CN113726401A - Satellite constellation reliability assessment method based on satellite survivability and link survivability - Google Patents

Satellite constellation reliability assessment method based on satellite survivability and link survivability Download PDF

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CN113726401A
CN113726401A CN202110574790.4A CN202110574790A CN113726401A CN 113726401 A CN113726401 A CN 113726401A CN 202110574790 A CN202110574790 A CN 202110574790A CN 113726401 A CN113726401 A CN 113726401A
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satellite
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survivability
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interference
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CN113726401B (en
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戴翠琴
张明健
雷继兆
张瑜
谢颖
杨洋
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Chongqing University of Post and Telecommunications
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Abstract

The invention requests to protect a satellite constellation reliability evaluation method based on satellite survivability and link survivability, and belongs to the technical field of wireless communication. The method divides satellite constellation reliability into satellite survivability and link survivability. The survivability of the satellite is represented through anti-interference performance, anti-intrusion performance and durability, the anti-interference performance is quantified according to anti-interference factors, the anti-intrusion performance is evaluated according to the distance of an intercepted intrusion signal, and the durability is defined according to the service life loss rate of a satellite battery; and characterizing the link survivability through connectivity and robustness, quantizing the connectivity according to the natural connectivity, and calculating the robustness according to a set link budget threshold. Evaluating the survivability of the satellite by adopting a greedy algorithm under the limitation of the power consumption of the satellite by calculating an anti-interference factor, an interception distance and a battery loss rate; evaluating the link survivability by adopting a genetic algorithm under the link loss limit through calculating the natural connectivity and the link budget; on the basis, quantitative evaluation of satellite constellation reliability is achieved by adopting a tabu search algorithm.

Description

Satellite constellation reliability assessment method based on satellite survivability and link survivability
Technical Field
The invention belongs to the technical field of wireless communication. In particular to a satellite constellation reliability assessment method based on satellite survivability and link survivability.
Background
An Ocean-oriented Satellite Internet of Things (OSIoT) is a multifunctional network architecture that integrates Satellite constellations and Ocean IoT devices to achieve positioning, communication, and navigation. The satellite constellation is used to enable continuous observation of marine information due to its all-weather and large-coverage communications capability. However, mobile marine equipment and the variable marine environment in the osilot result in unstable offshore nodes and intermittent communication links. Meanwhile, the reliability of satellite observation information is influenced by the time-varying nodes and links. In order to better ensure the timeliness and safety of information, the reliability of satellite constellations is a great concern. Generally, the evaluation of the reliability of a satellite constellation can be evaluated in terms of both satellite performance and link status.
Satellite performance refers to satellite survivability. Satellite survivability can be evaluated from the perspective of satellite interference immunity, intrusion resistance, durability, and the like. Optimization can be performed from both physical layer and network layer aspects for satellite interference immunity. With respect to satellite intrusion resistance, many studies have shown that the introduction of a unique intrusion-resistant system is an effective solution. For satellite durability, the method of power distribution to prolong the satellite life is mostly studied. However, considering only the survivability of the satellite nodes does not guarantee the reliability of the entire network.
Link status refers to link survivability. Link survivability consists mainly of both link connectivity and link robustness. For link connectivity, the conventional concept is to use it as a precondition for satellite traffic transmission and guarantee or to ensure smooth transmission of multimedia traffic. For link robustness, link loss is considered as a threat to normal operation of the in-orbit satellite, and more links are operated as much as possible under the limit of link budget, so that link robustness is improved. The traditional satellite reliability and link reliability assessment only considers a single performance index at present, which leads to one-sidedness of the assessment.
In order to solve the one-sided problem of reliability evaluation, the invention provides a satellite constellation evaluation scheme based on reliability to quantify the indexes. Determining a view field range of a target node by establishing a ground observation target node, and randomly capturing satellite nodes and links in a certain view field range; dividing the survivability of the satellite into satellite anti-interference performance, satellite anti-intrusion performance and satellite durability; dividing link survivability into link connectivity and link robustness; and sequentially acquiring and evaluating parameters of each index. Finally, a reliability evaluation algorithm is provided, and the reliability of the satellite constellation is quantitatively evaluated. Therefore, evaluation indexes of all aspects of the satellite constellation can be clearly and quantitatively obtained, and a unique reliability evaluation result can be generated in a key way by a method for setting a weight.
Disclosure of Invention
The present invention is directed to solving the above problems of the prior art. A satellite constellation reliability assessment method based on satellite survivability and link survivability is provided. The technical scheme of the invention is as follows:
a satellite constellation reliability assessment method based on satellite survivability and link survivability is characterized by firstly establishing a ground observation target node, determining a view field range of the target node, and arbitrarily capturing a satellite node and a link in a certain view field range, and comprises the following steps:
101. calculating the survivability S of the satellite in the field of view of the target node; converting an optimization target of the satellite survivability S into an anti-interference I, an anti-intrusion D and a durability U utility function, namely; quantifying the anti-interference performance according to the set anti-interference factor; evaluating the intrusion resistance according to the distance of the interception machine intercepting the intrusion signal; defining durability according to the service life loss rate of the satellite battery;
102. calculating the link survivability L in the field of view of the target node; converting an optimization target of the link survivability L into a link connectivity C and link robustness B utility function, namely evaluating the link connectivity through natural connectivity; calculating link robustness by setting a link budget threshold;
103. finally, a reliability evaluation algorithm is provided for quantitatively evaluating the reliability of the satellite constellation.
Further, the step 101 specifically includes the following steps:
(1) evaluating the anti-interference performance of the satellite by using a utility function 1;
utility function 1: satellite anti-interference refers to the processing capacity of a useful signal when a target satellite is influenced by an irrelevant interference signal; the interference resistance factor I is used for evaluating the satellite interference resistance:
Figure RE-GDA0003295970600000021
wherein the content of the first and second substances,
Figure RE-GDA0003295970600000031
representing the average interfering signal transmit power;
Figure RE-GDA0003295970600000032
refers to average interference signal antenna gain;
Figure RE-GDA0003295970600000033
is the average of the antenna gain of the satellite receiving antenna in the direction of the interfering signal;
Figure RE-GDA0003295970600000034
represents the average distance of the interfering signal source to the satellite;
Figure RE-GDA0003295970600000035
average bandwidth for the interference signal; p0Is the useful signal source transmit power; gt0Representing useful signal transmitting antenna gain; gr0Represents the gain of the satellite receiving antenna in the direction of the useful signal; h is0Representing the distance of the useful signal source to the satellite; b is0Representing a useful signal bandwidth; gamma represents the polarization mismatch loss of the interference signal and the useful signal receiving antenna;
the utility function 1 can be used for obtaining the interference signal, and the larger the proportion of the interference signal received by the satellite receiver is, the smaller the anti-interference factor of the satellite is; when the interference signal is larger than the useful signal, the anti-interference performance of the satellite is a negative value;
(2) evaluating the satellite intrusion resistance by using a utility function 2;
utility function 2: the anti-intrusion performance refers to the signal interception and capture capacity of a satellite when the satellite receives a malicious intrusion signal, the malicious signal interception and capture capacity of the satellite is related to an interception and capture distance and an interception and capture probability, and the interception and capture distance D and the interception and capture probability omega are used for evaluating the satellite anti-intrusion performance D:
Figure RE-GDA0003295970600000036
wherein the content of the first and second substances,
Figure RE-GDA0003295970600000037
to the theoretical mean intercept distance, duserFor the user's desired distance, PiTransmitting power for the intrusion signal, GtiTransmitting antenna gain for the intrusion signal, GriGain of receiving antenna for intruding signal, f signal wavelength, L0The sum of various losses is obtained, and omega is the interception probability of the interception machine;
Figure RE-GDA0003295970600000038
where k is the Boltzmann constant, T is the thermal noise temperature of the interceptor, N0Is the jammer noise figure, B0 is the jammer effective signal bandwidth,
Figure RE-GDA0003295970600000039
is the signal-to-noise ratio of the interceptor; according to the utility function 2, the larger the interception distance is, the more remote the intrusion signal can be intercepted, and the better the intrusion resistance of the satellite is;
(3) evaluating the durability of the satellite by using a utility function 3;
utility function 3: satellite launch early durability Uearly(t) durability in operation Umid(t) and late durability Ulast(t) the durability of the satellite in the operation period is jointly determined, and if the satellite fails in any period, the satellite can stop operating;
U＝Uearly(t)·Umid(t)·Ulast(t) (4)
wherein early durability is determined by early firing failure rate
Figure RE-GDA0003295970600000041
Determining that the satellite operation accidental fault rate is too small to be ignored, and determining that
Umid(t)＝1， (5)
Figure RE-GDA0003295970600000042
Figure RE-GDA0003295970600000043
Where μ is the loss time mean and σ is the loss failure time standard deviation.
Further, the step 102 defines and calculates link survivability, which includes link connectivity and link robustness, and specifically includes the following steps:
(1) evaluating the connectivity of the satellite-ground link and the inter-satellite link by using utility functions 4 and 5;
calculating connectivity conditions of the ISL and the SGL through a geometric model, wherein S1 and S2 are satellites, E is the position of a ground station or a ground area central point, and A is a satellite subsatellite point coordinate; h is the satellite orbit height, r is the earth orbit radius, and d is the satellite-ground distance; alpha is the half view angle of the satellite, theta is the half geocentric angle,
Figure RE-GDA0003295970600000044
is the user elevation angle, omega is the earth center angle between satellites, he is the ISL minimum clearance;
utility function 4: if the ground user coordinates are known
Figure RE-GDA0003295970600000045
Coordinate of point under satellite
Figure RE-GDA0003295970600000046
Angle theta between the star and the groundEA；
Figure RE-GDA0003295970600000047
Figure RE-GDA0003295970600000048
Then the satellite-ground link connectivity condition is obtained
Figure RE-GDA0003295970600000049
Utility function 5: if the satellite S is known1Longitude and latitude coordinates of
Figure RE-GDA00032959706000000410
And satellite S2Longitude and latitude coordinates of
Figure RE-GDA00032959706000000411
The maximum inter-satellite geocentric angle omega can be obtainedmaxRelation with actual inter-satellite geocentric angle omega
Figure RE-GDA0003295970600000051
Figure RE-GDA0003295970600000052
Then the inter-satellite link connectivity condition can be obtained
Figure RE-GDA0003295970600000053
According to the satellite number N in the ground field angle rangesatThe maximum connectivity C can be calculatedmax；
(2) Evaluating the robustness of the link by using a utility function 6;
utility function 6: link robustness is related to the power of the transmit section, antenna gain, and various losses and interference, and the link robustness B evaluation formula is as follows:
Figure RE-GDA0003295970600000054
wherein, (C/N)userSetting a link budget threshold for a user, wherein C/N is a link budget:
Figure RE-GDA0003295970600000055
wherein k is Boltzmann constant and is 1.38 × 10-23J/K＝-228.6dB·W/(K×Hz)，TpIs the equivalent noise temperature, B is the equivalent noise bandwidth of the receiving system, and N is the sum of the noise terms.
Further, the reliability evaluation algorithm of step 104 includes: carrying out level evaluation on each index in sequence, and distributing weight values to each index; setting the satellite constellation reliability as a total target; the survivability and the link survivability of the satellite are set as a criterion layer; anti-interference I, anti-intrusion D, durability U, link connectivity C and link robustness B are set as index layers; evaluating the survivability of the satellite by adopting a greedy algorithm under the limitation of the power consumption of the satellite by calculating an anti-interference factor, an interception distance and a battery loss rate; evaluating the link survivability by adopting a genetic algorithm under the link loss limit through calculating the natural connectivity and the link budget; quantitative evaluation of satellite constellation reliability is achieved by adopting a tabu search algorithm; and quantitatively evaluating the reliability R of the satellite constellation.
Further, in step 103, an analytic hierarchy process and a weighted overall evaluation formula are used, the survivability S and the link survivability L of the satellite are used as optimization target indexes, a constellation reliability evaluation model is established, and the reliability R of the satellite constellation is quantitatively evaluated, wherein the specific formula is as follows:
Max R＝λsS+λlL＝λs(λiI+λdD+λu U)+λl(λcC+λbB)， (16)
wherein:
λs+λl＝1， (17)
λi+λd+λu＝1， (18)
λc+λb＝1， (19)
Pbattery+Pantenna+Pcontrol≤Psum， (20)
Lfsl+Lcloud+Lrain+Lsnow+Lother≤Lsum (21)
wherein λ iss、λl、λi、λd、λu、λc、λbRespectively representing weights represented by respective evaluation indexes of satellite survivability, link survivability, satellite anti-interference performance, satellite anti-intrusion performance, satellite durability, link connectivity and link robustness. Pbattery、Pantenna、PcontrolRespectively represents the power consumption of a satellite battery, the power consumption of satellite antenna transmission and the power consumption of satellite attitude orbit control, PsumRepresenting the overall power consumption of the satellite. L isfsl、Lcloud、Lrain、Lsnow、LotherRepresenting free space loss, extreme weather loss (cloud, rain, snow loss), and other losses, respectively. L issumIndicating the total loss of the link
The objective function (16) quantifies satellite constellation reliability by weighting the indices as a whole. The constraint (17) is a weighting parameter for satellite survivability and link reliability; the limiting conditions (18) are weighting parameters for satellite anti-interference, satellite anti-intrusion and satellite durability; the constraint (19) is a weighting parameter for link connectivity and link robustness; the limiting condition (20) refers to that the power consumption of a battery, the power consumption of an antenna and the power consumption of attitude track control are not higher than the set total power consumption; the constraints (21) mean that free space losses, extreme weather losses, and other losses should not be greater than the set total losses.
Further, evaluating the survivability of the satellite by a greedy algorithm under the limit of the power consumption of the satellite; evaluating the link survivability by adopting a genetic algorithm under the link loss limit through calculating the natural connectivity and the link budget; the method adopts a tabu search algorithm to realize quantitative evaluation of satellite constellation reliability, and specifically comprises the following steps: firstly, importing ground and satellite nodes in a simulation scene so as to randomly generate an initial population; generating a topological structure of each time slot by taking a ground target node as a center; then, importing parameters of the reliability evaluation indexes to generate a neighborhood solution set; then, introducing a greedy algorithm and a genetic algorithm to generate maximum values of satellite survivability and link survivability as much as possible under limited satellite power consumption and link budget to obtain a repair solution and a candidate solution; and finally, updating a neighborhood table with link budget limit according to a tabu search algorithm, setting the satellite reliability as a characteristic value, updating a tabu table, and searching the optimal reliability value in the latest tabu table. On the basis, an optimal satellite constellation reliability evaluation result is finally generated.
The invention has the following advantages and beneficial effects:
the reliability evaluation scheme of the satellite constellation is provided by analyzing the actual conditions of unstable nodes and easy loss of links in the ocean-oriented satellite Internet of things (OSIoT), and the problem of the transmission reliability of the satellite constellation under extreme conditions, and combining the problem of the information transmission reliability of ocean Internet of things equipment in the China ocean field. The main innovation of the invention is to provide concepts and calculation formulas of satellite survivability and link survivability. Thereby comprehensively evaluating the reliability of the satellite constellation. In the existing research, the reliability of the constellation is mostly evaluated from the performance of a single node or the state of a link, and the evaluation result is relatively comprehensive and difficult to generate a useful evaluation result for the actual satellite constellation. The reliability assessment method proposed by the present invention is therefore not easily imaginable by the skilled person. Furthermore, according to the characteristics of Chinese ocean monitoring, the invention invents an overall reliability weighting formula and a targeted reliability evaluation intelligent algorithm, so that the invention has uniqueness and creativity. Due to the particularities and complexities of satellite survivability and link survivability, both satellite energy consumption and link loss of the satellite constellation make significant deviations in the evaluation of constellation reliability. The invention fully analyzes the states and parameters of each satellite node and the satellite-ground link, and develops a reliability evaluation algorithm to meet the difference of the reliability of the existing fixed satellite constellation to the real-time ground state. In the existing research, the research model set by the researcher is too ideal, and changeable limiting conditions under extreme scenes are not considered. Therefore, the invention has the characteristics of creativity and difficult realization in solution. Through a reliability evaluation algorithm, the reliability evaluation result of the satellite constellation is generated in real time by intelligently calculating the reliability performance of various satellites. The automatic evaluation of the reliability of the constellation is comprehensively and efficiently realized. The continuity and the reliability of the satellite constellation to the ground communication transmission are improved. Meanwhile, according to the actual geographic condition, the reliability index of the satellite constellation is better subjected to specialized evaluation.
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FIG. 1 is a graph of coverage performance analysis for a preferred embodiment of the present invention;
FIG. 2 is a schematic diagram of a reliability assessment intelligence algorithm;
FIG. 3 is a flowchart of the reliability evaluation algorithm-based evaluation of the present invention
Detailed Description
The technical solutions in the embodiments of the present invention will be described in detail and clearly with reference to the accompanying drawings. The described embodiments are only some of the embodiments of the present invention.
The technical scheme for solving the technical problems is as follows:
the technical scheme for solving the technical problems is as follows: a reliability-based satellite constellation evaluation scheme is proposed to de-quantify the above-mentioned indicators. The reliability evaluation scheme of the satellite constellation evaluates from two aspects of satellite survivability and link survivability. Wherein satellite survivability takes into account satellite interference immunity, intrusion resistance and durability; link survivability contains link connectivity and link budget. And then, a weighted summation formula is utilized to obtain a constellation reliability evaluation result containing satellite survivability and link survivability. Finally, an intelligent optimization algorithm for reliability assessment is designed to automatically generate optimal reliability assessment results. The method comprises the following specific steps:
and quantitatively evaluating the reliability R of the satellite constellation by using a weighted overall evaluation formula.
And providing a reliability evaluation algorithm to automatically generate an optimal satellite constellation reliability evaluation result.
The first step is as follows: the selected satellite covers the ground area, and ten, twenty or thirty ground target nodes with different numbers are set by using STK software. And determining the field of view range by the target node for the user elevation angle of the satellite.
The second step is that: and introducing a space-time diagram, and arbitrarily grabbing satellite nodes and links of a certain time slot. And counting the number of satellite nodes in the field of view of the target node, and the number of inter-satellite links and inter-satellite links. And establishing an evaluation model for the constellation reliability evaluation of the target node.
The third step: and importing actual satellite constellation specific parameters such as satellite orbit parameters, satellite transmitting power and the like. Satellite survivability S and link survivability L within the field of view of the target node are calculated using utility functions 1-6, respectively. In particular, the optimization goals of satellite survivability S are interference immunity I, intrusion immunity D, and durability U. The optimization goals of the link survivability L are link connectivity C and link robustness B. Calculating satellite anti-interference I by using a utility function 1; calculating satellite anti-intrusion property D by using the utility function 2; satellite endurance U is calculated using utility function 3. Calculating the connectivity of the inter-satellite link and the satellite-ground link by using the utility function 4-5; the robustness of the link is calculated using the utility function 6.
The fourth step: and carrying out weighted summation on each performance result obtained in the third step by using an overall weighted summation formula to obtain the evaluation results of the satellite survivability, the link survivability and the constellation reliability.
The fifth step: and by utilizing a reliability evaluation algorithm, limiting conditions of satellite energy consumption and link loss are added, and the reliability evaluation result is maximized in a targeted manner. Making it more practical.
Preferably, the third step defines and calculates satellite interference immunity, intrusion resistance, and durability, respectively. Including utility functions 1-3:
utility function 1: satellite interference immunity refers to the ability of a target satellite to process a desired signal when it is affected by an extraneous interfering signal. The interference immunity of a satellite is generally related to the satellite receiving antenna gain, the useful signal source transmitting antenna gain, and the interfering signal source transmitting antenna gain. The interference rejection factor is used to evaluate the satellite's interference rejection:
Figure RE-GDA0003295970600000091
utility function 2: the anti-intrusion property refers to the capability of a satellite for intercepting signals when the satellite receives malicious intrusion signals. The ability of a satellite to intercept malicious signals is typically related to the interception distance and the probability of interception. The intercept distance D and the intercept probability ω are used to evaluate the satellite intrusion resistance D:
Figure RE-GDA0003295970600000092
utility function 3: satellite durability is designed to quantify the actual operating life of a satellite based on early launch failures, operational occasional failures, and late loss failures. Satellite launch early durability Uearly(t) durability in operation Umid(t) and late durability Ulast(t) together determine the endurance of the satellite during its operating cycle. If a failure occurs during any one period, the satellite can cease operation.
U＝Uearly(t)·Umid(t)·Ulast(t) (4)
Preferably, the third step defines and calculates link connectivity and link robustness, respectively.
Including utility functions 4-6:
utility function 4: if the ground user coordinates are known
Figure RE-GDA0003295970600000101
Coordinate of point under satellite
Figure RE-GDA0003295970600000102
Angle theta between the star and the groundEA。
Figure RE-GDA0003295970600000103
Figure RE-GDA0003295970600000104
Then the satellite-ground link connectivity condition is obtained
Figure RE-GDA0003295970600000105
Utility function 5: if the satellite S is known1Longitude and latitude coordinates of
Figure RE-GDA0003295970600000106
And satellite S2Longitude and latitude coordinates of
Figure RE-GDA0003295970600000107
The maximum inter-satellite geocentric angle omega can be obtainedmaxRelation with actual inter-satellite geocentric angle omega
Figure RE-GDA0003295970600000108
Figure RE-GDA0003295970600000109
Then the inter-satellite link connectivity condition can be obtained
Figure RE-GDA00032959706000001010
Utility function 6: the link robustness is related to the power of the transmitting section, the antenna gain, and various losses and interferences, so to determine the link robustness, the factors of the receiving antenna gain, the noise performance, and the like of the receiving system must be considered at the same time, and the link robustness evaluation formula is as follows:
Figure RE-GDA00032959706000001011
preferably, the satellite survivability S and the link survivability L are used as optimization target indexes by applying a weighted overall evaluation formula, a constellation reliability evaluation model is established, and the reliability R of the satellite constellation is quantitatively evaluated, wherein the specific formula is as follows:
Max R＝λsS+λlL＝λs(λiI+λdD+λu U)+λl(λcC+λb B)， (16)
the concepts and models involved in the present disclosure are as follows:
1. network model
The main research scenario of the present invention is ocean oriented satellite internet of things (OSIoT). OSIoT includes terrestrial IoT and marine IoT. The terrestrial IoT device is primarily a communication means by a terrestrial cellular network and the secondary communication means is a constellation of communication satellites. The marine IoT uses the maritime satellite constellation as the primary means of communication. The OSIoT is composed of three layers, a spatial layer, a ground layer, and a user layer. The space layer mainly comprises a maritime satellite constellation and a communication satellite constellation, the ground layer mainly comprises a marine sensor and a land base station, and the user side mainly comprises marine IoT equipment (such as a ship, a buoy, a submarine and the like) and ground IoT equipment (such as a mobile phone, a computer, an automobile and the like). The ground IoT equipment can communicate through the ground base station, and the sea IoT equipment selects a satellite to communicate due to the complex sea environment and the long distance between the equipment. Assume that the communication satellite does not establish a connection with a marine IoT device.
2. The technical scheme of the invention is as follows:
the invention provides a reliability-based satellite constellation evaluation scheme which is proposed to de-quantify the indexes. First, one OSIoT model is constructed comprising a space segment, a ground segment, and a user segment. The dynamic network model of OSIoT is analyzed based on STG and problems are modeled to assess the reliability of the satellite constellation. Next, a reliability-based satellite constellation evaluation scheme is evaluated separately from both the satellite survivability and the link survivability. Wherein satellite survivability takes into account satellite interference immunity, intrusion resistance and durability; link survivability contains link connectivity and link budget. Meanwhile, an intelligent optimization algorithm for reliability evaluation is designed to automatically generate an optimal reliability evaluation result. Finally, several typical satellite constellations were introduced to verify the validity and utility of the proposed evaluation scheme.
3. An objective function:
Max R＝λsS+λlL＝λs(λiI+λdD+λuU)+λl(λcC+λbB) (16)
it should also be noted that the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.
The above examples are to be construed as merely illustrative and not limitative of the remainder of the disclosure. After reading the description of the invention, the skilled person can make various changes or modifications to the invention, and these equivalent changes and modifications also fall into the scope of the invention defined by the claims.

Claims (6)

1. A satellite constellation reliability assessment method based on satellite survivability and link survivability is characterized by comprising the following steps of:
101. calculating the survivability S of the satellite in the field of view of the target node; converting an optimization target of the satellite survivability S into an anti-interference I, an anti-intrusion D and a durability U utility function, namely; quantifying the anti-interference performance according to the set anti-interference factor; evaluating the intrusion resistance according to the distance of the interception machine intercepting the intrusion signal; defining durability according to the service life loss rate of the satellite battery;
102. calculating the link survivability L in the field of view of the target node; converting an optimization target of the link survivability L into a link connectivity C and link robustness B utility function, namely evaluating the link connectivity through natural connectivity; calculating link robustness by setting a link budget threshold;
103. finally, a reliability evaluation algorithm is provided for quantitatively evaluating the reliability of the satellite constellation.
2. The method for satellite constellation reliability assessment based on satellite survivability and link survivability according to claim 1, wherein the step 101 specifically comprises the steps of:
(1) evaluating the anti-interference performance of the satellite by using a utility function 1;
utility function 1: satellite anti-interference refers to the processing capacity of a useful signal when a target satellite is influenced by an irrelevant interference signal; the interference resistance factor I is used for evaluating the satellite interference resistance:
Figure RE-FDA0003199330860000011
wherein the content of the first and second substances,
Figure RE-FDA0003199330860000012
representing the average interfering signal transmit power;
Figure RE-FDA0003199330860000013
refers to average interference signal antenna gain;
Figure RE-FDA0003199330860000014
is the average of the antenna gain of the satellite receiving antenna in the direction of the interfering signal;
Figure RE-FDA0003199330860000015
represents the average distance of the interfering signal source to the satellite;
Figure RE-FDA0003199330860000016
average bandwidth for the interference signal; p0Is the useful signal source transmit power; gt0Representing useful signal transmitting antenna gain; gr0Represents the gain of the satellite receiving antenna in the direction of the useful signal; h is0Representing the distance of the useful signal source to the satellite; b is0Representing a useful signal bandwidth; gamma represents the polarization mismatch loss of the interference signal and the useful signal receiving antenna;
the utility function 1 can be used for obtaining the interference signal, and the larger the proportion of the interference signal received by the satellite receiver is, the smaller the anti-interference factor of the satellite is; when the interference signal is larger than the useful signal, the anti-interference performance of the satellite is a negative value;
(2) evaluating the satellite intrusion resistance by using a utility function 2;
utility function 2: the anti-intrusion performance refers to the signal interception and capture capacity of a satellite when the satellite receives a malicious intrusion signal, the malicious signal interception and capture capacity of the satellite is related to an interception and capture distance and an interception and capture probability, and the interception and capture distance D and the interception and capture probability omega are used for evaluating the satellite anti-intrusion performance D:
Figure RE-FDA0003199330860000021
wherein the content of the first and second substances,
Figure RE-FDA0003199330860000022
to the theoretical mean intercept distance, duserFor the user's desired distance, PiTransmitting power for the intrusion signal, GtiTransmitting antenna gain for the intrusion signal, GriGain of receiving antenna for intruding signal, f signal wavelength, L0The sum of various losses is obtained, and omega is the interception probability of the interception machine;
Figure RE-FDA0003199330860000023
where k is the Boltzmann constant, T is the thermal noise temperature of the interceptor, N0Is the jammer noise figure, B0 is the jammer effective signal bandwidth,
Figure RE-FDA0003199330860000024
is the signal-to-noise ratio of the interceptor; according to the utility function 2, the larger the interception distance is, the more remote the intrusion signal can be intercepted, and the better the intrusion resistance of the satellite is;
(3) evaluating the durability of the satellite by using a utility function 3;
utility function 3: satellite launch early durability Uearly(t) durability in operation Umid(t) and late durability Ulast(t) the durability of the satellite in the operation period is jointly determined, and if the satellite fails in any period, the satellite can stop operating;
U＝Uearly(t)·Umid(t)·Ulast(t) (4)
wherein early durability is determined by early firing failure rate
Figure RE-FDA0003199330860000025
Determining, satellitesThe accidental operation failure rate is overlooked, and then
Umid(t)＝1， (5)
Figure RE-FDA0003199330860000026
Figure RE-FDA0003199330860000031
Where μ is the loss time mean and σ is the loss failure time standard deviation.
3. The method for evaluating the reliability of a satellite constellation based on the survivability and the link survivability of the satellite according to claim 1, wherein the step 102 defines and calculates the link survivability, the link survivability includes link connectivity and link robustness, and specifically includes the following steps:
(1) evaluating the connectivity of the satellite-ground link and the inter-satellite link by using utility functions 4 and 5;
calculating connectivity conditions of the ISL and the SGL through a geometric model, wherein S1 and S2 are satellites, E is the position of a ground station or a ground area central point, and A is a satellite subsatellite point coordinate; h is the satellite orbit height, r is the earth orbit radius, and d is the satellite-ground distance; alpha is the half view angle of the satellite, theta is the half geocentric angle,
Figure RE-FDA0003199330860000032
is the user elevation angle, omega is the earth center angle between satellites, he is the ISL minimum clearance;
utility function 4: if the ground user coordinates are known
Figure RE-FDA0003199330860000033
Coordinate of point under satellite
Figure RE-FDA0003199330860000034
Angle between the star and the groundθEA；
Figure RE-FDA0003199330860000035
Figure RE-FDA0003199330860000036
Then the satellite-ground link connectivity condition is obtained
Figure RE-FDA0003199330860000037
Utility function 5: if the satellite S is known1Longitude and latitude coordinates of
Figure RE-FDA0003199330860000038
And satellite S2Longitude and latitude coordinates of
Figure RE-FDA0003199330860000039
The maximum inter-satellite geocentric angle omega can be obtainedmaxRelation with actual inter-satellite geocentric angle omega
Figure RE-FDA00031993308600000310
Figure RE-FDA00031993308600000311
Then the inter-satellite link connectivity condition can be obtained
Figure RE-FDA00031993308600000312
According to the satellite number N in the ground field angle rangesatThe maximum can be calculatedDegree of connectivity Cmax；
(2) Evaluating the robustness of the link by using a utility function 6;
utility function 6: link robustness is related to the power of the transmit section, antenna gain, and various losses and interference, and the link robustness B evaluation formula is as follows:
Figure RE-FDA0003199330860000041
wherein, (C/N)userSetting a link budget threshold for a user, wherein C/N is a link budget:
Figure RE-FDA0003199330860000042
wherein k is Boltzmann constant and is 1.38 × 10-23J/K＝-228.6dB·W/(K×Hz)，TpIs the equivalent noise temperature, B is the equivalent noise bandwidth of the receiving system, and N is the sum of the noise terms.
4. The method of claim 1, wherein the reliability assessment algorithm of step 103 comprises: carrying out level evaluation on each index in sequence, and distributing weight values to each index; setting the satellite constellation reliability as a total target; the survivability and the link survivability of the satellite are set as a criterion layer; anti-interference I, anti-intrusion D, durability U, link connectivity C and link robustness B are set as index layers; evaluating the survivability of the satellite by adopting a greedy algorithm under the limitation of the power consumption of the satellite by calculating an anti-interference factor, an interception distance and a battery loss rate; evaluating the link survivability by adopting a genetic algorithm under the link loss limit through calculating the natural connectivity and the link budget; quantitative evaluation of satellite constellation reliability is achieved by adopting a tabu search algorithm; and quantitatively evaluating the reliability R of the satellite constellation.
5. The satellite constellation reliability assessment method based on satellite survivability and link survivability according to claim 4, wherein in the step 103, an analytic hierarchy process and a weighted integral assessment formula are applied, the satellite survivability S and the link survivability L are used as optimization target indexes to establish a constellation reliability assessment model, and the reliability R of the satellite constellation is quantitatively assessed, and the specific formula is as follows:
Max R＝λsS+λlL＝λs(λiI+λdD+λuU)+λl(λcC+λbB)， (16)
wherein:
λs+λl＝1， (17)
λi+λd+λu＝1， (18)
λc+λb＝1， (19)
Pbattery+Pantenna+Pcontrol≤Psum， (20)
Lfsl+Lcloud+Lrain+Lsnow+Lother≤Lsum (21)
wherein λ iss、λl、λi、λd、λu、λc、λbRespectively representing weights represented by respective evaluation indexes of satellite survivability, link survivability, satellite anti-interference performance, satellite anti-intrusion performance, satellite durability, link connectivity and link robustness. Pbattery、Pantenna、PcontrolRespectively represents the power consumption of a satellite battery, the power consumption of satellite antenna transmission and the power consumption of satellite attitude orbit control, PsumRepresenting the overall power consumption of the satellite. L isfsl、Lcloud、Lrain、Lsnow、LotherRespectively representing free space loss, extreme weather loss (cloud, rain, snow loss), and other losses, LsumRepresents the link total loss;
the objective function (16) quantifies satellite constellation reliability by weighting the indices as a whole. The constraint (17) is a weighting parameter for satellite survivability and link reliability; the limiting conditions (18) are weighting parameters for satellite anti-interference, satellite anti-intrusion and satellite durability; the constraint (19) is a weighting parameter for link connectivity and link robustness; the limiting condition (20) refers to that the power consumption of a battery, the power consumption of an antenna and the power consumption of attitude track control are not higher than the set total power consumption; the constraints (21) mean that free space losses, extreme weather losses, and other losses should not be greater than the set total losses.
6. The satellite constellation reliability assessment method based on satellite survivability and link survivability of claim 5, wherein the satellite survivability is assessed by a greedy algorithm under the limit of satellite power consumption; evaluating the link survivability by adopting a genetic algorithm under the link loss limit through calculating the natural connectivity and the link budget; the method adopts a tabu search algorithm to realize quantitative evaluation of satellite constellation reliability, and specifically comprises the following steps: firstly, importing ground and satellite nodes in a simulation scene so as to randomly generate an initial population; generating a topological structure of each time slot by taking a ground target node as a center; then, importing parameters of the reliability evaluation indexes to generate a neighborhood solution set; then, introducing a greedy algorithm and a genetic algorithm to generate maximum values of satellite survivability and link survivability as much as possible under limited satellite power consumption and link budget to obtain a repair solution and a candidate solution; and finally, updating a neighborhood table with link budget limit according to a tabu search algorithm, setting the satellite reliability as a characteristic value, updating the tabu table, searching the optimal reliability value in the latest tabu table, and finally generating an optimal satellite constellation reliability evaluation result on the basis.
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