阅读说明：本技术 一种基于星座功能的通信卫星星座可靠性分析方法 (Communication satellite constellation reliability analysis method based on constellation function ) 是由 许瀚 高铭阳 饶建兵 雷亚珂 刘晨 于 2021-02-03 设计创作，主要内容包括：本发明的一个实施例公开了一种基于星座功能的通信卫星星座可靠性分析方法,包括：S100、构建具有星间链的低轨通信卫星星座的构型,其中所述构型包括多颗卫星和星间通信链路；S102、依据预定分析准则将所述构型转换成网络模型,其中所述卫星为节点,所述星间通信链路为有向边；S104、在所述网络模型中,以故障卫星为起点,计算所述网络模型中能够进行转发达到的卫星的最小路集E并根据所述最小路集利用容斥理论计算所述网络模型的可靠度R(G-0)＝P(E)。本发明提供了一种基于星座功能的通信卫星星座可靠性分析方法,为确定产品的可靠性指标提供依据,填补了通信卫星星座可靠性分析的空白,为通信卫星星座的可靠性分析提供了工程应用基础。(One embodiment of the invention discloses a constellation reliability analysis method of a communication satellite based on a constellation function, which comprises the following steps: s100, constructing a configuration of a low-orbit communication satellite constellation with inter-satellite links, wherein the configuration comprises a plurality of satellites and inter-satellite communication links; s102, converting the configuration into a network model according to a preset analysis criterion, wherein the satellite is a node, and the inter-satellite communication link is a directed edge; s104, in the network model, with the fault satellite as a starting point, calculating a minimum path set E of the satellite which can be forwarded in the network model, and calculating the reliability R (G) of the network model according to the minimum path set by using a repulsion theory 0 ) P (e). The invention provides a constellation reliability analysis method of a communication satellite based on a constellation function, which provides a basis for determining the reliability index of a product, fills the blank of the constellation reliability analysis of the communication satellite, and provides an engineering application basis for the reliability analysis of the constellation of the communication satellite.)

1. A constellation reliability analysis method for a communication satellite based on a constellation function is characterized by comprising the following steps:

s100, constructing a configuration of a low-orbit communication satellite constellation with inter-satellite links, wherein the configuration comprises a plurality of satellites and inter-satellite communication links;

s102, converting the configuration into a network model according to a preset analysis criterion, wherein the satellite is a node, and the inter-satellite communication link is a directed edge;

s104, in the network model, with the fault satellite as a starting point, calculating a minimum path set E of the satellite which can be forwarded in the network model, and calculating the reliability R (G) of the network model according to the minimum path set by using a repulsion theory₀)＝P(E)。

2. The method according to claim 1, wherein the configuration is formed by N satellites, wherein the N satellites are distributed in m orbital planes, the number N of satellites in each orbit is N/m, each satellite has 4 inter-satellite communication terminals, and inter-satellite communication is realized in 4 directions of forward direction and backward direction in the same orbit and forward and backward direction in different orbits.

3. The method of claim 2, wherein S104 comprises

Taking the node sequence as a first set E according to the satellite which can be reached by the fault satellite through one-time forwarding₁And the satellites that can be reached by two retransmissions have the node order as the second set E₂Get the minimum path set E ═ E₁∪E₂And calculating the reliability R (G) of the network model by using a repulsion theory₀)＝P(E₁∪E₂)。

4. The method of claim 2, wherein S104 comprises

According to the satellite which can be reached by the fault satellite through one retransmission and the satellite which can be reached by the satellite through one retransmission through another retransmission, a set G is formed by the satellites through the node sequence_iObtaining R (G)₀)＝1-(1-R(G_i))⁴＝1-(1-P(Re∪Re²∪Re²∪Re²))⁴

Wherein i is 1,2,3, 4;

re is the reliability of the communication link of the satellite, which can be achieved by the failed satellite through one-time forwarding.

5. The method of claim 1,

the predetermined analysis criteria are: for a designated area, it can be ensured that the users in the area keep continuous communication with the predetermined communication quality requirement, and then the constellation function is good.

6. The method of claim 5,

the analysis criterion is set based on that the single satellite user transmitting and receiving system and the feed transmitting and receiving system are not damaged at the same time and the satellite platform works reliably all the time.

7. A computer-readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the method according to any one of claims 1-6.

8. A computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, characterized in that the processor implements the method according to any of claims 1-6 when executing the program.

Technical Field

The invention relates to the technical field of reliability and satellite communication. And more particularly, to a constellation reliability analysis method for a communication satellite based on a constellation function, a computer-readable storage medium, and a computer device.

Background

In recent years, low earth orbit satellite communication becomes the mainstream trend of the development of the satellite communication field, and the demonstration and research and development of the low earth orbit communication satellite constellation are widely carried out at home and abroad, but the reliability analysis research on the communication satellite constellation is less.

The purpose of the communication satellite constellation is to realize global communication coverage, and the communication satellite constellation has the characteristics of large number of contained satellites, complex constellation function, multiple performance indexes and the like, and the complexity of reliability analysis is that the influence of local faults or whole satellite faults of a single satellite on the global coverage of the constellation is small, but under the condition of 2,3 or even more than ten satellites with faults, the influence analysis of the constellation function is extremely complex, and the reason is that the coverage of the constellation is greatly influenced by the distribution condition of the faulty satellite. In addition, when a local fault occurs in the satellite, the signal can still be forwarded through the inter-satellite link, so that the influence of the change of the constellation coverage is reduced, but the communication capacity and the communication rate of the satellite are reduced. The above problems lead to a very complex and difficult constellation reliability analysis. Under the background, the traditional series-parallel reliability model is not suitable any more, and the classical fault probability model such as Poisson distribution and binomial distribution can not reasonably reflect the constellation functional performance characteristics.

Disclosure of Invention

The invention aims to provide a constellation reliability analysis method of a communication satellite based on a constellation function, so as to solve at least one of the problems in the prior art.

In order to achieve the purpose, the invention adopts the following technical scheme:

in a first aspect, the present invention provides a method for analyzing reliability of a constellation of a communication satellite based on a constellation function, including:

s100, constructing a configuration of a low-orbit communication satellite constellation with inter-satellite links, wherein the configuration comprises a plurality of satellites and inter-satellite communication links;

s102, converting the configuration into a network model according to a preset analysis criterion, wherein the satellite is a node, and the inter-satellite communication link is a directed edge;

s104, in the network model, with the fault satellite as a starting point, calculating a minimum path set E of the satellite which can be forwarded in the network model, and calculating the reliability R (G) of the network model according to the minimum path set by using a repulsion theory₀)＝P(E)。

In a specific embodiment, the configuration is composed of N satellites, wherein the N satellites are distributed in m orbital planes, the number N of satellites in each orbit is N/m, each satellite has 4 inter-satellite communication terminals, and inter-satellite communication is realized in the forward and backward directions of the same orbit and the forward and backward directions of the different orbit sides.

In a specific embodiment, the S104 includes

Taking the node sequence as a first set E according to the satellite which can be reached by the fault satellite through one-time forwarding₁And the satellites that can be reached by two retransmissions have the node order as the second set E₂Get the minimum path set E ═ E₁∪E₂And calculating the reliability R (G) of the network model by using a repulsion theory₀)＝P(E₁∪E₂)。

In a specific embodiment, the S104 includes

According to the satellite which can be reached by the fault satellite through one retransmission and the satellite which can be reached by the satellite through one retransmission through another retransmission, a set G is formed by the satellites through the node sequence_iObtaining R (G)₀)＝1-(1-R(G_i))⁴＝1-(1-P(Re∪Re²∪Re²∪Re²))⁴

Wherein i is 1,2,3, 4;

re is the reliability of the communication link of the satellite, which can be achieved by the failed satellite through one-time forwarding.

In a specific embodiment, the predetermined analysis criteria is: for a designated area, it can be ensured that the users in the area keep continuous communication with the predetermined communication quality requirement, and then the constellation function is good.

In a specific embodiment, the analysis criteria are set based on that a single satellite user transceiver system and a feed transceiver system are not damaged at the same time and that the satellite platform is working reliably at all times.

In a second aspect, the present invention also provides a computer readable storage medium having stored thereon a computer program which, when executed by a processor, performs the method as provided in the first aspect of the application.

In a third aspect, the present invention also provides a computer device comprising a memory, a processor and a computer program stored on the memory and executable on the processor, wherein the processor executes the program to implement the method as provided in the first aspect of the present application.

The invention has the following beneficial effects:

the invention provides a constellation reliability evaluation method based on a network model and constraint by taking constellation coverage and communication performance indexes aiming at the current mainstream communication satellite constellation design scheme, provides a basis for determining the reliability indexes of products, fills the blank of constellation reliability analysis of communication satellites, and provides an engineering application basis for the reliability analysis of the communication satellite constellation.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings needed to be used in the description of the embodiments will be briefly introduced 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 based on these drawings without creative efforts.

Fig. 1 shows a flow chart of a constellation reliability analysis method for a communication satellite based on a constellation function according to an embodiment of the invention.

FIG. 2 illustrates a schematic diagram of a typical constellation configuration for a constellation of low earth orbit communication satellites having inter-satellite links, according to one embodiment of the invention;

FIG. 3 is a schematic diagram of a network model abstracted after constraint analysis of constellation function performance indicators according to an embodiment of the present invention;

FIG. 4 shows a sub-architectural diagram of a network model according to one embodiment of the invention;

fig. 5 shows a schematic diagram of the variation of the reliability of the substructure and the entire network with the single-sided reliability according to an embodiment of the present invention.

FIG. 6 shows a schematic block diagram of a computer device suitable for use in implementing embodiments of the present application.

Detailed Description

In order to more clearly illustrate the invention, the invention is further described below with reference to preferred embodiments and the accompanying drawings. Similar parts in the figures are denoted by the same reference numerals. It is to be understood by persons skilled in the art that the following detailed description is illustrative and not restrictive, and is not to be taken as limiting the scope of the invention.

First embodiment

As shown in fig. 1, an embodiment of the present invention discloses a method for analyzing reliability of a constellation of a communication satellite based on a constellation function, including:

s100, constructing a typical configuration of a low-earth orbit communication satellite constellation with inter-satellite chains, wherein the configuration comprises a plurality of satellites and inter-satellite communication links.

In one specific example, a typical configuration of a constellation of low earth orbit communication satellites with inter-satellite links is shown in fig. 2, wherein one circle in fig. 2 represents one satellite; a column of vertically arranged circles represents part of satellites on an orbital plane; the double-headed arrows represent inter-satellite chains, i.e. the direction and path of signal transmission.

In a specific example, the constellation includes N total satellites, and is divided into m orbital planes, that is, the N satellites are distributed in the m orbital planes, and the number N of satellites in each orbit is N/m. The single satellite has an inter-satellite communication function, inter-satellite communication can be realized in the forward direction and the backward direction of the same orbit and the forward direction and the backward direction of the different orbit side and in the 4 directions, a hardware layer represents that the single satellite has 4 inter-satellite communication terminals, and each terminal can realize the receiving and the transmitting of inter-satellite communication signals.

S102, converting the configuration into a network model according to a preset analysis criterion, wherein the satellite is a node, and the inter-satellite communication link is a directed edge; in a specific embodiment, the predetermined analysis criteria is: for a designated area, it can be ensured that the users in the area keep continuous communication with the predetermined communication quality requirement, and then the constellation function is good.

In a specific embodiment, the analysis criteria are set based on that a single satellite user transceiver system and a feed transceiver system are not damaged at the same time and that the satellite platform is working reliably at all times.

Wherein the predetermined analysis criteria are specified as follows: the function of the communication satellite constellation is to realize global coverage, then for a given area, the number of satellites capable of covering the area is limited, and if it can be ensured that users in the area keep continuous communication with certain communication quality (rate, time delay, etc.), it indicates that the constellation function is intact. The criterion is based on 2 assumptions: 1. the single satellite user transmitting and receiving system and the feed transmitting and receiving system are not damaged simultaneously; 2. satellite platforms are considered to be reliable at all times.

In a specific embodiment, based on the requirement of constellation coverage and communication indexes, when a satellite user side system or a feed side system covering a certain designated area fails at a certain time, signals need to be forwarded to an adjacent satellite through an inter-satellite chain and downloaded, and after analysis, due to the requirement of the communication indexes, at most two times of inter-satellite forwarding can be allowed. Thus, the abstracted network model is shown in FIG. 3 and denoted as network G₀。

The bold circles in fig. 3 represent the start and end points of the network model, where the sequence number 1 represents the start point of the network, and the sequence numbers 3, 5, 7, 9, 10, 11, 12, 13 represent the end points reachable by the path 2 (via two inter-satellite forwarding); the serial numbers 2, 4, 6 and 8 are the satellites that can be reached through one-time forwarding; directional arrows indicate the direction and path of signal transmission.

In a specific embodiment, the network model is simplified according to the characteristics of the network model and the reliability theory, and the reliability analysis and evaluation is carried out by utilizing the minimum road set and the containment theory.

S104, in the network model, with the fault satellite as a starting point, calculating and rooting a minimum path set E of the satellite which can be forwarded in the network modelCalculating the reliability R (G) of the network model according to the minimum path set by using a repulsion theory₀)＝P(E)。

In a specific embodiment, the S104 includes

Taking the node sequence as a first set E according to the satellite which can be reached by the fault satellite through one-time forwarding₁And the satellites that can be reached by two retransmissions have the node order as the second set E₂Get the minimum path set E ═ E₁∪E₂And calculating the reliability R (G) of the network model by using a repulsion theory₀)＝P(E₁∪E₂)。

In a specific embodiment, the circle with number 1 in fig. 3 is the failed satellite that should independently complete signal forwarding, and is the starting point of the network, and numbers 2, 4, 6, and 8 are the satellites that can be reached through one-time forwarding, and the node sequence is taken as a set, denoted as E₁，E₁Can be expressed as:

E₁＝({1,2}∪{1,4}∪{1,6}∪{1,8})

the sequence numbers 3, 5, 7, 9, 10, 11, 12, 13 are the satellites that can be reached through two retransmissions, with the node order as a set, denoted as E₂，E₂Can be expressed as:

E₂＝({1,2,3}∪{1,2,9}∪{1,2,10}∪{1,4,3}∪{1,4,5}∪{1,4,11}∪{1,6,5}∪{1,6,7}∪{1,6,12}∪{1,8,7}∪{1,8,9}∪{1,8,13})

it can be obtained that the above-mentioned sets are the minimum way sets of the network. Therefore, as long as any one of the above sets is connected, it can be determined that the whole network is connected, that is:

E＝E₁∪E₂

and finally, carrying out reliability analysis by using a repulsion theory aiming at the minimum path set. Let the reliability of the network be R (G)₀). From the theory of repulsion:

R(G₀)＝P(E₁∪E₂)＝P(P({1,2})∪P({1,4})∪...∪P({1,8,13}))

as can be seen, the term in the formula is 2^k-1, k being the number of subsets, in this case k 16. The amount of computation is too largeIs large. Therefore, the formula needs to be simplified.

In a specific embodiment, the S104 further includes: according to the satellite which can be reached by the fault satellite through one retransmission and the satellite which can be reached by the satellite through one retransmission through another retransmission, a set G is formed by the satellites through the node sequence_iObtaining R (G)₀)＝1-(1-R(G_i))⁴＝1-(1-P(Re∪Re²∪Re²∪Re²))⁴. Wherein i is 1,2,3, 4. Re is the reliability of the communication link of the satellite, which can be achieved by the failed satellite through one-time forwarding.

In one embodiment, the network model has a sub-structure as shown in fig. 4, and by analyzing the network structure, it can be found that the network in fig. 3 is composed of 4 networks in fig. 4, and represents 4 disjoint sets G_iE.g. G₁＝({1,2}∪{1,2,3}∪{1,2,9}∪{1,2,10})，G₂({1,4}, tuo {1,4,3}, tuo {1,4,5}, tuo {1,4,11 }). Therefore, any network in fig. 4 is connected, i.e. the connection of the whole network can be ensured, and the reliability of a single set is set as R (G)_i) From the configuration, R (G) is known_i) Are equal, so:

R(G₀)＝1-(1-R(G_i))⁴

thus, the problem is converted into P (G) pair_i) Solving of (c) can yield:

R(G_i)＝P(G_i)＝P(G₁)＝P({1,2}∪{1,2,3}∪{1,2,9}∪{1,2,10})

in this case, the number of terms in the formula is small, and the formula can be developed by using a repulsion theory. Assuming that the reliability of one edge, e.g., e1, is Re and the reliabilities of all edges are the same, R (G)_i) Can be expressed as:

R(G_i)＝P(G_i)＝P(Re∪Re²∪Re²∪Re²)

the reliability of the final system can be obtained through calculation. The graph of the substructures and overall network reliability as a function of single-sided reliability is shown in fig. 5. In fig. 5, the horizontal axis represents the reliability of a single inter-satellite communication link, and the vertical axis represents the variation in system reliability. As can be seen from fig. 5, the reliability of the sub-structure increases with the reliability of the single inter-satellite communication link and gradually approaches 1. Overall network reliability increases as the reliability of a single inter-satellite communication link increases and gradually approaches 1.

The invention provides a constellation reliability evaluation method based on a network model and constraint by taking constellation coverage and communication performance indexes aiming at the current mainstream communication satellite constellation design scheme, provides a basis for determining the reliability indexes of products, fills the blank of constellation reliability analysis of communication satellites, and provides an engineering application basis for the reliability analysis of the communication satellite constellation.

Second embodiment

Fig. 6 shows a schematic structural diagram of a computer device according to another embodiment of the present application. The computer device 50 shown in fig. 6 is only an example, and should not bring any limitation to the function and the scope of use of the embodiments of the present application. As shown in fig. 6, computer device 50 is embodied in the form of a general purpose computing device. The components of computer device 50 may include, but are not limited to: one or more processors or processing units 500, a system memory 516, and a bus 501 that couples various system components including the system memory 516 and the processing unit 500.

Bus 501 represents one or more of any of several types of bus structures, including a memory bus or memory controller, a peripheral bus, an accelerated graphics port, and a processor or local bus using any of a variety of bus architectures. By way of example, such architectures include, but are not limited to, Industry Standard Architecture (ISA) bus, micro-channel architecture (MAC) bus, enhanced ISA bus, Video Electronics Standards Association (VESA) local bus, and Peripheral Component Interconnect (PCI) bus.

Computer device 50 typically includes a variety of computer system readable media. Such media may be any available media that is accessible by computer device 50 and includes both volatile and nonvolatile media, removable and non-removable media.

The system memory 516 may include computer system readable media in the form of volatile memory, such as Random Access Memory (RAM)504 and/or cache memory 506. The computer device 50 may further include other removable/non-removable, volatile/nonvolatile computer system storage media. By way of example only, storage system 508 may be used to read from and write to non-removable, nonvolatile magnetic media (not shown in FIG. 6, and commonly referred to as a "hard disk drive"). Although not shown in FIG. 6, a magnetic disk drive for reading from and writing to a removable, nonvolatile magnetic disk (e.g., a "floppy disk") and an optical disk drive for reading from or writing to a removable, nonvolatile optical disk (e.g., a CD-ROM, DVD-ROM, or other optical media) may be provided. In these cases, each drive may be connected to the bus 501 by one or more data media interfaces. Memory 516 may include at least one program product having a set (e.g., at least one) of program modules that are configured to carry out the functions of embodiment one.

A program/utility 510 having a set (at least one) of program modules 512 may be stored, for example, in memory 516, such program modules 512 including, but not limited to, an operating system, one or more application programs, other program modules, and program data, each of which examples or some combination thereof may comprise an implementation of a network environment. Program modules 512 generally perform the functions and/or methodologies of the embodiments described herein.

Computer device 50 may also communicate with one or more external devices 70 (e.g., keyboard, pointing device, display 60, etc.), with one or more devices that enable a user to interact with the computer device 50, and/or with any devices (e.g., network card, modem, etc.) that enable the computer device 50 to communicate with one or more other computing devices. Such communication may occur via input/output (I/O) interfaces 502. Also, computer device 50 may communicate with one or more networks (e.g., a Local Area Network (LAN), a Wide Area Network (WAN) and/or a public network, such as the Internet) through network adapter 514. As shown in FIG. 6, network adapter 514 communicates with the other modules of computer device 50 via bus 501. It should be appreciated that although not shown in FIG. 6, other hardware and/or software modules may be used in conjunction with computer device 50, including but not limited to: microcode, device drivers, redundant processing units, external disk drive arrays, RAID systems, tape drives, and data backup storage systems, among others.

The processor unit 500 executes programs stored in the system memory 516 to execute various functional applications and data processing, for example, to implement a constellation reliability analysis method for a communication satellite based on constellation function provided in an embodiment of the present application.

Aiming at the existing problems, the computer equipment suitable for the constellation reliability analysis method of the communication satellite based on the constellation function is formulated, the blank of the constellation reliability analysis of the communication satellite is filled, an engineering application basis is provided for the reliability analysis of the constellation of the communication satellite, and the method has a wide application prospect.

Third embodiment

Another embodiment of the present application provides a computer-readable storage medium, on which a computer program is stored, which when executed by a processor implements the method provided by the first embodiment. In practice, the computer-readable storage medium may take any combination of one or more computer-readable media. The computer readable medium may be a computer readable signal medium or a computer readable storage medium.

A computer readable storage medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the foregoing. More specific examples (a non-exhaustive list) of the computer readable storage medium would include the following: an electrical connection having one or more wires, a portable computer diskette, a hard disk, a Random Access Memory (RAM), a read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical fiber, a portable compact disc read-only memory (CD-ROM), an optical storage device, a magnetic storage device, or any suitable combination of the foregoing. In the present embodiment, a computer readable storage medium may be any tangible medium that can contain, or store a program for use by or in connection with an instruction execution system, apparatus, or device.

A computer readable signal medium may include a propagated data signal with computer readable program code embodied therein, for example, in baseband or as part of a carrier wave. Such a propagated data signal may take many forms, including, but not limited to, electro-magnetic, optical, or any suitable combination thereof. A computer readable signal medium may also be any computer readable medium that is not a computer readable storage medium and that can communicate, propagate, or transport a program for use by or in connection with an instruction execution system, apparatus, or device.

Program code embodied on a computer readable medium may be transmitted using any appropriate medium, including but not limited to wireless, wireline, optical fiber cable, RF, etc., or any suitable combination of the foregoing. Computer program code for carrying out operations for aspects of the present application may be written in any combination of one or more programming languages, including an object oriented programming language such as Java, Smalltalk, C + +, and conventional procedural programming languages, such as the "C" programming language or similar programming languages. The program code may execute entirely on the user's computer, partly on the user's computer, as a stand-alone software package, partly on the user's computer and partly on a remote computer or entirely on the remote computer or server. In the case of a remote computer, the remote computer may be connected to the user's computer through any type of network, including a Local Area Network (LAN) or a Wide Area Network (WAN), or the connection may be made to an external computer (for example, through the Internet using an Internet service provider).

The invention provides a constellation reliability evaluation method based on a network model and constraint by taking constellation coverage and communication performance indexes aiming at the current mainstream communication satellite constellation design scheme, provides a basis for determining the reliability indexes of products, fills the blank of constellation reliability analysis of communication satellites, and provides an engineering application basis for the reliability analysis of the communication satellite constellation.

It should be understood that the above-mentioned embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention, and it will be obvious to those skilled in the art that other variations or modifications may be made on the basis of the above description, and all embodiments may not be exhaustive, and all obvious variations or modifications may be included within the scope of the present invention.