CN116800330A - Quick satellite aligning method and device - Google Patents
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Abstract
The invention discloses a quick satellite alignment method and a quick satellite alignment device, which firstly utilize satellite signal intensity average values in four directions of a two-dimensional rectangular coordinate system to estimate a quadrant where a target satellite is located, then utilize the maximum value and the secondary maximum value of the signal intensity of each point satellite in the quadrant to further judge the position where the target satellite is located, and compared with the existing cross scanning method which uses the maximum value of the signal intensity of the satellite scanned last time as a new scanning origin, the satellite searching time is greatly shortened, and the satellite searching precision is improved. The last searching step length and the next searching step length are not fixed, the next searching step length is estimated according to the distance between the maximum intensity point position and the maximum intensity point position in the last searching, the variable step length gives consideration to the star time length and the star precision, and the star efficiency is greatly improved.
Description
Technical Field
The invention belongs to the technical field of scanning satellite alignment, and particularly relates to a rapid satellite alignment method and device.
Background
The satellite alignment refers to a process of controlling a satellite terminal antenna to achieve alignment with a target satellite through a certain algorithm. In the prior art, a cross scanning method and a Chinese character 'Hui' shape scanning are common star alignment algorithms.
The cross scanning method is to scan and record AGC voltage value of each point from azimuth axis, compare with last recorded voltage value after each time recording, if this time voltage value is bigger than last voltage value, then continue forward, if this time voltage value is smaller than last voltage value, find maximum value on azimuth axis, then convert into pitch axis of the point, find maximum value point on pitch axis according to the principle, finally determine maximum value point in observable threshold value range is the position with highest signal transmission quality.
The character returning scanning is to scan the azimuth to the range limit value of the azimuth, then scan the azimuth to the range limit value of the azimuth in a pitching mode, shorten the scanning length after one period, scan the center successively until all positions are traversed, record the AGC voltage value of the beacon one by one and compare the AGC voltage value to find the maximum value.
The cross scan method does not achieve a complete scan, and since the cross scan method is based on the principle of finding maxima, the accuracy of the method is questionable. The character returning scanning needs to completely scan all the regions with the observable threshold value once, the time spent is long, the efficiency is low, and the requirement of the system on the rapidity cannot be met.
Disclosure of Invention
The invention aims to solve the problems of low scanning efficiency and long time consumption of the existing scanning satellite alignment method, and provides a rapid satellite alignment method and device which can rapidly judge the approximate azimuth of a satellite target relative to the pointing position of a current antenna, thereby greatly reducing the searching time of the satellite target and improving the satellite alignment efficiency.
The technical scheme of the invention is as follows: in a first aspect, the present invention provides a method for fast aligning satellites, comprising the steps of:
s1, constructing an initial two-dimensional rectangular coordinate system by taking the current antenna beam pointing position as an origin coordinate, and setting a first preset step lengthL 1 As the current search step.
S2, searching the target satellite signals along positive and negative directions of an x axis and a y axis of the current two-dimensional rectangular coordinate system respectively according to the current searching step length, and obtaining the multi-point target satellite signal intensity value.
And S3, estimating the position of the target satellite in the current two-dimensional rectangular coordinate system according to the signal intensity value of the multi-point target satellite.
And S4, estimating the origin coordinates, the x-axis direction and the y-axis direction of a two-dimensional rectangular coordinate system searched for the star next time.
S5, estimating the next searching step length of the star.
S6, judging whether the star aligning process meets the stopping condition, if so, ending the star aligning, otherwise, returning to the step S2 to perform next star aligning search.
Further, the method for searching the target satellite signal in step S2 includes: and respectively searching target satellite signals in the x-axis positive direction, the x-axis negative direction, the y-axis positive direction and the y-axis negative direction at the positions of 1 time of the current searching step length and 2 times of the current searching step length, namely respectively searching two points in the four directions of the current two-dimensional rectangular coordinate system, and adding the original points to form 9-point target satellite signal searching.
Further, the method for searching the target satellite signal in step S2 includes: and respectively searching target satellite signals in the x-axis positive direction, the x-axis negative direction, the y-axis positive direction and the y-axis negative direction at the positions of 1 time of the current searching step length, 2 times of the current searching step length and 3 times of the current searching step length, namely respectively performing three-point position searching in the four directions of the current two-dimensional rectangular coordinate system, and adding the original point positions, thereby forming the 13-point position target satellite signal searching.
Further, the target satellite signal in step S2 is a DVB signal and/or a beacon signal.
Further, the method for acquiring the multi-point target satellite signal intensity value in step S2 includes:
when the target satellite signal is a DVB signal or a beacon signal, the target satellite signal intensity value of each point position is the DVB signal intensity value or the beacon signal intensity value of the antenna at the point position.
When the target signal includes both DVB signal and DVB signalIn the case of a beacon signal, the target signal strength value for each point locationI w The method comprises the following steps:
；
wherein the method comprises the steps ofI D For the DVB signal strength value for that point location,I B for the beacon signal strength value for that point location,w D is a weighting coefficient for the DVB signal strength value,w B is a weighting coefficient for the beacon signal strength value,w D +w B =1。
further, step S3 includes the following sub-steps:
s31, calculating the average value of the satellite signal intensity in each axial direction according to the multi-point target satellite signal intensity value.
S32, sorting the satellite signal intensity average values in the directions of all axes, and estimating the quadrant of the target satellite according to the maximum value and the secondary maximum value of the sorting result.
S33, sequencing the satellite signal intensity values of the quadrants, and estimating the position of the target satellite in the current two-dimensional rectangular coordinate system.
Further, step S4 specifically includes:
according to the point position coordinates of maximum value and sub-maximum value of satellite signal intensityx 1 , y 1 ) And%x 2 , y 2 ) Calculating to obtain the origin coordinate of the two-dimensional rectangular coordinate system of the next star searchx i , y i )：
；
Wherein, I 1 、I 2 respectively is the point location [ (]x 1 , y 1 ) And%x 2 , y 2 ) Is set for the satellite signal strength values of (a),L 1,2 is the point location%x 1 , y 1 ) And%x 2 , y 2 ) The distance between the two plates is set to be equal,L i1, is the point location%x 1 , y 1 ) The origin coordinate of the two-dimensional rectangular coordinate system searched for the next starx i , y i ) The distance between the two plates is set to be equal,L i2, is the point location%x 2 , y 2 ) The origin coordinate of the two-dimensional rectangular coordinate system searched for the next starx i , y i ) The distance between the two plates is set to be equal,is the point location%x 1 , y 1 ) And%x 2 , y 2 ) And the included angle between the connecting line of the (C) and the y-axis of the two-dimensional coordinate system of the current star search.
In terms of coordinates [ (]x i , y i ) As the origin of the two-dimensional rectangular coordinate system for searching the star next time, to achieve the followingx 1 , y 1 ) And%x 2 , y 2 ) The direction perpendicular to the connecting line direction is used as the x axis of the two-dimensional rectangular coordinate system of the next star search, and the direction perpendicular to the connecting line direction is used as the y axis of the two-dimensional rectangular coordinate system of the next star search.
Further, the next search step for stars in step S5L i+1 The calculation formula of (2) is as follows:
；
wherein min (. Cndot.) represents taking the minimum value.
Further, the stop condition in step S6 is:
；
wherein the method comprises the steps ofR ant Representing the minimum scan resolution of the antenna.
In a second aspect, the present invention provides a fast satellite aligning device, including an antenna main body, an antenna driving device, and an antenna controller.
The antenna body is used for realizing communication with a target satellite.
The antenna driving device is used for adjusting the posture of the antenna main body and realizing the alignment of the antenna main body and the target satellite.
The antenna controller is used for demodulating the received signal from the antenna main body and providing corresponding control instructions for the antenna driving device so as to execute the steps of the rapid satellite alignment method.
The beneficial effects of the invention are as follows:
(1) The invention firstly utilizes the satellite signal intensity average value in four directions of the two-dimensional rectangular coordinate system to estimate the quadrant where the target satellite is located, and then utilizes the maximum value and the secondary maximum value of the satellite signal intensity of each point of the quadrant to further judge the position where the target satellite is located.
(2) The last searching step length and the next searching step length are not fixed, the next searching step length is estimated according to the distance between the maximum intensity point position and the maximum intensity point position in the last searching, the variable step length gives consideration to the star time length and the star precision, and the star efficiency is greatly improved.
Drawings
Fig. 1 is a flowchart of a fast satellite alignment method according to an embodiment of the present invention.
Fig. 2 is a schematic diagram of 9-point target satellite signal search according to an embodiment of the present invention.
FIG. 3 shows the origin coordinates of the two-dimensional rectangular coordinate system for the next star search according to the embodiment of the present inventionx i , y i ) A schematic is determined.
Detailed Description
Exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It is to be understood that the embodiments shown and described in the drawings are merely illustrative of the principles and spirit of the invention and are not intended to limit the scope of the invention.
Embodiment one:
the embodiment of the invention provides a rapid satellite aligning method, which comprises the following steps S1-S6 as shown in FIG. 1:
s1, constructing an initial two-dimensional rectangular coordinate system by taking the current antenna beam pointing position as an origin coordinate, and setting a first preset step lengthL 1 As the current search step.
In the embodiment of the invention, the antenna can be a common antenna or a phased array antenna.
In the embodiment of the present invention, the x-axis and y-axis directions of the initial two-dimensional rectangular coordinate system should be determined according to practical situations, for example, when the antenna is a phased array rectangular panel antenna, the x-axis and y-axis directions of the two-dimensional rectangular coordinate system may be kept consistent with the length and width directions of the rectangle, or the x-axis and y-axis directions of the two-dimensional rectangular coordinate system may be kept consistent with the width and length directions of the rectangle, respectively.
In the embodiment of the invention, a first preset step lengthL 1 The value obtaining method of (a) includes various methods, such as selecting the value of the first preset step according to an empirical value, or selecting the first preset step according to a calibration relation between the target satellite signal strength and the antenna pointing deviation angle obtained in advance, which is not limited herein.
S2, respectively along the positive and negative directions of the x axis and the y axis of the current two-dimensional rectangular coordinate system, and using the current searching step lengthL i And searching the target satellite signals to obtain the multi-point target satellite signal intensity values.
In the embodiment of the invention, when the star alignment is executed for the first time, the current two-dimensional rectangular coordinate system is the initial two-dimensional rectangular coordinate system, and the current searching step lengthL i For a first preset step lengthL 1 Starting from the second star alignment, the current two-dimensional rectangular coordinate system and the current searching step lengthL i And the method is obtained through estimation in the last satellite time matching steps S4-S5.
In the embodiment of the invention, the method for searching the target satellite signals can adopt 9-point target satellite signal searching and can also adopt 13-point target satellite signal searching.
The 9-point target satellite signal searching method comprises the following steps: in the x-axis positive direction, the x-axis negative direction, the y-axis positive direction, and the y-axis negative direction, the current search step length (1L i ) And 2 times the current search step (2L i ) The target satellite signal search is performed at the positions of the two-dimensional rectangular coordinate system, that is, two-point search is performed at the four directions of the current two-dimensional rectangular coordinate system, and the original point is added, so that the 9-point target satellite signal search is formed, as shown in fig. 2.
The method for searching the 13-point target satellite signals comprises the following steps: in the x-axis positive direction, the x-axis negative direction, the y-axis positive direction, and the y-axis negative direction, the current search step length (1L i ) 2 times the current search step (2L i ) And 3 times the current search step (3L i ) The target satellite signal search is respectively carried out on the positions of the two-dimensional rectangular coordinate system, namely three-point position search is respectively carried out on the four directions of the current two-dimensional rectangular coordinate system, and the original point positions are added, so that the 13-point position target satellite signal search is formed.
In the embodiment of the invention, the target satellite signal is preferably a DVB signal, can be a beacon signal, and can also be a DVB signal and a beacon signal.
In the embodiment of the present invention, the target satellite signal strength value of each point location should be determined according to a specific target satellite signal form. For example, when the target satellite signal is a DVB signal or a beacon signal, the target satellite signal strength value for each point is the DVB signal strength value or the beacon signal strength value for the antenna at that point. When the target signal includes both the DVB signal and the beacon signal, the target signal strength value for each point locationI w The method comprises the following steps:
；
wherein the method comprises the steps ofI D For the DVB signal strength value for that point location,I B for the beacon signal strength value for that point location,w D for DVB signalsThe weighting coefficients of the intensity values are such that,w B is a weighting coefficient for the beacon signal strength value,w D +w B =1. Weighting coefficientw D 、w B The specific values of (a) are chosen according to the specific capabilities of the DVB component and the beacon component in the antenna, e.g., when the DVB component and the beacon component have the same detection accuracy,w D 、w B can be selected to be 0.5; when the detection accuracy of the DVB component is better than the beacon component,w D selected to be greater thanw B The method comprises the steps of carrying out a first treatment on the surface of the When the detection accuracy of the beacon component is better than that of the DVB component,w B selected to be greater thanw D 。
And S3, estimating the position of the target satellite in the current two-dimensional rectangular coordinate system according to the signal intensity value of the multi-point target satellite.
In the embodiment of the invention, the step S3 includes the following substeps S31 to S33:
s31, calculating the average value of the satellite signal intensity in each axial direction according to the multi-point target satellite signal intensity value.
In the embodiment of the invention, taking a 9-point target satellite signal searching mode as an example, assume that the current searching step length (1L i ) 2 times the current search step (2L i ) The satellite signal intensity values of (a) are respectivelyI x+1 、I x+2 The negative x-axis direction is 1 times the current search step (1L i ) 2 times the current search step (2L i ) The satellite signal intensity values of (a) are respectivelyI x-1 、I x-2 The positive y-axis direction is 1 times the current search step (1L i ) 2 times the current search step (2L i ) The satellite signal intensity values of (a) are respectivelyI y+1 、I y+2 The y-axis negative direction is 1 times the current search step (1L i ) 2 times the current search step (2L i ) The satellite signal intensity values of (a) are respectivelyI y-1 、I y-2 According toI x+1 、I x+2 、I x-1 、I x-2 、I y+1 、I y+2 、I y-1 、I y-2 Calculating the average value of satellite signal intensity in the positive direction of the x-axisMean value of satellite signal intensity in negative x-axis direction +.>Mean value of satellite signal intensity in positive y-axis direction +.>And the satellite signal intensity average value in the negative y-axis direction +.>：
；
S32, sorting the satellite signal intensity average values in the directions of all axes, and estimating the quadrant of the target satellite according to the maximum value and the secondary maximum value of the sorting result.
In the embodiment of the invention, the pair、/>、/>、/>And sorting according to the sizes, and estimating the quadrant of the target satellite according to the sorted maximum value and the sub-maximum value.
For example, when the maximum and the sub-maximumRespectively is、/>Indicating that the target satellite is in the fourth quadrant of the current two-dimensional rectangular coordinate system; other inexhaustible cases and so on.
S33, sequencing the satellite signal intensity values of the quadrants, and estimating the position of the target satellite in the current two-dimensional rectangular coordinate system.
In step S32, only the quadrant in which the target satellite is located can be estimated, and in order to further determine the position of the target satellite in the current two-dimensional coordinate system, the determined satellite signal intensity values in the quadrant can be further ranked, and then the position of the target satellite is determined according to the ranking result.
Specifically, the maximum value and the sub-maximum value in the step S32 are respectively、/>For example, the target satellite is shown in the first quadrant of the current two-dimensional rectangular coordinate system. For the origin position coordinates in the first quadrant regionI 00 、I x+1 、I x+2 、I y+1 、I y+2 And sorting, and determining the position of the target satellite according to the maximum value and the secondary maximum value of the sorting result.
Illustratively, when the maximum and the sub-maximum are respectivelyI 00 、I y+1 When the target satellite is positioned in the positive y-axis direction of the current two-dimensional rectangular coordinate system, the target satellite can be determined; further, (0, 0) and (0, 1) of the target satellite in the y-axis positive direction can be determinedL i ) Between them; further, (0, 0) and (0, 1) of the target satellite in the y-axis positive direction can be determinedL i ) A position on the side closer to the origin.
Exemplary embodimentsWhen the maximum value and the sub-maximum value are respectivelyI x+1 、I y+1 The method comprises the steps that the positive x-axis direction and the positive y-axis direction of a first quadrant of a current two-dimensional rectangular coordinate system can be determined, wherein a target satellite is not located in the positive x-axis direction and the positive y-axis direction of the first quadrant of the current two-dimensional rectangular coordinate system; further, it may be determined that the target satellite is located at the position of the satellite selected from the group consisting of (0, 0), (0, 1L i ），（1L i ,0），（1L i ,1L i ) In the square area formed; still further, it may be determined that the target satellite is located at the position of the satellite defined by (0, 1L i ）），（1L i ,0），（1L i ,1L i ) In the triangular region of the formation.
Other inexhaustible conditions may be similarly inferred.
The above embodiment provides a specific implementation method of the 9-point target satellite signal searching method, and it should be understood that the specific implementation method of the 13-point target satellite signal searching method is similar to the above, and will not be described herein.
And S4, estimating the origin coordinates, the x-axis direction and the y-axis direction of a two-dimensional rectangular coordinate system searched for the star next time.
In practice, the search for large areas is usually not performed in small steps initially, as this takes a long time and is quite inefficient.
In the embodiment of the invention, the large area search is performed with a larger step length, and then the small step length is further searched in the reduced area, and the process is repeated until the star stopping condition is met. In this process, the origin coordinates and the search step length of the two-dimensional rectangular coordinate system of the next pair of satellites need to be determined.
As shown in FIG. 3, in the embodiment of the invention, the point position coordinates of the maximum value and the secondary maximum value of the satellite signal intensity are calculated according to the point position coordinatesx 1 , y 1 ) And%x 2 , y 2 ) Calculating to obtain the origin coordinate of the two-dimensional rectangular coordinate system of the next star searchx i , y i )：
；
Wherein, I 1 、I 2 respectively is the point location [ (]x 1 , y 1 ) And%x 2 , y 2 ) Is set for the satellite signal strength values of (a),L 1,2 is the point location%x 1 , y 1 ) And%x 2 , y 2 ) The distance between the two plates is set to be equal,L i1, is the point location%x 1 , y 1 ) The origin coordinate of the two-dimensional rectangular coordinate system searched for the next starx i , y i ) The distance between the two plates is set to be equal,L i2, is the point location%x 2 , y 2 ) The origin coordinate of the two-dimensional rectangular coordinate system searched for the next starx i , y i ) The distance between the two plates is set to be equal,is the point location%x 1 , y 1 ) And%x 2 , y 2 ) The included angle between the connection line of (c) and the y-axis of the two-dimensional coordinate system of the current satellite-to-satellite search is shown in fig. 3.
In terms of coordinates [ (]x i , y i ) As the origin of the two-dimensional rectangular coordinate system for searching the star next time, to achieve the followingx 1 , y 1 ) And%x 2 , y 2 ) The direction perpendicular to the connecting line direction is used as the x axis of the two-dimensional rectangular coordinate system of the next star search, and the direction perpendicular to the connecting line direction is used as the y axis of the two-dimensional rectangular coordinate system of the next star search.
S5, estimating the next searching step length of the star.
When the next search is performed in the reduced area, the target satellite is not likely to be accurately positioned by continuing the search with the last search step length, so that the search is performed in the reduced area with the reduced search step length in an adaptive manner, and the search duration and the search precision are both considered.
In the embodiment of the invention, the following isSearch step of secondary pair starL i+1 The calculation formula of (2) is as follows:
；
wherein min (. Cndot.) represents taking the minimum value.
S6, judging whether the star aligning process meets the stopping condition, if so, ending the star aligning, otherwise, returning to the step S2 to perform next star aligning search.
Because the electrical or mechanical scanning of the antenna is of minimal scanning resolution, the satellite alignment process essentially ensures that the target satellite is aligned to a certain degree of accuracy. Thus can be compared withL i1, 、L i2, Minimum scan resolution of the smaller of (a) and (b) antenna electrical or mechanical scanR ant To determine if the star-facing process is stopped. Specifically, whenIn other words, the origin coordinate of the two-dimensional rectangular coordinate system of the next star search determined at this time is the final position of the antenna alignment target satellite.
Embodiment two:
the embodiment of the invention provides a quick satellite aligning device which can be loaded with the quick satellite aligning method in the first embodiment so as to realize quick satellite aligning, and comprises an antenna main body, an antenna driving device and an antenna controller.
The antenna body is used for realizing communication with a target satellite, and the specific form of the antenna body is not limited, and the antenna body can be a traditional parabolic antenna or a flat antenna.
The antenna driving device is used for adjusting the posture of the antenna main body and realizing the alignment of the antenna main body and the target satellite. Typically, the antenna driving device generally comprises an azimuth driving device and a pitching driving device, and the antenna beam can be directed to a specific airspace by adjusting the azimuth direction and the pitching direction of the antenna main body.
The antenna controller is used for demodulating the received signal from the antenna main body and providing corresponding control instructions for the antenna driving device to execute the steps of the fast satellite alignment method as in the first embodiment.
Those of ordinary skill in the art will recognize that the embodiments described herein are for the purpose of aiding the reader in understanding the principles of the present invention and should be understood that the scope of the invention is not limited to such specific statements and embodiments. Those of ordinary skill in the art can make various other specific modifications and combinations from the teachings of the present disclosure without departing from the spirit thereof, and such modifications and combinations remain within the scope of the present disclosure.
Claims (10)
1. The quick satellite aligning method is characterized by comprising the following steps of:
s1, constructing an initial two-dimensional rectangular coordinate system by taking the current antenna beam pointing position as an origin coordinate, and setting a first preset step lengthL 1 As the current search step;
s2, searching target satellite signals along positive and negative directions of an x axis and a y axis of a current two-dimensional rectangular coordinate system respectively according to a current searching step length to obtain multi-point target satellite signal intensity values;
s3, estimating the position of the target satellite in the current two-dimensional rectangular coordinate system according to the signal intensity values of the multi-point target satellite;
s4, estimating the origin coordinates, the x-axis direction and the y-axis direction of a two-dimensional rectangular coordinate system searched for the star next time;
s5, estimating the search step length of the next star;
s6, judging whether the star aligning process meets the stopping condition, if so, ending the star aligning, otherwise, returning to the step S2 to perform next star aligning search.
2. The method for fast satellite alignment according to claim 1, wherein the method for searching for the target satellite signal in step S2 is as follows: and respectively searching target satellite signals in the x-axis positive direction, the x-axis negative direction, the y-axis positive direction and the y-axis negative direction at the positions of 1 time of the current searching step length and 2 times of the current searching step length, namely respectively searching two points in the four directions of the current two-dimensional rectangular coordinate system, and adding the original points to form 9-point target satellite signal searching.
3. The method for fast satellite alignment according to claim 1, wherein the method for searching for the target satellite signal in step S2 is as follows: and respectively searching target satellite signals in the x-axis positive direction, the x-axis negative direction, the y-axis positive direction and the y-axis negative direction at the positions of 1 time of the current searching step length, 2 times of the current searching step length and 3 times of the current searching step length, namely respectively performing three-point position searching in the four directions of the current two-dimensional rectangular coordinate system, and adding the original point positions, thereby forming the 13-point position target satellite signal searching.
4. The fast satellite alignment method according to claim 1, wherein the target satellite signal in step S2 is a DVB signal and/or a beacon signal.
5. The method for quickly aligning satellites according to claim 4, wherein the method for obtaining the signal intensity values of the multi-point target satellite in step S2 is as follows:
when the target satellite signal is DVB signal or beacon signal, the target satellite signal intensity value of each point is DVB signal intensity value or beacon signal intensity value of the antenna at the point;
when the target signal includes both the DVB signal and the beacon signal, the target signal strength value for each point locationI w The method comprises the following steps:
；
wherein the method comprises the steps ofI D For the DVB signal strength value for that point location,I B for the purpose ofThe beacon signal strength value of the spot,w D is a weighting coefficient for the DVB signal strength value,w B is a weighting coefficient for the beacon signal strength value,w D +w B =1。
6. the method according to claim 1, wherein the step S3 comprises the following sub-steps:
s31, calculating the average value of satellite signal intensity in each axial direction according to the multi-point target satellite signal intensity value;
s32, sorting the average value of the satellite signal intensity in each axis direction, and estimating the quadrant of the target satellite according to the maximum value and the secondary maximum value of the sorting result;
s33, sequencing the satellite signal intensity values of the quadrants, and estimating the position of the target satellite in the current two-dimensional rectangular coordinate system.
7. The method of fast star alignment according to claim 1, wherein the step S4 is specifically:
according to the point position coordinates of maximum value and sub-maximum value of satellite signal intensityx 1 , y 1 ) And%x 2 , y 2 ) Calculating to obtain the origin coordinate of the two-dimensional rectangular coordinate system of the next star searchx i , y i )：
；
Wherein, I 1 、I 2 respectively is the point location [ (]x 1 , y 1 ) And%x 2 , y 2 ) Is set for the satellite signal strength values of (a),L 1,2 is the point location%x 1 , y 1 ) And%x 2 , y 2 ) The distance between the two plates is set to be equal,L i1, is the point location%x 1 , y 1 ) Two with next star searchOrigin coordinate of rectangular coordinate systemx i , y i ) The distance between the two plates is set to be equal,L i2, is the point location%x 2 , y 2 ) The origin coordinate of the two-dimensional rectangular coordinate system searched for the next starx i , y i ) The distance between the two plates is set to be equal,is the point location%x 1 , y 1 ) And%x 2 , y 2 ) An included angle between the connecting line of the (C) and the y-axis of the two-dimensional coordinate system of the current star search;
in terms of coordinates [ (]x i , y i ) As the origin of the two-dimensional rectangular coordinate system for searching the star next time, to achieve the followingx 1 , y 1 ) And%x 2 , y 2 ) The direction perpendicular to the connecting line direction is used as the x axis of the two-dimensional rectangular coordinate system of the next star search, and the direction perpendicular to the connecting line direction is used as the y axis of the two-dimensional rectangular coordinate system of the next star search.
8. The method according to claim 7, wherein the next search step for stars in step S5L i+1 The calculation formula of (2) is as follows:
；
wherein min (. Cndot.) represents taking the minimum value.
9. The rapid satellite alignment method according to claim 7, wherein the stopping conditions in step S6 are:
；
wherein the method comprises the steps ofR ant Representing the minimum scan resolution of the antenna.
10. The quick satellite aligning device is characterized by comprising an antenna main body, an antenna driving device and an antenna controller;
the antenna main body is used for realizing communication with a target satellite;
the antenna driving device is used for adjusting the posture of the antenna main body and realizing the alignment of the antenna main body and a target satellite;
the antenna controller is configured to demodulate a received signal from the antenna main body and provide a corresponding control instruction to the antenna driving device, so as to perform the steps of the fast satellite alignment method according to any one of claims 1-9.
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