High-speed laser transmission system and method for complex data types between satellite-borne cabins

Abstract

The invention discloses a high-speed laser transmission system and method for satellite-borne inter-cabin complex data types, the system comprises a platform inter-cabin laser communication terminal, the platform inter-cabin laser communication terminal comprises a first processor, at least two first photoelectric transceiver modules and a plurality of groups of first data transceiver modules; the load cabin inter-cabin laser communication terminal comprises a second processor, at least two second photoelectric receiving and transmitting modules and a plurality of groups of second data receiving and transmitting modules. The system is suitable for a satellite magnetic levitation type cabin body structure, and the platform cabin and the load cabin are isolated through magnetic levitation so as to realize high-precision attitude control; a laser communication technology is utilized to simplify an on-satellite data transmission scheme, transmission cables are saved, the weight is reduced, cable disturbance is isolated, meanwhile, multi-channel multi-rate data transmission, forward error correction and link self-adaptive reconstruction are supported, and the real-time performance and reliability of data are ensured.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite magnetic floating cabin inter-transmission technology, in particular to a high-speed laser transmission system and method for complex data types between satellite cabins. BACKGROUND

[0002] In the current field of satellite applications, the payload puts forward higher and higher requirements on the precision and stability of satellite attitude control, and to achieve ultra-high pointing precision and ultra-high stability of satellite attitude control, the vibration rotating parts that interfere with satellite control need to be physically isolated, therefore, many satellite platforms in the prior art adopt the design of magnetic floating cabin separation of platform cabin and load cabin, which brings challenges to the design of satellite data transmission system.

[0003] In the prior art, the hardware scheme for data transmission between the platform cabin and the load cabin is relatively complex, and the data transmission method cannot realize forward error correction, nor can it realize adaptive reconstruction of the data transmission link, so that there are problems of occasional faults causing errors or even link breaks in the data transmission between the platform cabin and the load cabin, and poor anti-interference ability. SUMMARY

[0004] The purpose of the present application is to provide a high-speed laser transmission system and method for complex data types between satellite cabins, to solve the problem in the prior art that the hardware scheme for data transmission between the platform cabin and the load cabin is relatively complex, and the data transmission method cannot realize forward error correction, nor can it realize adaptive reconstruction of the data transmission link, so that there are problems of occasional faults causing errors or even link breaks in the data transmission between the platform cabin and the load cabin, and poor anti-interference ability.

[0005] To achieve the above purpose, the present application realizes by the following technical scheme: On the one hand, the present application provides a high-speed laser transmission system for complex data types between satellite cabins, comprising: a platform cabin inter-laser communication terminal, which is arranged in a platform cabin of a satellite magnetic floating cabin body, the platform cabin inter-laser communication terminal comprising: a first processor, and at least two first optoelectronic transceiver modules and a plurality of groups of first data transceiver modules connected with the first processor respectively, the plurality of groups of first data transceiver modules are connected with a satellite platform cabin single machine, for data transceiving with the satellite platform cabin single machine; The load cabin inter-cabin laser communication terminal is arranged in a load cabin of a satellite magnetic floating cabin body, and comprises a second processor, at least two second optoelectronic transceiver modules and a plurality of groups of second data transceiver modules connected with the second processor respectively, the at least two first optoelectronic transceiver modules are connected with the at least two second optoelectronic transceiver modules, for realizing inter-cabin data communication, and the plurality of groups of second data transceiver modules are connected with each single machine of the satellite load cabin, for performing data transmission and reception with each single machine of the satellite load cabin.

[0006] Preferably, the at least two first optoelectronic transceiver modules and the at least two second optoelectronic transceiver modules communicate data through a wired optical fiber channel and a space optical channel, and the wired optical fiber channel and the space optical channel are backup to each other.

[0007] Preferably, the first processor and the second processor are both FPGA processors; the FPGA processor comprises an inter-cabin data sending module and an inter-cabin data receiving module, and the inter-cabin data sending module and the inter-cabin data receiving module are used for processing the received or sent data.

[0008] In another aspect, the application also provides a high-speed laser transmission method for complex data types between satellite cabins, which adopts the high-speed laser transmission system for complex data types between satellite cabins. Data is collected from the satellite platform cabin single machine and the satellite load cabin single machine through the plurality of groups of first data transceiver modules and the plurality of groups of second data transceiver modules respectively, and is sent to the first processor and the second processor respectively; The first processor and the second processor integrate the data collected by them respectively, and judge the sending priority of the integrated data types; High-speed serial resources in the first processor and the second processor are used to realize high-speed transmission of inter-cabin data; Encoding is performed before data sending when the first processor or the second processor is used as a sending side, and decoding is performed to realize forward error correction when the first processor or the second processor is used as a receiving side; The first processor or the second processor is used to count inter-cabin data transmission error codes, and when the inter-cabin data transmission error codes are abnormal, channel abnormal self-adaptive switching is performed to realize link reconstruction.

[0009] Preferably, the first processor and / or the second processor integrates the data collected by them, which comprises integrating data types with the same transmission requirements in the collected data, and adding corresponding type identification numbers, and specifically comprises: The data transmitted from the platform cabin interlaser terminal to the payload cabin interlaser terminal includes: single-channel telemetry acquisition and remote control instruction to each single machine of the payload cabin, single-channel second pulse data to each single machine of the payload cabin, and single-channel high-speed injection data; the transmission frequencies of the three types of data are different, no data integration is performed, and only corresponding type identification numbers are added; The data transmitted from the payload cabin interlaser terminal to the platform cabin interlaser terminal includes: single-channel line array data, single-channel surface array data, single-channel window opening data, and five-channel telemetry data from each single machine, the five-channel telemetry data from each single machine is merged into the same data type, and the data is transmitted after framing; and only corresponding type identification numbers are added to the remaining data.

[0010] Preferably, the integrated data type is subjected to transmission priority judgment, specifically including: According to the order of real-time requirements, the integrated data type is subjected to first-round discrimination sorting, to ensure that data with transmission delay not exceeding a preset threshold is given priority; For data types with comparable real-time performance, transmission rate and frequency sorting is performed, to give priority to transmission of data types with high transmission rate and high frequency; For data with comparable transmission rate and frequency, single transmission length sorting is performed, to give priority to transmission of data types with short transmission length.

[0011] Preferably, the high-speed serial resource includes a high-speed serial Serdes resource, which is configured with a preset transmission rate value, and the preset transmission rate value is customized according to the model of the first processor and / or the second processor, to meet the transmission requirements of multiple external single machine interfaces.

[0012] Preferably, the high-speed transmission of inter-cabin data is realized by using the high-speed serial resource in the first processor and the second processor, specifically including: The first processor outputs the data subjected to transmission priority judgment to one of the at least two first optoelectronic transceiver modules by using the high-speed serial Serdes resource, or the second processor outputs the data subjected to transmission priority judgment to one of the at least two second optoelectronic transceiver modules by using the high-speed serial Serdes resource; The at least two first optoelectronic transceiver modules and the at least two second optoelectronic transceiver modules communicate data through a wired optical fiber channel and a spatial optical channel, and the wired optical fiber channel and the spatial optical channel back up each other.

[0013] Preferably, the first processor or the second processor as the sending side encodes before data transmission; and the first processor or the second processor as the receiving side decodes to realize forward error correction, specifically comprising: The first processor and the second processor are both FPGA processors; the FPGA processor comprises an inter-cabin data sending module and an inter-cabin data receiving module, The inter-cabin data sending module encodes the data sent by the first processor or the second processor as the sending side; and the inter-cabin data receiving module decodes the data received by the first processor or the second processor as the receiving side, and corrects the error data in the data domain within a preset error correction range.

[0014] Preferably, the error code of the inter-cabin data transmission is counted by a codec unit in the inter-cabin data receiving module, when the error code is too much to be corrected to cause data error, the internal instruction is used for adaptive switching of channel exception, and the other channel of the wired optical fiber channel and the space optical channel is enabled to complete link reconstruction.

[0015] Compared with the prior art, the present application has the following beneficial effects: 1. The present application sets corresponding receiving buffers in each data receiving module, integrates the data with the same transmission requirements, simplifies the data types of inter-cabin transmission, and improves the inter-cabin channel transmission efficiency; 2. The present application judges the priority of data transmission in the inter-cabin data sending module according to the real-time requirements and transmission length of the integrated data types, to ensure the ordered transmission of data; 3. The present application uses the high-speed serial resources in the FPGA to realize the high-speed transmission of inter-cabin data, to meet the transmission requirements of the transmission rate of multiple external single-machine interfaces; 4. The present application adds encoding in the inter-cabin data sending module before data transmission, and the receiving side FPGA decodes in the inter-cabin data receiving module, the decoding end can recover the error code caused by the inter-cabin transmission exception within the error correction capability range, effectively solving the influence of the transmission link caused by the large translation and tilt between the satellite magnetic floating cabins; 5. The inter-cabin optical fiber link and the space optical link are backup for each other, the FPGA counts the inter-cabin data transmission error code through the encoding and decoding functions in the inter-cabin data sending module and the inter-cabin data receiving module, when the error code is too much to be corrected to cause data error, the internal instruction is used for adaptive switching of channel exception, and the other channel is enabled to complete link reconstruction. BRIEF DESCRIPTION OF DRAWINGS

[0016] To more clearly illustrate the technical solution of the present invention, the accompanying drawings used in the description will be briefly introduced below. Obviously, the drawings described below are one embodiment of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort: Figure 1 A schematic diagram of the structure of a high-speed laser transmission system for complex data types between spacecraft cabins, provided in an embodiment of the present invention; Figure 2 A schematic diagram of the FPGA transmitting side framework for a high-speed laser transmission method for complex data types between spacecraft provided in an embodiment of the present invention; Figure 3 A schematic diagram of the FPGA receiver-side framework for a high-speed laser transmission method for complex data types between spacecraft cabins, provided in an embodiment of the present invention. Figure 4 This is a schematic diagram of the inter-vehicle transmission data frame structure for a high-speed laser transmission method for complex data types between spacecraft, provided in an embodiment of the present invention. Figure 5 This is a flowchart illustrating the link reconfiguration process of a high-speed laser transmission method for complex data types between spacecraft, provided in an embodiment of the present invention. Figure 6 This is a flowchart illustrating the process of handling module-to-module link switching failures in a high-speed laser transmission method for complex data types between spacecraft, provided as an embodiment of the present invention. Detailed Implementation

[0017] The following is in conjunction with the appendix Figures 1-6 The following detailed description further illustrates the high-speed laser transmission system and method for complex data types between spacecraft modules proposed in this invention. The advantages and features of this invention will become clearer from the following description. It should be noted that the accompanying drawings are in a very simplified form and use non-precise proportions, used only to facilitate and clearly illustrate the embodiments of this invention. Please refer to the accompanying drawings to make the objectives, features, and advantages of this invention more apparent and understandable. It should be understood that the structures, proportions, sizes, etc., depicted in the accompanying drawings are only for illustrative purposes to aid those skilled in the art and are not intended to limit the implementation conditions of this invention. Therefore, they have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to the size, without affecting the effects and objectives achieved by this invention, should still fall within the scope of the technical content disclosed in this invention.

[0018] On the one hand, refer to Figure 1As shown, the embodiment provides a high-speed laser transmission system for complex data types between satellite cabins, which comprises a platform cabin inter-cabin laser communication terminal and a payload cabin inter-cabin laser communication terminal. The platform cabin inter-cabin laser communication terminal is arranged in the platform cabin of a satellite magnetic floating cabin body, and comprises a first processor, at least two first optoelectronic transceiver modules and a plurality of groups of first data transceiver modules connected with the first processor respectively. The plurality of groups of first data transceiver modules are connected with satellite platform cabin single machines for data transceiving with the satellite platform cabin single machines. The payload cabin inter-cabin laser communication terminal is arranged in the payload cabin of the satellite magnetic floating cabin body, and comprises a second processor, at least two second optoelectronic transceiver modules and a plurality of groups of second data transceiver modules connected with the second processor respectively. The at least two first optoelectronic transceiver modules are connected with the at least two second optoelectronic transceiver modules for realizing inter-cabin data communication. The plurality of groups of second data transceiver modules are connected with satellite payload cabin single machines for data transceiving with the satellite payload cabin single machines. The at least two first optoelectronic transceiver modules and the at least two second optoelectronic transceiver modules communicate data through a wired optical fiber channel and a space optical channel, and the wired optical fiber channel and the space optical channel back up each other. The first processor and the second processor are both FPGA (Field Programmable Gate Array, Field Programmable Gate Array) processors; the FPGA processor comprises an inter-cabin data sending module and an inter-cabin data receiving module for processing received or sent data. As shown, Figure 1 As shown, the FPGA sending side sorts the data by priority, frames and encodes the data, and then performs parallel-serial conversion by using the high-speed serial Serdes (Serializer / Deserializer) resource in the processor. Finally, the data is modulated and sent through the optoelectronic conversion module; as shown, Figure 2 As shown, the FPGA receiving side demodulates the signal through the optoelectronic conversion module, performs serial-parallel conversion, RS decoding, data identification analysis and frame disassembly through the high-speed serial Serdes, and then distributes the corresponding data to each data transceiver module. At the same time, the FPGA receiving side judges the error bit count of RS decoding statistics in real time, and switches the inter-cabin channel through internal instructions when the error code is too large, to complete link reconstruction.

[0019] On the other hand, the embodiment also provides a high-speed laser transmission method for complex data types between satellite cabins, which adopts the high-speed laser transmission system for complex data types between satellite cabins described above, and the method comprises: Step S1: Data is collected from the satellite platform module and each unit of the satellite payload module through the multiple sets of first data transceiver modules and the multiple sets of second data transceiver modules, respectively, and sent to the first processor and the second processor, respectively.

[0020] Step S2: The first processor and the second processor integrate the data they have collected and determine the priority of sending the integrated data type.

[0021] The first processor and / or the second processor integrates the collected data, including: integrating data types with the same transmission requirements and adding corresponding type identifiers. Specifically, the data sent from the platform module inter-module laser terminal to the payload module inter-module laser terminal includes: single-channel telemetry acquisition and remote control commands to each unit in the payload module, single-channel second pulse data to each unit in the payload module, and single-channel high-speed injection data. In a specific example, the three data types include: 1. Single-channel telemetry acquisition and remote control commands to each unit in the payload module, with an RS422 interface transmission rate of 1Mbps, a telemetry acquisition transmission frequency of 250ms, and random remote control commands; 2. Single-channel second pulse data to each unit in the payload module, with an RS422 interface transmission frequency of 1Hz; 3. Single-channel high-speed injection data, with an RS422 interface transmission rate of 1Mbps and a transmission frequency of 100ms. The transmission frequencies of the three data types are different, so no data integration is performed; only corresponding type identifiers are added.

[0022] The data transmitted from the payload compartment inter-cabin laser terminal to the platform compartment inter-cabin laser terminal includes: single-channel linear array data, single-channel planar array data, single-channel windowed data, and five channels of telemetry data from various individual units. In a specific example, the data transmitted from the payload compartment inter-cabin laser terminal to the platform compartment inter-cabin laser terminal includes: 1. Single-channel TLK2711 linear array data, transmission rate 1.6Gbps, transmission frequency random; 2. Single-channel TLK2711 planar array data, transmission rate 1.6Gbps, transmission frequency random; 3. Single-channel RS422 windowed data, transmission rate 1Mbps, transmission frequency random; 4. Five channels of telemetry data from various individual units, transmission frequency 250ms. Because single-channel TLK2711 linear array data and single-channel TLK2711 planar array data may be transmitted simultaneously and at random frequencies, type merging is not performed. The five channels of telemetry data from various individual units are merged into one data type, framed, and then transmitted. The remaining data are only labeled with the corresponding type identifier. After data type integration is completed...

[0023] Thus, the data type integration was completed, simplifying the original 11 data types into 7 data types.

[0024] The sending priority judgment is performed on the integrated data types, and the sending priority judgment process includes: Step S2.1: According to the order of real-time requirements, the integrated data types are first round of discrimination sorting, and the data whose transmission delay does not exceed the preset threshold is ensured to be transmitted preferentially. In an embodiment, it specifically includes: first, according to the real-time requirements, the first round of discrimination sorting is performed, and the data with the highest real-time requirement is ensured to be transmitted preferentially; among the seven integrated data types, the platform cabin to the payload cabin second pulse data requires that the transmission delay does not exceed 10us, the telemetry acquisition and remote control instruction requires that the transmission delay does not exceed 5ms, and the high-speed injection data has no requirement, therefore, the priority of the platform cabin to the payload cabin data is: second pulse data> telemetry acquisition and remote control instruction> high-speed injection data; the payload cabin to the platform cabin data telemetry data requires that it is returned to the platform cabin within 20ms, and the real-time requirements of the remaining data are equivalent, and the following step S2.2 is executed for further sorting.

[0025] Step S2.2: For the data types with equivalent real-time requirements, according to the transmission rate and frequency sorting, the data types with fast transmission rate and high frequency are preferentially transmitted, and in an embodiment, it specifically includes: for the remaining data with equivalent real-time requirements, the second round of discrimination is performed according to the corresponding data transmission rate, and the data with fast transmission rate and high frequency is preferentially transmitted, and the FPGA internal cache is ensured not to overflow; the transmission rate of the TLK2711 linear array data and the TLK2711 area array data is fast, and the frequency is equivalent, therefore, the priority after sorting is: telemetry data> TLK2711 linear array data≈TLK2711 area array data> RS422 window data, and the step S2.3 is executed for further judgment.

[0026] Step S2.3: For the data with equivalent transmission rate and frequency, according to the single transmission length sorting, the data type with shorter transmission length is preferentially transmitted. For the data with equivalent transmission rate and frequency, the third round of discrimination is performed according to the single transmission length of the corresponding data, and the data type with shorter single transmission length is preferentially transmitted, and the rationality of the inter-cabin link time-sharing transmission is ensured; the single transmission length of the TLK2711 linear array data is greater than that of the TLK2711 area array data, therefore, the final priority of the payload cabin to the platform cabin data is: telemetry data> TLK2711 area array data> TLK2711 linear array data> RS422 window data.

[0027] Step S3: high-speed transmission of inter-cabin data is realized by using high-speed serial resources in the first processor and the second processor. The high-speed serial resources include high-speed serial Serdes resources configured at a preset transmission rate value (in this example, the preset transmission rate value is 2.5 Gbps), which is customized according to the model of the first processor and / or the second processor to meet the transmission requirements of multiple external single-machine interfaces. By using the high-speed serial Serdes resources, the first processor outputs the data after priority judgment to one of the at least two first optoelectronic transceiver modules, or the second processor outputs the data after priority judgment to one of the at least two second optoelectronic transceiver modules; the at least two first optoelectronic transceiver modules and the at least two second optoelectronic transceiver modules communicate data through wired fiber channel and spatial optical channel, and the wired fiber channel and the spatial optical channel are backed up to each other.

[0028] The FPGA dedicated high-speed serial Serdes resources are used instead of traditional interfaces, and are output to the optoelectronic transceiver modules for optical-electric conversion and then transmitted through the inter-cabin optical link. The transmission rate of 2.5 Gbps per channel meets the transmission requirements of multiple external single-machine interfaces with a transmission rate of 1 Mbps to 1.6 Gbps. According to different FPGA models, the currently commonly used FPGA high-speed serial Serdes resources have a transmission rate of 100 Mbps to 58 Gbps per channel. Users can customize the configuration according to the transmission requirements to meet the subsequent development needs of the project.

[0029] Step S4: as shown in Figure 2 and Figure 3 When the first processor or the second processor is on the sending side, encoding is performed before data transmission; when the first processor or the second processor is on the receiving side, decoding is performed to realize forward error correction. The first processor and the second processor both use FPGA processors; the FPGA processor includes an inter-cabin data sending module and an inter-cabin data receiving module. When the first processor or the second processor is on the sending side, the inter-cabin data sending module encodes the data it sends; when the first processor or the second processor is on the receiving side, the inter-cabin data receiving module decodes the data it receives and corrects the error data in the data field within a preset error correction range.

[0030] RS (Reed-Solomon, Reed-Solomon) encoding and decoding are added in the inter-cabin data sending module of the sending side FPGA and the inter-cabin data receiving module of the receiving side FPGA as channel coding; RS encoding and decoding is a forward error correction code, which has strong burst error correction capability and flexibility. The decoding end can recover the error code generated by the inter-cabin transmission anomaly within the error correction capability, effectively solving the influence of the transmission link caused by the large translation and tilt between the satellite magnetic suspension cabins, and the error correction steps are as follows: Step S4.1: Fill the integrated framed data to an integer multiple of 223 bytes to the inter-cabin data sending module, and the RS encoding function in the module will add a check field to the tail of the valid data. The final data length is an integer multiple of 255 bytes, and the final format is as shown in Figure 4 ; Step S4.2: When the inter-cabin data receiving module receives the data frame from the inter-cabin, the data is decoded by the RS decoding function to restore the original data of an integer multiple of 223 bytes, and the error data in the data field is corrected within the error correction range.

[0031] Step S4.3: RS encoding is a non-binary BCH code, which is the strongest error correction code among all (n, k) linear block codes. When the check polynomial of RS encoding is RS (n, k), n represents the code length, and k represents the number of information segment symbols. The maximum burst error correction capability is t=(n-k) / 2. In this embodiment, RS (255, 223) is used, so the maximum burst error correction capability of each 223 information segment symbols is 16 symbols.

[0032] Step S5: The first processor or the second processor is used to count the inter-cabin data transmission error code. When the inter-cabin data transmission error code is abnormal, channel abnormal adaptive switching is performed to realize link reconstruction. When the first processor or the second processor is used as the sending side, encoding is performed before data sending; when the first processor or the second processor is used as the receiving side, decoding is performed to realize forward error correction. Specifically, the encoding and decoding unit in the inter-cabin data receiving module is used to count the inter-cabin data transmission error code. When the error code is too much to be corrected to cause data error, the internal instruction is used to perform channel abnormal adaptive switching to enable another channel of the wired optical fiber channel and the space optical channel to complete link reconstruction.

[0033] The optical fiber link and the space optical link between the platform cabin inter-cabin communication terminal and the load cabin inter-cabin communication terminal are backup to each other. The inter-cabin data receiving module of the receiving end FPGA counts the inter-cabin data transmission error code through the RS encoding and decoding function. When the error code is too much to be corrected to cause data error, the internal instruction is used to switch the transmission channel to another optical-electric conversion module to realize inter-cabin channel switching and complete link reconstruction, as shown in Figure 5The switching steps are described in detail: Step S5.1: Based on the RS coding function of step S4, the inter-cabin data receiving module of step S4.2 will output the error symbol count of the current frame in real time after receiving and decoding, and will synchronously output the error correction failure flag when the error number exceeds the maximum burst error correction capability.

[0034] Step S5.2: The inter-cabin data receiving module of the FPGA monitors the error correction failure flag, and when the number of consecutive error correction failures is greater than a certain threshold, it is determined that the current link communication is abnormal.

[0035] Step S5.3: The FPGA that detects the link communication abnormality sends a link switching instruction to the opposite cabin inter-cabin laser communication terminal, and after sending, it performs the link switching operation.

[0036] Step S5.4: If the opposite cabin inter-cabin laser communication terminal receives the link switching instruction normally, the link switching is completed to realize the link reconstruction, and if the receiving instruction is abnormal, the following step S5.5 is executed.

[0037] Step S5.5: Referring to Figure 6 When the link switching instruction is not received, the opposite cabin has completed the inter-cabin link switching, so the inter-cabin laser communication terminal of the cabin will have no data reception. According to the principle that telemetry acquisition and telemetry data are periodically sent, when there is no data reception for a fixed threshold time, the inter-cabin laser communication terminal of the cabin will automatically switch to another communication link, thereby completing the link switching to realize the link reconstruction.

[0038] In summary, the embodiment provides a high-speed laser transmission system and method for complex data types between satellite cabins, which is suitable for satellite magnetic floating cabin structure, wherein the platform cabin and the load cabin are isolated by magnetic floating to achieve high-precision attitude control. The system simplifies the satellite data transmission scheme by using laser communication technology, saves transmission cables, reduces weight and isolates cable disturbance, while supporting multi-channel multi-rate data transmission, forward error correction and link adaptive reconstruction, ensuring data real-time and reliability. The method in the embodiment sets up corresponding receiving buffer for each data receiving module, integrates data with the same transmission requirements, simplifies the data types of inter-cabin transmission, and improves the inter-cabin channel transmission efficiency; the priority of data transmission is judged according to the real-time requirement and the transmission length of the integrated data type in the inter-cabin data sending module, to ensure the ordered transmission of data; the high-speed serial Serdes resource in the FPGA is used to realize the high-speed transmission of inter-cabin data, to meet the transmission requirements of multiple external single machine interfaces with transmission rates of 1Mbps~1.6Gbps; RS encoding is added in the inter-cabin data sending module before data transmission, and RS decoding is performed in the inter-cabin data receiving module of the receiving side FPGA, so that the decoding end can recover the error code generated by the abnormal inter-cabin transmission within the error correction capability, effectively solving the influence of large translation and tilt between satellite magnetic floating cabins on the transmission link; the inter-cabin optical fiber link and the space optical link are backup for each other, and the FPGA counts the inter-cabin data transmission error code through the RS encoding and decoding functions in the inter-cabin data sending module and the inter-cabin data receiving module. When the error code is too much to be corrected, the internal instruction is used for adaptive switching of channel exception, and another channel is enabled to complete the link reconstruction.

[0039] It should be noted that in this document, the terms "comprising", "including", or any other variant thereof are intended to cover non-exclusive inclusions, so that processes, methods, articles or devices including a series of elements not only include those elements, but also include other elements not explicitly listed, or inherent elements of such processes, methods, articles or devices. Without more limitations, the element defined by the statement "including a" does not exclude the presence of other identical elements in the process, method, article or device including the element.

[0040] It should be noted that the apparatus and method disclosed in the embodiments herein can also be implemented in other ways. The apparatus embodiments described above are merely exemplary, and the schematic flowcharts and block diagrams in the accompanying drawings show possible implementation architectures, functions and operations of the apparatus, method and computer program product according to the embodiments herein. In this regard, each block in the flowcharts and block diagrams can represent a module, a program segment or a part of code which contains one or more executable instructions for implementing the specified logic function. It should also be noted that in some alternative implementations, the functions noted in the blocks can occur in a different order than that noted in the accompanying drawings. For example, two consecutive blocks can actually be executed substantially in parallel, and they can also be executed in reverse order, depending on the involved functions. It should also be noted that each block in the block diagrams and / or flowcharts, and the combination of blocks in the block diagrams and / or flowcharts, can be implemented by a dedicated hardware-based system for performing the specified functions or actions, or can be implemented by a combination of dedicated hardware and computer instructions.

[0041] In addition, each functional module in the embodiments herein can be integrated together to form an independent part, or each module can exist independently, or two or more modules can be integrated to form an independent part.

[0042] Although the present application has been described in detail through the preferred embodiments above, it should be recognized that the above description is not to be considered as limiting the present application. Various modifications and alterations to this application will be apparent to those skilled in the art upon reading the above description. It is intended that the scope of the application be defined by the following claims and their equivalents.

Claims

1. A high-speed laser transmission system for spaceborne inter-caps complex data types, characterized in that, include: The platform module inter-module laser communication terminal is installed in the platform module of the satellite magnetic levitation cabin. The platform module inter-module laser communication terminal includes: a first processor, and at least two first optoelectronic transceiver modules and multiple sets of first data transceiver modules respectively connected to the first processor. The multiple sets of first data transceiver modules are connected to the satellite platform module unit and are used to transmit and receive data with the satellite platform module unit. The inter-cargo laser communication terminal is installed inside the payload compartment of the satellite's magnetic levitation hull. The inter-cargo laser communication terminal includes: a second processor, and at least two second optoelectronic transceiver modules and multiple sets of second data transceiver modules respectively connected to the second processor. The at least two first optoelectronic transceiver modules are connected to the at least two second optoelectronic transceiver modules to realize inter-cargo data communication. The multiple sets of second data transceiver modules are connected to each individual unit in the satellite payload compartment to perform data transmission and reception with each individual unit in the satellite payload compartment.

2. The high-speed laser transmission system for space-borne inter-caps complex data types of claim 1, wherein, The at least two first optoelectronic transceiver modules and the at least two second optoelectronic transceiver modules communicate with each other via wired optical fiber channels and spatial optical channels, and the wired optical fiber channels and spatial optical channels serve as backups for each other.

3. The high-speed laser transmission system for space-borne complex data types between bays as recited in claim 1, wherein, Both the first processor and the second processor are FPGA processors; the FPGA processor includes an inter-cabin data transmission module and an inter-cabin data reception module, which are used to process the received or transmitted data.

4. A method for high-speed laser transmission of complex data types between space-borne compartments, characterized in that, It employs a high-speed laser transmission system for complex data types between spacecraft as described in any one of claims 1-3, the method comprising: Data is collected from the individual units of the satellite platform module and the satellite payload module by the multiple sets of first data transceiver modules and the multiple sets of second data transceiver modules, respectively, and then sent to the first processor and the second processor, respectively. The first processor and the second processor integrate the data they have collected and determine the priority of sending the integrated data type. High-speed serial resources in the first and second processors are used to achieve high-speed data transmission between compartments; When the first processor or the second processor is the transmitting side, the data is encoded before transmission; when the first processor or the second processor is the receiving side, the data is decoded to achieve forward error correction. The first processor or the second processor is used to count the inter-cabin data transmission errors. When the inter-cabin data transmission error is abnormal, channel abnormality adaptive switching is performed to achieve link reconstruction.

5. The method for high speed laser transmission of complex data types between space-borne capsules of claim 4, wherein, The first processor and / or the second processor integrates the data they have collected, including: integrating data of the same transmission requirements in the collected data and adding corresponding type identifiers, specifically: The data transmitted from the platform cabin inter-cabin laser terminal to the payload cabin inter-cabin laser terminal includes: single-channel telemetry acquisition and remote control instruction to each single machine of the payload cabin, single-channel second pulse data to each single machine of the payload cabin, and single-channel high-speed injection data; the transmission frequencies of the three types of data are different, and no data integration is performed, only corresponding type identification numbers are added; The data transmitted from the payload cabin inter-cabin laser terminal to the platform cabin inter-cabin laser terminal includes: single-channel linear array data, single-channel surface array data, single-channel window opening data, and five-channel telemetry data from each single machine, the five-channel telemetry data from each single machine is merged into the same data type, and the data is transmitted after framing, and only corresponding type identification numbers are added to the remaining data.

6. The method for high speed laser transmission of complex data types between space-borne capsules of claim 4, wherein, The sending priority of the integrated data type is judged, and the specific process includes: According to the order of real-time requirements, the integrated data type is subjected to first-round discrimination and sorting, to ensure that the data with transmission delay not exceeding the preset threshold value is given priority; For data types with comparable real-time performance, the transmission rate and frequency are sorted, and the data type with high transmission rate and frequency is given priority in transmission; For data with comparable transmission rate and frequency, the single transmission length is sorted, and the data type with shorter transmission length is given priority in transmission.

7. The method for high speed laser transmission of complex data types between space-borne capsules of claim 4, wherein, The high-speed serial resource includes a high-speed serial Serdes resource, which is configured with a preset transmission rate value, and the preset transmission rate value is customized according to the model of the first processor and / or the second processor to meet the transmission requirements of multiple external single machine interfaces.

8. The method for high speed laser transmission of complex data types between space-borne capsules of claim 7, wherein, The high-speed transmission of inter-cabin data is realized by using the high-speed serial resource in the first processor and the second processor, and the specific process includes: The first processor outputs the data after the sending priority judgment to one of the at least two first optoelectronic transceiver modules by using the high-speed serial Serdes resource, or the second processor outputs the data after the sending priority judgment to one of the at least two second optoelectronic transceiver modules; The at least two first optoelectronic transceiver modules and the at least two second optoelectronic transceiver modules communicate data through a wired optical fiber channel and a spatial optical channel, and the wired optical fiber channel and the spatial optical channel back up each other.

9. The method for high speed laser transmission of complex data types between space-borne capsules of claim 8, wherein, When the first processor or the second processor is on the sending side, encoding is performed before data transmission; When the first processor or the second processor is on the receiving side, decoding is performed to realize forward error correction, and the specific process includes: The first processor and the second processor both adopt FPGA processors; the FPGA processor includes an inter-cabin data sending module and an inter-cabin data receiving module, When the first processor or the second processor is on the sending side, the inter-cabin data sending module encodes the data it sends; when the first processor or the second processor is on the receiving side, the inter-cabin data receiving module decodes the data it receives and corrects the error data in the data field within a preset error correction range.

10. The method for high speed laser transmission of complex data types between space-borne capsules of claim 9, wherein, The inter-cabin data receiving module is used for receiving the inter-cabin data, and the codec unit in the inter-cabin data receiving module is used for counting the error code of the inter-cabin data transmission; when the error code is too much to be corrected to cause data error, the internal instruction is used for performing self-adaptive switching of the channel, and the other channel of the wired fiber channel and the space optical channel is enabled to complete link reconstruction.

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