CN116248165A - Frequency compatible model calculation method and system suitable for NGSO satellite constellation - Google Patents
Frequency compatible model calculation method and system suitable for NGSO satellite constellation Download PDFInfo
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Abstract
The invention discloses a frequency compatible model calculation method suitable for NGSO satellite constellation, comprising the following steps: acquiring sampling information of an interference satellite system and a demand satellite system at a time sampling point, and calculating according to the sampling information to obtain an interference link and a demand link; and fusing the interference link and the demand link to obtain a possible interference path. The invention also provides a frequency compatible model computing system suitable for the NGSO satellite constellation. The invention can effectively solve the problems of large workload of the existing manual calculation, unnecessary calculation caused by mainstream software under the condition of small-scale constellation and incapability of calculating under the condition of large-scale constellation by pre-screening the interference model.
Description
Technical Field
The invention relates to the technical field of satellite network and frequency compatibility calculation, in particular to a frequency compatibility model calculation method and system suitable for NGSO satellite constellations.
Background
With the rapid development of science and technology and information, a phenomenon of sharing frequency bands occurs among a plurality of NGSO satellite constellation systems, communication equipment of the satellite systems can be interfered by signals in the same frequency band or near frequency bands sent by other satellite systems, and frequency compatibility among the NGSO satellite constellation systems needs to be analyzed, so that a frequency compatibility model among the NGSO satellite constellations is obtained.
The traditional frequency compatible model calculation method mainly adopts manual calculation. Currently, NGSO satellite constellation systems are developed more fully, the complexity and diversity of the systems have been developed to a new level, and the traditional manual calculation model has the following defects:
1. since the overall calculation cannot be performed from the system level, the accuracy and precision of the calculation cannot be ensured;
2. low orbit satellite systems are generally large, too many links need to be calculated, the links are time-varying, the calculation workload is huge, and the progress of work is seriously affected if manual calculation is performed.
Therefore, designers need an effective tool to simulate and analyze the frequency compatibility of the satellite communication system, especially the problem of the diversity of the satellite system, and the problem of the diversity of the satellite system is concerned.
The main mode adopted by the frequency simulation analysis software of the current mainstream is that after sampling time periods, the interference model (interference link, demand link and interference path) is comprehensively calculated at each time sampling point, and the following problems exist:
1. In the case of frequency compatibility between small-scale NGSO satellite constellations, there are only a few time sampling points with potential interference, the overall calculation of the interference model for the remaining time sampling points causes unnecessary waste of calculation resources,
2. under the condition that the number of nodes of the ultra-large scale NGSO constellation is excessive, the overall calculation of the interference model causes excessive calculation resources required by a single step, and the program is blocked and cannot execute the calculation.
Disclosure of Invention
The invention aims to provide a frequency compatible model calculation method and a system suitable for between NGSO satellite constellations, which can effectively solve the problems that the existing manual calculation workload is large, the main stream software causes unnecessary calculation under the condition of small-scale constellations, and the calculation cannot be performed under the condition of large-scale constellations
In order to solve the technical problems, the invention provides a frequency compatible model calculation method suitable for between NGSO satellite constellations, which comprises the following steps:
acquiring sampling information of an interference satellite system and a demand satellite system at a time sampling point; the sampling information of the interference satellite system comprises an input satellite orbit parameter of the interference satellite system, an input earth station motion model parameter of the interference satellite system, a link direction of the interference satellite system and a working limit of the interference satellite system; the sampling information of the required satellite system comprises required satellite system input satellite orbit parameters, required satellite system input earth station motion model parameters, required satellite system link direction and required satellite system work limit; the interference satellite system operation limit comprises an interference satellite system visual angle operation limit and an interference satellite system link operation limit; the required satellite system operation limit comprises a required interference satellite system visual angle operation limit and a required interference satellite system link operation limit;
According to the satellite orbit parameters input by the interference satellite system, calculating the space position of the satellite system, and generating a satellite node space matrix of the satellite system;
according to the parameters of the earth station motion model input by the interference satellite system, calculating the space position of the earth station of the satellite system, and generating an earth station node space matrix of the satellite system;
calculating a possible interference link according to a satellite node space matrix of a satellite system, an earth station node space matrix of the satellite system, an interference satellite system link direction and an interference satellite system visual angle work limit;
generating an interference link according to the possible interference link and the interference satellite system link work limit;
according to the satellite orbit parameters input by the demand satellite system, calculating the space position of the satellite of the demand satellite system, and generating a satellite node space matrix of the demand satellite system;
inputting the earth station motion model parameters according to the demand satellite system, calculating the space position of the earth station of the demand satellite system, and generating an earth station node space matrix of the demand satellite system;
calculating a possible required link according to a satellite node space matrix of the required satellite system, an earth station node space matrix of the required satellite system, a link direction of the required satellite system and a view angle operation limit of the required satellite system;
Generating a demand link according to the possible demand link and the demand satellite system link work limit;
and fusing the interference link and the demand link to obtain a possible interference path.
Preferably, the method for fusing the interference link and the demand link specifically comprises the following steps:
the transmitting node of the interference link and the receiving node of the demand link are used as the transmitting node and the receiving node of the possible interference path.
Preferably, the method further comprises the following steps:
the possible interference paths are screened.
Preferably, the method screens possible interference paths, and specifically comprises the following steps:
judging whether the working frequencies of a transmitting node and a receiving node of a possible interference path are overlapped or not; if the working frequencies of the transmitting node and the receiving node of the possible interference path are not overlapped, eliminating the possible interference path;
judging whether a transmitting node of a possible interference path is a satellite and whether the possible interference path is blocked by the earth; if the transmitting node of the possible interference path is a satellite and the possible interference path is blocked by the earth, eliminating the possible interference path.
Preferably, the possible interference link is calculated according to a satellite node space matrix of the satellite system, an earth station node space matrix of the satellite system, an interference satellite system link direction and an interference satellite system view angle operation limit, and the method specifically comprises the following steps:
Calculating parameters of a possible interference link between the ith satellite and the jth earth station:
a) Elevation angle theta of earth station I-ij The calculation formula is as follows:
b) Satellite field angle
The calculation formula is as follows:
c) Meets the maximum field angle of the satellite
And minimum elevation angle theta of earth station I-max Sampling time point set P of (a) I-ij The calculation formula is as follows:
wherein: h SI-i A satellite node space matrix for an ith satellite system of the interfering satellite system; h EI-j The space matrix of the earth station node of the j satellite system which is the interference satellite system is k, and k is the k time sampling point.
Preferably, the interference link is generated according to the possible interference link and the interference satellite system link operation limit, and specifically comprises the following steps:
the link working limit of the interference satellite system comprises the maximum link number EImax of a single satellite, the maximum link number SImax of a single earth station and a link working strategy; the link working strategy comprises a highest elevation angle strategy and a longest time keeping strategy;
judging whether the possible interference link of the time sampling point k contains an interference link of the time sampling point k-1 or not;
if the possible interference link of the time sampling point k does not contain the interference link of the time sampling point k-1, screening the possible interference link of the time sampling point k, wherein the number of the satellite connected earth stations does not exceed the maximum number of links of the single satellite EImax, and the number of the satellite connected earth stations does not exceed the maximum number of links of the single earth station SImax;
Selecting working elevation angle theta from all time sampling points I-i,j The minimum ak possible interference links are selected, and the number of the possible interference links of the time sampling point k, in which the number of the satellite connected earth stations does not exceed the maximum number of links of a single satellite EImax and the number of the satellite connected earth stations does not exceed the maximum number of links of the single earth station SImax.
Preferably, the possible demand link is calculated according to the satellite node space matrix of the demand satellite system, the earth station node space matrix of the demand satellite system, the link direction of the demand satellite system and the view angle operation limit of the demand satellite system, and the method specifically comprises the following steps:
calculating parameters of a possible demand link between the ith satellite and the jth earth station:
a) Requiring earth station elevation angle theta W-i,j The calculation formula is as follows:
b) Demand satellite field angle
The calculation formula is as follows:
c) Meeting the requirement of the maximum field angle of the satellite
And a minimum elevation angle theta of the required earth station W-max Sampling time point set P of (a) W-i,j The calculation formula is as follows:
wherein: h SW-i Satellite node space matrix for ith demand satellite system of demand satellite system, H EW-j The space matrix of earth station nodes of the j-th demand satellite system for the demand satellite system.
Preferably, the possible demand link is calculated according to the satellite node space matrix of the demand satellite system, the earth station node space matrix of the demand satellite system, the link direction of the demand satellite system and the view angle operation limit of the demand satellite system, and the method specifically comprises the following steps:
The link operation limit of the interference satellite system comprises the maximum number of links EWMax of a single satellite, the maximum number of links SWmax of a single earth station and a link operation strategy; the demand link working strategy comprises a demand highest elevation angle strategy and a demand longest time keeping strategy;
judging whether the possible demand link of the time sampling point k contains the possible demand link of the time sampling point k-1 or not;
if the possible requirement links of the time sampling point k do not contain the possible requirement links of the time sampling point k-1, screening the possible requirement links of the time sampling point k, wherein the number of the satellite connection earth stations does not exceed the maximum number of required single satellite links EWMax, and the number of the satellite connection earth stations does not exceed the maximum number of required single earth station links SWmax;
selecting working elevation angle theta from all time sampling points I-i,j And (3) selecting possible required links of time sampling points k, wherein the number of the possible required links is smaller than or equal to the maximum number of required links EWMax of a single satellite, and the number of the possible required links of time sampling points k, which are smaller than or equal to the maximum number of required links SWmax of the single satellite, are not larger than or equal to the number of the required links of the satellite.
Preferably, the input satellite orbit parameters include no later than the simulation start time T s Six orbits of each satellite in a WGS-84 coordinate system of the moment Ta, and the space positions are satellite node X-axis coordinates, Y-axis coordinates and Z-axis coordinates in the WGS-84 coordinate system; the parameters of the earth station input by the interference satellite system comprise a certain moment Tb which is not later than the simulation starting time Ts, longitude/latitude/altitude of each earth station under a WGS-84 coordinate system at the moment Tb and a motion model, and the spatial positions are X-axis coordinates, Y-axis coordinates and Z-axis coordinates under the WGS-84 coordinate system.
The link direction of the interference satellite system comprises ground-to-air and air-to-ground;
the interference satellite system view angle operation limit comprises a satellite maximum view angle
Minimum elevation angle theta of earth station I-max ；
In a preferred embodiment, the demand input satellite orbit parameters include: the space position is the X-axis coordinate, Y-axis coordinate and Z-axis coordinate of a satellite node under the WGS-84 coordinate system, wherein the number of orbits of each satellite under the WGS-84 coordinate system is not later than a certain moment Tc of the simulation starting time Ts;
the requiring satellite system to input earth station parameters includes: a certain time Td not later than the simulation start time Ts, longitude/latitude/altitude of each earth standing under a WGS-84 coordinate system of the time Td, and a motion model, wherein the spatial positions are an X-axis coordinate, a Y-axis coordinate and a Z-axis coordinate under the WGS-84 coordinate system;
The required satellite link direction comprises ground-to-air and air-to-ground;
the desired satellite system operational constraints include desired satellite maximum field angle
Requiring minimum elevation angle theta of earth station W-max 。
The invention also provides a frequency compatible model computing system suitable for the NGSO satellite constellation, which is suitable for the frequency compatible model computing method between the NGSO satellite constellations, and comprises the following steps:
the sampling module is used for acquiring sampling information of the interference satellite system and the demand satellite system at a time sampling point; the sampling information of the interference satellite system comprises an input satellite orbit parameter of the interference satellite system, an input earth station motion model parameter of the interference satellite system, a link direction of the interference satellite system and a working limit of the interference satellite system; the sampling information of the required satellite system comprises required satellite system input satellite orbit parameters, required satellite system input earth station motion model parameters, required satellite system link direction and required satellite system work limit; the interference satellite system operation limit comprises an interference satellite system visual angle operation limit and an interference satellite system link operation limit; the required satellite system operation limit comprises a required interference satellite system visual angle operation limit and a required interference satellite system link operation limit;
The first satellite matrix conversion module is used for calculating the space position of a satellite of the satellite system according to the satellite orbit parameters input by the interference satellite system and generating a satellite node space matrix of the satellite system;
the first earth station matrix conversion module is used for inputting earth station motion model parameters according to the interference satellite system, calculating the space position of an earth station of the satellite system and generating an earth station node space matrix of the satellite system;
the possible interference link calculation module is used for calculating a possible interference link according to a satellite node space matrix of a satellite system, an earth station node space matrix of the satellite system, an interference satellite system link direction and an interference satellite system visual angle operation limit;
the first screening module is used for generating an interference link according to the possible interference link and the interference satellite system link work limit;
the second satellite matrix conversion module is used for inputting satellite orbit parameters according to the required satellite system, calculating the space position of satellites of the required satellite system and generating a satellite node space matrix of the required satellite system;
the second earth station matrix conversion module is used for inputting earth station motion model parameters according to the required satellite system, calculating the space position of the earth station of the required satellite system and generating an earth station node space matrix of the required satellite system;
The possible demand link calculation module is used for calculating the possible demand link according to the satellite node space matrix of the demand satellite system, the earth station node space matrix of the demand satellite system, the link direction of the demand satellite system and the view angle work limit of the demand satellite system.
The second screening module is used for generating a demand link according to the possible demand link and the demand satellite system link work limit;
and the fusion module is used for fusing the interference link and the demand link to obtain a possible interference path.
Compared with the prior art, the invention has the beneficial effects that:
the invention provides a frequency compatible model calculation method suitable for NGSO satellite constellations, which can effectively solve the problems that the existing manual calculation workload is large, the main stream software causes unnecessary calculation under the condition of small-scale constellations, and the calculation cannot be performed under the condition of large-scale constellations by pre-screening an interference model.
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The following describes the embodiments of the present invention in further detail with reference to the accompanying drawings.
FIG. 1 is a schematic flow chart of a method for calculating a frequency compatible model between NGSO satellite constellations;
fig. 2 is a schematic diagram of a time sampling point determination scheme according to the present invention.
Detailed Description
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present invention. The present invention may be embodied in many other forms than those herein described, and those skilled in the art will readily appreciate that the present invention may be similarly embodied without departing from the spirit or essential characteristics thereof, and therefore the present invention is not limited to the specific embodiments disclosed below.
The terminology used in the one or more embodiments of the specification is for the purpose of describing particular embodiments only and is not intended to be limiting of the one or more embodiments of the specification. As used in this specification, one or more embodiments and the appended claims, the singular forms "a," "an," and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It should also be understood that the term "and/or" as used in one or more embodiments of the present specification refers to and encompasses any or all possible combinations of one or more of the associated listed items.
It should be understood that, although the terms first, second, etc. may be used in one or more embodiments of this specification to describe various information, these information should not be limited by these terms. These terms are only used to distinguish one type of information from another. For example, a first may also be referred to as a second, and similarly, a second may also be referred to as a first, without departing from the scope of one or more embodiments of the present description. The word "if" as used herein may be interpreted as "at … …" or "at … …" or "responsive to a determination", depending on the context.
The invention is described in further detail below with reference to fig. 1-2:
as shown in fig. 1, the present invention provides a method for calculating a frequency compatible model between NGSO satellite constellations, comprising the following steps:
determining a plurality of time sampling points, and acquiring sampling information of an interference satellite system and a demand satellite system at the time sampling points; the sampling information of the interference satellite system comprises an input satellite orbit parameter of the interference satellite system, an input earth station motion model parameter of the interference satellite system, a link direction of the interference satellite system and a working limit of the interference satellite system; the sampling information of the required satellite system comprises required satellite system input satellite orbit parameters, required satellite system input earth station motion model parameters, required satellite system link direction and required satellite system work limit; the interference satellite system operation limit comprises an interference satellite system visual angle operation limit and an interference satellite system link operation limit; the required satellite system operation limit comprises a required interference satellite system visual angle operation limit and a required interference satellite system link operation limit;
according to the satellite orbit parameters input by the interference satellite system, calculating the space position of the satellite system, and generating a satellite node space matrix of the satellite system;
According to the parameters of the earth station motion model input by the interference satellite system, calculating the space position of the earth station of the satellite system, and generating an earth station node space matrix of the satellite system;
and calculating possible interference links according to the satellite node space matrix of the satellite system, the earth station node space matrix of the satellite system, the link direction of the interference satellite system and the view angle operation limit of the interference satellite system.
Generating an interference link according to the possible interference link and the interference satellite system link work limit;
according to the satellite orbit parameters input by the demand satellite system, calculating the space position of the satellite of the demand satellite system, and generating a satellite node space matrix of the demand satellite system;
inputting the earth station motion model parameters according to the demand satellite system, calculating the space position of the earth station of the demand satellite system, and generating an earth station node space matrix of the demand satellite system;
and calculating possible required links according to the satellite node space matrix of the required satellite system, the earth station node space matrix of the required satellite system, the link direction of the required satellite system and the view angle operation limit of the required satellite system.
Generating a demand link according to the possible demand link and the demand satellite system link work limit;
And fusing the interference link and the demand link to obtain a possible interference path.
In this embodiment:
and independently calculating the node space position of the interference system by a matrix operation mode, generating a possible interference link set, and screening according to constellation related conditions to obtain the interference link set and the working frequency.
And independently calculating the node space position of the demand system in a matrix operation mode, generating a possible demand link list, and screening according to constellation related conditions to obtain a demand link set and working frequency.
And (3) independently comparing the interference link set with the demand link set to generate a possible interference path set, and screening through frequency and earth shielding to obtain the interference path set.
In a preferred embodiment, the method for fusing the interference link and the demand link specifically comprises the following steps:
the transmitting node of the interference link and the receiving node of the demand link are used as the transmitting node and the receiving node of the possible interference path.
Preferably, one embodiment further comprises the steps of:
the possible interference paths are screened.
In a preferred embodiment, the method screens possible interference paths, and specifically comprises the following steps:
judging whether the working frequencies of a transmitting node and a receiving node of a possible interference path are overlapped or not; if the working frequencies of the transmitting node and the receiving node of the possible interference path are not overlapped, eliminating the possible interference path;
Judging whether a transmitting node of a possible interference path is a satellite and whether the possible interference path is blocked by the earth; if the transmitting node of the possible interference path is a satellite and the possible interference path is blocked by the earth, eliminating the possible interference path.
In a preferred embodiment, the method calculates the possible interference link according to the satellite node space matrix of the satellite system, the earth station node space matrix of the satellite system, the link direction of the interference satellite system and the view angle operation limit of the interference satellite system, and specifically comprises the following steps:
calculating parameters of a possible interference link between the ith satellite and the jth earth station:
a) Elevation angle theta of earth station I-ij The calculation formula is as follows:
b) Satellite field angle
The calculation formula is as follows:
c) Meets the maximum field angle of the satellite
And minimum elevation angle theta of earth station I-max Sampling time point set P of (a) I-ij The calculation formula is as follows:
wherein: h SI-i A satellite node space matrix for an ith satellite system of the interfering satellite system; h EI-j The space matrix of the earth station node of the j satellite system which is the interference satellite system is k, and k is the k time sampling point.
In a preferred embodiment, the method generates the interference link according to the possible interference link and the interference satellite system link operation limit, and specifically comprises the following steps:
The link working limit of the interference satellite system comprises the maximum link number EImax of a single satellite, the maximum link number SImax of a single earth station and a link working strategy; the link working strategy comprises a highest elevation angle strategy and a longest time keeping strategy;
judging whether the possible interference link of the time sampling point k contains an interference link of the time sampling point k-1 or not;
if the possible interference link of the time sampling point k does not contain the interference link of the time sampling point k-1, screening the possible interference link of the time sampling point k, wherein the number of the satellite connected earth stations does not exceed the maximum number of links of the single satellite EImax, and the number of the satellite connected earth stations does not exceed the maximum number of links of the single earth station SImax;
selecting working elevation angle theta from all time sampling points I-i,j The smallest ak bars may interfere with the link,and screening possible interference links of time sampling points k, wherein the number of the satellite connection earth stations does not exceed the maximum number of links EImax of a single satellite, and the number of the satellite connection earth stations does not exceed the maximum number of links SImax of the single earth station.
In a preferred embodiment, the method calculates the possible demand link according to the satellite node space matrix of the demand satellite system, the earth station node space matrix of the demand satellite system, the link direction of the demand satellite system and the view angle operation limit of the demand satellite system, and specifically comprises the following steps:
Calculating parameters of a possible demand link between the ith satellite and the jth earth station:
a) Requiring earth station elevation angle theta W-i,j The calculation formula is as follows:
b) Demand satellite field angle
The calculation formula is as follows:
c) Meeting the requirement of the maximum field angle of the satellite
And a minimum elevation angle theta of the required earth station W-max Sampling time point set P of (a) W-i,j The calculation formula is as follows:
wherein: h SW-i Satellite node space matrix for ith demand satellite system of demand satellite system, H EW-j The space matrix of earth station nodes of the j-th demand satellite system for the demand satellite system.
In a preferred embodiment, the method calculates the possible demand link according to the satellite node space matrix of the demand satellite system, the earth station node space matrix of the demand satellite system, the link direction of the demand satellite system and the view angle operation limit of the demand satellite system, and specifically comprises the following steps:
the link operation limit of the interference satellite system comprises the maximum number of links EWMax of a single satellite, the maximum number of links SWmax of a single earth station and a link operation strategy; the demand link working strategy comprises a demand highest elevation angle strategy and a demand longest time keeping strategy;
judging whether the possible demand link of the time sampling point k contains the possible demand link of the time sampling point k-1 or not;
If the possible requirement links of the time sampling point k do not contain the possible requirement links of the time sampling point k-1, screening the possible requirement links of the time sampling point k, wherein the number of the satellite connection earth stations does not exceed the maximum number of required single satellite links EWMax, and the number of the satellite connection earth stations does not exceed the maximum number of required single earth station links SWmax;
selecting working elevation angle theta from all time sampling points I-i,j And (3) selecting possible required links of time sampling points k, wherein the number of the possible required links is smaller than or equal to the maximum number of required links EWMax of a single satellite, and the number of the possible required links of time sampling points k, which are smaller than or equal to the maximum number of required links SWmax of the single satellite, are not larger than or equal to the number of the required links of the satellite.
Preferably, the input satellite orbit parameters include no later than the simulation start time T s Six orbits of each satellite in a WGS-84 coordinate system of the moment Ta, and the space positions are satellite node X-axis coordinates, Y-axis coordinates and Z-axis coordinates in the WGS-84 coordinate system.
In a preferred embodiment, the satellite disturbance system inputs the earth station parameters including a certain time Tb no later than the simulation start time Ts, longitude/latitude/altitude of each earth station under the WGS-84 coordinate system of the time Tb, and a motion model, and the space position is X-axis coordinate, Y-axis coordinate and Z-axis coordinate under the WGS-84 coordinate system.
The interfering satellite system link direction includes ground-to-air and air-to-ground,
the interference satellite system view angle operation limit comprises a satellite maximum view angle
Minimum elevation angle theta of earth station I-max 。
In a preferred embodiment, the demand input satellite orbit parameters include: and the space position is the X-axis coordinate, the Y-axis coordinate and the Z-axis coordinate of the satellite node under the WGS-84 coordinate system, wherein the space position is not later than a certain moment Tc of the simulation starting time Ts and is six orbits of each satellite under the WGS-84 coordinate system of the moment Tc.
The requiring satellite system to input earth station parameters includes: a certain time Td no later than the simulation start time Ts, longitude/latitude/altitude of each earth standing under the WGS-84 coordinate system of the time Td, and a motion model, wherein the space positions are X-axis coordinates, Y-axis coordinates and Z-axis coordinates under the WGS-84 coordinate system.
The required satellite link direction comprises ground-to-air and air-to-ground;
the desired satellite system operational constraints include desired satellite maximum field angle
Requiring minimum elevation angle theta of earth station W-max ；
In order to better illustrate the technical effects of the present invention, the present invention provides the following specific examples to illustrate the technical processes described above:
step 1, sampling in a simulation time period (assuming that the simulation start time is Ts and the simulation end time is Te) according to a certain time interval Deltat, and determining a series of time sampling points (t 1, t2, …, tk and …), wherein the number of the sampling points is m, as shown in fig. 2;
And 2, independently calculating the space position of each satellite of the interference satellite system at a series of sampling points according to the satellite orbit parameters input by the interference satellite system, and storing the space position in a matrix form. Wherein the input satellite orbit parameters include: not later than the start time T of the simulation s Six orbits of each satellite in a WGS-84 coordinate system of the moment Ta, and the space positions are satellite node X-axis coordinates, Y-axis coordinates and Z-axis coordinates in the WGS-84 coordinate system. The six-rail, WGS-84 coordinate system may be replaced with other equivalent forms. Assuming that the number of the interference satellite systems is n1, the ith satellite node space matrix H of the interference satellite systems SI-i The method can be expressed as follows:
and step 3, independently calculating the spatial position of each earth station of the interference satellite system at a series of sampling points according to the parameters of the earth station motion model input by the interference satellite system, and storing the spatial position in a matrix form. Wherein the interfering satellite system inputs the earth station parameters including: a certain time Tb no later than the simulation start time Ts, longitude/latitude/altitude of each earth standing under the WGS-84 coordinate system of the time Tb, a motion model (motion speed, motion direction and the like), and the space position is X-axis coordinate, Y-axis coordinate and Z-axis coordinate under the WGS-84 coordinate system. The longitude/latitude/altitude above, the WGS-84 coordinate system, and the motion model may be replaced with other equivalent forms. Assuming that the number of earth station nodes of an interference satellite system is n2, the j-th earth station node space matrix H of the interference satellite system EI-j The method can be expressed as follows:
and step 4, independently forming a possible interference link list according to the link direction of the interference satellite system, and calculating a visible sampling point set of each possible interference link according to the working limit of the interference satellite system. The interference satellite link direction comprises ground-to-air and air-to-ground, wherein under the ground-to-air condition, the transmitting node is an earth station, the receiving node is a satellite, under the air-to-ground condition, the transmitting node is a satellite, and the receiving node is an earth station; interfering satellite system view angle operational constraints include satellite maximum view angle
Minimum elevation angle theta of earth station I-max 。
Calculating parameters of a possible interference link between the ith satellite and the jth earth station:
a) Elevation angle theta of earth station I-ij The calculation formula is as follows:
b) Satellite field angle
The calculation formula is as follows:
c) Meets the maximum field angle of the satellite
And minimum elevation angle theta of earth station I-max Time sample point set P of (2) I-ij The calculation formula is as follows:
and 5, generating an interference link list according to the working limit of the interference satellite system. The link operation limit of the interference satellite system comprises the maximum number of links of a single satellite, the maximum number of links of a single earth station and a link operation strategy, wherein the maximum number of links of the single satellite EImax is the maximum number of connectable earth stations of the single satellite, the maximum number of links of the single earth station SImax is the maximum number of connectable satellites of the single earth station, and the link operation strategy comprises a highest elevation angle strategy and a longest time keeping strategy. The method is realized in 2 steps:
Firstly, the time sets of all the links are arranged according to time sampling points, so that a possible interference link matrix of each time sampling point can be obtained, and the possible interference link matrix of the kth sampling point can be expressed as follows:
P I-k ＝{(i，j)|k∈P I-i，j }
secondly, according to the time sampling point sequence, the P is point by point I-k Screening to obtain P' I-k The screening requirements are as follows:
a) Maximum time retention:
1) The number of the earth stations connected with the single satellite is not more than EImax;
2) The number of single earth station connection satellites does not exceed SImax;
3) If the set of possible interference links of the time sampling point k comprises the set of interference links of the time sampling point k-1, the sets of interference links of the time sampling points k and k-1 are consistent;
4) If the set of possible interference links of the time sampling point k does not contain the set of interference links of the time sampling point k-1, randomly selecting links conforming to the 1 st and 2 nd) for the elements which are not contained;
b) Maximum elevation angle:
1) The number of the earth stations connected with the single satellite is not more than EImax;
2) The number of single earth station connection satellites does not exceed SImax;
3) Selecting working elevation angle theta I-i,j The largest ck in sequence may interfere with the link, where ck=min (ak, nl).
And step 6, independently calculating the space position of each satellite of the demand satellite system at a series of sampling points according to the satellite orbit parameters input by the demand satellite system, and storing the space position in a matrix form. Wherein the input satellite orbit parameters include: and the space position is the X-axis coordinate, the Y-axis coordinate and the Z-axis coordinate of the satellite node under the WGS-84 coordinate system, wherein the space position is not later than a certain moment Tc of the simulation starting time Ts and is six orbits of each satellite under the WGS-84 coordinate system of the moment Tc. The six-rail, WGS-84 coordinate system may be replaced with other equivalent forms. Assuming that the number of interfering satellite systems is n3, the ith satellite node space matrix H of the required satellite system SW-i The method can be expressed as follows:
and 7, inputting the motion model parameters of the earth station according to the required satellite system, independently calculating the spatial position of each earth station of the required satellite system at a series of sampling points, and storing the spatial positions in a matrix form. Wherein the requiring the satellite system to input the earth station parameters includes: a certain time Td no later than the simulation start time Ts, longitude/latitude/altitude of each earth standing in the WGS-84 coordinate system at the time Td, a motion model (motion speed, motion direction, etc.), and spatial positions are X-axis coordinates, Y-axis coordinates, and Z-axis coordinates in the WGS-84 coordinate system. The longitude/latitude/altitude above, the WGS-84 coordinate system, and the motion model may be replaced with other equivalent forms. Assuming that the number of earth station nodes of an interference satellite system is n4, the j-th earth station node space matrix H of the satellite system is required EW-j The method can be expressed as follows:
and 8, independently forming a possible demand link list according to the direction of the demand satellite system link, and calculating a time sampling point set of each possible demand link according to the working limit of the demand satellite system. The satellite link direction comprises ground-to-air and air-to-ground, wherein under the ground-to-air condition, the transmitting node is an earth station, the receiving node is a satellite, under the air-to-ground condition, the transmitting node is a satellite, and the receiving node is an earth station; the desired satellite system operational constraints include desired satellite maximum field angle 
Requiring minimum elevation angle theta of earth station W-max 。
Calculating parameters of a possible demand link between the ith satellite and the jth earth station:
a) Elevation angle theta of earth station W-i,j The calculation formula is as follows:
b) Satellite field angle
The calculation formula is as follows:
c) Meeting the requirement of the maximum field angle of the satellite
And a minimum elevation angle theta of the required earth station W-max Time sample point set P of (2) W-i,j The calculation formula is as follows:
and 9, generating a demand link list according to the working limit of the demand satellite system. The required satellite system operation limit comprises the maximum number of links of the required single satellite, the maximum number of links of the required single earth station and a required link operation strategy, wherein the maximum number of links of the required single satellite EWMax is the maximum number of connectable earth stations of the required single satellite, the maximum number of links of the required single earth station SWmax is the maximum number of connectable satellites of the required single earth station, and the required link operation strategy comprises a required highest elevation angle strategy and a required longest time keeping strategy. The method is realized in 2 steps:
firstly, the time sets of all the links are arranged according to time sampling points, so that a possible required link matrix of each time sampling point can be obtained, and a possible interference link matrix of a kth sampling point can be expressed as follows:
P W-k ＝{(i，j)k∈P W-i，j }P I ' W-k
Secondly, according to the time sampling point sequence, the P is point by point W-k Screening to obtain P' W-k The screening requirements are as follows:
a) Maximum time retention:
1) The number of the earth stations connected with the single satellite is required to be not more than EWMax;
2) The number of the satellite connection earth stations is required to be not more than SWmax;
3) If the set of possible interference links of the time sampling point k comprises the set of interference links of the time sampling point k-1, the sets of interference links of the time sampling points k and k-1 are consistent;
if the possible interference link set of the time sampling point k does not contain the interference link set of the time sampling point k-1, randomly selecting links conforming to the 1 st and 2 nd) for the elements which are not contained;
b) Maximum elevation angle:
1) The number of the earth stations connected with the single satellite does not exceed EWMax;
2) The number of the earth stations connected with a single satellite does not exceed SWmax;
3) Selecting working elevation angle theta I-i,j The largest ck in turn may interfere with the link, where ck = min (ak, nl);
step 10, according to the time sampling point sequence, P is point by point I ' -k And P' W-k Fusion is carried out on the set P of possible interference paths IW-k Wherein the set of interference paths contains all combinations of "interfering transmitting node-demand receiving node";
step 11, the possible interference paths are filtered for the 1 st time to generate an interference path set P I ' W-k The screening principle is as follows: if the working frequencies of the interference transmitting node and the demand receiving node in the interference path are not overlapped, then in the set P IW-k Directly removing the element;
step 12, the possible interference paths are screened for the 2 nd time, which can be divided into the following cases: if the transmitting node is a satellite and the interfering path is obscured by the earth, the element is deleted.
In the several embodiments provided by the present invention, it should be understood that the disclosed apparatus and method may be implemented in other manners. For example, the above-described apparatus embodiments are merely illustrative, and the division of modules, or units is merely a logical function division, and there may be additional divisions when actually implemented, e.g., multiple units, modules, or components may be combined or integrated into another apparatus, or some features may be omitted, or not performed.
The units may or may not be physically separate, and the components shown as units may be one physical unit or a plurality of physical units, may be located in one place, or may be distributed in a plurality of different places. Some or all of the units may be selected according to actual needs to achieve the purpose of the solution of this embodiment.
In addition, each functional unit in the embodiments of the present invention may be integrated in one processing unit, or each unit may exist alone physically, or two or more units may be integrated in one unit. The integrated units may be implemented in hardware or in software functional units.
In particular, according to embodiments of the present disclosure, the processes described above with reference to flowcharts may be implemented as computer software programs. For example, embodiments of the present disclosure include a computer program product comprising a computer program embodied on a computer readable medium, the computer program comprising program code for performing the method shown in the flowcharts. In such embodiments, the computer program may be downloaded and installed from a network via a communication portion, and/or installed from a removable medium. The above-described functions defined in the method of the present invention are performed when the computer program is executed by a Central Processing Unit (CPU). The computer readable medium of the present invention may be a computer readable signal medium or a computer readable storage medium, or any combination of the two. The computer readable storage medium can be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared, or semiconductor system, apparatus, or device, or any combination of the above.
The flowcharts and block diagrams in the figures illustrate the architecture, functionality, and operation of possible implementations of systems, methods and computer program products according to various embodiments of the present invention. In this regard, each block in the flowchart or block diagrams may represent a module, segment, or portion of code, which comprises one or more executable instructions for implementing the specified logical function(s). It should also be noted that, in some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession may, in fact, be executed substantially concurrently, or the blocks may sometimes be executed in the reverse order, depending upon the functionality involved. It will also be noted that each block of the block diagrams and/or flowchart illustration, and combinations of blocks in the block diagrams and/or flowchart illustration, can be implemented by special purpose hardware-based systems which perform the specified functions or acts, or combinations of special purpose hardware and computer instructions.
The foregoing is merely illustrative of specific embodiments of the present invention, and the scope of the present invention is not limited thereto, but any changes or substitutions within the technical scope of the present invention should be covered by the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. The frequency compatible model calculation method suitable for the NGSO satellite constellation is characterized by comprising the following steps:
acquiring sampling information of an interference satellite system and a demand satellite system at a time sampling point; the sampling information of the interference satellite system comprises an input satellite orbit parameter of the interference satellite system, an input earth station motion model parameter of the interference satellite system, a link direction of the interference satellite system and a working limit of the interference satellite system; the sampling information of the required satellite system comprises required satellite system input satellite orbit parameters, required satellite system input earth station motion model parameters, required satellite system link direction and required satellite system work limit; the interference satellite system operation limit comprises an interference satellite system visual angle operation limit and an interference satellite system link operation limit; the required satellite system operation limit comprises a required interference satellite system visual angle operation limit and a required interference satellite system link operation limit;
according to the satellite orbit parameters input by the interference satellite system, calculating the space position of the satellite system, and generating a satellite node space matrix of the satellite system;
according to the parameters of the earth station motion model input by the interference satellite system, calculating the space position of the earth station of the satellite system, and generating an earth station node space matrix of the satellite system;
Calculating a possible interference link according to a satellite node space matrix of a satellite system, an earth station node space matrix of the satellite system, an interference satellite system link direction and an interference satellite system visual angle work limit;
generating an interference link according to the possible interference link and the interference satellite system link work limit;
according to the satellite orbit parameters input by the demand satellite system, calculating the space position of the satellite of the demand satellite system, and generating a satellite node space matrix of the demand satellite system;
inputting the earth station motion model parameters according to the demand satellite system, calculating the space position of the earth station of the demand satellite system, and generating an earth station node space matrix of the demand satellite system;
calculating a possible required link according to a satellite node space matrix of the required satellite system, an earth station node space matrix of the required satellite system, a link direction of the required satellite system and a view angle operation limit of the required satellite system;
generating a demand link according to the possible demand link and the demand satellite system link work limit;
and fusing the interference link and the demand link to obtain a possible interference path.
2. The method for computing the frequency compatibility model between NGSO satellite constellations according to claim 1, wherein the interfering link and the demand link are fused, comprising the steps of:
The transmitting node of the interference link and the receiving node of the demand link are used as the transmitting node and the receiving node of the possible interference path.
3. The method for computing a frequency compatible model between NGSO satellite constellations according to claim 2, further comprising the steps of:
the possible interference paths are screened.
4. A method for computing a frequency compatible model between NGSO satellite constellations according to claim 3, wherein the method for screening the possible interference paths comprises the steps of:
judging whether the working frequencies of a transmitting node and a receiving node of a possible interference path are overlapped or not; if the working frequencies of the transmitting node and the receiving node of the possible interference path are not overlapped, eliminating the possible interference path;
judging whether a transmitting node of a possible interference path is a satellite and whether the possible interference path is blocked by the earth; if the transmitting node of the possible interference path is a satellite and the possible interference path is blocked by the earth, eliminating the possible interference path.
5. The method for calculating the frequency compatibility model between NGSO satellite constellations according to claim 1, wherein the possible interference link is calculated according to a satellite node space matrix of the satellite system, an earth station node space matrix of the satellite system, an interference satellite system link direction and an interference satellite system view angle operation limit, comprising the steps of:
Calculating parameters of a possible interference link between the ith satellite and the jth earth station:
a) Elevation angle theta of earth station I-ij The calculation formula is as follows:
b) Satellite field angle
The calculation formula is as follows:
c) Meets the maximum field angle of the satellite
And minimum elevation angle theta of earth station I-max Sampling time point set P of (a) I-ij The calculation formula is as follows:
wherein: h SI-i A satellite node space matrix for an ith satellite system of the interfering satellite system; h EI-j The space matrix of the earth station node of the j satellite system which is the interference satellite system is k, and k is the k time sampling point.
6. The method for computing a frequency compatibility model between constellations of NGSO satellites according to claim 5 wherein the generating of the interfering links is based on operational constraints of the likely interfering links and the interfering satellite system links, comprising the steps of:
the link working limit of the interference satellite system comprises the maximum link number EImax of a single satellite, the maximum link number SImax of a single earth station and a link working strategy; the link working strategy comprises a highest elevation angle strategy and a longest time keeping strategy;
judging whether the possible interference link of the time sampling point k contains an interference link of the time sampling point k-1 or not;
if the possible interference link of the time sampling point k does not contain the interference link of the time sampling point k-1, screening the possible interference link of the time sampling point k, wherein the number of the satellite connected earth stations does not exceed the maximum number of links of the single satellite EImax, and the number of the satellite connected earth stations does not exceed the maximum number of links of the single earth station SImax;
Selecting working elevation angle theta from all time sampling points I-i,j The minimum ak possible interference links are selected, and the number of the possible interference links of the time sampling point k, in which the number of the satellite connected earth stations does not exceed the maximum number of links of a single satellite EImax and the number of the satellite connected earth stations does not exceed the maximum number of links of the single earth station SImax.
7. The method for calculating the frequency compatibility model between NGSO satellite constellations according to claim 1, wherein the possible demand links are calculated according to a satellite node space matrix of the demand satellite system, an earth station node space matrix of the demand satellite system, a link direction of the demand satellite system and a view angle operation limit of the demand satellite system, comprising the steps of:
calculating parameters of a possible demand link between the ith satellite and the jth earth station:
a) Requiring earth station elevation angle theta W-i,j The calculation formula is as follows:
b) Demand satellite field angle
The calculation formula is as follows:
c) Meeting the requirement of the maximum field angle of the satellite
And a minimum elevation angle theta of the required earth station W-max Is of (1)Sample time Point set P W-i,j The calculation formula is as follows:
wherein: h SW-i Satellite node space matrix for ith demand satellite system of demand satellite system, H EW-j The space matrix of earth station nodes of the j-th demand satellite system for the demand satellite system.
8. The method for computing a frequency compatible model between NGSO satellite constellations according to claim 7, wherein the computing a possible demand link according to a satellite node space matrix of the demand satellite system, an earth station node space matrix of the demand satellite system, a demand satellite system link direction, and a demand satellite system view angle operation limit, comprises the steps of:
the link operation limit of the interference satellite system comprises the maximum number of links EWMax of a single satellite, the maximum number of links SWmax of a single earth station and a link operation strategy; the demand link working strategy comprises a demand highest elevation angle strategy and a demand longest time keeping strategy;
judging whether the possible demand link of the time sampling point k contains the possible demand link of the time sampling point k-1 or not;
if the possible requirement links of the time sampling point k do not contain the possible requirement links of the time sampling point k-1, screening the possible requirement links of the time sampling point k, wherein the number of the satellite connection earth stations does not exceed the maximum number of required single satellite links EWMax, and the number of the satellite connection earth stations does not exceed the maximum number of required single earth station links SWmax;
selecting working elevation angle theta from all time sampling points I-i,j And (3) selecting possible required links of time sampling points k, wherein the number of the possible required links is smaller than or equal to the maximum number of required links EWMax of a single satellite, and the number of the possible required links of time sampling points k, which are smaller than or equal to the maximum number of required links SWmax of the single satellite, are not larger than or equal to the number of the required links of the satellite.
9. The method for computing a frequency compatible model between NGSO satellite constellations according to claim 1, wherein:
the input satellite orbit parameters include not later than the simulation start time T s Six orbits of each satellite in a WGS-84 coordinate system of the moment Ta, and the space positions are satellite node X-axis coordinates, Y-axis coordinates and Z-axis coordinates in the WGS-84 coordinate system; the parameters of the earth station input by the interference satellite system comprise a certain moment Tb which is not later than the simulation starting time Ts, longitude/latitude/altitude of each earth station under a WGS-84 coordinate system at the moment Tb and a motion model, and the spatial positions are X-axis coordinates, Y-axis coordinates and Z-axis coordinates under the WGS-84 coordinate system.
The link direction of the interference satellite system comprises ground-to-air and air-to-ground;
the interference satellite system view angle operation limit comprises a satellite maximum view angle
Minimum elevation angle theta of earth station I-max ；
In a preferred embodiment, the demand input satellite orbit parameters include: the space position is the X-axis coordinate, Y-axis coordinate and Z-axis coordinate of a satellite node under the WGS-84 coordinate system, wherein the number of orbits of each satellite under the WGS-84 coordinate system is not later than a certain moment Tc of the simulation starting time Ts;
the requiring satellite system to input earth station parameters includes: a certain time Td not later than the simulation start time Ts, longitude/latitude/altitude of each earth standing under a WGS-84 coordinate system of the time Td, and a motion model, wherein the spatial positions are an X-axis coordinate, a Y-axis coordinate and a Z-axis coordinate under the WGS-84 coordinate system;
the required satellite link direction comprises ground-to-air and air-to-ground;
the desired satellite system operational constraints include desired satellite maximum field angle
Requiring minimum elevation angle theta of earth station W-max 。/>
10. A frequency compatible model computing system for NGSO satellite constellations, implementing the method for computing a frequency compatible model for NGSO satellite constellations according to any one of claims 1 to 9, comprising:
the sampling module is used for acquiring sampling information of the interference satellite system and the demand satellite system at a time sampling point; the sampling information of the interference satellite system comprises an input satellite orbit parameter of the interference satellite system, an input earth station motion model parameter of the interference satellite system, a link direction of the interference satellite system and a working limit of the interference satellite system; the sampling information of the required satellite system comprises required satellite system input satellite orbit parameters, required satellite system input earth station motion model parameters, required satellite system link direction and required satellite system work limit; the interference satellite system operation limit comprises an interference satellite system visual angle operation limit and an interference satellite system link operation limit; the required satellite system operation limit comprises a required interference satellite system visual angle operation limit and a required interference satellite system link operation limit;
The first satellite matrix conversion module is used for calculating the space position of a satellite of the satellite system according to the satellite orbit parameters input by the interference satellite system and generating a satellite node space matrix of the satellite system;
the first earth station matrix conversion module is used for inputting earth station motion model parameters according to the interference satellite system, calculating the space position of an earth station of the satellite system and generating an earth station node space matrix of the satellite system;
the possible interference link calculation module is used for calculating a possible interference link according to a satellite node space matrix of a satellite system, an earth station node space matrix of the satellite system, an interference satellite system link direction and an interference satellite system visual angle operation limit;
the first screening module is used for generating an interference link according to the possible interference link and the interference satellite system link work limit;
the second satellite matrix conversion module is used for inputting satellite orbit parameters according to the required satellite system, calculating the space position of satellites of the required satellite system and generating a satellite node space matrix of the required satellite system;
the second earth station matrix conversion module is used for inputting earth station motion model parameters according to the required satellite system, calculating the space position of the earth station of the required satellite system and generating an earth station node space matrix of the required satellite system;
The possible demand link calculation module is used for calculating the possible demand link according to the satellite node space matrix of the demand satellite system, the earth station node space matrix of the demand satellite system, the link direction of the demand satellite system and the view angle work limit of the demand satellite system.
The second screening module is used for generating a demand link according to the possible demand link and the demand satellite system link work limit;
and the fusion module is used for fusing the interference link and the demand link to obtain a possible interference path.
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117544255A (en) * | 2023-11-09 | 2024-02-09 | 中国人民解放军军事科学院***工程研究院 | NGSO satellite interference condition matrix manifold visualization method and device |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110263199A1 (en) * | 2003-12-07 | 2011-10-27 | Gogo Llc | Spectrum sharing between an aircraft-based air-to-ground communication system and existing geostationary satellite services |
| CN110838866A (en) * | 2019-10-09 | 2020-02-25 | 中国空间技术研究院 | Method for sharing same frequency of NGSO satellite system and GSO satellite system |
| WO2020066470A1 (en) * | 2018-09-28 | 2020-04-02 | 日本電信電話株式会社 | Interference power estimation method, interference power estimation device, and program |
| CN111447001A (en) * | 2020-03-09 | 2020-07-24 | 航天行云科技有限公司 | Uplink power control method and device for terminal equipment |
| CN114257293A (en) * | 2021-12-22 | 2022-03-29 | 军事科学院***工程研究院网络信息研究所 | Modeling method for interference of NGSO constellation on GEO satellite communication earth station based on space-time cut set |
-
2022
- 2022-12-17 CN CN202211628432.8A patent/CN116248165A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110263199A1 (en) * | 2003-12-07 | 2011-10-27 | Gogo Llc | Spectrum sharing between an aircraft-based air-to-ground communication system and existing geostationary satellite services |
| WO2020066470A1 (en) * | 2018-09-28 | 2020-04-02 | 日本電信電話株式会社 | Interference power estimation method, interference power estimation device, and program |
| CN110838866A (en) * | 2019-10-09 | 2020-02-25 | 中国空间技术研究院 | Method for sharing same frequency of NGSO satellite system and GSO satellite system |
| CN111447001A (en) * | 2020-03-09 | 2020-07-24 | 航天行云科技有限公司 | Uplink power control method and device for terminal equipment |
| CN114257293A (en) * | 2021-12-22 | 2022-03-29 | 军事科学院***工程研究院网络信息研究所 | Modeling method for interference of NGSO constellation on GEO satellite communication earth station based on space-time cut set |
Non-Patent Citations (4)
| Title |
|---|
| HAYDER AL-HRAISHAWI等: "A Survey on Nongeostationary Satellite Systems: The Communication Perspective", 《 IEEE COMMUNICATIONS SURVEYS & TUTORIALS》, 9 August 2022 (2022-08-09) * |
| 李伟等: "基于空间位置概率的NGSO通信星座干扰仿真分析研究", 《电波科学学报》, 31 March 2021 (2021-03-31) * |
| 杜利;史俊松;: "行云工程在八大重点行业的典型应用", 卫星应用, no. 03, 25 March 2020 (2020-03-25) * |
| 靳瑾;李娅强;张晨;匡麟玲;晏坚;: "全球动态场景下非静止轨道通信星座干扰发生概率和***可用性", 清华大学学报(自然科学版), no. 09, 15 September 2018 (2018-09-15) * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117544255A (en) * | 2023-11-09 | 2024-02-09 | 中国人民解放军军事科学院***工程研究院 | NGSO satellite interference condition matrix manifold visualization method and device |
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