Laser and VDES on-orbit data processing system

Abstract

The invention provides a laser and VDES on-orbit data processing system, and the system comprises a laser load data processing unit which is used for receiving laser load data, recovering laser inter-satellite data to original data, and transmitting the original data to a VDES load in real time; sending the laser service data to an on-satellite data storage management unit; the VDES load data processing unit is used for receiving the data of the VDES load, organizing transmission frames of the inter-satellite data and then forwarding the inter-satellite data to the laser load in real time; sending the VDES service data to an on-satellite data storage management unit; the S-frequency-band transceiving network unit is used for playing back and framing the on-satellite data, sending the on-satellite data to a ground station, receiving the data of the ground station and forwarding the data to a corresponding load; the on-satellite data storage management unit is used for storage management and supporting on-orbit adjustment of the size of a storage partition; and the satellite service computer data processing unit is used for executing the remote control instruction, feeding back a system state, receiving engineering parameters and sending the engineering parameters to the satellite data storage management unit.

Description

Technical Field

[0001] The invention belongs to the field of satellite-borne data processing, and in particular relates to a laser and VDES on-orbit data processing system. Background Art

[0002] The Automatic Identification System (AIS) is the core of data communication between ships and between ships and shores at sea. The VHF Data Exchange System (VDES) is an enhanced and upgraded version of the Automatic Identification System. On the basis of integrating the existing AIS functions (with all the functions of AIS), it adds special application messages and broadband VHF data exchange functions that support two-way data communication between ships and shore stations, and between ships; at the same time, it expands the information broadcasting capabilities such as broadcasting and special information channels such as meteorological navigation, which is of great significance to the development of the maritime radio digital communication industry.

[0003] The laser and VDES on-orbit data processing system is an important component of the VDES technology verification satellite. The main task of the laser and VDES on-orbit data processing system is to complete the data interaction and storage management between the VDES payload, laser payload and satellite computer and other equipment on the satellite; to build the satellite-to-ground uplink link, receive and demodulate the S-band uplink data transmission signal output by the S-band transceiver network; at the same time, to build the downlink link, send and modulate the downlink data transmission signal, and convert the frequency to the S-band and output it to the S-band transceiver network, and then the S-band transceiver network outputs it to the QV transponder, and then the payload data is downlinked after the satellite enters the country. Summary of the invention

[0004] In view of the problems that existing on-board data storage devices are not capable of real-time forwarding of internal satellite payload data, are not capable of simultaneously establishing laser payloads on satellites, data transmission between VDES payloads and satellite-to-ground links, and are not capable of data interaction between different satellites in a satellite constellation, the purpose of the present invention is to overcome the above-mentioned defects of the prior art and proposes a laser and VDES on-orbit data processing system.

[0005] In order to achieve the above-mentioned object, the present invention proposes a laser and VDES on-orbit data processing system, the system comprising: a laser payload data processing unit, a VDES payload data processing unit, an S-band transceiver network unit, an on-board data storage management unit and a satellite computer data processing unit, wherein:

[0006] The laser payload data processing unit is used to receive the data of the laser payload, perform serial-to-parallel conversion and format detection, and restore the laser intersatellite data to the original data according to the protocol and then forward it to the VDES payload in real time; the laser service data is sent to the on-board data storage management unit for storage management;

[0007] The VDES payload data processing unit is used to receive data from the VDES payload, perform serial-to-parallel conversion and format detection, and for inter-satellite data, organize the transmission frame according to the protocol and forward it to the laser payload in real time; for VDES service data, send it to the on-board data storage management unit for storage management;

[0008] The S-band transceiver network unit is used to establish downlink and uplink with the ground station, to send the satellite data playback frame to the ground station, and to receive data from the ground station and forward it to the corresponding payload according to the protocol;

[0009] The on-board data storage management unit is used to complete the storage management of different types of data on the satellite and support on-orbit adjustment of the storage partition size;

[0010] The satellite computer data processing unit is used to execute the remote control instructions of the satellite computer, perform on-orbit tasks and feedback the system status to the satellite computer. It is also used to receive the engineering parameters of the satellite computer and send them to the on-board data storage management unit to complete the on-orbit data storage management.

[0011] Preferably, the laser payload includes more than one, and a cold standby mode is adopted, supporting only one laser payload to work independently in orbit at the same time; the VDES payload includes one or more than one, and a hot standby mode is adopted, supporting one VDES payload to work independently in orbit at the same time or two VDES payloads to work simultaneously in orbit.

[0012] Preferably, the processing process of the laser payload data processing unit includes:

[0013] Perform serial-to-parallel conversion and format detection on the received laser payload data. If bytes B0 to B3 are 0xFAF32000, it is valid data, otherwise it is invalid data.

[0014] For valid data, further judgment is made: if B4~B5 is 0x47F8, it is laser intersatellite data, which is restored to the original data according to the protocol and forwarded to the VDES payload in real time; otherwise, it is laser service data and is sent to the laser storage area of ​​the onboard data storage management unit for storage management.

[0015] Preferably, the interface of the laser payload data processing unit adopts a three-wire LVDS, and the receiving and sending clock frequencies are both 60 MHz.

[0016] Preferably, the processing process of the VDES payload data processing unit includes:

[0017] The received VDES payload data is converted into serial and parallel data and its format is detected. If the bytes B0 to B1 are 0xEB90 or 0xEB9A, it is valid data, otherwise it is invalid data. Among them, 0xEB9A is VDES intersatellite data, which is forwarded to the laser payload in real time after the transmission frame is organized according to the protocol; 0xEB90 is VDES service data, which is sent to the VDES storage area of ​​the onboard data storage management unit for storage management.

[0018] Preferably, the interface of the VDES payload data processing unit adopts a three-wire LVDS, with a receiving operating frequency of 10 MHz and a sending operating frequency of 2 MHz.

[0019] Preferably, the S-band transceiver network unit includes one S-band uplink receiver and one S-band downlink transmitter, wherein:

[0020] The center frequency of the uplink reception is 2245 MHz, the working frequency band is 2240 MHz to 2250 MHz, the code rate is 1 Mbps, (7 / 8) LDPC channel coding is adopted, and the modulation mode is QPSK;

[0021] The center frequency of the downlink transmission is 2495 Mbps, the working frequency band is 2490 MHz to 2500 MHz, the code rate is 5 Mbps, (7 / 8) LDPC channel coding is adopted, and the modulation mode is QPSK.

[0022] Preferably, the on-board data storage management unit adopts solid-state storage with a capacity of not less than 4Tbit and adopts SLC-type NAND Flash. The storage management of different types of data on the satellite includes: an engineering parameter storage area for storing whole satellite engineering parameters, a VDES storage area for storing VDES payload data, a laser storage area for storing laser payload data, and a data transmission upload storage area for storing data transmission uplink data. The size of each storage interval supports on-orbit reallocation.

[0023] Preferably, the satellite computer data processing unit interacts with the satellite computer via a CAN bus.

[0024] Preferably, the system further comprises: a power supply unit for converting two 12V power supplies provided by the satellite into internal power and having a surge suppression circuit.

[0025] Compared with the prior art, the advantages of the present invention are:

[0026] 1. The present invention has the data interaction function between the satellite internal laser payload and the VDES payload;

[0027] 2. The present invention has the function of data interaction between satellites;

[0028] 3. The present invention has the ability to manage engineering parameters, VDES data, laser data and uploaded data in partitions, and supports on-orbit adjustment of partition size;

[0029] 4. The present invention supports the establishment of downlink and uplink satellite-to-ground links between satellites and the ground through the S frequency band, realizing the functions of satellite data downlink and ground data uplink;

[0030] 5. The present invention only requires a 12V secondary voltage to be provided externally, and other voltages are generated internally, which reduces the demand on the power supply of the entire satellite. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] Figure 1 It is a schematic diagram of the laser payload, VDES payload, satellite computer, and S-band network data flow of the present invention;

[0032] Figure 2 This is a schematic diagram of the satellite-to-ground output downlink data flow;

[0033] Figure 3 This is a schematic diagram of the uplink data flow from satellite to ground;

[0034] Figure 4 It is a schematic diagram of the internal voltage conversion of the present invention. DETAILED DESCRIPTION

[0035] The purpose of the present invention is to realize the storage management and data forwarding of on-orbit data of on-board laser payloads, VDES payloads, satellite computer and other payloads, and to build a satellite-to-ground link to realize the mutual transmission of satellite and ground station data.

[0036] The main functions of this system are to complete the reception and transmission of laser communication payload A(B) data; reception and transmission of VDES payload A / B data; processing and forwarding of data transmitted between VDES payload and laser payload according to the protocol; receiving and demodulating the S-band uplink data transmission signal output by the S-band transceiver network; sending and modulating the downlink data transmission signal, and converting the frequency to the S-band and outputting it to the S-band transceiver network, which then outputs it to the QV transponder.

[0037] The system includes:

[0038] The laser payload data processing unit is used to complete the data interaction between the system and the laser payload. The interface adopts a three-wire LVDS, and the receiving and sending clock frequencies are both 60MHz. The laser payload adopts a cold standby mode, and only supports one payload to work independently on orbit at the same time; the reception and data format detection of the laser payload data are used to complete the serial-to-parallel conversion and format detection of the laser payload data. In one embodiment, if the data B0~B3 bytes are 0xFAF32000, it is valid data, otherwise it is invalid data; if the data B4~B5 is 0x47F8, the data is laser intersatellite data, which needs to be restored to the original data by protocol and then forwarded to the VDES payload in real time; the others are laser business data, which need to be stored and managed on orbit.

[0039] The VDES payload data processing unit is used to complete the data interaction between the system and the VDES payload. The interface adopts a three-wire LVDS, with a receiving clock frequency of 10MHz and a sending clock frequency of 2Mhz. The VDES payload adopts a hot standby mode, which can support one payload to work independently on orbit or two payloads to work on orbit at the same time; the reception and data format detection of the VDES payload data are used to complete the serial-to-parallel conversion and format detection of the VDES payload data. In one embodiment, if the data B0~B1 bytes are 0xEB90 or 0xEB9A, it is valid data, otherwise it is invalid data; among them, 0xEB9A is VDES inter-satellite data, which needs to be forwarded to the laser payload in real time after the transmission frame is organized according to the protocol; 0xEB90 is VDES business data, which needs to be managed for on-orbit data storage.

[0040] The S-band transceiver network unit is used for data interaction between the system and the S-band transceiver network. After the satellite enters the country, if the data downlink task is started, the on-board data will be replayed and composed into transmission frames to be sent to the ground station; if the uplink task is started, the data frame of the ground station will be received and forwarded to the corresponding payload according to the protocol; in one embodiment, the S-band transceiver network has 1 S-band uplink reception and 1 S-band downlink transmission. Its uplink center frequency is 2245MHz, the working frequency band is 2240MHz~2250MHz, the code rate is 1Mbps, (7 / 8) LDPC channel coding is adopted, the modulation method is QPSK, and the capture time is not more than 8s; the downlink center frequency is 2495Mbps, the working frequency band is 2490MHz~2500MHz, the code rate is 5Mbps, (7 / 8) LDPC channel coding is adopted, the modulation method is QPSK, and the carrier frequency accuracy is not more than 2×10 -6 .

[0041] The on-board data storage management unit is used to complete the storage management of on-board data. It supports four fixed storage partitions, namely, the engineering parameter storage area, the VDES storage area, the laser storage area, and the digital transmission upload area: the engineering parameter storage area stores the engineering parameters of the entire satellite, the VDES storage area stores the VDES A / B data, the laser storage area stores the laser communication payload A (B) data, and the digital transmission upload area stores the data uploaded via the digital transmission uplink; in one embodiment, the solid-state storage capacity of the on-board data storage management unit is not less than 4Tbit, and SLC-type NAND Flash is used. The initial storage interval allocation is as follows: 256Gbit is allocated to the engineering parameter storage area, 2Tbit is allocated to the VDES storage area, 1Tbit is allocated to the laser storage area, and 768Gbit is allocated to the digital transmission upload area. The storage interval supports on-orbit reallocation.

[0042] The satellite service computer data processing unit is used for the execution of commands and status monitoring between the system and the satellite service computer. The system and the satellite service computer exchange data through the CAN bus. On the one hand, it executes commands from the satellite service computer, performs on-orbit tasks and feeds back the system status to the satellite service computer. On the other hand, it receives the engineering parameters of the satellite service computer and completes the on-orbit storage management of data. In one embodiment, the satellite service computer unit communicates with the satellite service computer through the CAN bus, collects the internal telemetry of the system and sends it to the satellite service, executes and forwards the remote control instructions from the satellite service, and completes the on-orbit tasks. At the same time, it stores the engineering parameters from the satellite service, transmits them to the ground after the satellite enters the space, and analyzes the on-orbit working status of the satellite service computer.

[0043] The power supply unit is used for the satellite to supply power to the system. The satellite provides two 12V secondary voltages to the system, and the system completes the conversion of internal voltages such as 5V, 3.3V, 1.8V, and 1.5V. In one embodiment, the power supply unit is provided with two 12V secondary electricity by the satellite, and the voltage ripple is not greater than 100mV. The system is equipped with a surge suppression circuit, and has the ability to convert the 12V voltage into 5V, 3.3V, 2.5V, 1.8V, 1.5V, 1.3V, 1.2V, 1.0V and 0.75V for internal use of the system.

[0044] The system has the ability to exchange data between satellites. It is used to build a satellite constellation. Different satellites are connected through laser links to achieve mutual data transmission.

[0045] The technical solution of the present invention is described in detail below with reference to the accompanying drawings and embodiments.

[0046] Example

[0047] The embodiment of the present invention provides a laser and VDES on-orbit data processing system, which realizes data processing between laser payload and VDES payload in satellite, data interaction between different satellites, and data interaction between satellite and ground station through satellite-to-ground link.

[0048] like Figure 1 As shown, the system receives VDES payload A / B data (VDES payload A and B can be hot-backed up) through the LVDS interface, and determines the data type based on the frame header information. If B0~B1 is 0xEB90, it is a business data frame, and the data is packaged according to the CCSDS102.0-B-5 packet telemetry protocol, and the data is stored and managed on-orbit; if B0~B1 is 0xEB9A, it is an intersatellite data frame, which is framed according to the laser communication payload protocol format and forwarded to the laser communication payload A(B) in real time. The system receives laser communication payload A(B) data through the LVDS interface (the laser payload is cold-backed up). If the virtual channel is forwarded to the VDES payload, the VDES intersatellite data frame encapsulated in the laser protocol is extracted and forwarded to the VDES payload A / B in real time. Otherwise, the data is packaged according to the CCSDS102.0-B-5 packet telemetry protocol, and the data is stored and managed on-orbit. The solid-state large-capacity storage provided by the system supports four fixed storage partitions: engineering parameter storage area, VDES storage area, laser storage area, and digital transmission upload area. The engineering parameter storage area stores the engineering parameters of the entire satellite, the VDES storage area stores VDES A / B data, the laser storage area stores laser communication payload A(B) data, and the digital transmission upload area stores ground data uploaded through the digital transmission uplink channel.

[0049] After the satellite establishes the satellite-to-ground link upon entry, the satellite can send a command through the satellite computer to start the data satellite-to-ground playback mode, such as Figure 2As shown: read real-time industrial parameter data, read industrial parameter data recorded in industrial parameter storage area, VDES storage area, laser storage area, VDES payload A / B data, laser communication payload A(B) data, assemble AOS transmission frame, LDPC channel coding, QPSK modulation, up-convert to S band and then output to S band transceiver network. In satellite-to-ground playback mode, the system supports sequential playback of each partition, playback by storage address, and on-demand playback by time; supports autonomous erasure of each partition and command erasure of each partition / all partitions; has bad block management and error correction capabilities; supports re-partitioning of each partition and adjustment of partition size. In addition, the system supports inter-satellite laser playback: read VDES storage area data and data upload storage area data, frame according to the laser communication payload protocol format and send to laser communication payload A(B). If there is VDES payload real-time data, the VDES payload real-time data will be forwarded to laser communication at the same time. It should be noted that the satellite-to-ground playback mode and the inter-satellite laser playback mode are mutually exclusive; and whether in the satellite-to-ground playback mode or the inter-satellite laser playback mode, the VDES inter-satellite data frame real-time forwarding function is supported.

[0050] After the satellite establishes the satellite-to-ground link upon entry, the system receives QV digital uplink data, such as Figure 3 As shown: according to the virtual channel, if the virtual channel is the reconstructed data of the laser communication payload B, the B_PDU data field data in the uplink AOS frame is extracted, and forwarded to the laser communication payload B in real time through LVDS; if the virtual channel is the service data of the laser communication payload A or B, the source packets are grouped and stored in the data transmission upload area; if the virtual channel is the VDES payload data, the B_PDU data field data in the uplink AOS frame is extracted, and forwarded to the VDES payload A / B in real time through LVDS; if the virtual channel is the reconstructed data of the multiplexer modulator, the system processes it by itself and completes the on-orbit reconstruction of the program.

[0051] At the same time, the system exchanges data with the satellite computer through the CAN bus, sends telemetry data reflecting the working status of the multiplexer modulator, receives control instructions, system time and other information from the satellite computer, and completes the working mode and working status conversion of the multiplexer modulator.

[0052] like Figure 4 Shown is a schematic diagram of the internal voltage conversion of the present invention.

[0053] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention is described in detail with reference to the embodiments, it should be understood by those skilled in the art that any modification or equivalent replacement of the technical solutions of the present invention does not depart from the spirit and scope of the technical solutions of the present invention and should be included in the scope of the claims of the present invention.

Claims

1. A laser and VDES on-orbit data processing system, characterized in that: The system includes: a laser payload data processing unit, a VDES payload data processing unit, an S-band transceiver network unit, an onboard data storage management unit and a satellite computer data processing unit, wherein: The laser payload data processing unit is used to receive the data of the laser payload, perform serial-to-parallel conversion and format detection, and restore the laser intersatellite data to the original data according to the protocol and then forward it to the VDES payload in real time; the laser service data is sent to the on-board data storage management unit for storage management; The VDES payload data processing unit is used to receive data from the VDES payload, perform serial-to-parallel conversion and format detection, and for inter-satellite data, organize the transmission frame according to the protocol and forward it to the laser payload in real time; for VDES service data, send it to the on-board data storage management unit for storage management; The S-band transceiver network unit is used to establish downlink and uplink with the ground station, to send the satellite data playback frame to the ground station, and to receive data from the ground station and forward it to the corresponding payload according to the protocol; The on-board data storage management unit is used to complete the storage management of different types of data on the satellite and support on-orbit adjustment of the storage partition size; The satellite computer data processing unit is used to execute the remote control instructions of the satellite computer, perform on-orbit tasks and feedback the system status to the satellite computer. It is also used to receive the engineering parameters of the satellite computer and send them to the on-board data storage management unit to complete the on-orbit data storage management.

2. The laser and VDES on-orbit data processing system according to claim 1, characterized in that: The laser payload includes more than one, and adopts a cold standby mode, supporting only one laser payload to work independently in orbit at the same time; the VDES payload includes one or more, and adopts a hot standby mode, supporting one VDES payload to work independently in orbit at the same time or two VDES payloads to work simultaneously in orbit.

3. The laser and VDES on-orbit data processing system according to claim 2, characterized in that: The processing process of the laser load data processing unit includes: Perform serial-to-parallel conversion and format detection on the received laser payload data. If bytes B0 to B3 are 0xFAF32000, it is valid data, otherwise it is invalid data. For valid data, further judgment is made: if B4~B5 is 0x47F8, it is laser intersatellite data, which is restored to the original data according to the protocol and forwarded to the VDES payload in real time; otherwise, it is laser service data and is sent to the laser storage area of ​​the onboard data storage management unit for storage management.

4. The laser and VDES on-orbit data processing system according to claim 2, characterized in that: The interface of the laser payload data processing unit adopts a three-wire LVDS, and the receiving and sending clock frequencies are both 60 MHz.

5. The laser and VDES on-orbit data processing system according to claim 2, characterized in that: The processing process of the VDES payload data processing unit includes: The received VDES payload data is converted into serial and parallel data and its format is detected. If the bytes B0 to B1 are 0xEB90 or 0xEB9A, it is valid data, otherwise it is invalid data. Among them, 0xEB9A is VDES intersatellite data, which is forwarded to the laser payload in real time after the transmission frame is organized according to the protocol; 0xEB90 is VDES service data, which is sent to the VDES storage area of ​​the onboard data storage management unit for storage management.

6. The laser and VDES on-orbit data processing system according to claim 2, characterized in that: The interface of the VDES payload data processing unit adopts a three-wire LVDS, with a receiving operating frequency of 10 MHz and a sending operating frequency of 2 MHz.

7. The laser and VDES on-orbit data processing system according to claim 1, characterized in that: The S-band transceiver network unit includes one S-band uplink receiving channel and one S-band downlink transmitting channel, wherein: The center frequency of the uplink reception is 2245 MHz, the working frequency band is 2240 MHz to 2250 MHz, the code rate is 1 Mbps, (7 / 8) LDPC channel coding is adopted, and the modulation mode is QPSK; The center frequency of the downlink transmission is 2495 Mbps, the working frequency band is 2490 MHz to 2500 MHz, the code rate is 5 Mbps, (7 / 8) LDPC channel coding is adopted, and the modulation mode is QPSK.

8. The laser and VDES on-orbit data processing system according to claim 1, characterized in that: The on-board data storage management unit adopts solid-state storage with a capacity of not less than 4Tbit and adopts SLC-type NAND Flash. The storage management of different types of data on the satellite includes: an engineering parameter storage area for storing whole satellite engineering parameters, a VDES storage area for storing VDES payload data, a laser storage area for storing laser payload data, and a data transmission upload storage area for storing data transmission uplink data. The size of each storage interval supports on-orbit reallocation.

9. The laser and VDES on-orbit data processing system according to claim 1, characterized in that: The satellite computer data processing unit interacts with the satellite computer via the CAN bus.

10. The laser and VDES on-orbit data processing system according to claim 1, characterized in that: The system further comprises: a power supply unit, which is used to convert two 12V power lines provided by the satellite into internal power and is provided with a surge suppression circuit.

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