CN113009512B - System for determining spacecraft antenna installation position and antenna pointing selection - Google Patents
System for determining spacecraft antenna installation position and antenna pointing selection Download PDFInfo
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/02—Details of the space or ground control segments
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
- G01S19/38—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system
- G01S19/39—Determining a navigation solution using signals transmitted by a satellite radio beacon positioning system the satellite radio beacon positioning system transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
- G01S19/42—Determining position
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S3/00—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received
- G01S3/02—Direction-finders for determining the direction from which infrasonic, sonic, ultrasonic, or electromagnetic waves, or particle emission, not having a directional significance, are being received using radio waves
- G01S3/14—Systems for determining direction or deviation from predetermined direction
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Abstract
The invention belongs to the technical field of spacecraft flight measurement and control, and particularly relates to a system for determining the installation position and the antenna direction selection of a spacecraft antenna, which comprises the following components: the antenna installation angle detection device comprises a setting module, a geometric visible arc section operation module, an antenna installation angle traversal range operation module, a first judgment module, an intersection range operation module, a link margin operation module, a second judgment module, a third judgment module, a result operation module and a result output module; compared with the prior art, the method and the device have the advantages that the antenna installation position and the antenna direction meeting the measurement and control task requirements are automatically calculated according to the selected spacecraft orbit data, the antenna directional diagram, the measurement and control station layout and the measurement and control communication link constraint of the spacecraft and the ground equipment, and the automatic design of the spacecraft antenna installation position and the antenna direction is realized.
Description
Technical Field
The invention belongs to the technical field of spacecraft flight measurement and control, and particularly relates to a system for determining the installation position and the antenna pointing selection of a spacecraft antenna.
Background
In a spacecraft flight measurement and control task, the antenna installation position of a spacecraft is an important constraint factor in task design. During the flight of the spacecraft, the distance and the azimuth angle of radar of a ground measurement and control station and an offshore measurement ship relative to the spacecraft are constantly changed, and an antenna on the spacecraft is installed in a fixed position relative to the spacecraft. The antenna mounting position on the spacecraft meets the requirement of measurement and control coverage. The existing method for determining the antenna installation position is mainly determined according to an antenna directional gain line graph, the antenna installation position is mainly selected manually, mature immobilized selection standard measurement is not available, and a fully automatic selection mode is not available.
Disclosure of Invention
Technical problem to be solved
The technical problem to be solved by the invention is as follows: and automatically designing the installation position and the antenna pointing direction of the spacecraft, which meet the requirements, according to the measurement and control task requirements.
(II) technical scheme
In order to solve the technical problem, the invention provides a determination system for selecting the installation position and the direction of an antenna of a spacecraft, which is used for calculating the installation position and the direction of the antenna based on a four-dimensional discrete traversal search method of an antenna installation angle alpha and an antenna installation angle beta and an azimuth angle Az and a pitch angle El under an antenna coordinate system;
the system comprises: the antenna installation angle detection device comprises a setting module, a geometric visible arc section operation module, an antenna installation angle traversal range operation module, a first judgment module, an intersection range operation module, a link margin operation module, a second judgment module, a third judgment module, a result operation module and a result output module;
(1) The setting module is used for setting spacecraft orbits, antenna directional diagrams, stations 1 and 2, 8230, station layout to station N and measurement and control communication link constraints; setting four-dimensional discrete traversal search granularity of alpha, beta, az and El;
(2) The geometric visible arc operation module is used for calculating a geometric visible arc between the spacecraft orbit and the station n according to the position relation of the spacecraft orbit and the station n; wherein N =1, 2, 3 \ 8230n, and N, station N is calculated from station 1;
calculating the geometric visibility of the ground stations to the spacecraft according to the position information of the spacecraft orbit, the position information of the measurement and control stations and the constraint information, and calculating to obtain a geometric visible arc section;
(3) The antenna installation angle traversal range operation module is used for calculating the traversal ranges [ alpha n1, alpha n2] and [ beta n1, beta n2] of the antenna installation angle alpha n in the geometric visible arc section of the station n according to the data ranges of the geometric visible arc section and the antenna installation angle obtained by the geometric visible arc section operation module;
(4) The first judging module is used for judging whether N = N, wherein N is the total number of the survey stations, if so, the intersection range operation module is triggered to work, and if not, the N = N +1 is made to jump back to the geometric visible arc section operation module for continuous calculation;
(5) The intersection range operation module is used for solving intersection ranges [ alpha 1, alpha 2] and [ beta 1, beta 2] of alpha and beta of all the geometric visible arc sections of the observation stations as traversal ranges of alpha and beta;
obtaining [ alpha 1, alpha 2] = [ alpha 11, alpha 12] < alpha 21, alpha 22] < alpha 8230 \8230; [ alpha (N) 1, alpha (N) 2] < alpha (N1, alpha N2];
and [ β 1, β 2] = [ β 11, β 12] andgate [ β 21, β 22] andgate8230\8230 \ 8230 [ β (N) 1, β (N) 2] andgate [ β N1, β N2];
if [ alpha 1, alpha 2] and [ beta 1, beta 2] exist, the traversal ranges of alpha and beta visible by N stations are met, if [ alpha 1, alpha 2] and [ beta 1, beta 2] do not exist, the intersection ranges [ alpha 1, alpha 2] and [ beta 1, beta 2] of alpha and beta which can meet as many stations as possible are reserved as the traversal ranges of alpha and beta;
(6) The link margin operation module is used for calculating link margins F (alpha, beta, az, el) according to alpha, beta, az, el and four-dimensional discrete traversal search granularity;
in the ranges of alpha belonging to [ alpha 1, alpha 2], beta belonging to [ beta 1, beta 2], az belonging to [0 ], 180 degrees ], el belonging to [0 ], 180 degrees ], a fixed element method is adopted, search granularity is traversed according to four-dimensional dispersion, antenna gain G is searched through an antenna directional diagram according to Az and El, and link margin F (alpha, beta, az, el) of each search element is calculated;
(7) The second judging module is used for judging whether the link margin F (alpha, beta, az, el) meets the constraint condition of the measurement and control communication link, if so, retaining (alpha, beta, az, el), and otherwise, discarding (alpha n, beta, az, el);
(8) The third judging module is used for judging whether all the search elements are traversed or not, and under the condition that all the search elements are not traversed, the link margin operation module and the second judging module are used for repeatedly executing the link margin operation and the link margin judgment until all the search elements are traversed, namely all the alpha, beta, az and El in the alpha, beta 2, az, 0 degrees, 180 degrees, el, beta 1, beta 2, az, 0 degrees and El are traversed;
(9) The result operation module is used for calculating the range of the antenna installation position and the range of the azimuth angle and the pitch angle under the antenna coordinate system according to the calculated search elements (alpha, beta, az and El) which simultaneously meet the visibility and the link constraint;
calculating to obtain alpha [ alpha min, alpha max ], beta [ beta min, beta max ], az [ Azmin, azmax ], el [ Elmin, elmax ] which simultaneously meet visibility and link constraint according to (alpha, beta, az, el) obtained by four-dimensional traversal search;
(10) The result output module is used for outputting the value range of alpha, beta, az and El which meets the visibility and link constraint and meets the maximum station number and the specific stations;
the specific output parameters are as follows: the maximum number N of the test stations is met, wherein N is less than or equal to N; specific station name measurement; antenna installation angles alpha [ alpha min, alpha max ], beta [ beta min, beta max ]; azimuth and pitch angles Az [ Azmin, azmax ], el [ Elmin, elmax ] in the antenna coordinate system.
Wherein, in the setting module working process, the spacecraft orbit: and obtaining the position and speed information corresponding to each moment of the spacecraft in the orbit time period by the ephemeris file of the spaceflight, and further determining the orbit of the spacecraft by the position and speed information.
Wherein, in the working process of the setting module, the antenna directional diagram is as follows: for querying the corresponding antenna gain according to Az and El.
Wherein, in the setting module working process, the survey station layout: the system comprises position information of a measurement and control station, a measurement ship and a relay satellite and constraint information of azimuth, pitch and slant distance.
Wherein, in the working process of the setting module, the measurement and control communication link constraint is as follows: for calculating link margins.
In the working process of the setting module, the four-dimensional discrete traversal search granularity of α, β, az, and El is the calculation step size of the traversal search, and the calculation units of α, β, az, and El are all degrees, so the calculation step size is in degrees.
In the working process of the antenna installation angle traversal range operation module, for each survey station, calculating values of alpha and beta corresponding to each time point in a geometric visible arc section according to the calculated numerical ranges of the geometric visible arc section and the antenna installation angle, and after calculation is finished, calculating the value range of the obtained alpha and beta, namely the traversal range [ alpha n1, alpha n2] of the antenna installation angle alpha n in the geometric visible arc section of the station n, wherein the traversal range [ beta n1, beta n2] of the beta n;
for example, the geometric visible arc of the station 1 has a traversal range [ α 11, α 12] of the antenna installation angle α 1, and the traversal range [ β 11, β 12] of β 1.
The first judgment module is used for judging whether the calculation of the geometric visible arc sections corresponding to all the measurement and control stations and the traversal ranges of alpha and beta in the geometric visible arc sections of the stations is finished.
In the working process of the second judging module, each searching element can calculate a link margin according to the working content of the link margin calculating module, whether the link margin of the searching element meets a link constraint condition is judged, if the link constraint condition is met, the antenna mounting position and the azimuth angle and the pitch angle under the antenna coordinate system are reasonable, and if the link margin of the searching element does not meet the link constraint condition, the antenna mounting position and the azimuth angle and the pitch angle under the antenna coordinate system are unreasonable.
In the working process of the result operation module, the results of alpha, beta, az and El are segmented.
(III) advantageous effects
Compared with the prior art, the system comprises: the antenna installation angle detection device comprises a setting module, a geometric visible arc section operation module, an antenna installation angle traversal range operation module, a first judgment module, an intersection range operation module, a link margin operation module, a second judgment module, a third judgment module, a result operation module and a result output module; according to the selected spacecraft orbit data, the antenna directional diagram, the measurement and control station layout and the measurement and control communication link constraint of the spacecraft and the ground equipment, the antenna installation position and the antenna pointing direction meeting the measurement and control task requirements are automatically calculated, and the automatic design of the spacecraft antenna installation position and the antenna pointing direction is realized.
Drawings
FIGS. 1-1 and 1-2 are diagrams defining angles α and β;
fig. 2 is a working flow chart of the installation position and the antenna pointing direction of the spacecraft antenna by adopting four-dimensional discrete traversal search.
Detailed Description
In order to make the objects, contents, and advantages of the present invention clearer, the following detailed description of the embodiments of the present invention will be made in conjunction with the accompanying drawings and examples.
In order to solve the technical problems, the invention provides a determination system for selecting the installation position and the antenna pointing direction of a spacecraft antenna, as shown in fig. 1-1, fig. 1-2 and fig. 2, the system calculates the installation position and the antenna pointing direction of the antenna based on a four-dimensional discrete traversal search method of an antenna installation angle alpha and an antenna installation angle beta and an azimuth angle Az and a pitch angle El under an antenna coordinate system;
the system comprises: the antenna installation angle detection device comprises a setting module, a geometric visible arc section operation module, an antenna installation angle traversal range operation module, a first judgment module, an intersection range operation module, a link margin operation module, a second judgment module, a third judgment module, a result operation module and a result output module;
(1) The setting module is used for setting spacecraft orbits, antenna directional diagrams, stations 1 and 2, 8230, station layout to station N and measurement and control communication link constraints; setting four-dimensional discrete traversal search granularity of alpha, beta, az and El;
(2) The geometric visible arc operation module is used for calculating a geometric visible arc between the spacecraft orbit and the station n according to the position relation of the spacecraft orbit and the station n; wherein N =1, 2, 3 \ 8230n, and N, station N is calculated from station 1;
calculating the geometric visibility of the ground station to the spacecraft according to the position information of the spacecraft orbit, the position information of the measurement and control station and the constraint information, and calculating to obtain a geometric visible arc section;
(3) The antenna installation angle traversal range operation module is used for calculating the traversal ranges [ alpha n1, alpha n2] and [ beta n1, beta n2] of the antenna installation angle alpha n in the geometric visible arc section of the station n according to the data ranges of the geometric visible arc section and the antenna installation angle obtained by the geometric visible arc section operation module;
(4) The first judging module is used for judging whether N = N, wherein N is the total number of the survey stations, if so, the intersection range operation module is triggered to work, and if not, N = N +1 is made to jump back to continue to be calculated by the geometric visible arc section operation module;
(5) The intersection range operation module is used for solving intersection ranges [ alpha 1, alpha 2] and [ beta 1, beta 2] of alpha and beta of all the geometric visible arc sections of the measuring stations as traversal ranges of alpha and beta;
obtaining [ alpha 1, alpha 2] = [ alpha 11, alpha 12] < alpha 21, alpha 22] < alpha 8230 \8230; [ alpha (N) 1, alpha (N) 2] < alpha (N1, alpha N2];
and [ β 1, β 2] = [ β 11, β 12] andgate [ β 21, β 22] andgate8230\8230; [ β (N) 1, β (N) 2] andgate [ β N1, β N2];
if [ alpha 1, alpha 2] and [ beta 1, beta 2] exist, the traversal range of alpha and beta visible by N stations is satisfied, if [ alpha 1, alpha 2] and [ beta 1, beta 2] do not exist, the intersection range [ alpha 1, alpha 2] and [ beta 1, beta 2] of alpha and beta which can satisfy as many stations as possible are reserved as the traversal range of alpha and beta;
(6) The link margin operation module is used for calculating link margins F (alpha, beta, az, el) according to alpha, beta, az, el and four-dimensional discrete traversal search granularity;
in the range of alpha epsilon [ alpha 1, alpha 2], beta epsilon [ beta 1, beta 2], az epsilon [0 degrees ], 180 degrees ], el [0 degrees ], a fixed element method is adopted, search granularity is traversed according to four-dimensional dispersion, antenna gain G is searched through an antenna directional diagram according to Az and El, and link margin F (alpha, beta, az, el) of each search element is calculated;
(7) The second judging module is used for judging whether the link margin F (alpha, beta, az, el) meets the constraint condition of the measurement and control communication link, if so, retaining (alpha, beta, az, el), and if not, discarding (alpha n, beta, az, el);
(8) The third judging module is used for judging whether all the search elements are traversed or not, and under the condition that all the search elements are not traversed, the link margin operation module and the second judging module are used for repeatedly executing the link margin operation and the link margin judgment until all the search elements are traversed, namely all the alpha, beta, az and El in the alpha, beta 2, az, 0 degrees, 180 degrees, el, beta 1, beta 2, az, 0 degrees and El are traversed;
(9) The result operation module is used for calculating the range of the antenna installation position and the range of the azimuth angle and the pitch angle under the antenna coordinate system according to the calculated search elements (alpha, beta, az and El) which simultaneously meet the visibility and the link constraint;
according to (alpha, beta, az, el) obtained by four-dimensional traversal search, alpha [ alpha min, alpha max ], beta [ beta min, beta max ], az [ Azmin, azmax ], el [ Elmin, elmax ] which simultaneously meet visibility and link constraint are obtained through calculation;
(10) The result output module is used for outputting the value range of alpha, beta, az and El which meets the visibility and link constraint and meets the maximum station number and the specific stations;
the specific output parameters are as follows: the maximum number N of the test stations is met, wherein N is less than or equal to N; specific station name measurement; antenna installation angles alpha [ alpha min, alpha max ], beta [ beta min, beta max ]; azimuth angle and pitch angle Az [ Azmin, azmax ], el [ Elmin, elmax ] in antenna coordinate system.
Wherein, in the setting module working process, the spacecraft orbit: and obtaining the position and speed information corresponding to each moment of the spacecraft in the orbit time period by the ephemeris file of the spaceflight, and further determining the orbit of the spacecraft by the position and speed information.
Wherein, in the working process of the setting module, the antenna directional diagram is as follows: for querying the corresponding antenna gain according to Az and El.
Wherein, in the setting module working process, the survey station layout: the system comprises position information of a measurement and control station, a measurement ship and a relay satellite and constraint information of azimuth, pitch and slant distance.
Wherein, in the working process of the setting module, the measurement and control communication link constraint is as follows: for calculating link margin.
In the working process of the setting module, the four-dimensional discrete traversal search granularity of α, β, az, and El is the calculation step size of the traversal search, and the calculation units of α, β, az, and El are all ° so that the calculation step size is in ° unit.
In the working process of the antenna installation angle traversal range operation module, for each survey station, calculating values of alpha and beta corresponding to each time point in a geometric visible arc section according to the calculated numerical ranges of the geometric visible arc section and the antenna installation angle and time points, and after calculation is finished, calculating the value range of the obtained alpha and beta, namely the traversal range [ alpha n1, alpha n2] of the antenna installation angle alpha n in the geometric visible arc section of the station n, wherein the traversal range [ beta n1, beta n2] of the beta n;
for example, the geometric visible arc of the station 1 has a traversal range [ α 11, α 12] of the antenna installation angle α 1, and the traversal range [ β 11, β 12] of β 1.
The first judgment module is used for judging whether the calculation of the geometric visible arc sections corresponding to all the measurement and control stations and the traversal ranges of alpha and beta in the geometric visible arc sections of the stations is finished.
In the working process of the second judging module, each searching element can calculate a link margin according to the working content of the link margin calculating module, whether the link margin of the searching element meets the link constraint condition is judged, if the link margin of the searching element meets the link constraint condition, the antenna installation position and the azimuth angle and the pitch angle under the antenna coordinate system are reasonable, and if the link margin of the searching element does not meet the link constraint condition, the antenna installation position and the azimuth angle and the pitch angle under the antenna coordinate system are unreasonable.
Wherein, in the working process of the result operation module, the results of alpha, beta, az and El are segmented.
In addition, the invention also provides a method for determining the installation position and the antenna pointing direction selection of the spacecraft, as shown in fig. 1-1, fig. 1-2 and fig. 2, the method calculates the installation position and the antenna pointing direction of the antenna based on a four-dimensional discrete traversal search method of the antenna installation angles alpha and beta and the azimuth angle Az and the pitch angle El under an antenna coordinate system;
the method comprises the following steps:
step S1: setting up spacecraft orbit, antenna directional diagram, station 1, station 2 \8230, station 8230, station layout to station N and measurement and control communication link constraint; setting four-dimensional discrete traversal search granularity of alpha, beta, az and El;
step S2: calculating a geometric visible arc section between the spacecraft orbit and the station n according to the position relation of the spacecraft orbit and the station n; wherein N =1, 2, 3 \ 8230n, and N, station N is calculated from station 1;
calculating the geometric visibility of the ground stations to the spacecraft according to the position information of the spacecraft orbit, the position information of the measurement and control stations and the constraint information, and calculating to obtain a geometric visible arc section;
and step S3: according to the data ranges of the geometric visible arc section and the antenna installation angle obtained by the calculation in the step S2, calculating the traversal ranges [ alpha n1, alpha n2] of the antenna installation angle alpha n in the geometric visible arc section of the station n and the traversal ranges [ beta n1, beta n2] of beta n;
and step S4: judging whether N = N, wherein N is the total number of the stations to be tested, if so, entering step S5, otherwise, enabling N = N +1, and jumping back to step S2 to continue calculation;
step S5: solving intersection ranges [ alpha 1, alpha 2] and [ beta 1, beta 2] of alpha and beta of all stations geometric visible arc sections as traversal ranges of alpha and beta;
obtaining [ alpha 1, alpha 2] = [ alpha 11, alpha 12] < alpha 21, alpha 22] < alpha 8230 \8230; [ alpha (N) 1, alpha (N) 2] < alpha (N1, alpha N2];
and [ β 1, β 2] = [ β 11, β 12] andgate [ β 21, β 22] andgate8230\8230; [ β (N) 1, β (N) 2] andgate [ β N1, β N2];
if [ alpha 1, alpha 2] and [ beta 1, beta 2] exist, the traversal range of alpha and beta visible by N stations is satisfied, if [ alpha 1, alpha 2] and [ beta 1, beta 2] do not exist, the intersection range [ alpha 1, alpha 2] and [ beta 1, beta 2] of alpha and beta which can satisfy as many stations as possible are reserved as the traversal range of alpha and beta;
step S6: calculating link margin F (alpha, beta, az, el) according to alpha, beta, az, el and four-dimensional discrete traversal search granularity;
in the ranges of alpha belonging to [ alpha 1, alpha 2], beta belonging to [ beta 1, beta 2], az belonging to [0 ], 180 degrees ], el belonging to [0 ], 180 degrees ], a fixed element method is adopted, search granularity is traversed according to four-dimensional dispersion, antenna gain G is searched through an antenna directional diagram according to Az and El, and link margin F (alpha, beta, az, el) of each search element is calculated;
step S7: judging whether the link margin F (alpha, beta, az, el) meets the constraint condition of the measurement and control communication link, if so, retaining (alpha, beta, az, el), and if not, abandoning (alpha n, beta, az, el);
step S8: repeating the steps S6-S7 until all search elements are traversed, namely, until all alpha, beta, az and El in alpha, beta [ alpha 1, alpha 2], beta [ beta 1, beta 2], az [0 DEG, 180 DEG ], el [0 DEG, 180 DEG ] are traversed;
step S9: calculating the range of the installation position of the antenna and the range of the azimuth angle and the pitch angle under an antenna coordinate system according to the calculated search elements (alpha, beta, az, el) which simultaneously satisfy the visibility and the link constraint;
according to (alpha, beta, az, el) obtained by four-dimensional traversal search, alpha [ alpha min, alpha max ], beta [ beta min, beta max ], az [ Azmin, azmax ], el [ Elmin, elmax ] which simultaneously meet visibility and link constraint are obtained through calculation;
step S10: outputting the value range of alpha, beta, az and El which meets the visibility and link constraint and meets the maximum station number and the specific stations;
the specific output parameters are as follows: the maximum number N of the test stations is met, wherein N is less than or equal to N; specific station name measurement; antenna installation angles alpha [ alpha min, alpha max ], beta [ beta min, beta max ]; azimuth and pitch angles Az [ Azmin, azmax ], el [ Elmin, elmax ] in the antenna coordinate system.
Wherein, in step 1, the spacecraft orbit: and obtaining the position and speed information corresponding to each moment of the spacecraft in the orbit time period by the ephemeris file of the spaceflight, and further determining the orbit of the spacecraft by the position and speed information.
Wherein, in the step 1, the antenna pattern: for querying the corresponding antenna gain according to Az and El.
Wherein, in the step 1, the layout of the survey station: the method comprises position information and constraint information of azimuth, pitch and slant distance of a measurement and control station, a measurement ship and a relay satellite.
Wherein, in the step 1, the measurement and control communication link constraint is as follows: for calculating link margin.
In step 1, the four-dimensional discrete traversal search granularity of α, β, az, and El is a calculation step size of the traversal search, and the calculation units of α, β, az, and El are all ° so that the calculation step size is in ° unit.
In step 3, for each survey station, calculating values of α and β corresponding to each time point in the geometrically visible arc segment according to the calculated numerical ranges of the geometrically visible arc segment and the antenna installation angle, and after the calculation is completed, calculating the range of the value domains of the α and β, namely the traversal range [ α n1, α n2] of the antenna installation angle α n in the geometrically visible arc segment of the station n, wherein the traversal range [ β n1, β n2] of β n;
for example, the geometric visible arc of the station 1 has a traversal range [ α 11, α 12] of the antenna installation angle α 1, and the traversal range [ β 11, β 12] of β 1.
And 4, judging whether the calculation of the geometric visible arc sections corresponding to all the measurement and control stations and the traversal ranges of alpha and beta in the geometric visible arc sections of the stations is finished or not.
In step S7, each search element in step S6 may calculate a link margin, and determine whether the link margin of the search element satisfies a link constraint condition, if the link constraint is satisfied, the antenna mounting position and the azimuth angle and the pitch angle in the antenna coordinate system are reasonable, and if the link margin is not satisfied, the antenna mounting position and the azimuth angle and the pitch angle in the antenna coordinate system are unreasonable.
In step 9, the results of α, β, az, and El are segmented.
The above description is only a preferred embodiment of the present invention, and it should be noted that, for those skilled in the art, several modifications and variations can be made without departing from the technical principle of the present invention, and these modifications and variations should also be regarded as the protection scope of the present invention.
Claims (10)
1. A spacecraft antenna installation position and antenna pointing direction selection determining system is characterized in that the system calculates the antenna installation position and the antenna pointing direction based on a four-dimensional discrete traversal search method of an antenna installation angle alpha and an antenna installation angle beta and an azimuth angle Az and a pitch angle El under an antenna coordinate system;
the system comprises: the antenna installation angle detection device comprises a setting module, a geometric visible arc section operation module, an antenna installation angle traversal range operation module, a first judgment module, an intersection range operation module, a link margin operation module, a second judgment module, a third judgment module, a result operation module and a result output module;
(1) The setting module is used for setting spacecraft orbits, antenna directional diagrams, stations 1 and 2, 8230, station layout to station N and measurement and control communication link constraints; setting four-dimensional discrete traversal search granularity of alpha, beta, az and El;
(2) The geometric visible arc operation module is used for calculating a geometric visible arc between the spacecraft orbit and the station n according to the position relation of the spacecraft orbit and the station n; wherein N =1, 2, 3 \8230N, and station N is calculated from station 1;
calculating the geometric visibility of the ground station to the spacecraft according to the position information of the spacecraft orbit, the position information of the measurement and control station and the constraint information, and calculating to obtain a geometric visible arc section;
(3) The antenna installation angle traversal range operation module is used for calculating the traversal ranges [ alpha n1, alpha n2] of the antenna installation angles alpha n and [ beta n1, beta n2] of the antenna installation angles alpha n in the geometric visible arc section of the station n according to the data ranges of the geometric visible arc section and the antenna installation angles obtained by the geometric visible arc section operation module;
(4) The first judging module is used for judging whether N = N, N is the total number of the survey stations, if yes, the intersection range operation module is triggered to work, and if not, N = N +1 is made, and the calculation is continued by the geometric visible arc section operation module;
(5) The intersection range operation module is used for solving intersection ranges [ alpha 1, alpha 2] and [ beta 1, beta 2] of alpha and beta of all the geometric visible arc sections of the measuring stations as traversal ranges of alpha and beta;
obtaining [ alpha 1, alpha 2] = [ alpha 11, alpha 12] andgate [ alpha 21, alpha 22] andgate8230\8230; [ alpha (N) 1, alpha (N) 2] andgate [ alpha N1, alpha N2];
and [ β 1, β 2] = [ β 11, β 12] andgate [ β 21, β 22] andgate8230\8230 \ 8230 [ β (N) 1, β (N) 2] andgate [ β N1, β N2];
if [ alpha 1, alpha 2] and [ beta 1, beta 2] exist, the traversal ranges of alpha and beta visible by N stations are met, if [ alpha 1, alpha 2] and [ beta 1, beta 2] do not exist, the intersection ranges [ alpha 1, alpha 2] and [ beta 1, beta 2] of alpha and beta which can meet as many stations as possible are reserved as the traversal ranges of alpha and beta;
(6) The link margin operation module is used for calculating link margins F (alpha, beta, az, el) according to alpha, beta, az, el and four-dimensional discrete traversal search granularity;
in the range of alpha epsilon [ alpha 1, alpha 2], beta epsilon [ beta 1, beta 2], az epsilon [0 degrees ], 180 degrees ], el epsilon [0 degrees ], 180 degrees ], a fixed element method is adopted, the search granularity is traversed according to four-dimensional dispersion, the antenna gain G is searched through an antenna directional diagram according to Az and El, and the link margin F (alpha, beta, az, el) of each search element is calculated;
(7) The second judging module is used for judging whether the link margin F (alpha, beta, az, el) meets the constraint condition of the measurement and control communication link, if so, retaining (alpha, beta, az, el), and if not, discarding (alpha n, beta, az, el);
(8) The third judging module is used for judging whether all search elements are traversed or not, and under the condition that all search elements are not traversed, the link margin operation module and the second judging module are used for repeatedly executing the link margin operation and the link margin judgment until all the search elements are traversed until all the alpha, beta, az and El are traversed in the alpha, beta 1, beta 2, az, 0 degrees, 180 degrees, el, 0 degrees and 180 degrees;
(9) The result operation module is used for calculating the range of the installation position of the antenna and the range of the azimuth angle and the pitch angle under the antenna coordinate system according to the search elements (alpha, beta, az and El) which are obtained by calculation and simultaneously meet the visibility and the link constraint;
according to (alpha, beta, az, el) obtained by four-dimensional traversal search, alpha [ alpha min, alpha max ], beta [ beta min, beta max ], az [ Azmin, azmax ], el [ Elmin, elmax ] which simultaneously meet visibility and link constraint are obtained through calculation;
(10) The result output module is used for outputting the value range of alpha, beta, az and El which meets the visibility and link constraint and meets the maximum station number and the specific stations;
the specific output parameters are as follows: the maximum number N of the test stations is met, wherein N is less than or equal to N; specific station name measurement; antenna installation angles alpha [ alpha min, alpha max ], beta [ beta min, beta max ]; azimuth and pitch angles Az [ Azmin, azmax ], el [ Elmin, elmax ] in the antenna coordinate system.
2. A spacecraft antenna installation position and antenna pointing direction selection determination system as claimed in claim 1, wherein during operation of said setup module, said spacecraft orbit: and obtaining the position and speed information corresponding to each moment of the spacecraft in the orbit time period by the ephemeris file of the spaceflight, and further determining the orbit of the spacecraft by the position and speed information.
3. A system for determining a spacecraft antenna installation location and antenna pointing direction selection according to claim 1, wherein during operation of said setup module said antenna pattern: for querying the corresponding antenna gain according to Az and El.
4. A spacecraft antenna installation position and antenna pointing direction selection determination system as claimed in claim 1 wherein, during operation of said setup module, said survey station layout: the system comprises position information of a measurement and control station, a measurement ship and a relay satellite and constraint information of azimuth, pitch and slant distance.
5. The system for determining spacecraft antenna installation location and antenna pointing selection according to claim 1, wherein during operation of the setup module, the measurement and control communication link constraints are: for calculating link margins.
6. The system for determining the installation position and the pointing direction selection of the spacecraft antenna according to claim 1, wherein in the working process of the setting module, the four-dimensional discrete traversal search granularity of α, β, az, and El is a calculation step size of the traversal search, and the calculation units of α, β, az, and El are all ° so that the calculation step size is in ° unit.
7. The system for determining the selection of the antenna installation position and the antenna orientation of the spacecraft according to claim 1, wherein in the working process of the antenna installation angle traversal range operation module, for each survey station, according to the numerical range of the geometric visible arc section and the antenna installation angle obtained through calculation, the values of α and β corresponding to each time point in the geometric visible arc section are calculated according to the time points, after the calculation is completed, the value range of the obtained α and β is calculated, the traversal range [ α n1, α n2] of the antenna installation angle α n in the geometric visible arc section of the station n, and the traversal range [ β n1, β n2] of β n are calculated;
the geometric view of the station 1 shows the traversal range [ alpha 11, alpha 12] of the antenna installation angle alpha 1 in the arc segment, and the traversal range [ beta 11, beta 12] of the beta 1.
8. The system for determining spacecraft antenna installation position and antenna pointing selection according to claim 1, wherein the first determining module is configured to determine whether the calculation of the geometrically visible arc segments corresponding to all the measurement and control stations and the traversal ranges of α and β in the geometrically visible arc segments of the stations is completed.
9. The system for determining spacecraft antenna installation position and antenna pointing direction selection according to claim 1, wherein during operation of the second determination module, each search element can calculate a link margin according to the operation content of the link margin operation module, and determine whether the link margin of the search element satisfies the link constraint condition, if the link constraint is satisfied, the antenna installation position and the azimuth angle and the pitch angle under the antenna coordinate system are reasonable, and if the link margin is not satisfied, the antenna installation position and the azimuth angle and the pitch angle under the antenna coordinate system are unreasonable.
10. A system for determining the installation location and the pointing direction of a spacecraft antenna as claimed in claim 1, wherein said results calculation module is operative so that the results of α, β, az, and El are segmented.
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