CN111464940A - Method and system for scheduling communication-guide integrated constellation beams - Google Patents

Method and system for scheduling communication-guide integrated constellation beams Download PDF

Info

Publication number
CN111464940A
CN111464940A CN202010292714.XA CN202010292714A CN111464940A CN 111464940 A CN111464940 A CN 111464940A CN 202010292714 A CN202010292714 A CN 202010292714A CN 111464940 A CN111464940 A CN 111464940A
Authority
CN
China
Prior art keywords
target
satellite
satellites
determining
user
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CN202010292714.XA
Other languages
Chinese (zh)
Other versions
CN111464940B (en
Inventor
陈曦
魏齐辉
冯佳傲
王晓伟
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shanghai Qingshen Technology Development Co ltd
Tsinghua University
Original Assignee
Shanghai Qingshen Technology Development Co ltd
Tsinghua University
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shanghai Qingshen Technology Development Co ltd, Tsinghua University filed Critical Shanghai Qingshen Technology Development Co ltd
Priority to CN202010292714.XA priority Critical patent/CN111464940B/en
Publication of CN111464940A publication Critical patent/CN111464940A/en
Application granted granted Critical
Publication of CN111464940B publication Critical patent/CN111464940B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04W—WIRELESS COMMUNICATION NETWORKS
    • H04W4/00—Services specially adapted for wireless communication networks; Facilities therefor
    • H04W4/02—Services making use of location information
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04W—WIRELESS COMMUNICATION NETWORKS
    • H04W72/00—Local resource management
    • H04W72/04—Wireless resource allocation
    • H04W72/044—Wireless resource allocation based on the type of the allocated resource
    • H04W72/046—Wireless resource allocation based on the type of the allocated resource the resource being in the space domain, e.g. beams
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04W—WIRELESS COMMUNICATION NETWORKS
    • H04W84/00—Network topologies
    • H04W84/02—Hierarchically pre-organised networks, e.g. paging networks, cellular networks, WLAN [Wireless Local Area Network] or WLL [Wireless Local Loop]
    • H04W84/04—Large scale networks; Deep hierarchical networks
    • H04W84/06—Airborne or Satellite Networks

Abstract

The invention provides a method and a system for scheduling a communication-guide integrated constellation wave beam, which relate to the technical field of satellite communication and comprise the following steps: determining a target position in a to-be-navigated area within a first preset time period; determining an initial satellite in all satellites contained in a first preset time period to be conducted to obtain a first communication satellite collection; determining a target satellite based on the first communication satellite set to obtain a second communication satellite set, wherein the target satellite is a first preset number of initial satellites with the smallest geometric factor formed by the first communication satellite set and the target position; the target position is sent to the satellite in the second communication satellite set, so that the downlink beam of the satellite in the second communication satellite set points to the target position in the first preset time period, and the technical problem that the energy utilization rate of a communication and guide integrated constellation is low when a user navigates in the prior art is solved.

Description

Method and system for scheduling communication-guide integrated constellation beams
Technical Field
The invention relates to the technical field of satellite communication, in particular to a method and a system for scheduling a communication-guide integrated constellation beam.
Background
Modern satellite communication systems mostly adopt a beam-oriented communication system, communication time slots and communication beams are allocated to users according to needs, and the communication beams are always directed to target users by adjusting beam directions, so that the bandwidth and the energy utilization efficiency are maximized. In conventional beam-oriented satellite communications, the radio coverage of a satellite for a particular region of the ground is typically only heavy. The downlink radio signals of satellite communication can also be used for navigation, but in satellite navigation positioning, users usually need 4 times of radio coverage to realize positioning, and need at least 5 times of radio coverage to effectively find faults and resolve anomalies.
With the development of satellite communication constellations, the satellite communication constellations have shown a large-scale trend, the number of satellites is often hundreds of thousands, and a plurality of satellites can completely cover the same area at the same time, so that a ground user in a hot spot region can be supported like a navigation satellite to realize navigation and positioning by using downlink signals of satellite communication.
However, under the condition that multiple satellites can cover the same area, the prior art also has the technical problem of how to perform beam scheduling so as to realize optimization of user positioning accuracy by using the minimum number of satellites.
No effective solution has been proposed to the above problems.
Disclosure of Invention
In view of the above, the present invention provides a method and a system for scheduling a beam of a turn-on-turn constellation, so as to solve the technical problem in the prior art that the energy utilization rate of the turn-on-turn constellation is low when navigating for a user.
In a first aspect, an embodiment of the present invention provides a method for scheduling a common constellation beam, including: determining the target position in the area to be navigated within a first preset time period, wherein the corresponding areas to be navigated within different preset time periods are different; determining initial satellites in all satellites included in a communication one-body constellation in the first preset time period based on a preset elevation threshold value to obtain a first communication satellite set, wherein the initial satellites are satellites in the communication one-body constellation, and the elevation angle between the orbit position and the target position is smaller than a preset elevation angle; determining a target satellite in the first communication satellite set to obtain a second communication satellite set, wherein the target satellite is a first preset number of initial satellites with the smallest geometric factor formed by the first communication satellite set and the target position; and sending the target position to a satellite in the second communication satellite set, so that a downlink beam of the satellite in the second communication satellite set points to the target position within the first preset time period.
Further, determining the target position in the area to be navigated within the first preset time period includes: determining the area to be navigated based on a coverage request of a ground user, wherein the area to be navigated is an area covered at least once by beams of a second preset number of communication satellites in all the satellites every time a preset time period passes within the first preset time period; determining any position in the area to be navigated as the target position.
Further, the coverage request carries a current location vector of the ground user; determining the area to be navigated based on the coverage request of the ground user, including: a conversion step of converting the current position vector of the ground user into longitude and latitude high coordinates, wherein PxThe current position vector of the xth ground user is obtained, X is an integer from 1 to X, and X is the number of the ground users; a first determination step, in which a target user in the ground users is determined, and the target user is determined as an initial user, wherein the target user is a ground user corresponding to a longitude and latitude high coordinate with a maximum latitude coordinate and a minimum longitude coordinate in the ground users; a second determining step of determining the longitude and latitude high coordinate of the intermediate user based on the longitude and latitude high coordinate of the initial user, wherein the longitude and latitude high coordinate of the intermediate user is increased in longitudeThe longitude and latitude height coordinate of the ground user with the smallest clockwise rotation angle between the longitude and latitude height coordinate of the initial user in the direction; a third determination step, determining the longitude and latitude height coordinate of the intermediate user as the longitude and latitude height coordinate of the initial user; and a first execution step of repeatedly executing the second determination step and the third determination step until the longitude and latitude high coordinate of the intermediate user is the longitude and latitude high coordinate of the target user, and determining the longitude and latitude high coordinate of the target user and the area surrounded by the longitude and latitude high coordinate of the intermediate user to be the area to be navigated.
Further, based on a preset elevation threshold, determining an initial satellite among all satellites included in the integrated constellation that is conducted within the first preset time period to obtain a first communication satellite set, and obtaining the first communication satellite set, including: calculating the orbit positions of all the satellites at a target moment, wherein the target moment is (t)2+t1) /2, wherein t1Is the starting time of the first preset time period, t2The ending time of the first preset time period is the ending time of the first preset time period; determining elevation angles between the on-orbit positions and the target positions of all the satellites based on the on-orbit positions and the target positions of all the satellites; and determining the satellites with the elevation angles larger than a preset elevation angle in all the satellites as the initial satellites to obtain the first communication satellite collection.
Further, the target satellite includes: a first target satellite and a second target satellite; determining a target satellite in the first communication satellite collection to obtain a second communication satellite collection, including: calculating an azimuth between the in-orbit position of the initial satellite and the target position at the target time; determining the number of first target satellites based on a target correspondence table and the preset number, wherein the number of the first target satellites is the number of zenith satellites corresponding to the preset number of target satellites, and the target correspondence table is used for representing the correspondence among the preset number of target satellites, the zenith satellites and the minimum geometric factor; based on an azimuth between an in-orbit position and the target position of the initial satellite and the initial satelliteElevation angles between the orbit positions and the target positions of the initial satellites are constructed, a target matrix is constructed, wherein the target matrix is a matrix with D being 6(Q-u) × (Q-u), and the ith row and the jth column of elements D of the matrix Di,jThe characteristic azimuth angles are in the interval [ (i-1) × 360/{6(Q-u) }, i × 360/{6(Q-u) }]Within the interval [ (j-1) (90-theta)thre)/(Q-u)，j(90-θthre)/(Q-u)]The number of initial satellites in the satellite array is 1-6 (Q-u), 1-j-Q-u, Q is the first preset number, and u is the number of the first target satellites; determining the first target satellite in the target matrix based on a preset search sequence and the number of the first target satellites; and determining the second target satellite in the target matrix based on a preset condition.
Further, determining the second target satellite in the target matrix based on a preset condition includes: a fourth determination step of
Figure BDA0002449793180000041
Then will element
Figure BDA0002449793180000042
Any one initial satellite included in (1) is determined as the second target satellite, and Q-u second target satellites are obtained, wherein i is 1,2, …,6, and k is 0,1, …, (Q-u-1); a step of calculation, if
Figure BDA0002449793180000043
Then calculate
Figure BDA0002449793180000044
Obtaining a calculation result, and determining a target value based on the calculation result, wherein the target value is
Figure BDA0002449793180000045
And is
Figure BDA0002449793180000046
The value of time k, j0＝arg minjDi,j＞0，j1＝arg maxjDi,j> 0, mod (i + -1, 6) is used to characterize the remainder of (i + -1)/6; a fifth determination step of determining the element
Figure BDA0002449793180000047
Determining any initial satellite contained in the satellite data to be an initial target satellite, and determining the number of the initial target satellites, wherein k is the target value; a sixth determination step of determining the initial target satellite as the second target satellite if the number of the initial target satellites is equal to (Q-u); a second execution step of j is performed if the number of the second target satellites is less than (Q-u)0Is updated to j0+1, and repeating the fourth determining step, the calculating step, the fifth determining step, and the sixth determining step until (Q-u) second target satellites are determined.
In a second aspect, an embodiment of the present invention further provides a system for scheduling a constellation beam of a traffic guide system, including: the navigation device comprises a first determining unit, a second determining unit, a third determining unit and a sending unit, wherein the first determining unit is used for determining the target position in a to-be-navigated area within a first preset time period, and the corresponding to-be-navigated areas within different preset time periods are different; the second determining unit is configured to determine, based on a preset elevation threshold value, an initial satellite from all satellites included in the integrated conducting constellation in the first preset time period to obtain a first communication satellite set, where the initial satellite is a satellite whose elevation angle between the orbit position and the target position is smaller than a preset elevation angle from among the satellites included in the integrated conducting constellation; the third determining unit is configured to determine a target satellite in the first communication satellite set to obtain a second communication satellite set, where the target satellite is a preset number of satellites in the first communication satellite set with a smallest geometric factor formed by the target position; the sending unit is configured to send the target position to a satellite in the second set of communication satellites, so that a downlink beam of the satellite in the second set of communication satellites points to the target position within the first preset time period.
Further, the first determination unit is configured to: determining the area to be navigated based on a coverage request of a ground user, wherein the area to be navigated is an area covered at least once by beams of a preset number of communication satellites every preset time within the first preset time period; determining any position in the area to be navigated as the target position.
Further, the first determination unit is configured to perform the following steps: a conversion step of converting the current position vector of the ground user into longitude and latitude high coordinates, wherein PxThe current position vector of the xth ground user is obtained, X is an integer from 1 to X, and X is the number of the ground users; a first determination step, in which a target user in the ground users is determined, and the target user is determined as an initial user, wherein the target user is a ground user corresponding to a longitude and latitude high coordinate with a maximum latitude coordinate and a minimum longitude coordinate in the ground users; a second determination step, wherein the longitude and latitude high coordinate of the intermediate user is determined based on the longitude and latitude high coordinate of the initial user, wherein the longitude and latitude high coordinate of the intermediate user is the longitude and latitude high coordinate of the ground user with the smallest clockwise rotation angle between the longitude increasing direction and the longitude and latitude high coordinate of the initial user; a third determination step, determining the longitude and latitude height coordinate of the intermediate user as the longitude and latitude height coordinate of the initial user; and a first execution step of repeatedly executing the second determination step and the third determination step until the longitude and latitude high coordinate of the intermediate user is the longitude and latitude high coordinate of the target user, and determining the longitude and latitude high coordinate of the target user and the area surrounded by the longitude and latitude high coordinate of the intermediate user to be the area to be navigated.
Further, the second determination unit is configured to: calculating the orbit positions of all the satellites at a target moment, wherein the target moment is (t)2+t1) /2, wherein t1Is the starting time of the first preset time period, t2The ending time of the first preset time period is the ending time of the first preset time period; determining the total satellites based on the on-orbit positions and the target positions of the total satellitesAn elevation angle between the rail position and the target position; and determining the satellites with the elevation angles larger than a preset elevation angle in all the satellites as the initial satellites to obtain the first communication satellite collection.
In the embodiment of the invention, firstly, a target position in a to-be-navigated area within a first preset time period is determined; determining initial satellites in all satellites included in a communication one-body constellation in a first preset time period based on a preset elevation threshold value to obtain a first communication satellite set, wherein the initial satellites are satellites in the communication one-body constellation, and the elevation angle between the orbit position and the target position is smaller than the preset elevation angle; determining target satellites in the first communication satellite set to obtain a second communication satellite set, wherein the target satellites are a preset number of satellites with the smallest geometric factor formed by the first communication satellite set and the target positions; and sending the target position to the satellites in the second communication satellite set so that the downlink beams of the satellites in the second communication satellite set point to the target position within a first preset time period.
In the embodiment of the invention, when a plurality of satellites can cover the same area, due to the fact that how to perform beam scheduling in the prior art, the optimization of the positioning accuracy of a user can be realized by using the minimum number of satellites, the technical problem that the energy utilization rate is low when the integrated navigation constellation is used for navigating the user in the prior art is solved by determining the key position (target position) in a hot spot area (namely an area to be navigated) which needs to be navigated in a first preset time period, determining a preset number of satellites (namely satellites in a second target satellite set) with the minimum geometric factor in the satellites corresponding to the target position, and pointing the downlink beams of the preset number of satellites to the target position in the first preset time period, therefore, the technical effect of improving the energy utilization rate of the navigation integrated constellation when the navigation is performed on the user is achieved.
Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention will be realized and attained by the structure particularly pointed out in the written description and claims hereof as well as the appended drawings.
In order to make the aforementioned and other objects, features and advantages of the present invention comprehensible, preferred embodiments accompanied with figures are described in detail below.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a flowchart of a method for scheduling a turn-on-one constellation beam according to an embodiment of the present invention;
fig. 2 is a flowchart of a method for determining a first target satellite set according to an embodiment of the present invention;
fig. 3 is a flowchart of a method for determining a second target satellite set according to an embodiment of the present invention;
fig. 4 is a schematic diagram of a system for scheduling a general constellation beam according to an embodiment of the present invention.
Detailed Description
To make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The first embodiment is as follows:
according to an embodiment of the present invention, there is provided an embodiment of a method for beamforming a constellation beam, where it is noted that the steps illustrated in the flowchart of the drawings may be performed in a computer system, such as a set of computer-executable instructions, and that although a logical order is illustrated in the flowchart, in some cases, the steps illustrated or described may be performed in an order different than here.
Fig. 1 is a flowchart of a method for scheduling a common constellation beam according to an embodiment of the present invention, as shown in fig. 1, the method includes the following steps:
step S102, determining a target position in a to-be-navigated area within a first preset time period;
step S104, determining initial satellites in all satellites included in a communication integral constellation in the first preset time period to obtain a first communication satellite set, wherein the initial satellites are satellites in the communication integral constellation, and the elevation angle between the orbit position and the target position is smaller than a preset elevation angle threshold value;
step S106, determining a target satellite based on the first communication satellite set to obtain a second communication satellite set, wherein the target satellite is a first preset number of initial satellites with the smallest geometric factor formed by the first communication satellite set and the target position;
step S108, sending the target position to a satellite in the second communication satellite set, so that the downlink beam of the satellite in the second communication satellite set points to the target position within the first preset time period.
In the embodiment of the invention, when a plurality of satellites can cover the same area, due to the fact that how to perform beam scheduling in the prior art, the optimization of the positioning accuracy of a user can be realized by using the minimum number of satellites, the technical problem that the energy utilization rate is low when the integrated navigation constellation is used for navigating the user in the prior art is solved by determining the key position (target position) in a hot spot area (namely an area to be navigated) which needs to be navigated in a first preset time period, determining a preset number of satellites (namely satellites in a second target satellite set) with the minimum geometric factor in the satellites corresponding to the target position, and pointing the downlink beams of the preset number of satellites to the target position in the first preset time period, therefore, the technical effect of improving the energy utilization rate of the navigation integrated constellation when the navigation is performed on the user is achieved.
It should be noted that the above steps S102 to S108 are generally executed by the ground operation control station.
In this embodiment of the present invention, step S102 further includes the following steps:
step S201, determining the area to be navigated based on a coverage request of a ground user, wherein the area to be navigated is an area covered at least once by beams of a second preset number of communication satellites in all satellites every time a preset time period passes within the first preset time period;
it should be noted that, in general, the second predetermined number is greater than 5.
Step S202, determining any position in the area to be navigated as the target position.
In the embodiment of the invention, a ground operation and control station receives a coverage request of a ground user of a communication satellite, wherein the coverage request carries a current position vector of the ground user and a speed vector of the ground user.
Then, the ground operation control calculates a hot spot area P to be covered (i.e., an area to be navigated) according to the current position and the driving speed vector of the user.
S121, assuming that X total ground users exist currently, and the current position vector of the X-th ground user is PxThe current velocity vector is Vx；
S122, the position vector P is processedkConverted into longitude and latitude height coordinate system Lx；
S123, taking the point with the largest latitude from the latitudes and longitudes of all X ground users, and taking the point with the smallest longitude as a starting point (namely, the longitude and latitude height coordinate of the initial user), and recording the point as a0Finding the point of minimum rotation in the clockwise direction along the direction of increasing longitude (i.e., the intermediate user)Longitude and latitude high coordinate) of (a)1；
S124, for m is more than or equal to 1, using aiAs a starting point, a point with the smallest rotation angle in the clockwise direction is searched along the longitude increasing direction and is marked as am+1；
S125, updating m to m +1, repeating S124 to obtain longitude and latitude height coordinates of a plurality of intermediate users, and returning to a0；
S126, from the { a0a1…a0And the closed convex polygon formed by the method is the area to be navigated.
The target position p is defined as0Can be artificially set, and generally, the central point geographical position of the area P to be navigated is selected as the target position P0。
In the embodiment of the present invention, as shown in fig. 2, step S104 further includes the following steps:
step S401, calculating the orbit positions of all the satellites at a target time, wherein the target time is (t)2+t1) /2, wherein t1Is the starting time of the first preset time period, t2The ending time of the first preset time period is the ending time of the first preset time period;
step S402, determining elevation angles between the orbit positions and the target positions of all the satellites based on the orbit positions and the target positions of all the satellites;
step S403, determining a satellite with an elevation angle greater than a preset elevation angle threshold value among all satellites as the initial satellite, and obtaining the first communication satellite set.
In the embodiment of the invention, a preset elevation angle theta is set firstlythreAnd calculating the orbit positions of all the satellites at the target time, wherein the target time is (t)2+t1) /2, wherein t1Is the starting time of the first preset time period, t2And the time is the end time of the first preset time period.
Note that, the preset elevation angle θ is generally setthreIs 10 degrees.
Then, according to the on-orbit positions and the target positions of all the satellites, the elevation angles between the on-orbit positions and the target positions of all the satellites are determined.
And finally, determining the satellites with the elevation angles larger than the preset elevation angle in all the satellites as initial satellites to obtain a first communication satellite collection C1。
In an embodiment of the present invention, as shown in fig. 3, the target satellite includes: a first target satellite and a second target satellite, and step S106 further includes the steps of:
step S601, calculating an azimuth angle between the orbit position of the initial satellite and the target position at the target moment;
step S602, determining the number of first target satellites based on a target correspondence table and the preset number, wherein the number of the first target satellites is the number of zenith satellites corresponding to the preset number of target satellites, and the target correspondence table is used for representing the correspondence among the preset number of target satellites, the zenith satellites and the minimum geometric factor;
step S603, constructing a target matrix based on the azimuth angle between the orbit position of the initial satellite and the target position and the elevation angle between the orbit position of the initial satellite and the target position, wherein the target matrix is a matrix with D being 6(Q-u) × (Q-u), and the ith row and the jth column of elements D of the matrix Di,jThe characteristic azimuth angles are in the interval [ (i-1) × 360/{6(Q-u) }, i × 360/{6(Q-u) }]Within the interval [ (j-1) (90-theta)thre)/(Q-u)，j(90-θthre)/(Q-u)]The number of initial satellites in the satellite array is 1-6 (Q-u), 1-j-Q-u, Q is the first preset number, and u is the number of the first target satellites;
step S604, determining the first target satellite in the target matrix based on a preset search sequence and the number of the first target satellites, wherein the number of the first target satellites is u;
step S605, based on a preset condition, determines the second target satellite in the target matrix.
The number Q of target satellites included in the second set of target satellites is considered to be set, and generally, Q is set to 6 or 8. The larger Q means that the geometric factor is smaller, and the final positioning accuracy is higher, while the larger Q means that the finding of the optimal geometric factor needs a larger amount of calculation, and the constellation size of the communication satellite restricts the value of Q.
In an embodiment of the invention, an azimuth between the in-orbit position of the initial satellite and the target position at the target time is calculated.
Then, the number u of the required first target satellites is determined by inquiring a target corresponding table, and the target corresponding table is as follows:
Figure BDA0002449793180000111
Figure BDA0002449793180000121
then, the initial satellites are grouped by combining the elevation angle between the in-orbit position and the target position of the initial satellite at the target time and the azimuth angle between the in-orbit position and the target position of the initial satellite at the target time, which are calculated in the step S104, and a grouping result is obtained, and then a target matrix is constructed according to the grouping result.
It should be noted that the initial satellites are grouped by the following grouping method: equally divided into 6(Q-u) zones, each zone ranging from 360/{6(Q-u) } degrees in azimuth, and equally divided into (Q-u) zones, each ranging from (90-theta) in elevationthre) V (Q-u) degrees.
And determining the number of the initial satellites contained in each group according to the groups and the azimuth angles and the elevation angles of the initial satellites, and constructing a target matrix according to the number of the initial satellites contained in each group.
It should be noted that the target matrix is a matrix with D being 6(Q-u) × (Q-u), and the ith row and the jth column of the matrix D are elements Di,jThe characteristic azimuth angles are in the interval [ (i-1) × 360/{6(Q-u) }, i × 360/{6(Q-u) }]Within the interval [ (j-1) (90-theta)thre)/(Q-u)，j(90-θthre)/(Q-u)]The number of initial satellites in the first target satellite group is 1-6 (Q-u), 1-j-Q-u, Q is the first preset number, and u is the number of the first target satellites.
And then determining the first target satellite in the target matrix according to a preset search sequence and the number of the first target satellites.
It should be noted that the preset search sequence is from jth1The first row of columns starts with increasing leading number and the following columns decrease in number.
And according to a preset searching sequence, searching u initial satellites with the largest elevation angles in the target matrix, and determining the u initial satellites as u first target satellites.
Note that j is0＝argminjDi,j> 0 (i.e., the smallest number of columns among the number of columns in the object matrix containing an element value of 0 is determined as j0)，j1＝argmaxjDi,j> 0 (i.e., the largest number of columns among the number of columns in the object matrix containing an element value of 0 is determined as j1)。
It should be noted that, assuming that the number of the first target satellites is 3, when 1 first target satellite is determined from the first element of the target matrix, and thus 3 first target satellites are determined from the second element, 1 first target satellite may be determined from the first element, and optionally 2 first target satellites may be determined from the second element, so as to obtain 3 first target satellites.
And finally, determining the second target satellite in the target matrix according to a preset condition.
The method comprises the following specific steps:
a fourth determination step of
Figure BDA0002449793180000131
Then will element
Figure BDA0002449793180000132
Is determined as the second oneTwo target satellites, resulting in (Q-u) second target satellites, wherein i ═ 1,2, …,6, k ═ 0,1, …, (Q-u-1);
a step of calculation, if
Figure BDA0002449793180000133
Then calculate i0＝
Figure BDA0002449793180000134
Obtaining a calculation result, and determining a target value based on the calculation result, wherein the target value is
Figure BDA0002449793180000135
And is
Figure BDA0002449793180000136
The value of time k, j0＝arg minjDi,j＞0，j1＝arg maxjDi,j> 0, mod (i + -1, 6) is used to characterize the remainder of (i + -1)/6;
a fifth determination step of determining the element
Figure BDA0002449793180000137
Determining any initial satellite contained in the satellite data to be an initial target satellite, and determining the number of the initial target satellites, wherein k is the target value;
a sixth determination step of determining the initial target satellite as the second target satellite if the number of the initial target satellites is equal to (Q-u);
a second execution step of j is performed if the number of the second target satellites is less than (Q-u)0Is updated to j0+1, and repeatedly performing the fourth determining step, the calculating step, the fifth determining step, and the sixth determining step until a second target satellite is reached (Q-u).
In the embodiment of the invention, if
Figure BDA0002449793180000141
Then will element
Figure BDA0002449793180000142
Any one initial satellite included in (b) is determined as the second target satellite, and (Q-u) second target satellites are obtained, where i is 1,2, …,6, and k is 0,1, …, (Q-u-1).
It should be noted that, in the following description,
Figure BDA0002449793180000143
for characterizing the i +6k th row, j, in the object matrix0Whether the elevation angle interval and the azimuth angle interval corresponding to the elements of the row contain the initial satellite or not is judged, if so, the initial satellite is included in the elevation angle interval and the azimuth angle interval corresponding to the elements of the row
Figure BDA0002449793180000144
Then line i +6k, j is indicated0The elements of the column correspond to elevation and azimuth intervals that do not include the initial satellite, if
Figure BDA0002449793180000145
Then line i +6k, j is indicated0The initial satellite is contained in the elevation angle interval and the azimuth angle interval corresponding to the elements of the column.
For example, if j of the target matrix is 1 when i0The element values of the elements of the first, seventh, thirteenth up to row 6(Q-u-1) of the column are all 1, then
Figure BDA0002449793180000146
Figure BDA0002449793180000147
Then from the jth of the target matrix0One of the initial satellites included in the elements of the first, seventh, thirteenth, and up to row 6(Q-u-1) of the column is selected to obtain (Q-u) initial satellites (i.e., (Q-u) second target satellites).
If it is
Figure BDA0002449793180000148
Then calculate
Figure BDA0002449793180000149
Obtaining a calculation result, and determining a target value based on the calculation result, wherein the target value is
Figure BDA00024497931800001410
And is
Figure BDA00024497931800001411
The value of time k, j0＝arg minjDi,j＞0，j1＝arg maxjDi,j> 0, mod (i + -1, 6) is used to characterize the remainder of (i + -1)/6;
for example, if j of the target matrix is 1 when i0The values of the elements in the seventh and thirteenth rows among the elements in the first, seventh and thirteenth rows through row 6(Q-u-1) are 0, i0And determining whether the element values of the adjacent row elements of the seventh row and the element values of the adjacent row elements of the thirteenth row are 1, and if so, selecting one initial satellite as the second target satellite from the initial satellites included in the element values of the adjacent row elements of the seventh row and the elements of the adjacent row elements of the twelfth row.
If the element values of the adjacent row elements of the seventh row and the adjacent row elements of the eleventh row are still 0, j is added0Is updated to j0+1, steps S21 through S25 are executed again until (Q-u) second target satellites are determined.
It should be noted that, in general, the (Q-u) second target satellites can be obtained by performing the steps S21 to S25 twice.
In the embodiment of the invention, the method is suitable for a macro-satellite constellation, namely the number of satellites is large, which means that the satellite selection algorithm applied to the traditional navigation constellation is extremely large in calculation amount and is not available. Meanwhile, because the number of visible satellites is huge, in the method, the result can be obtained by repeatedly executing the fourth determining step, the calculating step, the fifth determining step and the sixth determining step for 1 to 2 times, so that the satellite obtained after repeated execution is used as a target satellite, the method can quickly select a satellite set (namely a second communication satellite set) with the optimal geometric distribution and the minimum geometric factor, and the application requirement can be well met.
In addition, for the purpose of calculating the accuracy of the result, the fourth determining step, the calculating step, the fifth determining step, and the sixth determining step may be repeatedly performed until j0+1＝j1Thereby obtaining a plurality of satellites, and then finding (Q-u) satellites with the smallest geometric factor from the plurality of satellites as the second target satellite.
Example two:
the present application further provides an embodiment of a system for scheduling a turn-on-turn constellation beam, as shown in fig. 4, fig. 4 is a schematic diagram of the system for scheduling a turn-on-turn constellation beam according to the embodiment of the present invention.
As shown in fig. 4, the above-mentioned pilot constellation beam scheduling system includes: a first determining unit 10, a second determining unit 20, a third determining unit 30 and a transmitting unit 40.
The first determining unit 10 is configured to determine a target position in the area to be navigated within a first preset time period;
the second determining unit 20 is configured to determine, based on a preset elevation threshold value, an initial satellite from all satellites included in the integrated conducting constellation in the first preset time period to obtain a first communication satellite set, where the initial satellite is a satellite whose elevation angle between the orbit position and the target position is smaller than a preset elevation angle from among the satellites included in the integrated conducting constellation;
the third determining unit 30 is configured to determine a target satellite in the first communication satellite set to obtain a second communication satellite set, where the target satellite is a preset number of satellites in the first communication satellite set with a smallest geometric factor formed by the target position;
the sending unit 40 is configured to send the target position to the satellites in the second set of communication satellites, so that the downlink beams of the satellites in the second set of communication satellites point to the target position within the first preset time period.
In the embodiment of the invention, when a plurality of satellites can cover the same area, due to the fact that how to perform beam scheduling in the prior art, the optimization of the positioning accuracy of a user can be realized by using the minimum number of satellites, the technical problem that the energy utilization rate is low when the integrated navigation constellation is used for navigating the user in the prior art is solved by determining the key position (target position) in a hot spot area (namely an area to be navigated) which needs to be navigated in a first preset time period, determining a preset number of satellites (namely satellites in a second target satellite set) with the minimum geometric factor in the satellites corresponding to the target position, and pointing the downlink beams of the preset number of satellites to the target position in the first preset time period, therefore, the technical effect of improving the energy utilization rate of the navigation integrated constellation when the navigation is performed on the user is achieved.
Preferably, the first determination unit is configured to: determining the area to be navigated based on a coverage request of a ground user, wherein the area to be navigated is an area covered at least once by beams of a preset number of communication satellites every preset time within the first preset time period; determining any position in the area to be navigated as the target position.
Preferably, the coverage request carries a current location vector of the ground user; the first determination unit is configured to perform the following steps: a conversion step of converting the current position vector of the ground user into longitude and latitude high coordinates, wherein PxThe current position vector of the xth ground user is obtained, X is an integer from 1 to X, and X is the number of the ground users; a first determination step, in which a target user in the ground users is determined, and the target user is determined as an initial user, wherein the target user is a ground user corresponding to a longitude and latitude high coordinate with a maximum latitude coordinate and a minimum longitude coordinate in the ground users; a second determination step of determining the longitude and latitude high coordinate of the intermediate user based on the longitude and latitude high coordinate of the initial user, wherein the longitude and latitude high coordinate of the intermediate user is increased in longitudeThe longitude and latitude height coordinate of the ground user with the smallest clockwise rotation angle between the large direction and the longitude and latitude height coordinate of the initial user; a third determination step, determining the longitude and latitude height coordinate of the intermediate user as the longitude and latitude height coordinate of the initial user; and a first execution step of repeatedly executing the second determination step and the third determination step until the longitude and latitude high coordinate of the intermediate user is the longitude and latitude high coordinate of the target user, and determining the longitude and latitude high coordinate of the target user and the area surrounded by the longitude and latitude high coordinate of the intermediate user to be the area to be navigated.
Preferably, the second determination unit is configured to: calculating the orbit positions of all the satellites at a target moment, wherein the target moment is (t)2+t1) /2, wherein t1Is the starting time of the first preset time period, t2The ending time of the first preset time period is the ending time of the first preset time period; determining elevation angles between the on-orbit positions and the target positions of all the satellites based on the on-orbit positions and the target positions of all the satellites; and determining the satellites with the elevation angles larger than a preset elevation angle in all the satellites as the initial satellites to obtain the first communication satellite collection.
Preferably, the target satellites include a first target satellite and a second target satellite, the third determining unit is used for calculating an azimuth angle between an orbit position of the initial satellite and the target position at the target moment, determining the number of first target satellites based on a target correspondence table and the preset number, wherein the number of the first target satellites is the number of zenith satellites corresponding to the preset number of target satellites, the target correspondence table is used for representing the correspondence among the preset number of target satellites, the zenith satellites and the minimum geometric factor, and constructing a target matrix based on the azimuth angle between the orbit position of the initial satellite and the target position and the elevation angle between the orbit position of the initial satellite and the target position, the target matrix is a matrix with D being 6(Q-u) × (Q-u), and the ith row and jth column element D of the matrix Di,jThe characteristic azimuth angles are in the interval [ (i-1) × 360/{6(Q-u) }, i × 360/{6(Q-u)}]Within the interval [ (j-1) (90-theta)thre)/(Q-u)，j(90-θthre)/(Q-u)]The number of initial satellites in the satellite array is 1-6 (Q-u), 1-j-Q-u, Q is the first preset number, and u is the number of the first target satellites; determining the first target satellite in the target matrix based on a preset search sequence and the number of the first target satellites; and determining the second target satellite in the target matrix based on a preset condition.
Preferably, the third determining unit is configured to perform the following steps: a fourth determination step of
Figure BDA0002449793180000181
Then will element
Figure BDA0002449793180000182
Any one initial satellite included in (1) is determined as the second target satellite, and Q-u second target satellites are obtained, wherein i is 1,2, …,6, and k is 0,1, …, (Q-u-1); a step of calculation, if
Figure BDA0002449793180000183
Figure BDA0002449793180000184
Then calculate
Figure BDA0002449793180000185
Obtaining a calculation result, and determining a target value based on the calculation result, wherein the target value is
Figure BDA0002449793180000186
And is
Figure BDA0002449793180000187
The value of time k, j0＝arg minjDi,j＞0，j1＝arg maxjDi,j> 0, mod (i + -1, 6) +6k is used to characterize the remainder of (i + -1)/6; a fifth determination step of determining the element
Figure BDA0002449793180000188
Determining any initial satellite contained in the satellite data to be an initial target satellite, and determining the number of the initial target satellites, wherein k is the target value; a sixth determination step of determining the initial target satellite as the second target satellite if the number of the initial target satellites is equal to (Q-u); a second execution step of, if the number of the second targets is less than (Q-u), dividing j0Is updated to j0+1, and repeating the fourth determining step, the calculating step, the fifth determining step, and the sixth determining step until (Q-u) second target satellites are determined.
In addition, in the description of the embodiments of the present invention, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In the description of the present invention, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc., indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience in describing the present invention and simplifying the description, but do not indicate or imply that the system or element being referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the several embodiments provided in this application, it should be understood that the disclosed system, and method may be implemented in other ways. The above-described system embodiments are merely illustrative, and for example, the division of the units is only one logical functional division, and there may be other divisions in actual implementation, and for example, a plurality of units or components may be combined or integrated into another system, or some features may be omitted, or not executed. In addition, the shown or discussed mutual coupling or direct coupling or communication connection may be an indirect coupling or communication connection of systems or units through some communication interfaces, and may be in an electrical, mechanical or other form.
The units described as separate parts may or may not be physically separate, and parts displayed as units may or may not be physical units, may be located in one place, or may be distributed on a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment.
In addition, functional units in the embodiments of the present invention may be integrated into one processing unit, or each unit may exist alone physically, or two or more units are integrated into one unit.
Finally, it should be noted that: the above-mentioned embodiments are only specific embodiments of the present invention, which are used for illustrating the technical solutions of the present invention and not for limiting the same, and the protection scope of the present invention is not limited thereto, although the present invention is described in detail with reference to the foregoing embodiments, those skilled in the art should understand that: any person skilled in the art can modify or easily conceive the technical solutions described in the foregoing embodiments or equivalent substitutes for some technical features within the technical scope of the present disclosure; such modifications, changes or substitutions do not depart from the spirit and scope of the embodiments of the present invention, and they should be construed as being included therein. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims (10)

1. A method for scheduling a general-purpose constellation beam, comprising:
determining the target position in the area to be navigated within a first preset time period, wherein the corresponding areas to be navigated within different preset time periods are different;
determining initial satellites in all satellites included in the all-in-one constellation in the first preset time period to obtain a first communication satellite set, wherein the initial satellites are satellites in the all-in-one constellation, and the elevation angles between the orbit positions and the target positions of the all-in-one constellation are smaller than a preset elevation angle threshold value;
determining a target satellite based on the first communication satellite set to obtain a second communication satellite set, wherein the target satellite is a first preset number of initial satellites with the smallest geometric factor formed by the first communication satellite set and the target position;
and sending the target position to a satellite in the second communication satellite set, so that a downlink beam of the satellite in the second communication satellite set points to the target position within the first preset time period.
2. The method of claim 1, wherein determining the target location in the area to be navigated within the first preset time period comprises:
determining the area to be navigated based on a coverage request of a ground user, wherein the area to be navigated is an area covered at least once by beams of a second preset number of communication satellites in all the satellites every time a preset time period passes within the first preset time period;
determining any position in the area to be navigated as the target position.
3. The method of claim 2, wherein the coverage request carries a current location vector of the ground user;
determining the area to be navigated based on the coverage request of the ground user, including:
a conversion step of converting the current position of the ground userThe vector is converted into a longitude and latitude high coordinate, wherein PxThe current position vector of the xth ground user is obtained, X is an integer from 1 to X, and X is the number of the ground users;
a first determination step, in which a target user in the ground users is determined, and the target user is determined as an initial user, wherein the target user is a ground user corresponding to a longitude and latitude high coordinate with a maximum latitude coordinate and a minimum longitude coordinate in the ground users;
a second determination step, wherein the longitude and latitude high coordinate of the intermediate user is determined based on the longitude and latitude high coordinate of the initial user, wherein the longitude and latitude high coordinate of the intermediate user is the longitude and latitude high coordinate of the ground user with the smallest clockwise rotation angle between the longitude increasing direction and the longitude and latitude high coordinate of the initial user;
a third determination step, determining the longitude and latitude height coordinate of the intermediate user as the longitude and latitude height coordinate of the initial user;
and a first execution step of repeatedly executing the second determination step and the third determination step until the longitude and latitude high coordinate of the intermediate user is the longitude and latitude high coordinate of the target user, and determining the longitude and latitude high coordinate of the target user and the area surrounded by the longitude and latitude high coordinate of the intermediate user to be the area to be navigated.
4. The method of claim 1, wherein determining an initial satellite among all satellites included in the constellation that are conducted within the first predetermined time period to obtain a first communication satellite set, and obtaining the first communication satellite set comprises:
calculating the orbit positions of all the satellites at a target moment, wherein the target moment is (t)2+t1) /2, wherein t1Is the starting time of the first preset time period, t2The ending time of the first preset time period is the ending time of the first preset time period;
determining elevation angles between the on-orbit positions and the target positions of all the satellites based on the on-orbit positions and the target positions of all the satellites;
and determining the satellite with the elevation angle larger than a preset elevation angle threshold value in all the satellites as the initial satellite to obtain the first communication satellite collection.
5. The method of claim 4, wherein the target satellite comprises: a first target satellite and a second target satellite;
determining a target satellite in the first communication satellite collection to obtain a second communication satellite collection, including:
calculating an azimuth between the in-orbit position of the initial satellite and the target position at the target time;
determining the number of first target satellites based on a target correspondence table and the preset number, wherein the number of the first target satellites is the number of zenith satellites corresponding to the preset number of target satellites, and the target correspondence table is used for representing the correspondence among the preset number of target satellites, the zenith satellites and the minimum geometric factor;
constructing an object matrix based on an azimuth angle between the orbit position and the target position of the initial satellite and an elevation angle between the orbit position and the target position of the initial satellite, wherein the object matrix is a matrix with D being 6(Q-u) × (Q-u), and an ith row and a jth column element D of the matrix Di，jThe characteristic azimuth angles are in the interval [ (i-1) × 360/{6(Q-u) }, i × 360/{6(Q-u) }]Within the interval [ (j-1) (90-theta)thre)/(Q-u)，j(90-θthre)/(Q-u)]The number of initial satellites in the satellite array is 1-6 (Q-u), 1-j-Q-u, Q is the first preset number, and u is the number of the first target satellites;
determining the first target satellite in the target matrix based on a preset search sequence and the number of the first target satellites;
and determining the second target satellite in the target matrix based on a preset condition.
6. The method of claim 5, wherein determining the second target satellite in the target matrix based on a preset condition comprises:
a fourth determination step of
Figure FDA0002449793170000031
Then will element
Figure FDA0002449793170000032
Wherein, i is 1,2, 6, k is 0,1, 6, (Q-u-1);
a step of calculation, if
Figure FDA0002449793170000041
Then calculate
Figure FDA0002449793170000042
Figure FDA0002449793170000043
Obtaining a calculation result, and determining a target value based on the calculation result, wherein the target value is
Figure FDA0002449793170000044
And is
Figure FDA0002449793170000045
The value of time k, j0＝arg minjDi，j＞0，j1＝arg maxjDi，j> 0, mod (i + -1, 6) is used to characterize the remainder of (i + -1)/6;
a fifth determination step of determining the element
Figure FDA0002449793170000046
Determining any initial satellite contained in the satellite data to be an initial target satellite, and determining the number of the initial target satellites, wherein k is the target value;
a sixth determination step of determining the initial target satellite as the second target satellite if the number of the initial target satellites is equal to (Q-u);
a second execution step of j is performed if the number of the second target satellites is less than (Q-u)0Is updated to j0+1, and repeating the fourth determining step, the calculating step, the fifth determining step, and the sixth determining step until (Q-u) second target satellites are determined.
7. A system for scheduling a pilot-integrated constellation beam, comprising: a first determining unit, a second determining unit, a third determining unit and a transmitting unit, wherein,
the first determining unit is used for determining the target position in the area to be navigated within a first preset time period, wherein the corresponding areas to be navigated within different preset time periods are different;
the second determining unit is configured to determine, based on a preset elevation threshold value, an initial satellite from all satellites included in the integrated conducting constellation in the first preset time period to obtain a first communication satellite set, where the initial satellite is a satellite whose elevation angle between the orbit position and the target position is smaller than the preset elevation threshold value from among the satellites included in the integrated conducting constellation;
the third determining unit is configured to determine a target satellite in the first communication satellite set to obtain a second communication satellite set, where the target satellite is a first preset number of initial satellites in the first communication satellite set, where the first preset number of initial satellites is the smallest in geometric factor with the target position;
the sending unit is configured to send the target position to a satellite in the second set of communication satellites, so that a downlink beam of the satellite in the second set of communication satellites points to the target position within the first preset time period.
8. The system of claim 7, wherein the first determination unit is configured to:
determining the area to be navigated based on a coverage request of a ground user, wherein the area to be navigated is an area covered at least once by beams of a second preset number of communication satellites in all the satellites every time a preset time period passes within the first preset time period;
determining any position in the area to be navigated as the target position.
9. The system of claim 8, wherein the coverage request carries a current location vector of the ground user; the first determination unit is configured to perform the following steps:
a conversion step of converting the current position vector of the ground user into longitude and latitude high coordinates, wherein PxThe current position vector of the xth ground user is obtained, X is an integer from 1 to X, and X is the number of the ground users;
a first determination step, in which a target user in the ground users is determined, and the target user is determined as an initial user, wherein the target user is a ground user corresponding to a longitude and latitude high coordinate with a maximum latitude coordinate and a minimum longitude coordinate in the ground users;
a second determination step, wherein the longitude and latitude high coordinate of the intermediate user is determined based on the longitude and latitude high coordinate of the initial user, wherein the longitude and latitude high coordinate of the intermediate user is the longitude and latitude high coordinate of the ground user with the smallest clockwise rotation angle between the longitude increasing direction and the longitude and latitude high coordinate of the initial user;
a third determination step, determining the longitude and latitude height coordinate of the intermediate user as the longitude and latitude height coordinate of the initial user;
and a first execution step of repeatedly executing the second determination step and the third determination step until the longitude and latitude high coordinate of the intermediate user is the longitude and latitude high coordinate of the target user, and determining the longitude and latitude high coordinate of the target user and the area surrounded by the longitude and latitude high coordinate of the intermediate user to be the area to be navigated.
10. The system of claim 7, wherein the second determination unit is configured to:
calculating the orbit positions of all the satellites at a target moment, wherein the target moment is (t)2+t1) /2, wherein t1Is the starting time of the first preset time period, t2The ending time of the first preset time period is the ending time of the first preset time period;
determining elevation angles between the on-orbit positions and the target positions of all the satellites based on the on-orbit positions and the target positions of all the satellites;
and determining the satellite with the elevation angle larger than a preset elevation angle threshold value in all the satellites as the initial satellite to obtain the first communication satellite collection.
CN202010292714.XA 2020-04-14 2020-04-14 Method and system for scheduling communication-guide integrated constellation beams Active CN111464940B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202010292714.XA CN111464940B (en) 2020-04-14 2020-04-14 Method and system for scheduling communication-guide integrated constellation beams

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202010292714.XA CN111464940B (en) 2020-04-14 2020-04-14 Method and system for scheduling communication-guide integrated constellation beams

Publications (2)

Publication Number Publication Date
CN111464940A true CN111464940A (en) 2020-07-28
CN111464940B CN111464940B (en) 2021-03-30

Family

ID=71679065

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202010292714.XA Active CN111464940B (en) 2020-04-14 2020-04-14 Method and system for scheduling communication-guide integrated constellation beams

Country Status (1)

Country Link
CN (1) CN111464940B (en)

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103532611A (en) * 2013-10-17 2014-01-22 中国人民解放军理工大学 Mixed orbit IGSO (inclined geosynchronous satellite orbit) constellation capable of covering target area and global scale
CN106656330A (en) * 2017-01-21 2017-05-10 航天恒星科技有限公司 Spatial optical communication method and spatial optical communication system
CN108234012A (en) * 2016-12-12 2018-06-29 波音公司 Accelerate satellite acquisition scheme
CN110208822A (en) * 2019-05-28 2019-09-06 西安空间无线电技术研究所 A kind of communication means based on low rail moving communication satellite
US20200007604A1 (en) * 2015-02-10 2020-01-02 Viasat, Inc. Transport path-aware quality of service for mobile communications
CN110927751A (en) * 2019-12-09 2020-03-27 中国电子科技集团公司第五十四研究所 Array antenna self-adaptive correction implementation method based on carrier phase measurement

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103532611A (en) * 2013-10-17 2014-01-22 中国人民解放军理工大学 Mixed orbit IGSO (inclined geosynchronous satellite orbit) constellation capable of covering target area and global scale
US20200007604A1 (en) * 2015-02-10 2020-01-02 Viasat, Inc. Transport path-aware quality of service for mobile communications
CN108234012A (en) * 2016-12-12 2018-06-29 波音公司 Accelerate satellite acquisition scheme
CN106656330A (en) * 2017-01-21 2017-05-10 航天恒星科技有限公司 Spatial optical communication method and spatial optical communication system
CN110208822A (en) * 2019-05-28 2019-09-06 西安空间无线电技术研究所 A kind of communication means based on low rail moving communication satellite
CN110927751A (en) * 2019-12-09 2020-03-27 中国电子科技集团公司第五十四研究所 Array antenna self-adaptive correction implementation method based on carrier phase measurement

Also Published As

Publication number Publication date
CN111464940B (en) 2021-03-30

Similar Documents

Publication Publication Date Title
CN111431585B (en) Access method and device of large-scale NGSO satellite constellation
US9716547B2 (en) Method and apparatus for beam selection for a multibeam, multi-satellite communications system
CN101631349B (en) Method, device and wireless operation maintenance center for positioning terminal
CN108493611A (en) Antenna for satellite communication in motion and telecommunication satellite fast alignment device, method and system
CN115001567B (en) Beidou short message communication resource planning method and device
CN113411149B (en) Low-orbit satellite mobile communication ground experiment system
CN108919174B (en) Short wave radio direction finding system and method of irregular antenna array structure
CN105165078A (en) Locating method and device
CN112039564B (en) Satellite large-scale MIMO wide-coverage pre-coding transmission method
EP4012941A1 (en) Method and apparatus for beam selection for a multibeam, multi-satellite communications system
CN113051743A (en) Terminal guidance system based on track online planning
CN111464940B (en) Method and system for scheduling communication-guide integrated constellation beams
CN111417205A (en) Method for broadcasting downlink signaling by using dynamic spot beam and satellite system
CN109459016B (en) Micro-nano satellite cluster relative positioning method based on position fingerprints
CN111366953A (en) Beidou Ka complex phased array antenna tracking visible report generation algorithm
KR102545275B1 (en) Apparatus and method for generating revising information of sattellite location coordinates using optimal information of virtual reference station
WO2017190441A1 (en) Positioning method and apparatus and positioning device
CN117254847B (en) Quick satellite searching method and device for low-orbit satellite terminal
CN109037969B (en) A kind of structure the formation method and the cloth array 1 system of satellite antenna for satellite communication in motion array
CN116165651A (en) Light and small SAR satellite flat fly mode construction method and system
JP2004088443A (en) Method and system for transmitting power by microwave
US20160359537A1 (en) System and Method for Providing a Distributed Directional Aperture for Cellular Communication
CN113872678A (en) Intra-satellite terminal mobility management method
WO2020066470A1 (en) Interference power estimation method, interference power estimation device, and program
CN213028045U (en) Auxiliary satellite alignment device for antenna

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant