Disclosure of Invention
The aim of the invention is to overcome the defects in the prior art, and provide a low-orbit satellite network beam-jumping resource scheduling method based on star group cooperation, so as to shorten response time, improve solution quality and meet the requirements of a multi-star overlapped scene.
In order to achieve the above object, the present invention provides a technical solution comprising:
1. a low orbit satellite network beam hopping resource scheduling method based on constellation cooperation comprises the following steps:
determining a cooperative constellation and coverage range thereof, performing wave position division on satellites in the constellation, and determining satellite parameters;
The service demand Q of the ground wave position is counted, and a backbone satellite and an auxiliary satellite are determined according to the running track of the satellite;
All auxiliary satellites transmit service requirements Q and wave position information to backbone satellites, the backbone satellites order according to service sizes, service is preferentially carried out on Gao Xuqiu wave positions, and service is carried out on low-requirement wave positions;
determining an active beam time slot matrix H for beam scheduling of the satellite in each time slot;
And the backbone satellite transmits the activated beam time slot matrix to the auxiliary satellite, calculates the service rate of each service rate to the ground user, and calculates and obtains the system capacity D according to the service rate.
Further, the determining the cooperative constellation and the coverage area thereof comprises determining backbone satellites and auxiliary satellites and the coverage areas thereof, wherein the backbone satellites and the auxiliary satellites lock the areas of the satellites through the positions of the satellites, the coverage radius of each satellite is a length circle, and the coverage area of each satellite is surrounded by the circle.
Further, the determining the backbone satellite and the auxiliary satellite according to the running track of the satellite is to determine the satellite in the central position of the satellite in the running track as the backbone satellite, and determine the satellites around the backbone satellite as the auxiliary satellite.
Further, the determining the active beam time slot matrix H includes the following steps:
7a) Creating a space activated beam time slot matrix H of M x T according to the number M of activated beams and the beam hopping period T;
7b) The backbone satellite searches for an unactivated wave position with the maximum service requirement in a first time slot and adds the unactivated wave position into an activated time slot matrix H;
7c) The backbone satellite searches for the next inactive wave bit with the largest service requirement, calculates the distance between the inactive wave bit and the wave bit in the active time slot matrix H, and judges whether the distance between the wave bits is larger than the beam isolation radius R:
if so, adding the wave bit into an active beam time slot matrix H;
Otherwise, continuing to search until all wave bits are traversed.
7D) If there are unassigned wave bits, they are inserted into the active beam slot matrix H.
2. A low orbit satellite network beam hopping resource scheduling system based on constellation cooperation comprises:
The cooperative partitioning module is used for determining cooperative constellation, coverage area and wave position partitioning;
The business statistics module is used for determining the business requirement Q of the ground wave position;
the master-slave architecture module is used for determining backbone satellites and auxiliary satellites;
The information transmission module is used for information transmission between the backbone satellite and the cooperative satellite;
the matrix calculation module is used for calculating an activated beam time slot matrix H by using a backbone satellite;
the service rate module is used for calculating a service rate C by the backbone satellite and the auxiliary satellite;
the effective service rate module is used for calculating an effective service rate V by the backbone satellite and the auxiliary satellite, namely taking smaller values of service requirements and service rates;
And the capacity calculation module is used for calculating the system capacity D by the backbone satellite and the auxiliary satellite. I.e. the effective service rates of the backbone satellite and the satellite assist are added.
Compared with the prior art, the invention has the following advantages:
With the increasing scale of satellite constellations, the traditional beam hopping resource allocation method has low execution efficiency due to long response time and does not consider the scene of multi-satellite coverage, and can not meet the requirement of high capacity of a satellite communication system. Aiming at the problem, the low-orbit satellite network beam-jumping resource scheduling method based on the cooperative constellation divides the cooperative constellation while considering a multi-satellite coverage scene, determines a backbone satellite and an auxiliary satellite, takes charge of overall calculation by the backbone satellite through information interaction between the backbone satellite and the auxiliary satellite, effectively shortens the response time of resource allocation, can meet the requirement of the multi-satellite overlapping scene, and simultaneously modularizes a scheduling system, improves the execution efficiency and effectively improves the capacity of the whole satellite communication system.
In order to make the above objects, features and advantages of the present invention more comprehensible, examples accompanied with figures are described in detail below.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings, and it is apparent that the described embodiments are some examples of the present invention, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The satellite communication network is mainly built by low orbit satellite constellations, has the advantages of wide coverage, low construction cost, high flexibility and the like, and has an irreplaceable importance in the 6G era. In order to provide broadband transmission and seamless coverage, the low-orbit satellite constellation needs to achieve multiple coverage. In addition, due to the non-uniformity of the geographic distribution of the ground users and the high mobility of the low-orbit satellites, the traffic demand in the area observed by the low-orbit satellites exhibits spatio-temporal non-uniformity. Meanwhile, in order to realize efficient spectrum utilization, a future low-orbit satellite communication system needs to adopt a mode of combining full-frequency multiplexing and beam hopping.
Embodiment 1, a low-orbit satellite network beam hopping resource scheduling method based on constellation cooperation.
Referring to fig. 1, the implementation steps of this example include the following:
and step 1, determining initial parameters and a cooperative star group.
In the existing low-orbit satellite system, due to the characteristics of small size and multiple coverage of the terminal, the terminal is more easily interfered by the adjacent low-orbit satellites. Therefore, in the multi-satellite coverage scene, not only the on-demand allocation of the beam resources of each satellite is considered, but also the anti-interference among satellites is reasonably designed to improve the capacity of the whole system. The larger the constellation size, the more serious the inter-satellite interference, and the more difficult it is to meet the high capacity requirement. To achieve the goal of global coverage, a large-scale constellation is still required. The constellation configuration mainly comprises the number of orbits, the number of satellites per orbit, the orbit height, the orbit inclination angle and the phase factor. By increasing the number of orbits and the number of satellites per orbit, a large-scale constellation configuration can be constructed.
As an example, the constellation configuration selected in the present invention is shown in table 1, and the number of orbits is 30, the number of satellites per orbit is 60, the orbit height is 508, the orbit inclination is 53, and the phase factor is 0.
Table 1 constellation configuration
| Parameters (parameters) | Low orbit satellite |
| Track height (km) | 508 |
| Track inclination angle | 53 |
| Constellation attributes | Inclined track constellation |
| Track number | 30 |
| Number of satellites per orbit | 60 |
| Phase factor | 0 |
In a practical scenario, the constellation configuration is mainly determined by the traffic demand.
In calculating the capacity of a low orbit satellite system, it is common to refer to satellite parameters such as number of wave bands, number of active beams, isolation radius, frequency of use, power, bandwidth, and cycle of beam hopping. As an example, the parameters selected in the present invention, as shown in table 2, include a wave position 475, a number of active beams 16, an isolation radius 80, a frequency of use 30, a power 500, a bandwidth 500, a beam hopping period 32, a noise decibel-174, a backbone satellite signal gain 100, and an auxiliary satellite signal gain 90.
TABLE 2 satellite parameters
| Parameters (parameters) | Low orbit satellite |
| Wave position | 475 |
| Number of active beams | 16 |
| Isolation radius (km) | 80 |
| Frequency of use (GHz) | 30 |
| Power (W) | 500 |
| Bandwidth (MHz) | 500 |
| Cycle of beam jump | 32 |
| Noise decibel | -174 |
| Backbone satellite signal gain | -132.66 |
| Auxiliary satellite signal gain | -130.01 |
In some examples, a cooperative constellation is generally divided by 9 satellites, including 1 backbone satellite and 8 auxiliary satellites, and the coverage radius is combined with the area where the satellites are located as the center, the coverage radius of each satellite is a length, and a circle is drawn, and the area surrounded by the circle is the coverage of the satellite.
And step 2, dividing the wave position and determining the service requirement.
2.1 Dividing the wave position:
The satellites in the constellation are divided into wave positions, including the longitude and latitude of the wave position, the number of wave positions,
Setting a wave bit as 475 according to the satellite parameters in table 2, and dividing the wave bit according to the wave bit by taking the area of the satellite as the center and taking the format of a cellular cell, namely a regular hexagon, wherein the center of the cellular cell is the longitude and latitude of the wave bit;
2.2 Service demand determination:
the service requirement is generated by a ground terminal, namely, a satellite collects the ground service requirement Q through a wide-area beam, and the size of the service requirement is determined through the size of the collected ground service.
The business requirements comprise working mail, data inquiry, network chat, voice video conference, uploading and downloading of files.
And 3, information interaction is carried out among satellites.
3.1 Determining backbone satellites and secondary satellites:
a satellite in a central position in the orbit is determined as a backbone satellite according to the orbit of the satellite,
Determining satellites around the backbone satellite as auxiliary satellites;
According to the classification of the backbone satellite and the auxiliary satellite, the ground service requirement Q is divided into a service requirement Q1 and a service requirement Q2, and the service requirements Q1 and the service requirement Q2 correspond to the results collected by the backbone satellite and the auxiliary satellite respectively;
3.2 Backbone satellite and auxiliary satellite information interactions:
The auxiliary satellite transmits the service requirement and wave position information to the backbone satellite through an inter-satellite link;
The backbone satellite sorts the acquired wave positions, and preferentially serves the wave positions with high service demands and serves the wave positions with low service demands.
And 4, calculating an activated beam time slot matrix H.
Referring to fig. 2, the present step includes:
4.1 The backbone satellite creates a space-activated beam time slot matrix H of M x T according to two satellite parameters of the activated beam number M and the beam hopping period T in the table 2;
4.2 Searching an unactivated wave position with the maximum service requirement in the first time slot by the backbone satellite, and adding the unactivated wave position into an activated wave beam time slot matrix H;
4.3 The backbone satellite searches for the next inactive wave bit with the largest service requirement, and calculates the distance d between the backbone satellite and the wave bit in the active wave beam time slot matrix H according to a formula between two points:
Where x1 is the abscissa of wave position 1, y1 is the ordinate of wave position 1, x2 is the abscissa of wave position 2, and y2 is the ordinate of wave position 2;
4.4 Judging whether the distance d between the wave bits is larger than the beam isolation radius R:
if the number of the selected wave beams is larger than the upper limit of the number of the wave beams, adding wave bits into an activated time slot matrix H;
Otherwise, continuing to search until all wave bits are traversed, if unassigned wave bits exist, inserting the unassigned wave bits into the active beam time slot matrix H, and completing the calculation of the active beam time slot matrix H.
And 5, calculating the satellite service rate.
5.1 The backbone satellite calculates the signal power S1 of the backbone satellite from the power W and the backbone satellite signal gain Sat1 in table 2:
S1＝W*10Sat1/10;
5.2 The auxiliary satellite calculates the signal power S2 of the auxiliary satellite according to the power W and the auxiliary satellite signal gain Sat2 in table 2:
S2＝W*10Sat2/10;
5.3 Backbone satellite and secondary satellite calculate gaussian noise power N1 and N2, respectively, from the channel bandwidth B, noise decibels J in table 2:
N1＝N2＝N＝(B*106)*(10J/10)/103;
5.4 The backbone satellite and the satellite calculates the service rates C1 and C2, respectively, for the terrestrial users based on the channel bandwidths B in table 2:
C1＝B log2(1+S1/N)
C2＝R log2(1+S2/N)。
and 6, calculating the capacity of the low-orbit satellite according to the service rate.
6.1 The service rates C1 and C2 of the backbone satellite and the auxiliary satellite to the ground users are compared with the service demands Q1 and Q2 respectively, the minimum value between the service rates C1 and C2 is taken, and the effective service rates V1 and V2 are obtained:
V1＝min(C1,Q1)
V2＝min(C2,Q2)
Wherein, V1 is the effective service rate of the backbone satellite, V2 is the effective service rate of the auxiliary satellite, Q1 is the service requirement of the backbone satellite, and Q2 is the service requirement of the auxiliary satellite;
6.2 Adding the effective service rates of the backbone satellite and the service satellite to obtain a low-orbit satellite capacity D:
D=V1+V2。
Embodiment 2a low orbit satellite network beam hopping resource scheduling system based on constellation cooperation.
Referring to fig. 3, the present example includes a cooperative partitioning module 1, a traffic statistics module 2, a master-slave architecture module 3, an information transmission module 4, a matrix calculation module 5, a service rate module 6, an effective service rate module 7, and a capacity calculation module 8, wherein:
the cooperative partitioning module 1 is used for determining cooperative constellation, coverage area and wave position partitioning, providing basic data for the subsequent service statistics module 2, and defining the statistical range;
The service statistics module 2 determines the service requirement Q of the ground wave position according to the statistical range of the collaborative dividing module 1 and provides service requirement data for the effective service rate calculation module 7;
the master-slave architecture module 3 is used for determining backbone satellites and auxiliary satellites and providing positions of the backbone satellites and the auxiliary satellites for the information transmission module 4;
The information transmission module 4 is used for transmitting information between the backbone satellite and the cooperative satellite according to the positions of the backbone satellite and the auxiliary satellite provided by the master-slave architecture module 3, so that timely and accurate transmission of the information among the satellites is ensured, and data transmission service is provided for the matrix calculation module 5;
The matrix calculation module 5 calculates an activated beam time slot matrix H according to the data transmission service provided by the information transmission module 4, optimizes signal transmission and resource utilization, and provides the activated beam time slot matrix H for the service rate module 6;
The service rate module 6 calculates service rates according to the activated beam time slot matrix H provided by the matrix calculation module 5, provides a quantization basis for service availability and quality, and provides service rate data for the effective service rate module;
the effective service rate module 7 calculates effective service rate according to the service demand data provided by the service statistics module 2 and the service rate provided by the service rate module 6, ensures that the supply meets the actual demand, and provides effective service rate data for the capacity calculation module 8;
the capacity calculation module 8 calculates the system capacity according to the effective service rate, backbone satellite and auxiliary satellite provided by the service rate module 7, and evaluates the overall processing capacity of the system, so as to ensure that the system can meet the requirements of all users;
the modules are interrelated and interdependent to each other to form an efficient and flexible satellite communication architecture. By optimizing and cooperating each module, the performance and coverage capability of the system can be significantly improved.
The effects of the present invention can be further illustrated by the following simulation results,
Simulation conditions
The number of orbits is 30, the number of satellites per orbit is 60, the orbit height is 508, the orbit dip is 53, the phase factor is 0, the wave position is 475, the number of active beams is 16, the isolation radius is 80, the use frequency is 30, the power is 500, the bandwidth is 500, the beam jumping period is 32, the noise decibel is-174, the backbone satellite signal gain is-132.66, and the auxiliary satellite signal gain is-130.01.
Second, simulation content
Under the simulation condition, the invention and the existing service are used as three resource scheduling methods of guiding, random scheduling and polling method to schedule the low-orbit satellite network beam hopping resource respectively, and the result is shown in figure 4.
As can be seen from fig. 4, the system capacity of the present invention is higher than that of the existing three methods, and the average improvement is 30%. Meanwhile, the response time is lower, the execution efficiency is high, and the method is more suitable for satellite communication networks in large-scale constellations.
The foregoing embodiments are merely for illustrating the technical solution of the present invention, but not for limiting the same, and although the present invention has been described in detail with reference to the foregoing examples, it will be understood by those skilled in the art that modifications may be made to the technical solution described in the foregoing embodiments, or equivalents may be substituted for some or all of the technical features thereof, without departing from the spirit of the corresponding technical solution from the scope of the technical solution of the embodiments of the present invention.
It should be noted that, the step numbers in the description and the claims of the present invention are only for the purpose of clearly describing the embodiments of the present invention, so that it is convenient to understand that the sequence of the numbers is not limited.