Cooperative guidance success rate analysis method for coupled constellation

Abstract

This invention relates to a method for analyzing the success rate of coordinated guidance for coupled constellations, comprising: acquiring coordinated guidance mission parameters of the coupled constellations; calculating the inter-satellite link establishment time index based on the acquired coordinated guidance mission parameters; calculating the inter-satellite link stability index based on the acquired coordinated guidance mission parameters; calculating the inter-satellite link anti-interference capability index based on the acquired coordinated guidance mission parameters; and performing a coordinated guidance success rate analysis for coupled constellations based on the calculated inter-satellite link establishment time index, inter-satellite link stability index, and inter-satellite link anti-interference capability index. This invention analyzes the success rate of constellation coordinated guidance by calculating the inter-satellite link network establishment time, link stability, and anti-interference capability of the coupled constellations, and calculates the coordinated guidance success rate of constellations for Earth observation.

Description

Technical Field

[0001] This invention relates to the field of remote sensing satellite Earth observation mission planning technology, and in particular to a method for analyzing the success rate of coordinated guidance for coupled constellations. Background Technology

[0002] With the rapid development of aerospace technology and space applications, the number of spacecraft in orbit is increasing, and remote sensing satellite constellations with multiple payloads and coupled configurations have become one of the important means to cope with complex meteorological environments.

[0003] Coupled constellations possess a rich array of satellite payloads and a tightly integrated constellation configuration, enabling them to effectively cope with complex and ever-changing meteorological environments. To determine the success rate of coordinated guidance for Earth observation using coupled constellations, a scientific and intuitive method is needed to calculate and visualize this success rate. Summary of the Invention

[0004] To address the technical problems existing in the prior art, the present invention aims to provide a cooperative guidance success rate analysis for coupled constellations.

[0005] To achieve the above-mentioned objectives, this invention provides a method for analyzing the success rate of cooperative guidance for coupled constellations, comprising the following steps:

[0006] Step S1: Obtain the parameters of the coupled constellation collaborative guidance task;

[0007] Step S2: Calculate the inter-satellite link establishment time index based on the obtained coupled constellation collaborative guidance mission parameters;

[0008] Step S3: Calculate the inter-satellite link stability index based on the obtained coupled constellation collaborative guidance mission parameters;

[0009] Step S4: Calculate the inter-satellite link anti-interference capability index based on the obtained coupled constellation collaborative guidance mission parameters;

[0010] Step S5: Based on the calculated inter-satellite link establishment time, inter-satellite link stability, and inter-satellite link anti-interference capability indicators, conduct a cooperative guidance success rate analysis for coupled constellations.

[0011] According to one technical solution of the present invention, in step S1, the mission parameters include scenario parameters, satellite parameters, inter-satellite link parameters, ground target parameters, and cooperative mission parameters;

[0012] The scene parameters include the start and end times of the scene;

[0013] The satellite parameters include satellite ID, satellite type, orbit parameters, satellite name, satellite position, satellite Id, satellite EIRP, satellite orbit information, antenna power, quality factor G / T, antenna receiving gain G_RS, feeder loss L_FRS, equivalent noise temperature Ts, receiver threshold [C / N]th, saturated flux density SFD, and anti-interference quality factor. The satellite position includes the satellite's latitude, longitude, and altitude.

[0014] The inter-satellite link parameters include transmission frequency band, transmission rate, transmission delay, interference frequency, interference power amplifier transmit power, interference antenna aperture, inter-satellite communication distance, effective information rate, information rate, operating frequency band, duplex mode, transmission content, star network topology diagram, and time aggregation diagram.

[0015] The ground target parameters include target ID, target type, target location, and target observation requirements;

[0016] The observation mission parameters include mission ID, mission start time, mission end time, and satellite attitude.

[0017] According to one technical solution of the present invention, step S2 specifically includes:

[0018] Real-time monitoring and collection of key parameters at each stage of the network construction process, including timestamps, status, and results;

[0019] Based on the collected data, link networking scheme, and optimized link information, calculate the inter-satellite link establishment time:

[0020] The inter-satellite link establishment time is related to transmission delay and queuing delay;

[0021] The formula for calculating the transmission delay on the possible inter-satellite link between satellite A and satellite B is as follows:

[0022]

[0023] Among them, T pi D is the propagation delay of the i-th link in the possible inter-satellite links between satellite A and satellite B. i is the length of the i-th link, and c is the speed of light, representing the transmission rate of wireless or laser signals;

[0024] Suppose there exists a packet that enters a given output queue buffer at time t, then the queuing delay T of the i-th link is... qi The calculation formula is:

[0025]

[0026] Among them, L avThe average length of the existing packets in the given output queue is given, V is the inter-planetary link bandwidth, and n(t) is the number of packets in the given output queue at time t.

[0027] The route update period for the i-th link is t. s Starting at time , the average expected queuing delay of packets within the route update interval is expressed as:

[0028]

[0029] Where Δt represents the propagation time step;

[0030] There may be an inter-satellite link (ISL) between satellite A and satellite B. A→B The i-th link in t s The chain establishment time T within the route update interval starting from the current moment. i The sum of transmission delay and queuing delay is expressed as:

[0031] T i (ISL A→B ) = T pi (t s )+T Qi (t s )

[0032] The inter-satellite link establishment time T in the link network is equal to the total link establishment time T of all links in the link network. i sum:

[0033]

[0034] Where M represents the total number of links in the link network.

[0035] According to one technical solution of the present invention, step S3 specifically includes:

[0036] Step S31: Calculate the relative positions of the satellites within the coupled constellation;

[0037] Step S32: Obtain channel quality parameters between satellites, including signal strength and signal intensity;

[0038] Step S33: Use a mathematical model to calculate the stability index of the inter-satellite link.

[0039] According to one technical solution of the present invention, step S33 specifically includes:

[0040] Step S331: Calculate the inter-satellite link lifetime.

[0041] Assuming in When satellite A enters the line-of-sight range of satellite B, an inter-satellite link (ISL) is established between them.A→B ; and At any given moment, satellite A will leave the line-of-sight range of satellite B, at which point the inter-satellite link (ISL) will be interrupted. A→B If the connection is lost, the inter-satellite link (ISL) will be disconnected during this connection / disconnection process. A→B Survival time T k (A→B) represents the time from time... At the time The duration, i.e.:

[0042]

[0043]

[0044] Where k = 1, 2, ..., N, N represents the number of times the inter-satellite link between satellite A and satellite B will switch on and off within one system cycle of the coupled constellation; V A→B,k ↑ represents the relative velocity of satellite A when it enters the line-of-sight range of satellite B, V A→B,k ↓ indicates the relative velocity of satellite A when it leaves the line-of-sight range of satellite B;

[0045] Inter-satellite link at time t Remaining survival time T(S) j →S i ,t) is represented as:

[0046]

[0047] Where k = 1, 2, ..., N;

[0048] Step S332: Calculate the inter-satellite link propagation delay:

[0049] At time t, the inter-satellite link (ISL) A→B The propagation delay is defined as:

[0050] D(A→B, t) = r(A→B, t) / c

[0051] Where r(A→B, t) is the distance between satellite A and satellite B at time t; c is the speed of light;

[0052] Step S333: Calculate the degree of interference from the space environment on inter-satellite communication.

[0053] The degree of interference P of the space environment on inter-satellite communication SI It can be represented as:

[0054]

[0055] in, The influence of the Sun on inter-satellite links is expressed by the duration t of the solar transit. sun To measure; This indicates the impact of Earth's obstruction on satellite communications; The values ​​e1, e2, and e3 represent the impact of inter-satellite link bit error rate on communication quality. For P SI The contribution factors are e1≤0, e2≤0, e3≤0;

[0056] Step S334: Based on the calculated inter-satellite link survival time, inter-satellite link propagation delay, and the degree of interference from the space environment on inter-satellite communication, perform inter-satellite link stability calculations:

[0057] Inter-satellite link (ISL) at time t A→B The formula for calculating the inter-satellite link stability parameter P(A→B, t) is:

[0058]

[0059] Among them, D ISL，min To minimize the inter-satellite link propagation delay within the coupled constellation, T ISL，max w is the maximum inter-satellite link survival time within the coupled constellation. d w is the weighting coefficient for inter-satellite link propagation delay. l w is the weighting factor for the remaining lifetime of inter-satellite links. s is the spatial interference weighting coefficient, and w d +w l +w s =1.

[0060] According to one technical solution of the present invention, step S4 specifically includes:

[0061] Step S41: Calculate the anti-interference capability of a single satellite using the receiver bit error rate and the average availability of the link time.

[0062] Step S42: Calculate the overall network's anti-interference capability.

[0063] According to one technical solution of the present invention, in step S41, the formula for calculating the bit error rate of the receiving end is:

[0064]

[0065] or

[0066]

[0067] Where r is the signal-to-noise ratio at the receiver. M is the number of phases in phase shift keying; Equation (1) is a statistical value obtained through direct statistics; Equation (2) is a calculated value obtained through measurement or configuration values;

[0068] The formula for calculating the average availability of the link time is as follows:

[0069] r AB =T2 / T1

[0070] Where, r AB r represents the average availability of the link between satellite A and satellite B. AB ∈[0,1]; T1 is the inter-satellite link (ISL). A→B Normal link establishment time under interference-free conditions, T2 is the inter-satellite link ISL. A→B The normal time for the disrupted chain establishment process.

[0071] According to a technical solution of the present invention, in step S42, the overall anti-interference capability of the inter-satellite link is defined by the average availability R of the entire network, and the calculation of the overall network anti-interference capability specifically includes:

[0072] The availability matrix of the inter-satellite link network G(N,E) under a specific interference scenario and within a statistical time T, at time t, is as follows:

[0073]

[0074] Where, r AB Let R be the average availability of connectivity between satellite A and satellite B in the inter-satellite link network G(N,E) at time t, and R be a symmetric matrix.

[0075] The average availability of the entire network under the specific interference scenario is then expressed as:

[0076]

[0077] Define X interference test scenarios. Using the Monte Carlo method, perform Monte Carlo tests on the average availability of the entire network under specific interference scenarios to obtain the average availability of the entire network across all interference test scenarios. This average availability is defined as the probability average of the average availability of the entire network under each scenario. Then:

[0078]

[0079] Where R is the average availability of the entire network under traversal interference scenarios; R x This represents the average availability of the entire network under the xth interference scenario.

[0080] According to one technical solution of the present invention, step S5 specifically includes:

[0081] The inter-satellite link establishment time T, inter-satellite link stability parameter P(A→B, t), and average availability rate R of the entire inter-satellite link network are compared with their corresponding threshold values. If all three parameters reach the threshold value, it indicates that the collaborative guidance is successful; otherwise, it indicates that the collaborative guidance has failed.

[0082] According to one technical solution of the present invention, it further includes:

[0083] Step S6: Display the success rate analysis results of the coordinated guidance for coupled constellations. The display format includes two-dimensional maps and data charts.

[0084] Compared with the prior art, the present invention has the following advantages:

[0085] This invention proposes a cooperative guidance success rate analysis for coupled constellations. By calculating the link establishment time, link stability, and link anti-interference capability of the inter-satellite links of the coupled constellations, and then calculating the cooperative guidance success rate of the coupled constellations based on the calculated link establishment time, link stability, and link anti-interference capability, a quantitative evaluation of the constellation cooperative guidance success rate can be achieved. This method has the advantages of high evaluation efficiency, simple calculation method, high feasibility, and strong applicability, which helps to improve the overall performance and application value of the Earth observation system. Attached Figure Description

[0086] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention, and those skilled in the art can obtain other drawings based on these drawings without creative effort.

[0087] Figure 1 This schematic diagram illustrates a flowchart of a cooperative guidance success rate analysis method for coupled constellations provided in one embodiment of the present invention.

[0088] Figure 2 This schematic diagram illustrates a flowchart for obtaining the inter-satellite link network establishment time according to an embodiment of the present invention;

[0089] Figure 3 The flowchart illustrating the network connection stability calculation according to one embodiment of the present invention is shown. Detailed Implementation

[0090] The description of the embodiments in this specification should be taken in conjunction with the accompanying drawings, which should form part of the complete specification. In the drawings, the shape or thickness of the embodiments may be exaggerated and may be indicated in a simplified or convenient manner. Furthermore, parts of the various structures in the drawings will be described separately; it is worth noting that elements not shown in the figures or not described in words are in a form known to those skilled in the art.

[0091] The descriptions of the embodiments herein, including any references to directions and orientations, are for ease of description only and should not be construed as limiting the scope of the invention. The following description of preferred embodiments involves combinations of features, which may exist independently or in combination; the invention is not particularly limited to the preferred embodiments. The scope of the invention is defined by the claims.

[0092] like Figures 1 to 3 As shown, the present invention provides a method for analyzing the success rate of cooperative guidance for coupled constellations, comprising the following steps:

[0093] Step S1: Obtain the parameters of the coupled constellation collaborative guidance task;

[0094] In step S1, the mission parameters include scenario parameters, satellite parameters, inter-satellite link parameters, ground target parameters, and collaborative mission parameters.

[0095] The scene parameters include the start and end times of the scene;

[0096] The satellite parameters include satellite ID, satellite type, orbit parameters, satellite name, satellite position, satellite Id, satellite EIRP, satellite orbit information, antenna power, quality factor G / T, antenna receiving gain G_RS, feeder loss L_FRS, equivalent noise temperature Ts, receiver threshold [C / N]th, saturated flux density SFD, and anti-interference quality factor. The satellite position includes the satellite's latitude, longitude, and altitude.

[0097] The inter-satellite link parameters include transmission frequency band, transmission rate, transmission delay, interference frequency, interference power amplifier transmit power, interference antenna aperture, inter-satellite communication distance, effective information rate, information rate, operating frequency band, duplex mode, transmission content, star network topology diagram, and time aggregation diagram.

[0098] The ground target parameters include target ID, target type, target location, and target observation requirements;

[0099] The observation mission parameters include mission ID, mission start time, mission end time, and satellite attitude.

[0100] Step S2: Calculate the inter-satellite link establishment time index based on the obtained coupled constellation collaborative guidance mission parameters;

[0101] The calculation of the success rate of coupled constellation collaborative guidance includes the calculation of indicators such as inter-satellite link establishment time, link stability, and anti-interference capability.

[0102] Step S2 specifically includes:

[0103] Real-time monitoring and collection of key parameters at each stage of the network construction process, including timestamps, status, and results;

[0104] Based on the collected data, link networking scheme, and optimized link information, calculate the inter-satellite link establishment time:

[0105] The inter-satellite link establishment time is related to transmission delay and queuing delay.

[0106] Transmission delay describes the variation in inter-satellite link length and characterizes the interconnection between satellites on different orbital planes in a network. Let the formula for calculating the transmission delay on a possible inter-satellite link between satellite A and satellite B be:

[0107]

[0108] Among them, T pi D is the propagation delay of the i-th link in the possible inter-satellite links between satellite A and satellite B. i is the length of the i-th link, c is the speed of light, and represents the transmission rate of wireless or laser signals.

[0109] Queuing delay is used to describe changes in traffic load in a satellite network. Because traffic load changes are both sudden and continuous, only real-time data can accurately reflect these changes. Assuming a packet enters a given output queue buffer at time t, the queuing delay T of the i-th link is... qi The calculation formula is:

[0110]

[0111] Among them, L av The average length of the existing packets in the given output queue is given, V is the inter-planetary link bandwidth, and n(t) is the number of packets in the given output queue at time t.

[0112] Let the route update period of the i-th link be t. s Starting at time , the average expected queuing delay of packets within the route update interval is expressed as:

[0113]

[0114] Where Δt represents the propagation time step;

[0115] There may be an inter-satellite link (ISL) between satellite A and satellite B. A→B The i-th link in t s The chain establishment time T within the route update interval starting from the current moment. i The sum of transmission delay and queuing delay is expressed as:

[0116] T i (ISL A→B ) = T pi (t s )+T Qi (t s )

[0117] Since the delay parameter is additive, the inter-satellite link establishment time T in the link network is equal to the establishment time T of all links in the link network. i sum:

[0118]

[0119] Where M represents the total number of links in the link network.

[0120] The average queuing delay is the queuing delay T of all links. Qi The arithmetic mean.

[0121] Step S3: Calculate the inter-satellite link stability index based on the obtained coupled constellation collaborative guidance mission parameters;

[0122] The inter-satellite link networking stability analysis and calculation is responsible for calculating the inter-satellite link networking capability and analyzing link stability and other indicators.

[0123] Step S3 specifically includes:

[0124] Step S31: Calculate the relative positions of the satellites within the coupled constellation;

[0125] Step S32: Obtain channel quality parameters between satellites, including signal strength and signal intensity;

[0126] Step S33: Use a mathematical model to calculate the stability index of the inter-satellite link.

[0127] Inter-satellite link stability primarily measures the ability of a communication link connecting two nodes in a satellite network to maintain connectivity and provide optimal data transmission. Inter-satellite link stability is mainly related to factors such as inter-satellite link lifetime, inter-satellite link propagation delay, and the degree of interference from the space environment on inter-satellite communication.

[0128] Step S33 specifically includes:

[0129] Step S331: Calculate the inter-satellite link lifetime.

[0130] Assuming in When satellite A enters the line-of-sight range of satellite B, an inter-satellite link (ISL) is established between them. A→B ; and At any given moment, satellite A will leave the line-of-sight range of satellite B, at which point the inter-satellite link (ISL) will be interrupted. A→B If the connection is lost, the inter-satellite link (ISL) will be disconnected during this connection / disconnection process. A→B Survival time T k (A→B) represents the time from time... At the time The duration, i.e.:

[0131]

[0132] Where k = 1, 2, ..., N, N represents the number of times the inter-satellite link between satellite A and satellite B will switch on and off within one system cycle of the coupled constellation; V A→B,k ↑ represents the relative velocity of satellite A when it enters the line-of-sight range of satellite B, V A→B,k ↓ represents the relative velocity of satellite A when it leaves the line-of-sight range of satellite B; the survival time of inter-satellite links also changes dynamically within a system cycle, and the maximum survival time among all inter-satellite links that undergo dynamic switching is defined as the maximum inter-satellite link survival time T within the coupled constellation. max .

[0133] Inter-satellite link at time t Remaining survival time T(S) j →S i ,t) is represented as:

[0134]

[0135] Where k = 1, 2, ..., N;

[0136] Step S332: Calculate the inter-satellite link propagation delay:

[0137] At time t, the inter-satellite link (ISL) A→B The propagation delay is defined as:

[0138] D(A→B, t) = r(A→B, t) / c

[0139] Where r(A→B, t) is the distance between satellite A and satellite B at time t; c is the speed of light. The propagation delay of the inter-satellite link also changes dynamically within one system cycle, defined as D. min This represents the minimum inter-satellite link propagation delay within the coupled constellation.

[0140] Step S333: Calculate the degree of interference from the space environment on inter-satellite communication.

[0141] The space environment interferes with satellite communications (mainly inter-satellite communications) in many ways, among which there are three main factors. This indicates the impact of the sun on inter-satellite links. When receivers at both ends of an inter-satellite link are facing or close to the sun, its radiation can cause strong background interference to the transmitted signal, affecting the quality of inter-satellite communication and even interrupting the link. This is especially true for inter-satellite communication using laser links, where this radiation can physically damage optoelectronic sensors, leading to link interruption. This phenomenon is called "solar interference." Solar interference is an issue that cannot be ignored when designing inter-satellite links and satellite routing. The degree of impact of solar interference on inter-satellite communication can be expressed by the duration t of the solar interference. sun To measure.

[0142] This describes the impact of Earth's obstruction on satellite communications. When Earth blocks sunlight during a satellite's movement, placing the satellite in Earth's shadow, it loses solar energy and relies solely on its onboard photovoltaic cells for power; this phenomenon is called a stellar eclipse. During a stellar eclipse, the satellite's full-load operation will inevitably cause communication interruptions, a factor that cannot be ignored when designing inter-satellite links. Furthermore, various cosmic rays in space also affect satellite communication channels; the longer the inter-satellite link, the greater this impact, and consequently, the higher the bit error rate. This is used to represent the impact of the link bit error rate on communication quality. It is the distance between the satellite and the Earth, r(S) j →S i A function of t).

[0143] The degree of interference P of the space environment on inter-satellite communication SI It can be represented as:

[0144]

[0145] in, The influence of the Sun on inter-satellite links is expressed by the duration t of the solar transit. sun To measure; This indicates the impact of Earth's obstruction on satellite communications; The values ​​e1, e2, and e3 represent the impact of inter-satellite link bit error rate on communication quality. For P SI The contribution factors are e1≤0, e2≤0, e3≤0;

[0146] Step S334: Based on the calculated inter-satellite link survival time, inter-satellite link propagation delay, and the degree of interference from the space environment on inter-satellite communication, perform inter-satellite link stability calculations:

[0147] Inter-satellite link (ISL) at time t A→B The formula for calculating the inter-satellite link stability parameter P(A→B, t) is:

[0148]

[0149] Among them, D ISL，min To minimize the inter-satellite link propagation delay of the system, T ISL，max w is the maximum inter-satellite link survival time within the coupled constellation. d w is the weighting coefficient for inter-satellite link propagation delay. l w is the weighting factor for the remaining lifetime of inter-satellite links. s is the spatial interference weighting coefficient, and w d +w l +w s =1.

[0150] Step S4: Calculate the inter-satellite link anti-interference capability index based on the obtained coupled constellation collaborative guidance mission parameters;

[0151] The Inter-Satellite Link Network Anti-Interference Capability Analysis and Calculation is responsible for calculating the inter-satellite link network establishment capability and analyzing indicators such as anti-interference capability.

[0152] Step S4 specifically includes:

[0153] Step S41: Calculate the anti-interference capability of a single satellite using the receiver bit error rate and the average availability of the link time.

[0154] Single-satellite anti-interference capability is the foundation of overall network anti-interference capability; the better the single-satellite anti-interference performance, the better the overall network anti-interference capability. Single-satellite anti-interference capability mainly refers to the receiving characteristics of the satellite receiving link, including the anti-interference capability of the spread spectrum signal system itself and the anti-interference performance improvement brought about by spatial / frequency / time-domain anti-interference technologies. Apart from the maximum interference tolerance, for communication, the single-satellite anti-interference capability index mainly refers to the bit error rate performance after anti-interference.

[0155] The anti-interference capability of a single satellite is defined by two indicators: the receiver bit error rate (BER) and the link time average availability. The receiver bit error rate refers to the proportion of erroneously received symbols to the total number of transmitted symbols. More precisely, the bit error rate is the probability that symbols are transmitted incorrectly in the transmission system.

[0156] In step S41, the formula for calculating the bit error rate at the receiving end is:

[0157]

[0158] or

[0159]

[0160] Where r is the signal-to-noise ratio at the receiver. M is the number of phases of phase shift keying; Equation (1) is the statistical value obtained by direct statistics; Equation (2) is the calculated value obtained by measurement or configuration; when the number of statistics is large enough, the results of the two should be similar. If direct statistics can be obtained, Equation (1) is used. If statistics cannot be obtained, the corresponding measurement or configuration value in Equation (2) can be used for calculation.

[0161] The formula for calculating the average availability of the link time is as follows:

[0162] r AB =T2 / T1

[0163] Where, r AB r represents the average availability of the link between satellite A and satellite B. AB ∈[0,1]; T1 is the inter-satellite link (ISL). A→B Normal link establishment time under interference-free conditions, T2 is the inter-satellite link ISL. A→B The normal time for the disrupted chain establishment process.

[0164] For inter-satellite link networks, the average availability of a single link represents the availability of link establishment between network node pairs within a specific time period, and is a probabilistic indicator. Link availability is a probabilistic indicator with a maximum value of 1 (fully available, working normally at full capacity) and a minimum value of 0 (corresponding to a complete inability to establish a link between two nodes).

[0165] Step S42: Calculate the overall network's anti-interference capability.

[0166] In step S42, the overall anti-interference capability of inter-satellite links is defined by the average availability R of the entire network. The calculation of the overall network anti-interference capability specifically includes:

[0167] The availability matrix of the inter-satellite link network G(N,E) under a specific interference scenario and within a statistical time T, at time t, is as follows:

[0168]

[0169] Where, r AB Let R be the average availability of connectivity between satellite A and satellite B in the inter-satellite link network G(N,E) at time t, and R be a symmetric matrix.

[0170] The average availability of the entire network under the specific interference scenario is then expressed as:

[0171]

[0172] Define X interference test scenarios. Using the Monte Carlo method, perform Monte Carlo tests on the average availability of the entire network under specific interference scenarios to obtain the average availability of the entire network across all interference test scenarios. This average availability is defined as the probability average of the average availability of the entire network under each scenario. Then:

[0173]

[0174] Where R is the average availability of the entire network under traversal interference scenarios; R x This represents the average availability of the entire network under the xth interference scenario.

[0175] Step S5: Based on the calculated inter-satellite link establishment time, inter-satellite link stability, and inter-satellite link anti-interference capability indicators, conduct a cooperative guidance success rate analysis for coupled constellations.

[0176] The inter-satellite link establishment time T, the inter-satellite link stability parameter P(A→B, t), and the average availability rate of the entire inter-satellite link network R are compared with the set threshold values. If all three parameters reach the threshold values, it indicates that the collaborative guidance is successful; otherwise, it indicates that the collaborative guidance has failed.

[0177] Step S6: Display the success rate analysis results of the coordinated guidance for coupled constellations. The display format includes two-dimensional maps and data charts.

[0178] It should be noted that, in this document, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or terminal device that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or terminal device. Unless otherwise specified, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or terminal device that includes said element.

[0179] Finally, it should be noted that the above description represents a preferred embodiment of the present invention. It should be pointed out that although preferred embodiments have been described, those skilled in the art, once they understand the basic inventive concept of the present invention, can make various improvements and modifications without departing from the principles described herein. These improvements and modifications should also be considered within the scope of protection of the present invention. Therefore, the appended claims are intended to be interpreted as including both the preferred embodiments and all changes and modifications falling within the scope of the embodiments of the present invention.

Claims

1. A method for analyzing the success rate of collaborative guidance in coupled constellations, characterized in that, Includes the following steps: Step S1: Obtain the parameters of the coupled constellation collaborative guidance task; Step S2: Calculate the inter-satellite link establishment time index based on the obtained coupled constellation collaborative guidance mission parameters; Step S3: Calculate the inter-satellite link stability index based on the obtained coupled constellation collaborative guidance mission parameters; Step S4: Calculate the inter-satellite link anti-interference capability index based on the obtained coupled constellation collaborative guidance mission parameters; Step S5: Based on the calculated inter-satellite link establishment time index, inter-satellite link stability index, and inter-satellite link anti-interference capability index, conduct a cooperative guidance success rate analysis for coupled constellations. Step S3 specifically includes: Step S31: Calculate the relative positions of the satellites within the coupled constellation; Step S32: Obtain channel quality parameters between satellites, including signal strength; Step S33: Use a mathematical model to calculate the stability index of the inter-satellite link; Step S33 specifically includes: Step S331: Calculate the inter-satellite link survival time; Step S332: Calculate the inter-satellite link propagation delay; Step S333: Calculate the degree of interference of the space environment on inter-satellite communication; Step S334: Based on the calculated inter-satellite link survival time, inter-satellite link propagation delay, and the degree of interference from the space environment on inter-satellite communication, perform inter-satellite link stability calculation.

2. The method for analyzing the success rate of cooperative guidance for coupled constellations according to claim 1, characterized in that, In step S1, the mission parameters include scenario parameters, satellite parameters, inter-satellite link parameters, ground target parameters, and collaborative mission parameters. The scene parameters include the start and end times of the scene; The satellite parameters include satellite ID, satellite type, orbit parameters, satellite name, satellite position, satellite Id, satellite EIRP, satellite orbit information, antenna power, quality factor G / T, antenna receiving gain G_RS, feeder loss L_FRS, equivalent noise temperature Ts, receiver threshold [C / N]th, saturated flux density SFD, and anti-interference quality factor. The satellite position includes the satellite's latitude, longitude, and altitude. The inter-satellite link parameters include transmission frequency band, transmission rate, transmission delay, interference frequency, interference power amplifier transmit power, interference antenna aperture, inter-satellite communication distance, effective information rate, information rate, operating frequency band, duplex mode, transmission content, star network topology diagram, and time aggregation diagram. The ground target parameters include target ID, target type, target location, and target observation requirements; The collaborative task parameters include task ID, task start time, task end time, and satellite working attitude.

3. The method for analyzing the success rate of cooperative guidance for coupled constellations according to claim 2, characterized in that, Step S2 specifically includes: Real-time monitoring and collection of key parameters at each stage of the network construction process, including timestamps, status, and results; Based on the collected data, link networking scheme, and optimized link information, calculate the inter-satellite link establishment time: The inter-satellite link establishment time is related to transmission delay and queuing delay; The formula for calculating the transmission delay on the possible inter-satellite link between satellite A and satellite B is as follows: in, It is the propagation delay of the i-th link in the possible inter-satellite links between satellite A and satellite B. It is the length of the i-th link. The speed of light represents the transmission rate of wireless or laser signals. Suppose there exists a packet that enters a given output queue buffer at time t, then the queuing delay of the i-th link is... The calculation formula is: in, The average length of the existing packets in the given output queue. For inter-planetary link bandwidth, At any moment The number of groups in the given output queue at that time; The routing update period for the i-th link is in Starting at time , the average expected queuing delay of packets within the route update interval is expressed as: in, Indicates the time step of the process; There may be an interplanetary link between satellite A and satellite B. The i-th link in Chain establishment time within the route update interval starting from a given moment The sum of transmission delay and queuing delay is expressed as: The inter-satellite link establishment time for the link network The establishment time of all links in the link network. sum: in, This represents the total number of links in the link network.

4. The method for analyzing the success rate of cooperative guidance for coupled constellations according to claim 1, characterized in that, The calculation of inter-satellite link survival time in step S331 includes: Assuming in Time Satellite Entering the satellite Within line-of-sight range, they establish inter-satellite links. ; and Time Satellite Will leave the satellite The line-of-sight range, at which time the inter-satellite link If the connection is lost, the inter-satellite link will be disconnected during this connection / disconnection process. Survival time From time At the time The duration, i.e.: in, N represents the number of satellites in a system cycle of the coupled constellation. With satellite The number of times the inter-satellite link will switch on and off; This represents the relative velocity of satellite A when it enters the line-of-sight range of satellite B. This represents the relative velocity of satellite A when it leaves the line-of-sight range of satellite B; Inter-satellite link at time t Remaining survival time Represented as: in, ; The calculation of inter-satellite link propagation delay in step S332 includes: At time t, the inter-satellite link The propagation delay is defined as: in, For satellite at time t With satellite The distance between; The speed of light; In step S333, calculating the degree of interference of the space environment on inter-satellite communication includes: The degree of interference from the space environment to inter-satellite communication It can be represented as: in, The duration of the solar transit indicates the Sun's influence on inter-satellite links. To measure; This indicates the impact of Earth's obstruction on satellite communications; This indicates the impact of inter-satellite link bit error rate on communication quality. , , They are respectively right Contribution factor ; In step S334, the inter-satellite link stability calculation is performed based on the calculated inter-satellite link survival time, inter-satellite link propagation delay, and the degree of interference from the space environment on inter-satellite communication. This includes: Inter-satellite link at time t Inter-satellite link stability parameters The calculation formula is: in, To minimize the inter-satellite link propagation delay within the coupled constellation, This represents the maximum inter-satellite link survival time within the coupled constellation. This is a weighting coefficient for the propagation delay of inter-satellite links. This is a weighting factor for the remaining lifetime of inter-satellite links. For spatial interference weighting coefficients, and .

5. The method for analyzing the success rate of cooperative guidance for coupled constellations according to claim 1, characterized in that, Step S4 specifically includes: Step S41: Calculate the anti-interference capability of a single satellite using the receiver bit error rate and the average availability of the link time. Step S42: Calculate the overall network's anti-interference capability.

6. The method for analyzing the success rate of cooperative guidance for coupled constellations according to claim 5, characterized in that, In step S41, the formula for calculating the bit error rate at the receiving end is: （1） or （2） in, The signal-to-noise ratio at the receiving end. ; The number of phases in phase shift keying; Equation (1) is a statistical value obtained through direct statistics; Equation (2) is a calculated value obtained through measurement or configuration. The formula for calculating the average availability of the link time is as follows: in, The average availability of the link between satellite A and satellite B. ∈[0,1]; T1 is an inter-satellite link Normal link establishment time under interference-free conditions, T2 is the inter-satellite link. The normal time for the disrupted chain establishment process.

7. The method for analyzing the success rate of cooperative guidance for coupled constellations according to claim 6, characterized in that, In step S42, the overall anti-interference capability of inter-satellite links is defined by the average availability R of the entire network. The calculation of the overall network anti-interference capability specifically includes: The availability matrix of the inter-satellite link network G(N,E) under a specific interference scenario and within a statistical time T, at time t, is as follows: in, For the node satellites in the inter-satellite link network G(N,E) at time t, the state is as follows: To satellite Average availability of connectivity between them It is a symmetric matrix; The average availability of the entire network under the specific interference scenario is then expressed as: definition For each interference test scenario, the Monte Carlo method is used to perform a Monte Carlo test on the average availability of the entire network under a specific interference scenario, thereby obtaining the average availability of the entire network across all interference test scenarios. This average availability is defined as the probability average of the average availability of the entire network under each scenario. Then: in, To iterate through the average availability of the entire network under interference scenarios; Indicates the first Average availability of the entire network under various interference scenarios.

8. The method for analyzing the success rate of cooperative guidance for coupled constellations according to claim 7, characterized in that, Step S5 specifically includes: The inter-satellite link establishment time T and inter-satellite link stability parameters were determined through calculation. The average availability R of the entire inter-satellite link network is compared with its corresponding threshold value. If all three parameters reach the threshold value, it indicates that the collaborative guidance is successful; otherwise, it indicates that the collaborative guidance has failed.

9. The method for analyzing the success rate of cooperative guidance for coupled constellations according to claim 1, characterized in that, Also includes: Step S6: Display the success rate analysis results of the coordinated guidance for coupled constellations. The display format includes two-dimensional maps and data charts.

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