invention solves the problem of the unchangeable identifiers of traditional satellites, can meet the urgent needs of satellite networking applications, has the function of maintaining and managing on-orbit satellite IDs for large-scale constellations, and also has the function of quickly recovering satellite identifiers through the CPU module after loss, further improving the reliability of satellite identifier data entry changes.

[0021] According to the present invention, a method for changing the ID number of an on-orbit satellite is provided, such as... Figures 1-3 As shown, it includes: Step S1: Add satellite identification words to the uplink remote control frame on the ground to change the remote control frame; Specifically, in step S1: The content written to the uplink remote control frame is determined by the CPU software, designers, and users.

[0022] Step S2: The onboard CPU module sends a remote control packet to the channel gateway to add a satellite identification word and modify the remote control packet; Specifically, in step S2: The CPU module can maintain the initial state of the satellite identification word, ensuring it matches the initial jumper satellite word at the channel gateway; it can also parse remote control frames that modify the satellite identification word, and perform self-refreshing storage of the satellite identification word (two out of three); the CPU module can prevent the satellite identification word from being lost due to power failure. The CPU module can perform real-time comparison of satellite identification word status through the telemetry of the channel gateway module itself; if the satellite identification word comparison of three consecutive telemetry packets is inconsistent, the channel gateway satellite identification word is refreshed through remote control packets; if the telemetry of the channel gateway module itself cannot be received, the method of periodically sending remote control packets to refresh the channel gateway satellite identification word is adopted. All other applications involving satellite identification characters in the CPU module's program need to be adapted accordingly; The format of the remote control packet sent to the channel gateway is: synchronization header + byte 1 + byte 2, totaling 4 bytes, of which the spacecraft identifier is 12 bits; The synchronization header is a fixed 2 bytes, with byte 1 being the satellite identification word (high 8 bits) and byte 2 being the satellite identification word (low 4 bits) + 0000.

[0023] Step S3: The satellite identification word is added to the FPGA module of the on-board channel gateway to change the remote control packet parsing, and the satellite identification word is stored by self-refreshing after taking two out of three; Specifically, in step S3: The channel gateway FPGA parses the satellite identification word, changes the remote control packet, and extracts the updated satellite identification word. The channel gateway FPGA displays the currently executed satellite identification word through telemetry. The channel gateway FPGA cancels some telemetry information based on resource availability and cancels the remote frame count for the most recently received remote frame VCID number.

[0024] Step S4: Add a new downlink telemetry frame to the downlink telemetry frame of the channel gateway module; Step S5: After completing the on-orbit change of the satellite ID number, the latest ID is synchronously returned to the ground for confirmation.

[0025] Specifically, satellite word-related information from the telemetry of the channel gateway board is transmitted to the ground in real-time telemetry. In case of anomalies, remote control frames are generated based on the telemetry satellite word information for remote control. The satellite signal is restored to the default jumper state by a momentary power failure command. Before the momentary power failure, the remote control output right of the channel gateway is switched to the working machine, and then the momentary power failure of the main machine and the momentary power failure of the backup machine are sent in sequence.

[0026] Example 2: Example 2 is a preferred embodiment of Example 1, and is used to illustrate the present invention in more detail.

[0027] The present invention also provides an on-orbit satellite ID number change system, which can be implemented by executing the process steps of the on-orbit satellite ID number change method. That is, those skilled in the art can understand the on-orbit satellite ID number change method as a preferred embodiment of the on-orbit satellite ID number change system.

[0028] An on-orbit satellite ID number changing system provided by the present invention includes: Module M1: Add satellite identification words to the uplink remote control frame on the ground to change the remote control frame; Specifically, in module M1: The content written to the uplink remote control frame is determined by the CPU software, designers, and users.

[0029] Module M2: The onboard CPU module sends a remote control packet to the channel gateway to add a satellite identification word and modify the remote control packet; Specifically, in module M2: The CPU module can maintain the initial state of the satellite identification word, ensuring it matches the initial jumper satellite word at the channel gateway; it can also parse remote control frames that modify the satellite identification word, and perform self-refreshing storage of the satellite identification word (two out of three); the CPU module can prevent the satellite identification word from being lost due to power failure. The CPU module can perform real-time comparison of satellite identification word status through the telemetry of the channel gateway module itself; if the satellite identification word comparison of three consecutive telemetry packets is inconsistent, the channel gateway satellite identification word is refreshed through remote control packets; if the telemetry of the channel gateway module itself cannot be received, the method of periodically sending remote control packets to refresh the channel gateway satellite identification word is adopted. All other applications involving satellite identification characters in the CPU module's program need to be adapted accordingly; The format of the remote control packet sent to the channel gateway is: synchronization header + byte 1 + byte 2, totaling 4 bytes, of which the spacecraft identifier is 12 bits; The synchronization header is a fixed 2 bytes, with byte 1 being the satellite identification word (high 8 bits) and byte 2 being the satellite identification word (low 4 bits) + 0000.

[0030] Module M3: The on-board channel gateway FPGA module adds satellite identification word modification remote control packet parsing, and satellite identification word two-out-of-three self-refresh storage; Specifically, in module M3: The channel gateway FPGA parses the satellite identification word, changes the remote control packet, and extracts the updated satellite identification word. The channel gateway FPGA displays the currently executed satellite identification word through telemetry. The channel gateway FPGA cancels some telemetry information based on resource availability and cancels the remote frame count for the most recently received remote frame VCID number.

[0031] Module M4: Add downlink telemetry frames to the channel gateway module's downlink telemetry frames; Module M5: After completing the on-orbit change of the satellite ID number, the latest ID will be synchronously returned to the ground for confirmation.

[0032] Specifically, satellite word-related information from the telemetry of the channel gateway board is transmitted to the ground in real-time telemetry. In case of anomalies, remote control frames are generated based on the telemetry satellite word information for remote control. The satellite signal is restored to the default jumper state by a momentary power failure command. Before the momentary power failure, the remote control output right of the channel gateway is switched to the working machine, and then the momentary power failure of the main machine and the momentary power failure of the backup machine are sent in sequence.

[0033] Example 3: Example 3 is a preferred example of Example 1, and is used to illustrate the present invention in more detail.

[0034] To address the current state of the technology, the purpose of this invention is to provide a method for changing the on-orbit satellite ID (satellite identifier). By adding a real-time comparison function to the channel gateway module's telemetry satellite identifier function to the CPU module, it can achieve both real-time maintenance of the channel gateway's satellite identifier and rapid recovery of the latest satellite identifier after a momentary power outage at the channel gateway. Combined with a timed maintenance function for telemetry channel anomalies, the satellite identifier can be known and maintained by both the channel gateway and the CPU module under various considered operating conditions, further improving the reliability of satellite identifier changes.

[0035] Typically, the onboard data stream originates from the remote control uplink interface, therefore Figure 2 The current remote control uplink data streams are analyzed to determine the aspects involved in the satellite ID number change. The modules involved in the satellite ID number change can be narrowed down to the channel gateway module and the CPU module.

[0036] When the IO module sends or receives short messages, it only truncates the length and does not make any judgments; the downlink telemetry part of the channel gateway only judges the telemetry frame header.

[0037] The principle for changing the satellite ID number in orbit is to use existing hardware interfaces as much as possible, and to achieve this function only by changing the FPGA or software.

[0038] The CPU module is the central hub for all satellite identification words and their processing. A data stream for satellite identification word changes was designed to address this characteristic, such as... Figure 3 As shown, it includes the following steps: Step S1: Add satellite identification words to the uplink remote control frame on the ground to change the remote control frame; Step S2: The onboard CPU module sends a remote control packet to the channel gateway to add a satellite identification word and modify the remote control packet; Step S3: The satellite identification word is added to the FPGA module of the on-board channel gateway to change the remote control packet parsing, and the satellite identification word is stored by self-refreshing after taking two out of three; Step S4: Add a new downlink telemetry frame to the downlink telemetry frame of the channel gateway module; Step S5: After completing the on-orbit change of the satellite ID number, synchronize the latest ID back to the ground for confirmation. All changes to satellite identifiers are transmitted via CPU registers. After receiving the register, the CPU stores the latest satellite identifier and sends the satellite identifier change remote control packet to the channel gateway module via the telemetry group acquisition command interface (asynchronous serial port). Upon receiving the satellite identifier change remote control packet, the channel gateway module updates and stores the latest satellite identifier.

[0039] The change of satellite identification word does not affect the system, other subsystems, the hardware environment of subsystems and stand-alone machines, and the function of annotating the satellite identification word after the change is reasonable and feasible, so the change can be implemented.

[0040] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0041] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for changing the ID number of an on-orbit satellite, characterized in that, include: Step S1: Add satellite identification words to the uplink remote control frame on the ground to change the remote control frame; Step S2: The onboard CPU module sends a remote control packet to the channel gateway to add a satellite identification word and modify the remote control packet; Step S3: The satellite identification word is added to the FPGA module of the on-board channel gateway to change the remote control packet parsing, and the satellite identification word is stored by self-refreshing after taking two out of three; Step S4: Add a new downlink telemetry frame to the downlink telemetry frame of the channel gateway module; Step S5: After completing the on-orbit change of the satellite ID number, the latest ID is synchronously returned to the ground for confirmation.

2. The method for changing the on-orbit satellite ID number according to claim 1, characterized in that, In step S1: The content written to the uplink remote control frame is determined by the CPU software, designers, and users.

3. The method for changing the on-orbit satellite ID number according to claim 1, characterized in that, In step S2: The CPU module can maintain the initial state of the satellite identification word, which is consistent with the initial jumper satellite word of the channel gateway; it can also parse the remote control frame for changing the satellite identification word and store the satellite identification word by taking two out of three and refreshing it. The CPU module can identify satellite characters to prevent loss during power outages; The CPU module can perform real-time comparison of satellite identification word status through the telemetry of the channel gateway module itself; if the satellite identification word comparison of three consecutive telemetry packets is inconsistent, the channel gateway satellite identification word is refreshed through remote control packets; if the telemetry of the channel gateway module itself cannot be received, the method of periodically sending remote control packets to refresh the channel gateway satellite identification word is adopted. All other applications involving satellite identification characters in the CPU module's program need to be adapted accordingly; The format of the remote control packet sent to the channel gateway is: synchronization header + byte 1 + byte 2, totaling 4 bytes, of which the spacecraft identifier is 12 bits; The synchronization header is a fixed 2 bytes, with byte 1 being the satellite identification word (high 8 bits) and byte 2 being the satellite identification word (low 4 bits) + 0000.

4. The method for changing the on-orbit satellite ID number according to claim 1, characterized in that, In step S3: The channel gateway FPGA parses the satellite identification word, changes the remote control packet, and extracts the updated satellite identification word. The channel gateway FPGA displays the currently executed satellite identification word through telemetry. The channel gateway FPGA cancels some telemetry information based on resource availability and cancels the remote frame count for the most recently received remote frame VCID number.

5. The method for changing the on-orbit satellite ID number according to claim 1, characterized in that: The satellite word information in the telemetry of the channel gateway board is transmitted to the ground in real-time telemetry. In case of anomalies, remote control frames are generated based on the telemetry satellite word information for remote control. The satellite signal is restored to the default jumper state by a momentary power failure command. Before the momentary power failure, the remote control output right of the channel gateway is switched to the working machine, and then the momentary power failure of the main machine and the momentary power failure of the backup machine are sent in sequence.

6. An on-orbit satellite ID number change system, characterized in that, include: Module M1: Add satellite identification words to the uplink remote control frame on the ground to change the remote control frame; Module M2: The onboard CPU module sends a remote control packet to the channel gateway to add a satellite identification word and modify the remote control packet; Module M3: The on-board channel gateway FPGA module adds satellite identification word modification remote control packet parsing, and satellite identification word two-out-of-three self-refresh storage; Module M4: Add downlink telemetry frames to the channel gateway module's downlink telemetry frames; Module M5: After completing the on-orbit change of the satellite ID number, the latest ID will be synchronously returned to the ground for confirmation.

7. The on-orbit satellite ID number change system according to claim 6, characterized in that, In module M1: The content written to the uplink remote control frame is determined by the CPU software, designers, and users.

8. The on-orbit satellite ID number change system according to claim 6, characterized in that, In module M2: The CPU module can maintain the initial state of the satellite identification word, which is consistent with the initial jumper satellite word of the channel gateway; it can also parse the remote control frame for changing the satellite identification word and store the satellite identification word by taking two out of three and refreshing it. The CPU module can identify satellite characters to prevent loss during power outages; The CPU module can perform real-time comparison of satellite identification word status through the telemetry of the channel gateway module itself; if the satellite identification word comparison of three consecutive telemetry packets is inconsistent, the channel gateway satellite identification word is refreshed through remote control packets; if the telemetry of the channel gateway module itself cannot be received, the method of periodically sending remote control packets to refresh the channel gateway satellite identification word is adopted. All other applications involving satellite identification characters in the CPU module's program need to be adapted accordingly; The format of the remote control packet sent to the channel gateway is: synchronization header + byte 1 + byte 2, totaling 4 bytes, of which the spacecraft identifier is 12 bits; The synchronization header is a fixed 2 bytes, with byte 1 being the satellite identification word (high 8 bits) and byte 2 being the satellite identification word (low 4 bits) + 0000.

9. The on-orbit satellite ID number change system according to claim 6, characterized in that, In module M3: The channel gateway FPGA parses the satellite identification word, changes the remote control packet, and extracts the updated satellite identification word. The channel gateway FPGA displays the currently executed satellite identification word through telemetry. The channel gateway FPGA cancels some telemetry information based on resource availability and cancels the remote frame count for the most recently received remote frame VCID number.

10. The on-orbit satellite ID number change system according to claim 6, characterized in that: The satellite word information in the telemetry of the channel gateway board is transmitted to the ground in real-time telemetry. In case of anomalies, remote control frames are generated based on the telemetry satellite word information for remote control. The satellite signal is restored to the default jumper state by a momentary power failure command. Before the momentary power failure, the remote control output right of the channel gateway is switched to the working machine, and then the momentary power failure of the main machine and the momentary power failure of the backup machine are sent in sequence.

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