CN114465654B - Multi-source data flow control system adapting to double-star in-orbit - Google Patents
Multi-source data flow control system adapting to double-star in-orbit Download PDFInfo
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- CN114465654B CN114465654B CN202210044378.6A CN202210044378A CN114465654B CN 114465654 B CN114465654 B CN 114465654B CN 202210044378 A CN202210044378 A CN 202210044378A CN 114465654 B CN114465654 B CN 114465654B
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
- H04B7/1851—Systems using a satellite or space-based relay
- H04B7/18519—Operations control, administration or maintenance
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
- Y02D30/00—Reducing energy consumption in communication networks
- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
Abstract
The invention provides a multi-source data flow control system adapting to double-satellite orbit, which comprises a combination body formed by a first satellite and a second satellite; the first satellite comprises a first computer and a second computer, and the second satellite comprises a third computer and a fourth computer; the first computer and the second computer are in communication connection through a wired channel; the third computer and the fourth computer are in communication connection through a wired channel; the first computer and the third computer are in communication connection through a wired channel; the second computer and the fourth computer are communicatively connected by a wired channel. Aiming at the characteristics of double-star combined orbit entering tasks, the invention normalizes the combination body satellite-ground remote measurement and remote control, inter-satellite measurement and control data packaging and addressing modes; the satellite-ground remote measurement and control multi-point access and multi-route transmission of the combination are realized by utilizing the satellite measurement and control system resources; and setting multipath data interaction physical channels forming a ring topology between two stars to support data redirection between links.
Description
Technical Field
The invention relates to the field of satellite data management, in particular to a multi-point access, multi-path transmission, multi-priority concurrence, satellite-ground, on-satellite and inter-satellite integrated data flow control technology for double-satellite combined in-orbit telemetry and remote control. In more detail, the present invention relates to a multi-source data flow control system that accommodates dual star approach.
Background
Generally, a satellite taking GEO, MEO or IGSO as a task orbit adopts a body to carry a remote engine, and the power attitude control and data management of orbit transfer are independently completed by the satellite; or carried on the upper stage of the launch vehicle as the latter to transfer the in-orbit load. In the mode of transferring the double-star combination into the target track, the work of the combination body is completed by the cooperation of two stars, so that the coordinated and unified mode is needed to carry out the data management of the cooperation of the two stars, the resources on the two stars can be fully utilized, and the reliability of the transferring in-track task is improved.
The invention patent with patent document CN112706947A discloses a system-level reconstruction method of a combined spacecraft, which comprises the following steps: s1, when a certain cabin of the combined spacecraft breaks down, analyzing a fault mode; s2, selecting a corresponding system level reconstruction scheme according to the determined fixed mode. The patent document CN112467715A discloses a distributed power distribution and grounding method for a spacecraft. The method solves the problems of complex power supply and distribution design, high coupling degree, high cable weight cost, high cabin separation difficulty and the like of a large or multi-cabin spacecraft. None of the above approaches, however, involve inter-spacecraft cabin and assembly data communication and management.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a multi-source data flow control system suitable for double-star orbit entering.
The invention provides a multi-source data flow control system adapting to double-satellite orbit, which comprises a combination body formed by a first satellite and a second satellite;
the first satellite comprises a first computer and a second computer, and the second satellite comprises a third computer and a fourth computer;
the first computer and the second computer are in communication connection through a wired channel; the third computer and the fourth computer are in communication connection through a wired channel;
the first computer and the third computer are in communication connection through a wired channel; the second computer and the fourth computer are communicatively connected by a wired channel.
Preferably, the first satellite further comprises a first measurement and control channel and a second measurement and control channel, and the first computer and the second computer are both connected with the first measurement and control channel and the second measurement and control channel;
the second satellite further comprises a third measurement and control channel and a fourth measurement and control channel, and the third computer and the fourth computer are both connected with the third measurement and control channel and the fourth measurement and control channel.
Preferably, the first satellite comprises a first network, and two measurement and control access points which are connected with the measurement and control transponder are arranged on the first satellite and are in communication connection with a measurement and control channel on the first satellite through the first network;
the second satellite comprises a second network, two measurement and control access points which are connected with the measurement and control transponder are arranged on the second satellite, and the two measurement and control access points are in communication connection with a measurement and control channel on the second satellite through the second network.
Preferably, in the combined orbit approach of the first satellite and the second satellite, the combination body performs remote measurement and remote control on the ground, and measurement, control, attitude and orbit control data between two satellites and on-board platforms are uniformly packaged by adopting a data packet format conforming to CCSDS (common packet data service) subpackaging remote measurement/subpackaging remote control/advanced on-orbit system convention.
Preferably, data interaction is carried out in the first satellite and the second satellite by taking data packets as units, and the whole packet data structure is kept unchanged in the transmission process.
Preferably, a full duplex point-to-point wired communication channel is respectively arranged between the navigation guidance control computers and the star service computers of the double star; the navigation guidance control computers and the star service computers are respectively arranged among the double stars, and the full duplex point-to-point wired communication channels are formed among the four computers to form a full duplex ring topology.
Preferably, when the double-star works normally, two computers in the star perform platform measurement and control data interaction through a wired communication channel, and the two computers in the star perform gesture, platform measurement and control data interaction through the wired communication channel respectively, and each channel is exclusively used by one main type of data.
Preferably, when one of the two stars fails, the interactive data is redirected to the channel cascade links on the other three sides of the ring topology for continuous transmission.
Preferably, the different types of data on each channel are transmitted using time division multiplexing.
Preferably, the star-to-ground, inter-star and intra-star data multi-layer packaging method, packaging format and service data coding representation are unified and are irrelevant to transmission routes; data is transmitted between the source/sink only for hierarchical encapsulation/decapsulation, while the data packets remain unchanged and are packetized/decapsulated by and only the source/sink.
Compared with the prior art, the invention has the following beneficial effects:
1. aiming at the characteristics of the double-star combined orbit entering task, the invention normalizes the combination body satellite-ground remote measurement and remote control, inter-satellite measurement and control data packaging and addressing modes.
2. The invention utilizes the two on-board measurement and control system resources to realize the multipoint access and multipath routing of the combined body satellite-ground remote measurement and control; and setting multipath data interaction physical channels forming a ring topology between two stars to support data redirection between links.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of a dual-star combination multipoint access agility measurement and control.
Fig. 2 is a schematic diagram of a dual-star combined inter-star robust data interaction.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
As shown in fig. 1 and 2, the present invention provides a multi-source data flow control system adapted for double-satellite orbit, comprising a combination of a first satellite and a second satellite; the first satellite comprises a first computer and a second computer, and the second satellite comprises a third computer and a fourth computer; the first computer and the second computer are in communication connection through a wired channel; the third computer and the fourth computer are in communication connection through a wired channel; the first computer and the third computer are in communication connection through a wired channel; the second computer and the fourth computer are communicatively connected by a wired channel. The first satellite further comprises a first measurement and control channel and a second measurement and control channel, and the first computer and the second computer are both connected with the first measurement and control channel and the second measurement and control channel; the second satellite further comprises a third measurement and control channel and a fourth measurement and control channel, and the third computer and the fourth computer are both connected with the third measurement and control channel and the fourth measurement and control channel. The first satellite comprises a first network, two measurement and control access points which are connected with the measurement and control transponder are arranged on the first satellite, and the two measurement and control access points are in communication connection with a measurement and control channel on the first satellite through the first network; the second satellite comprises a second network, two measurement and control access points which are connected with the measurement and control transponder are arranged on the second satellite, and the two measurement and control access points are in communication connection with a measurement and control channel on the second satellite through the second network. And under the combined orbit entering mode of the first satellite and the second satellite, the combined body carries out remote measurement and remote control on the ground, and measurement, control, attitude and orbit control data of the two stars and the on-board platform are uniformly packaged by adopting a data packet format conforming to CCSDS (common packet data service) subpackaging remote measurement/subpackaging remote control/advanced on-orbit system. And the data interaction is carried out in the second satellite by taking the data packet as a unit between the first satellite and the second satellite, and the whole packet data structure is kept unchanged in the transmission process. The navigation guidance control computers and the star service computers of the double stars are respectively provided with a full duplex point-to-point wired communication channel; the navigation guidance control computers and the star service computers are respectively arranged among the double stars, and the full duplex point-to-point wired communication channels are formed among the four computers to form a full duplex ring topology. When the double stars work normally, two computers in the stars carry out platform measurement and control data interaction through wired communication channels, and two computers in the stars carry out gesture, platform measurement and control data interaction through wired communication channels respectively, and each channel is exclusive by one main type data. When one of the two stars fails, the interactive data is redirected to the channel cascade links of the other three sides of the ring topology for continuous transmission. The different types of data on each channel are transmitted by time division multiplexing. The star-to-ground, inter-star and intra-star data multi-layer packaging method, packaging format and service data coding representation are unified and are irrelevant to transmission routes; data is transmitted between the source/sink only for hierarchical encapsulation/decapsulation, while the data packets remain unchanged and are packetized/decapsulated by and only the source/sink.
The invention provides a normalization packaging method of double-star ground telemetry and remote control, inter-star and intra-star measurement and control data, which adopts a standardized multi-layer data format to package data, and utilizes data package service data to uniformly encode and characterize information source/sink addressing information, data types and data purposes, wherein the encoding and characterization are irrelevant with combination/separation flight states and data routes, so that the interaction of the satellite ground measurement and control data is completely uniform in data structures and definitions at different stages of tasks; the same package data is transmitted on the satellite, the ground, the space and the satellite, only the data package and the unpacking are carried out, and the service data or the application data is not modified.
The invention provides a satellite-ground agility measurement and control method during double-satellite combined orbit entering. In the state of the combination, any measurement and control transponder of the double-star measurement and control system can be used as an access point of a combination star-ground measurement and control link, and the double-star is subjected to all remote control and remote measurement and control of the combination orbit transfer measurement and control. The method enables satellite-ground measurement and control to flexibly select the transponder for remote measurement and control according to different postures of the assembly at the flight mission stage, and the failure rate of the measurement and control mission is reduced by one order of magnitude.
The invention provides an inter-satellite robust data interaction method during double-satellite combined orbit entering. On the premise of not having an on-board network, different point-to-point physical channels are arranged between two satellites, and a ring topology is formed; the method is used for carrying out different types of data interaction in parallel in normal time; and if any channel fails, redirecting the data of different types to a multi-hop link consisting of the perfect physical channels, and transmitting the data in a time division multiplexing mode. The method ensures that any data with different types among the double stars can be subjected to one-time heterogeneous backup, and improves the reliability of the task.
In the invention, under the double-star combined orbit entering mode, the combined body carries out ground remote measurement and remote control, the measurement, control, attitude and orbit control data of the two stars and the on-star platform are uniformly packaged by adopting a data packet format conforming to CCSDS (common control space division multiplexing) packet remote measurement/packet remote control/advanced on-orbit system contract, and the ground remote measurement and remote control wireless channel transmission respectively carries out channel packaging by adopting a remote measurement frame/remote control channel transmission unit format and coding and is packaged/unpackaged by a measurement and control channel gateway device; and the data interaction is directly carried out between two stars and the inside of the star by taking the data packet as a unit, and the whole packet data structure is kept unchanged in the transmission process. The remote measuring frame/remote control channel transmission unit spacecraft identifier represents different two stars of combined orbit, the data packet application process identifier represents a data information source/information destination, and the data packet auxiliary header represents the data type and the purpose. The service data are irrelevant to the combined/separated flight state and the data route, and the data structure and definition of the satellite-to-ground, inter-satellite and on-satellite measurement and control data interaction at different stages of the task are completely unified.
For the ground, any one measurement and control transponder can be selected as a channel access point for measurement and control of the whole assembly according to the actual gesture of the assembly in the transfer track-in stage and the visibility of a measurement and control antenna determined by the actual gesture; based on the general task defined by the service data, the ground can remotely measure and control the whole assembly without any additional processing on the uplink and downlink data. Meanwhile, according to the task requirements and the visible conditions of the measurement and control antenna, the ground can be subjected to measurement and control access through two or more transponders of the combined body in a multi-set measurement and control equipment or single equipment multi-target mode, and the combined body is subjected to remote measurement and control in a concurrent, parallel or multi-mode backup mode, so that the satellite-ground interaction efficiency and reliability are improved.
For the combination body among satellites and on the satellites, full duplex point-to-point wired communication channels are respectively arranged among navigation guidance control computers and the satellite computers, and full duplex point-to-point wired communication channels are respectively arranged among the navigation guidance control computers and the satellite computers, so that a full duplex ring topology is formed by four computers. During normal operation, two computers in the star perform platform measurement and control data interaction through a wired communication channel, and two computers in the star perform gesture, platform measurement and control data interaction through the wired communication channel respectively, wherein each channel is exclusively used by one main type of data; when one of the channels fails (a high probability occurs on the inter-satellite computer wired communication channel), the interactive data on the channel fails, and is redirected to the channel cascade links on the other three sides of the ring topology for continuous transmission, and the data of different types on each channel are transmitted in a time division multiplexing mode.
The star-to-ground, inter-star and intra-star data multi-layer packaging method, packaging format and service data coding representation are unified and are irrelevant to transmission routes; data is transmitted between the source/sink only for hierarchical encapsulation/decapsulation, while the data packets remain unchanged and are packetized/decapsulated by and only the source/sink.
The invention uses a plurality of measurement and control transponders loaded by the combination body to form a completely equivalent satellite-ground measurement and control multi-access point network. Multiple access points are used for supporting satellite-ground single-path, multi-path parallel or multi-path standby protection measurement and control requirements of a double-satellite transfer in different stages and different postures of the combined body. On the premise of not having an on-board and inter-board computer network, setting point-to-point physical channels among computers to be in ring topology, wherein each channel is exclusively used by main data during normal operation; when one channel fails, the rest channels are cascaded into a backup link, and different types of data are transmitted in a time division multiplexing way on each level of channels of the link; thereby forming a full link-redundancy heterogeneous storage system without increasing physical channel overhead.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (8)
1. A multi-source data flow control system suitable for double-satellite in-orbit, which is characterized by comprising a combination body formed by a first satellite and a second satellite;
the first satellite comprises a first computer and a second computer, and the second satellite comprises a third computer and a fourth computer;
the first computer and the second computer are in communication connection through a wired channel; the third computer and the fourth computer are in communication connection through a wired channel;
the first computer and the third computer are in communication connection through a wired channel; the second computer and the fourth computer are in communication connection through a wired channel;
the navigation guidance control computers and the star service computers of the double stars are respectively provided with a full duplex point-to-point wired communication channel; the navigation guidance control computers and the star service computers are respectively arranged among the double stars, and a full duplex point-to-point wired communication channel is formed among the four computers to form a full duplex ring topology;
when one of the two stars fails, the interactive data is redirected to the channel cascade links of the other three sides of the ring topology for continuous transmission.
2. The dual star trackable multi-source data flow control system of claim 1, wherein,
the first satellite further comprises a first measurement and control channel and a second measurement and control channel, and the first computer and the second computer are both connected with the first measurement and control channel and the second measurement and control channel;
the second satellite further comprises a third measurement and control channel and a fourth measurement and control channel, and the third computer and the fourth computer are both connected with the third measurement and control channel and the fourth measurement and control channel.
3. The multi-source data flow control system adapting to double-star orbit according to claim 2, wherein the first satellite comprises a first network, and two measurement and control access points for accessing to the measurement and control transponder are arranged on the first satellite and are in communication connection with a measurement and control channel on the first satellite through the first network;
the second satellite comprises a second network, two measurement and control access points which are connected with the measurement and control transponder are arranged on the second satellite, and the two measurement and control access points are in communication connection with a measurement and control channel on the second satellite through the second network.
4. The system of claim 1, wherein the first satellite and the second satellite are combined to perform ground telemetry and remote control, and the inter-satellite and on-board platform measurement, control, attitude and orbit control data are packaged in a unified data packet format conforming to the CCSDS-pack telemetry/pack remote control/advanced on-orbit system.
5. The dual-star in-orbit adaptive multi-source data flow control system according to claim 1, wherein the data interaction is performed in data packet units in the first satellite and the second satellite, and the whole packet data structure is kept unchanged during the transmission process.
6. The system of claim 1, wherein when the dual-star is operating normally, the two computers in the star perform platform measurement and control data interaction via wired communication channels, and the two computers in the star perform gesture, platform measurement and control data interaction via wired communication channels, respectively, and each channel is exclusive to one main type of data.
7. The dual star on-orbit adaptive multi-source data flow control system according to claim 1, wherein the different types of data on each channel are transmitted using time division multiplexing.
8. The multi-source data flow control system adapted to double star-in-orbit according to claim 1, wherein the star-to-ground, inter-star data multi-layer packaging method, packaging format, service data coding characterization are unified and are independent of transmission route; data is transmitted between the source/sink only for hierarchical encapsulation/decapsulation, while the data packets remain unchanged and are packetized/decapsulated by and only the source/sink.
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| JP2007517466A (en) * | 2003-12-29 | 2007-06-28 | ピアザト・エルエルシー | Inter-satellite cross-link communication system, apparatus, method, and computer program product |
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| CN101951296A (en) * | 2010-09-02 | 2011-01-19 | 航天东方红卫星有限公司 | Spread-spectrum TTC integrated testing system for three-satellite parallel testing |
| CN202632091U (en) * | 2012-03-26 | 2012-12-26 | 航天东方红卫星有限公司 | Three-satellite constellation distributed parallel test system |
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| CN111934747A (en) * | 2020-08-05 | 2020-11-13 | 上海卫星工程研究所 | System and method for realizing unified measurement and control of low-orbit formation satellites and transponder |
| CN113581492A (en) * | 2021-07-23 | 2021-11-02 | 上海卫星工程研究所 | Adaptive configuration method applied to dual-satellite combined in-orbit roles |
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