Data synchronization system, data synchronization method and software synchronization deployment method

Abstract

The invention discloses a data synchronization system, a data synchronization method and a software synchronization deployment method, and belongs to the technical field of aerospace data synchronization. The data synchronization system comprises a ground test launch control system, a rocket system and a satellite communication system; the ground test launch control system is arranged in a ground control center and is used for rocket test, launch process control and telemetry data processing, storage and display; the rocket-mounted system is used for controlling a rocket by completing receiving and sending of test launch control instructions, navigation guidance and attitude control; the satellite communication system is used for providing communication between the ground test launch control system and the rocket system; the satellite communication system comprises a satellite and a ground station with a ground gateway; and the ground station is used for packing and unpacking the received and sent data. According to the invention, rapid deployment of software on the rocket can be realized through a satellite wireless communication mode, and data transmission is not affected by signal interference caused by severe sites and weather.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace data synchronization, and in particular to a data synchronization system, a data synchronization method and a software synchronization deployment method. Background Art

[0002] Before the launch vehicle flight test, the data is interpreted based on the results of each test to confirm the correctness of the software and hardware. According to the results, the software may need to be modified and deployed, and upgraded and iterated. In the test, launch and control of the launch vehicle, the inspection of each system of the rocket, power supply and distribution, etc. require the ground system to issue instructions, which are generally achieved through wired or wireless communication to send and receive instructions and retrieve telemetry data.

[0003] In traditional space launches, when sending and receiving commands and synchronizing data, wired or wireless communication methods are used depending on the usage scenario. Wired communication lines are extremely susceptible to physical shock or vibration during the launch process, which can cause line breakage or loose connections, affecting communication quality or even interrupting communications. The internal space of the rocket is limited, and wired lines are difficult to arrange and maintain, requiring regular maintenance and inspections. The arrangement points are fixed and have poor flexibility. If a sea launch is adopted, wireless communication is generally used due to the distance limit between the rear test and launch control hall and the rocket. Wireless communication is easily affected by signal interference, affecting the transmission quality and stability of the signal. Wireless communication is easily affected by weather and environment, and bad weather reduces communication stability.

[0004] When deploying software upgrades, they are usually transmitted via CDs or USBs, which depends on the read and write speed of the storage medium. The read and write speed of optical drives is generally slow, and the memory capacity of the medium is limited, but the size of the transferred file is not fixed. If the file is frequently modified, deployment will be troublesome and time-consuming. At the same time, software upgrades can only be performed during the rocket construction or testing phase, and cannot be performed after the rocket is launched.

[0005] In view of this, it is necessary to provide a new technical solution to solve the above problems. Summary of the invention

[0006] In order to solve the above technical problems, the present application provides a data synchronization system and method, which can be applied to the aerospace field. It can realize the rapid deployment of on-rocket software through satellite wireless communication. The data transmission is not affected by signal interference caused by harsh sites and weather, and the software can also be deployed and upgraded after the rocket is launched.

[0007] A data synchronization system, comprising:

[0008] Ground test, launch and control system: The ground test, launch and control system is set up in the ground control center and is used for rocket testing, launch process control and telemetry data processing, storage and display;

[0009] Onboard system; the onboard system is used to control the rocket by completing the sending and receiving of test, launch and control instructions, navigation and guidance, and attitude control;

[0010] Satellite communication system; the satellite communication system is used to provide communication between the ground test, launch and control system and the onboard system; the satellite communication system includes a satellite and a ground station with a ground gateway; the ground station is used to pack and unpack received and sent data.

[0011] Preferably, the ground measurement, launch and control system includes a ground software management module, a measurement, launch and control terminal, a data browsing terminal, a data processing terminal and a data storage terminal.

[0012] Preferably, the onboard system includes an onboard software management module, flight master control software, safety control software, engine control software, inertial measurement software and comprehensive acquisition and editing software.

[0013] Preferably, it also includes a software management system; the software management system is used for version control and software backup of all software; the software management system includes an on-rocket software management module and a ground software management module; the on-rocket software management module is used for version control and software backup of the flight master control software, safety control software, engine control software, inertial measurement software and comprehensive editing software; the ground software management module is used for version control and software backup of the test, launch and control terminals, data browsing terminals, data processing terminals and data storage terminals.

[0014] Preferably, the software management system has a rollback module and a deployment log recording module.

[0015] According to another aspect of the present application, a software synchronization deployment method is also provided, which uses the data synchronization system to perform software synchronization deployment, including:

[0016] Place the latest version of the software to be deployed in the ground software management module;

[0017] The ground software management module compares and confirms the historical versions of the software to be deployed and displays the latest software version;

[0018] The ground software management module and the software other than the ground software management module in the ground test, launch and control system are directly upgraded and deployed through the ground network, and the version information of each software is obtained. After confirmation, it is directly deployed;

[0019] The ground management software places the software upgrade package on the rocket and transmits the software package to the ground station. The ground station communicates with the satellite through the ground gateway to realize encrypted communication data transmission;

[0020] After receiving the uplink data from the ground station, the satellite forwards the received data packet to the rocket receiving antenna;

[0021] The receiving antenna sends the data to the onboard software management module, which decrypts, verifies, and deploys the data.

[0022] The onboard software management module packages the software upgrade status feedback information and sends it to the rocket launch antenna;

[0023] The rocket launch antenna packages and encrypts the status feedback information according to the satellite communication protocol format and sends it to the satellite via an uplink;

[0024] The satellite feeds back the status to the ground gateway, which receives and demodulates the data to the ground station;

[0025] The ground station sends software upgrade status information to the ground software management module through the local area network or a dedicated communication link, and the ground software management module updates, archives and logs the software upgrade status.

[0026] Preferably, a digital signature mechanism is introduced in the ground station and onboard software management modules to ensure the authenticity and integrity of the software package and feedback information.

[0027] Preferably, when the ground station communicates with the satellite to achieve encrypted communication data transmission, a high-strength encryption algorithm is used to encrypt the transmitted data to prevent the data from being stolen or tampered with during transmission; a secure transmission protocol is used to ensure the security and reliability of the communication link.

[0028] According to another aspect of the present application, a data synchronization method is further provided, which uses the data synchronization system to perform data synchronization, including:

[0029] The ground test and launch control system generates instructions according to the communication protocol with the onboard system; the encrypted instruction data is sent to the ground station through the local area network, and the ground station adds an identification after receiving the instruction data;

[0030] The ground station sends data to the ground gateway via satellite communication protocol, and the ground gateway forwards it to the satellite;

[0031] The satellite sends the command data via a downlink to the rocket’s receiving antenna;

[0032] The rocket receiving antenna receives the downlink command data and passes it to the onboard software management module;

[0033] The on-arrow software management module verifies the digital signature of the received instructions to ensure data integrity and reliable source, decrypts the data, confirms the source and destination of the information, and forwards the instructions to the corresponding on-arrow software in the on-arrow system;

[0034] The on-arrow software executes the corresponding instructions and generates status feedback information;

[0035] The status feedback information is sent to the satellite after the status feedback data is encrypted via the transmitting antenna;

[0036] The satellite receives the feedback data, forwards it to the ground gateway and then sends it to the ground station;

[0037] The ground station decrypts and checks the data and then sends it to the ground test and launch control system;

[0038] The ground test and launch control system displays feedback information and records logs.

[0039] Preferably, the identifier after the ground station receives the instruction data is a timestamp.

[0040] Compared with the prior art, this application has at least the following beneficial effects:

[0041] 1. The present invention can realize the rapid deployment of software on the rocket through satellite wireless communication. The data transmission is not affected by signal interference caused by bad sites and weather. Moreover, the software can also be deployed and upgraded after the rocket is launched.

[0042] 2. The present invention can realize data encryption transmission through satellite communication technology, effectively ensuring the security of data transmission.

[0043] 3. The present invention uses satellite communication technology to transmit data, which is not affected by signal interference caused by adverse sites and weather, thereby improving the stability of data transmission.

[0044] 4. The present invention can reduce the risk of data transmission failure caused by damage to hardware such as cables. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Hereinafter, some specific embodiments of the present invention will be described in detail in an exemplary and non-limiting manner with reference to the accompanying drawings. The same reference numerals in the accompanying drawings indicate the same or similar components or parts. It should be understood by those skilled in the art that these drawings are not necessarily drawn to scale.

[0046] In the figure:

[0047] Figure 1 Schematic diagram of the system architecture of the data synchronization system of the present invention.

[0048] The above drawings include the following reference numerals:

[0049] 10. Ground measurement, launch and control system; 20. Satellite communication system; 21. Satellite; 22. Ground station; 30. Onboard system. DETAILED DESCRIPTION

[0050] In order to make the purpose, technical solution and advantages of the present application clearer, the technical solution of the present application will be clearly and completely described below in combination with the specific embodiments of the present application and the corresponding drawings. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of the present application.

[0051] like Figure 1 As shown, a data synchronization system includes: a ground measurement, launch and control system 10, an on-rocket system 30 and a satellite communication system 20.

[0052] Among them, the ground test, launch and control system 10 is set in the ground control center and is used for rocket testing, launch process control, and telemetry data processing, storage and display.

[0053] The onboard system 30 is used to control the rocket by completing the sending and receiving of test, launch and control instructions, navigation and guidance, and attitude control.

[0054] The satellite communication system 20 is used to provide communication between the ground test, launch and control system 10 and the onboard system 30; the satellite communication system 20 includes a satellite 21 and a ground station 22 with a ground gateway; the ground station 22 is used to pack and unpack received and sent data.

[0055] Furthermore, the ground test, launch and control system 10 includes a ground software management module, a test, launch and control terminal, a data browsing terminal, a data processing terminal and a data storage terminal.

[0056] The onboard system 30 includes an onboard software management module, flight master control software, safety control software, engine control software, inertial measurement software and comprehensive acquisition and editing software.

[0057] In addition, a data synchronization system also includes a software management system. The software management system is used for version control and software backup of all software. The software management system includes an on-rocket software management module and a ground software management module; the on-rocket software management module is used to perform version control and software backup on the flight master control software, safety control software, engine control software, inertial measurement software and comprehensive acquisition and editing software; the ground software management module is used to perform version control and software backup on the test, launch and control terminal, data browsing terminal, data processing terminal and data storage terminal.

[0058] In addition, the software management system has a rollback module and a deployment log recording module, which are used for rollback and deployment log recording of software versions respectively.

[0059] Based on the same inventive concept, the present invention also provides a software synchronization deployment method, which uses the data synchronization system to perform software synchronization deployment, including the following steps:

[0060] S101. Place the latest version of the software to be deployed in the ground software management module.

[0061] Among them, the latest version of the software to be deployed can be placed in the ground software management software through remote network, USB, etc.

[0062] S102. The ground software management module compares and confirms the historical versions of the software to be deployed, and displays the latest software version.

[0063] S103, the ground software management module and the software other than the ground software management module in the ground test, launch and control system 10 directly perform software upgrade deployment through the ground network, obtain the version information of each software, and directly deploy it after confirming that it is correct.

[0064] S104, the ground management software places the software upgrade package on the arrow and transmits the software package to the ground station 22. The ground station 22 communicates with the satellite through the ground gateway to realize encrypted communication data transmission.

[0065] S105. After receiving the uplink data from the ground station 22, the satellite 21 forwards the received data packet to the rocket receiving antenna.

[0066] S106. The receiving antenna sends the data to the on-arrow software management module, which decrypts, verifies, and deploys the data.

[0067] S107. The onboard software management module packages the software upgrade status feedback information and sends it to the rocket launch antenna.

[0068] S108. The rocket launch antenna packages and encrypts the status feedback information according to the satellite communication protocol format and sends it to satellite 21 via the uplink.

[0069] S109, the satellite 21 feeds back the status to the ground gateway, and the ground gateway receives and demodulates the data to the ground station 22.

[0070] S110. The ground station 22 sends software upgrade status information to the ground software management module via the local area network or a dedicated communication link, and the ground software management module updates, archives, and logs the software upgrade status.

[0071] Preferably, a digital signature mechanism is introduced in the ground station 22 and the onboard software management module to ensure the authenticity and integrity of the software package and feedback information.

[0072] Preferably, when the ground station 22 communicates with the satellite to realize encrypted communication data transmission, a high-strength encryption algorithm is used to encrypt the transmitted data to prevent the data from being stolen or tampered with during the transmission process; a secure transmission protocol is used to ensure the security and reliability of the communication link.

[0073] The encryption algorithm converts the original data (plaintext) into ciphertext through a series of complex mathematical transformations, making it difficult for unauthorized users to interpret the content. High-strength encryption algorithms are mainly reflected in their strong ability to resist various forms of cryptanalysis attacks, including brute force cracking, statistical analysis, etc.

[0074] In this solution, the high-strength encryption algorithm can use a symmetric encryption algorithm or an asymmetric encryption algorithm. Among them, the symmetric encryption algorithm can use the AES encryption algorithm or 3DES (triple data encryption algorithm). When using the AES encryption algorithm, a 256-bit key length is preferred. The asymmetric encryption algorithm can use the RSA encryption algorithm and the ECC encryption algorithm.

[0075] Based on the same inventive concept, the present invention also provides a data synchronization method, which uses the data synchronization system to perform data synchronization, including the following steps:

[0076] S201, the ground test, launch and control system 10 generates instructions according to the communication protocol with the onboard system 30; the encrypted instruction data is sent to the ground station 22 through the local area network, and the ground station 22 adds an identification after receiving the instruction data.

[0077] The identification after the ground station 22 receives the instruction data is a timestamp. In addition, in this process, a data integrity check is also required.

[0078] S202 , the ground station 22 sends the data to the ground gateway via the satellite communication protocol, and the ground gateway forwards it to the satellite 21 .

[0079] S203, Satellite 21 sends the command data to the rocket receiving antenna via a downlink.

[0080] S204, the rocket receiving antenna receives the downlink command data and passes it to the onboard software management module.

[0081] S205. The on-arrow software management module performs digital signature verification on the received instructions to ensure data integrity and reliable source, decrypts the data, confirms the source and destination of the information, and forwards the instructions to the corresponding on-arrow software in the on-arrow system 30.

[0082] S206, the on-arrow software executes corresponding instructions and generates status feedback information.

[0083] S207 , the state feedback information encrypts the state feedback data and sends it to the satellite 21 through the transmitting antenna.

[0084] S208 , the satellite 21 receives the feedback data, forwards it to the ground gateway and then sends it to the ground station 22 .

[0085] S209: The ground station 22 decrypts and checks the data and then sends it to the ground measurement, launch and control system 10.

[0086] S210. The ground test, launch and control system 10 displays feedback information and records it in a log.

[0087] It should be noted that the above are one-transmit-one-receive instructions. In addition, the onboard software can also periodically send telemetry data in real time through the rocket launch antenna, and finally provide the data to the ground test and launch control system 10 for data interpretation or real-time browsing.

[0088] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0089] It should be noted that the terms "first", "second", etc. in the specification and claims of the present application and the above-mentioned drawings are used to distinguish similar objects, and are not necessarily used to describe a specific order or sequence. It should be understood that the numbers used in this way can be interchanged where appropriate, so that the embodiments of the present application described herein can be implemented in an order other than those illustrated or described herein.

[0090] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A data synchronization system, characterized in that: include: Ground test and launch control system; The ground test, launch and control system is set up in the ground control center and is used for rocket testing, launch process control and telemetry data processing, storage and display; Onboard system; the onboard system is used to control the rocket by completing the sending and receiving of test, launch and control instructions, navigation and guidance, and attitude control; A satellite communication system; the satellite communication system is used to provide communication between a ground test, launch and control system and an onboard system; the satellite communication system includes a satellite and a ground station with a ground gateway; The ground station is used to pack and unpack received and sent data.

2. The data synchronization system according to claim 1, characterized in that: The ground test, launch and control system includes a ground software management module, a test, launch and control terminal, a data browsing terminal, a data processing terminal and a data storage terminal.

3. The data synchronization system according to claim 2, characterized in that: The onboard system includes an onboard software management module, flight master control software, safety control software, engine control software, inertial measurement software and comprehensive acquisition and editing software.

4. The data synchronization system according to claim 3, characterized in that: It also includes a software management system; the software management system is used for version control and software backup of all software; the software management system includes an on-rocket software management module and a ground software management module; the on-rocket software management module is used to perform version control and software backup of the flight master control software, safety control software, engine control software, inertial measurement software and comprehensive editing software; the ground software management module is used to perform version control and software backup of the test, launch and control terminals, data browsing terminals, data processing terminals and data storage terminals.

5. The data synchronization system according to claim 4, characterized in that: The software management system has a rollback module and a deployment log recording module.

6. A software synchronous deployment method, characterized in that: Utilizing the data synchronization system of claim 4 or 5 to perform software synchronization deployment comprises: Place the latest version of the software to be deployed in the ground software management module; The ground software management module compares and confirms the historical versions of the software to be deployed and displays the latest software version; The ground software management module and the software other than the ground software management module in the ground test, launch and control system are directly upgraded and deployed through the ground network, and the version information of each software is obtained. After confirmation, it is directly deployed; The ground management software places the software upgrade package on the rocket and transmits the software package to the ground station. The ground station communicates with the satellite through the ground gateway to realize encrypted communication data transmission; After receiving the uplink data from the ground station, the satellite forwards the received data packet to the rocket receiving antenna; The receiving antenna sends the data to the onboard software management module, which decrypts, verifies, and deploys the data. The onboard software management module packages the software upgrade status feedback information and sends it to the rocket launch antenna; The rocket launch antenna packages and encrypts the status feedback information according to the satellite communication protocol format and sends it to the satellite via an uplink; The satellite feeds back the status to the ground gateway, which receives and demodulates the data to the ground station; The ground station sends software upgrade status information to the ground software management module through the local area network or a dedicated communication link, and the ground software management module updates, archives and logs the software upgrade status.

7. The software synchronous deployment method according to claim 6, characterized in that: A digital signature mechanism is introduced in the ground station and onboard software management modules to ensure the authenticity and integrity of the software package and feedback information.

8. The software synchronization deployment method according to claim 7, characterized in that: When the ground station communicates with the satellite to achieve encrypted communication data transmission, a high-strength encryption algorithm is used to encrypt the transmitted data to prevent the data from being stolen or tampered with during the transmission process; a secure transmission protocol is used to ensure the security and reliability of the communication link.

9. A data synchronization method, characterized in that: Utilizing the data synchronization system of claim 4 or 5 to perform data synchronization comprises: The ground test and launch control system generates instructions according to the communication protocol with the onboard system; the encrypted instruction data is sent to the ground station through the local area network, and the ground station adds an identification after receiving the instruction data; The ground station sends data to the ground gateway via satellite communication protocol, and the ground gateway forwards it to the satellite; The satellite sends the command data via a downlink to the rocket’s receiving antenna; The rocket receiving antenna receives the downlink command data and passes it to the onboard software management module; The on-arrow software management module verifies the digital signature of the received instructions to ensure data integrity and reliable source, decrypts the data, confirms the source and destination of the information, and forwards the instructions to the corresponding on-arrow software in the on-arrow system; The on-arrow software executes the corresponding instructions and generates status feedback information; The status feedback information is sent to the satellite after the status feedback data is encrypted via the transmitting antenna; The satellite receives the feedback data, forwards it to the ground gateway and then sends it to the ground station; The ground station decrypts and checks the data and then sends it to the ground test and launch control system; The ground test and launch control system displays feedback information and records logs.

10. The data synchronization method according to claim 9, characterized in that: The identification after the ground station receives the instruction data is a timestamp.

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