CN111181847A - Combined spacecraft data processing method based on hierarchical routing - Google Patents
Combined spacecraft data processing method based on hierarchical routing Download PDFInfo
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- CN111181847A CN111181847A CN201911400661.2A CN201911400661A CN111181847A CN 111181847 A CN111181847 A CN 111181847A CN 201911400661 A CN201911400661 A CN 201911400661A CN 111181847 A CN111181847 A CN 111181847A
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L45/00—Routing or path finding of packets in data switching networks
- H04L45/02—Topology update or discovery
- H04L45/04—Interdomain routing, e.g. hierarchical routing
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L69/00—Network arrangements, protocols or services independent of the application payload and not provided for in the other groups of this subclass
- H04L69/06—Notations for structuring of protocol data, e.g. abstract syntax notation one [ASN.1]
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L69/00—Network arrangements, protocols or services independent of the application payload and not provided for in the other groups of this subclass
- H04L69/22—Parsing or analysis of headers
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Abstract
The invention relates to a combined spacecraft data processing method based on hierarchical routing, which comprises the following steps: a. uplink injection data and downlink telemetering data of a plurality of spacecraft cabin sections are transmitted between each spacecraft cabin section and the ground through a spacecraft identifier, a virtual channel and a data field three-layer identifier in a VCDU frame; b. the periodic interaction data between the spacecraft cabin sections and inside each spacecraft cabin section realize the periodic interaction of cross-cabin and cross-subsystem data through an application progress identifier APID and a secondary guide head in an EPDU packet; c. and the sporadic interaction data between the spacecraft cabin sections and inside each spacecraft cabin section realize interaction instructions among different spacecrafts in the combined spacecraft and different single-machine equipment on the spacecraft through a spacecraft identifier and a virtual channel two-layer identifier in a sub-packet remote control frame. The method of the invention can realize standardization and autonomy of data processing on the device, and enables the system to have good expansibility.
Description
Technical Field
The invention relates to a combined spacecraft data processing method based on hierarchical routing.
Background
The information management system is an important component of the spacecraft, generally comprises a data management subsystem (or a satellite management subsystem) and a measurement and control data transmission subsystem, and is responsible for realizing data management such as instruction remote measurement and the like of the spacecraft and remote measurement and control data transmission communication of the spacecraft.
At present, the existing spacecraft mainly adopts a mode of mixing the traditional PCM format and the AOS format for framing and coding communication of data, and the formats of data exchanged between different devices or aircrafts on the spacecraft are different and the formats of different space-ground links are different. In independent flying or short-term combination flying spacecraft, the traditional design can meet the use requirement due to the small scale of the system and the simple dynamic combination mode.
However, in a large combined spacecraft, because dynamic access and exit of a data source of a visiting aircraft are required to be supported, data exchange is required to be carried out across the spacecraft, and dynamic switching of a space-ground link among different spacecrafts is required to be supported, the traditional design has insufficient universality and poor expansibility, and the use requirements cannot be met. Therefore, in order to meet the normal work of the large combined spacecraft, a scheme which has good expansibility and supports cross-spacecraft data exchange and world link switching must be designed.
Disclosure of Invention
The invention aims to solve the problems and provides a combined spacecraft data processing method based on hierarchical routing.
In order to achieve the above object, the present invention provides a combined spacecraft data processing method based on hierarchical routing, which includes data processing between each spacecraft cabin in a combined spacecraft and the ground, data processing between each spacecraft cabin in the combined spacecraft and the spacecraft cabin, and data processing inside each spacecraft cabin in the combined spacecraft, and includes the following steps:
a. uplink injection data and downlink telemetering data of a plurality of spacecraft cabin sections are transmitted between each spacecraft cabin section and the ground through a spacecraft identifier, a virtual channel and a data field three-layer identifier in a VCDU frame;
b. the periodic interaction data between the spacecraft cabin sections and inside each spacecraft cabin section realize the periodic interaction of cross-cabin and cross-subsystem data through an application progress identifier APID and a secondary guide head in an EPDU packet;
c. and the sporadic interaction data between the spacecraft cabin sections and inside each spacecraft cabin section realize interaction instructions among different spacecrafts in the combined spacecraft and different single-machine equipment on the spacecraft through a spacecraft identifier and a virtual channel two-layer identifier in a sub-packet remote control frame.
According to an aspect of the present invention, in the step a, after the ground uplink injection data is encapsulated, the ground uplink injection data is uplink-transmitted to a high speed communication processor of a spacecraft cabin through a relay narrow beam KSA link, after the high speed communication processor receives the data in the format of a CADU, the high speed communication processor performs decoding and verification, and performs route identification on a VCDU after the data is correct, and if a space-ground link spacecraft identifier RSCID is the cabin and a space-ground link virtual channel identifier RVCID is a number of pipes of injection data, the data is transmitted to a number of pipes center computer of the cabin through a bus port to perform data routing of a next layer.
According to one aspect of the invention, after receiving the packet remote control frame data forwarded by the high-speed communication processor, the tube counting central computer of the spacecraft cabin firstly conducts de-checking, and after the de-checking is correct, the routing information is identified through a target spacecraft identifier TSCID and a target subsystem identifier TVCID in a main guide head, if the TSCID is the current spacecraft cabin, the data is forwarded to the next-stage computer through a bus according to the TVCID, and if the TSCID is other spacecraft cabins, the data frame is forwarded to the tube counting central computers of other spacecraft cabins through the bus, and the data is forwarded according to the same rule.
According to one aspect of the invention, in the step a, the attitude and orbit control computer fills the downlink telemetry source code according to the format to form an EPDU packet, the EPDU packet is sent to a tube counting center computer through a bus, each organized terminal data forms an EPDU packet sequence, the EPDU packet sequence is sent to the tube counting center computer of the spacecraft cabin section through the bus, the RSCID and the RVCID of the spacecraft in the sky and ground link are filled according to the format of the sky and ground link, then the EPDU packet sequence is sent to a high pass for coding and modulation, and the EPDU packet sequence is sent to the ground through a relay link.
According to an aspect of the invention, in the step b, the periodic interaction data between the spacecraft cabin and inside each spacecraft cabin adopts an EPDU packet format, and the identification of the data routing information is realized by applying a progress identifier APID and a secondary guide head;
the application progress identifier APID comprises a destination terminal spacecraft cabin section and a destination terminal subsystem, the auxiliary guide head is used for representing the source terminal spacecraft cabin section and the source terminal subsystem, and a data management center computer of the source terminal spacecraft cabin section carries out cross-cabin data routing according to information in the EPDU packet.
According to one aspect of the invention, in the step c, sporadic interaction data between the spacecraft cabin and inside each spacecraft cabin adopt a packet remote control frame format, the sending terminal requests the data counting center computer, the data counting center computer obtains the interaction data after receiving the request, and performs route identification, wherein the spacecraft identifier represents the spacecraft cabin at the destination end, the virtual channel identifier represents the subsystem at the destination end, and the data counting center computer transmits the information to the terminal spacecraft cabin data counting center computer at the destination end for route forwarding.
According to the combined spacecraft data processing method based on the hierarchical routing, the following beneficial effects can be achieved:
1. the ground, the inter-device and the intra-device all adopt AOS standard formats;
2. a layered routing protocol without data types is established, and autonomy of data processing on a support is supported;
3. the method adopts a standard format and a layered routing protocol to support the generalization of software design on the ground and a device;
4. and a standard layered routing protocol is adopted, so that the system is simple in expansion and higher in use flexibility.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
Fig. 1 schematically shows a flow chart of a hierarchical routing based combined spacecraft data processing method according to the invention;
FIG. 2 schematically illustrates a combined spacecraft information management system component block diagram, in accordance with one embodiment of the present invention;
FIG. 3 is a diagram of an overground hierarchical routing protocol encapsulation format;
FIG. 4 is a diagram of an overhead hierarchical routing data flow;
FIG. 5 is a block diagram of a hierarchical routing protocol encapsulation format under a device;
fig. 6 is a hierarchical routing data flow diagram under a device.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments will be briefly described below. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
In describing embodiments of the present invention, the terms "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like are used in an orientation or positional relationship that is based on the orientation or positional relationship shown in the associated drawings, which is for convenience and simplicity of description only, and does not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus, the above-described terms should not be construed as limiting the present invention.
The present invention is described in detail below with reference to the drawings and the specific embodiments, which are not repeated herein, but the embodiments of the present invention are not limited to the following embodiments.
Fig. 1 schematically shows a flow chart of a hierarchical routing based combined spacecraft data processing method according to the invention. In the invention, the combined spacecraft data processing method based on the hierarchical routing comprises the steps of processing data between each spacecraft cabin section in the combined spacecraft and the ground, processing data between each spacecraft cabin section in the combined spacecraft and the spacecraft cabin section, and processing data inside each spacecraft cabin section in the combined spacecraft. As shown in fig. 1, the combined spacecraft data processing method based on hierarchical routing according to the present invention includes the following steps:
a. uplink injection data and downlink telemetering data of a plurality of spacecraft cabin sections are transmitted between each spacecraft cabin section and the ground through a spacecraft identifier, a virtual channel and a data field three-layer identifier in a VCDU frame;
b. the periodic interaction data between the spacecraft cabin sections and inside each spacecraft cabin section realize the periodic interaction of cross-cabin and cross-subsystem data through an application progress identifier APID and a secondary guide head in an EPDU packet;
c. and the sporadic interaction data between the spacecraft cabin sections and inside each spacecraft cabin section realize interaction instructions among different spacecrafts in the combined spacecraft and different single-machine equipment on the spacecraft through a spacecraft identifier and a virtual channel two-layer identifier in a sub-packet remote control frame.
The above-described method of the present invention is described in detail below in a specific embodiment with reference to the accompanying drawings.
Fig. 2 schematically shows a block diagram of a combined spacecraft information management system according to an embodiment of the invention. As shown in fig. 2, in the present embodiment, the combi spacecraft is assembled and constructed by a plurality of flight vehicles in a combined cabin I, a combined cabin II, a combined cabin III, and the like, while supporting the system expansion by the data conversion device (data converter 1/2). After the combination is formed, the space and ground measurement and control adopt a centralized control mode, uplink data and downlink data are uniformly transmitted and received through one cabin section, and therefore the data on the device is required to support cross-cabin section and cross-subsystem routing forwarding.
FIG. 3 is a diagram of an uplink hierarchical routing protocol encapsulation format between a spacecraft segment and the ground (hereinafter referred to as "ground"); fig. 4 is a diagram of an overhead row hierarchical routing data flow. As shown in fig. 3 and 4, in the present embodiment, after the ground uplink injection data is encapsulated according to the illustrated format, the uplink is transmitted to the high-speed communication processor (hereinafter, simply referred to as "high pass") of the combination cabin I through the relay narrow beam KSA link, the high pass receives the data in the CADU format (fourth layer protocol) and then decodes and verifies the data, and then, the route identification is performed on the VCDU (third layer protocol) after the data is correct, and if the space and earth link spacecraft identifier RSCID is the cabin and the space and earth link virtual channel identifier RVCID is the number of pipes of injection data, the data is transmitted to the number of pipes center computer of the cabin through the bus port to perform the next layer data routing. After receiving the high-pass forwarded packet remote control frame data (second layer protocol), the counting tube central computer of the combined cabin I firstly conducts check-off, identifies routing information through a target spacecraft identifier (TSCID) and a target subsystem identifier (TVCID) in a main guide head after the data is correct, forwards the data to a next-level computer through a bus according to the TVCID if the TSCID is the cabin, and forwards the data frame to counting tube central computers of other cabins through the bus and forwards the data frame according to the same rule if the TSCID is other cabins. By the routing mechanism, the uplink data can be uplink to any cabin section in the combined aircraft through any cabin section.
FIG. 5 is a block diagram of a hierarchical routing protocol encapsulation format under a device; fig. 6 is a hierarchical routing data flow diagram under a device. As shown in fig. 5 and 6, in this embodiment, taking the combined bay II as an example, the attitude and orbit control computer fills the downlink telemetry source code according to the format to form an EPDU packet, sends the EPDU packet to the tube counting center computer through the bus, the tube counting center computer forms each organized terminal data into an EPDU packet sequence, sends the EPDU packet sequence to the tube counting center computer of the combined bay I through the bus, fills the space and ground link spacecraft identifier (RSCID) and the space and ground link virtual channel identifier (RVCID) according to the space and ground link format, and then sends the EPDU packet sequence to the tube counting center computer for encoding and modulation, and then sends the EPDU packet sequence to the downlink ground through the relay link. And the other cabin telemetry source code downlink grounds adopt the same routing processing mechanism.
Table 1 shows a package format of EPDU packets of periodic interaction data between spacecraft sections (hereinafter referred to as "inter-spacecraft") or inside each spacecraft section (hereinafter referred to as "intra-spacecraft") in a combined spacecraft.
TABLE 1
As can be seen from table 1, the EPDU packet format is used for the inter/intra-device periodic interaction data, and the identification of the data routing information is realized by applying the progress identifier APID and the sub header. The application progress identifier APID comprises a destination terminal spacecraft and a destination terminal subsystem, and the auxiliary guide head is used for representing the source terminal spacecraft and the source terminal subsystem. And the data center computer of the data source cabin segment performs cross-cabin data routing according to the information in the EPDU packet.
Table 2 shows the inter/intra sporadic interactive dataflow graph and hierarchical routing packet remote control frame encapsulation formats. .
TABLE 2
As can be seen from table 2, the inter-device/intra-device sporadic interactive data is in a packet remote control frame format, the sending terminal requests the counting center computer, and the counting center computer receives the request and then acquires the interactive data to perform route identification. The spacecraft identification represents a target spacecraft, the virtual channel identification represents a target subsystem, and the counting center computer sends the information to the target spacecraft counting center computer for routing and forwarding.
According to the method, on the basis of the AOS standard format, the definition of various data identifications is regulated by adopting the concept of hierarchical routing, the autonomous routing management of different service data flows among devices and in the devices is supported, the standardization and the autonomy of data processing on the devices are realized, and the system has good expansibility.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (6)
1. A combined spacecraft data processing method based on hierarchical routing is characterized by comprising the following steps of data processing between each spacecraft cabin section in a combined spacecraft and the ground, data processing between each spacecraft cabin section in the combined spacecraft and each spacecraft cabin section, and data processing inside each spacecraft cabin section in the combined spacecraft, wherein the data processing comprises the following steps:
a. uplink injection data and downlink telemetering data of a plurality of spacecraft cabin sections are transmitted between each spacecraft cabin section and the ground through a spacecraft identifier, a virtual channel and a data field three-layer identifier in a VCDU frame;
b. the periodic interaction data between the spacecraft cabin sections and inside each spacecraft cabin section realize the periodic interaction of cross-cabin and cross-subsystem data through an application progress identifier APID and a secondary guide head in an EPDU packet;
c. and the sporadic interaction data between the spacecraft cabin sections and inside each spacecraft cabin section realize interaction instructions among different spacecrafts in the combined spacecraft and different single-machine equipment on the spacecraft through a spacecraft identifier and a virtual channel two-layer identifier in a sub-packet remote control frame.
2. The hierarchical routing-based combined spacecraft data processing method according to claim 1, wherein in the step a, after ground uplink injection data is encapsulated, the ground uplink injection data is uplinked to a high-speed communication processor of a spacecraft cabin through a relay narrow beam KSA, the high-speed communication processor receives data in a CADU format, decodes and verifies the data, performs routing identification on a VCDU after the data is correct, and if a space-ground link spacecraft identifier RSCID is the cabin and a space-ground link virtual channel identifier RVCID is a number of pipes of injection data, sends a number of pipes of a cabin to a central computer of the next layer through a bus port for data routing.
3. The hierarchical routing based spacecraft data processing method of claim 2, wherein a tube center computer of a spacecraft bay receives packetized remote control frame data forwarded by the high-speed communication processor, performs de-checking, identifies routing information through a target spacecraft identifier (TSCID) and a target subsystem identifier (TVCID) in a pilot header after the TSCID is correct, forwards data to a next-stage computer through a bus if the TSCID is the spacecraft bay, and forwards data frames to tube center computers of other spacecraft bays through a bus if the TSCID is the other spacecraft bay, and routes the data according to the same rule.
4. The combined spacecraft data processing method based on hierarchical routing as claimed in claim 1, wherein in step a, the attitude and orbit control computer fills downlink telemetry source codes according to format to form an EPDU packet, the EPDU packet is sent to the tube counting center computer through the bus, each organized terminal data is formed into an EPDU packet sequence by the tube counting center computer, the EPDU packet sequence is sent to the tube counting center computer of the spacecraft cabin section through the bus, the RSCID and the RVCID are filled according to the sky and ground link format, and then the EPDU packet sequence is sent to the high pass for coding and modulation, and the EPDU packet sequence is sent to the ground through the relay link.
5. The combined spacecraft data processing method based on hierarchical routing of claim 1, wherein in the step b, periodic interaction data between spacecraft sections and inside each spacecraft section are in an EPDU packet format, and identification of data routing information is realized by applying A Progress Identifier (APID) and a secondary guide head;
the application progress identifier APID comprises a destination terminal spacecraft cabin section and a destination terminal subsystem, the auxiliary guide head is used for representing the source terminal spacecraft cabin section and the source terminal subsystem, and a data management center computer of the source terminal spacecraft cabin section carries out cross-cabin data routing according to information in the EPDU packet.
6. The combined spacecraft data processing method based on hierarchical routing of any one of claims 1 to 5, wherein in the step c, sporadic interaction data between spacecraft cabin segments and inside each spacecraft cabin segment adopt a packet remote control frame format, a sending terminal requests a data center computer, the data center computer obtains the interaction data after receiving the request, and performs routing identification, wherein a spacecraft identifier represents a destination spacecraft cabin segment, a virtual channel identifier represents a destination subsystem, and the data center computer transmits the information to the destination spacecraft cabin segment data center computer for routing forwarding.
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