CN111103900A - Satellite-to-satellite control method, device, system, storage medium and computer equipment - Google Patents
Satellite-to-satellite control method, device, system, storage medium and computer equipment Download PDFInfo
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Abstract
The application relates to a satellite alignment control method, a device, a system, a storage medium and computer equipment, which are used for acquiring the star position information of a target satellite and the geographic position information of a satellite antenna to obtain a first azimuth angle, a first pitch angle and a polarization angle; obtaining a magnetic declination of the satellite antenna according to the geographical position information to obtain a second azimuth angle; acquiring a pitch axis installation error deflection angle and an antenna deflection feed angle of the satellite antenna to obtain a second pitch angle; and taking the second azimuth angle, the second pitch angle and the polarization angle as corresponding satellite parameters of the satellite antenna. When the satellite is aimed, the azimuth angle of the satellite is compensated by the magnetic declination, the azimuth angle relative to the magnetic north can be obtained, the problem of inaccurate aiming of the satellite can be avoided by aiming the satellite according to the azimuth angle relative to the magnetic north, in addition, the declination angle information of the satellite antenna is combined to compensate the pitch angle, the accuracy of aiming the satellite can be further improved, and therefore the working performance of the satellite communication equipment is not influenced.
Description
Technical Field
The present application relates to the field of satellite communications technologies, and in particular, to a method, an apparatus, a system, a storage medium, and a computer device for controlling a satellite.
Background
With the development of scientific technology, the application of satellite communication technology is more and more common, and various satellite communication devices are more and more widely applied, such as: the portable satellite communication equipment can be used in the fields of news interviews, emergency rescue and disaster relief, scientific investigation and exploration, video consultation, petrochemical industry, public security, military and the like, and is an important tool for guaranteeing national information safety communication.
In the prior art, when a portable satellite communication device performs communication, satellite alignment is firstly required, that is, satellite alignment related parameters are obtained through a target satellite position and local longitude and latitude information, and then satellite alignment is performed according to the obtained related parameters. For the earth, there is a distinction between Magnetic North (Magnetic North), which is the North indicated by a compass, and True North (True North), which is the starting point of all meridians, also called geographic North. In the prior art, the satellite alignment parameters obtained during satellite alignment are parameters relative to true north, however, the parameters detected by the electronic compass in the satellite alignment process are parameters relative to magnetic north, and for some regions, the problem of inaccurate satellite alignment can be caused by the fact that the satellite alignment is directly performed by using the parameters of the electronic compass due to the existence of a magnetic declination (an included angle between the magnetic north and the true north), and the satellite alignment can not accurately cause serious influence on the working performance of the portable satellite communication equipment.
Disclosure of Invention
In view of the foregoing, it is necessary to provide a method, an apparatus, a system, a storage medium, and a computer device for controlling a satellite, which improve accuracy of satellite alignment, in order to solve the problems in the prior art.
A method of controlling a satellite, comprising:
acquiring star position information of a target satellite and geographical position information of a star antenna, and obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star position information and the geographical position information, wherein the first azimuth angle is an azimuth angle of the star antenna relative to true north;
obtaining a magnetic declination of the satellite-to-satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite-to-satellite antenna relative to magnetic north;
acquiring a pitching axis installation error deflection angle and an antenna deflection feed angle of the satellite antenna, and obtaining a second pitch angle according to the pitching axis installation error deflection angle, the antenna deflection feed angle and the first pitch angle;
and taking the second azimuth angle, the second pitch angle and the polarization angle as the satellite alignment parameters corresponding to the satellite alignment antenna.
In one embodiment, the star position information of the target satellite includes: satellite geostationary orbit radius and satellite longitude; the geographical position information of the opposite star antenna comprises: antenna longitude and antenna latitude;
the step of obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star information and the geographic position information comprises the following steps:
calculating a first azimuth angle and a first polarization angle according to the satellite longitude, the antenna longitude and the antenna latitude;
and calculating a first pitch angle according to the earth radius, the satellite geostationary orbit radius, the satellite longitude, the antenna longitude and the antenna latitude.
In one embodiment, the geographic location information of the pair of satellite antennas includes: antenna longitude, antenna latitude and antenna radial direction;
the step of obtaining the magnetic declination of the opposite satellite antenna according to the geographical position information comprises the following steps:
and calculating the magnetic declination of the opposite satellite antenna through a world geomagnetic model according to the longitude, the latitude and the radial direction of the antenna.
In one embodiment, the step of obtaining the second azimuth angle according to the declination and the first azimuth angle includes:
and performing summation operation on the magnetic declination and the first azimuth angle, and taking an operation result as a second azimuth angle.
In one embodiment, the step of obtaining a second pitch angle according to the pitch axis installation error deflection angle, the antenna deflection angle and the first pitch angle includes:
summing the antenna offset angle and the first pitch angle to obtain a first operation result;
and performing difference calculation on the first calculation result and the installation error deflection angle of the pitch axis to obtain a second calculation result, and taking the second calculation result as a second pitch angle.
A pair-star control device comprising:
the information acquisition module is used for acquiring the star position information of a target satellite and the geographic position information of a star antenna, and also used for acquiring the pitch axis installation error deflection angle and the antenna deflection angle of the star antenna;
the information processing module is used for obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star information and the geographic position information, wherein the first azimuth angle is an azimuth angle of the satellite antenna relative to true north; the satellite antenna system is also used for obtaining a magnetic declination of the satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite antenna relative to magnetic north; and the second azimuth angle, the second pitch angle and the polarization angle are used as the satellite alignment parameters corresponding to the satellite alignment antenna.
A pair-star control system comprising:
the antenna positioning device is used for measuring the geographic position information of the opposite satellite antenna;
the deflection angle acquisition device is used for acquiring a pitching axis installation error deflection angle and an antenna deflection feed angle of the opposite star antenna;
the satellite alignment control device is used for acquiring the satellite position information of a target satellite and the geographic position information measured by the antenna positioning device, and acquiring the installation error declination of the pitching axis and the antenna declination angle acquired by the declination acquisition device; obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star information and the geographic position information, wherein the first azimuth angle is an azimuth angle of the satellite antenna relative to true north; obtaining a magnetic declination of the satellite-to-satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite-to-satellite antenna relative to magnetic north; obtaining a second pitch angle according to the installation error deflection angle of the pitch shaft, the antenna deflection angle and the first pitch angle; and taking the second azimuth angle, the second pitch angle and the polarization angle as the satellite alignment parameters corresponding to the satellite alignment antenna.
In one embodiment, the method further comprises the following steps:
a satellite tuning demodulator for communicating with the target satellite;
the satellite alignment control device is further used for determining satellite alignment completion conditions of the satellite alignment antenna according to communication signal change information of the satellite adjustment demodulator during satellite alignment, and determining satellite alignment completion of the satellite alignment antenna and the target satellite when the communication signal strength reaches a preset strength threshold.
A computer device comprising a memory and a processor, the memory storing a computer program, the processor implementing the steps of the above-described method of controlling a satellite when executing the computer program.
A computer-readable storage medium, on which a computer program is stored which, when being executed by a processor, carries out the steps of the above-mentioned method of controlling a satellite.
The satellite alignment control method, the satellite alignment control device, the satellite alignment control system, the storage medium and the computer equipment acquire the satellite position information of a target satellite and the geographic position information of a satellite antenna, and obtain a first azimuth angle, a first pitch angle and a polarization angle according to the satellite position information and the geographic position information, wherein the first azimuth angle is an azimuth angle of the satellite antenna relative to true north; obtaining a magnetic declination of the satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite antenna relative to magnetic north; acquiring a pitch axis installation error deflection angle and an antenna deflection feed angle of the satellite antenna, and obtaining a second pitch angle according to the pitch axis installation error deflection angle, the antenna deflection feed angle and the first pitch angle; and taking the second azimuth angle, the second pitch angle and the polarization angle as corresponding satellite parameters of the satellite antenna. When the satellite is aimed, the azimuth angle of the satellite is compensated by the magnetic declination, the azimuth angle relative to the magnetic north can be obtained, the problem of inaccurate aiming of the satellite can be avoided by aiming the satellite according to the azimuth angle relative to the magnetic north, in addition, the declination angle information of the satellite antenna is combined to compensate the pitch angle, the accuracy of aiming the satellite can be further improved, and therefore the working performance of the satellite communication equipment is not influenced.
Drawings
FIG. 1 is a schematic diagram of azimuth, pitch, and polarization angles;
FIG. 2 is a schematic flow chart of a method for controlling a satellite in one embodiment;
FIG. 3 is a schematic structural diagram of a satellite control device in one embodiment;
FIG. 4 is a schematic flow chart of an exemplary star control system;
FIG. 5 is a schematic diagram of an interface of an opposite-star APP at an opposite-star terminal in one embodiment;
fig. 6 is a schematic structural diagram of an opposite-star antenna in one embodiment.
Detailed Description
In order to make the objects, technical solutions and advantages of the present application more apparent, the present application is described in further detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The satellite alignment control method can be applied to satellite communication devices/equipment/systems needing antenna satellite alignment, and the antenna satellite alignment refers to a process of aligning the center of an antenna beam to a target satellite by adjusting the azimuth angle, the pitch angle and the polarization angle of the antenna.
Specifically, as shown in fig. 1, the azimuth angle is an included angle between the due north direction and a clockwise direction of a beam center straight line (a dotted line in the figure) of the antenna, and the value range of the azimuth angle is 0 ° to 360 °. The elevation angle is an angle between a straight line direction (dotted line in the figure) of the beam center of the antenna and a horizontal line, and is generally an elevation angle. The polarization angle refers to the angle of a high-frequency head in the antenna relative to a standard position, the positive upper part is a polarization zero position (northeast coordinate system), the clockwise direction is positive, and the counterclockwise direction is negative. .
The antenna can ensure the corresponding satellite communication device/equipment/system to work stably and reliably only if the antenna is accurately aligned to the target satellite, so that the antenna-to-satellite is the basis for network access verification and daily service transmission of the satellite communication device/equipment/system, and the main steps in the antenna-to-satellite process are to adjust the azimuth angle, the pitch angle and the polarization angle of the antenna.
In one embodiment, as shown in fig. 2, a method for controlling a satellite is provided, which is described by taking as an example a control apparatus applied to a satellite communication device capable of performing satellite-to-satellite management, and includes the following steps:
step S100, acquiring star position information of a target satellite and geographical position information of a star antenna, and obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star position information and the geographical position information, wherein the first azimuth angle is an azimuth angle of the star antenna relative to true north.
When the satellite communication equipment needs to aim at the satellite, the control device firstly acquires corresponding star position information according to a target satellite selected by a user. The satellite position information of the satellite may be stored in a memory in advance, and when the control device acquires the information of the target satellite, the corresponding satellite position information may be matched from the memory. After obtaining the target satellite information, the control device may obtain the star position information corresponding to the target satellite by a method such as real-time inquiry.
In addition, the control device needs to acquire the geographic position information of the satellite antenna of the satellite communication device, and the geographic position information can be obtained through measurement of positioning devices/systems/software, such as longitude and latitude information and the like. After the control device obtains the star information of the target satellite and the geographical position information of the star antenna, the control device calculates according to the star information and the geographical position information to obtain a first azimuth angle, a first pitch angle and a polarization angle, wherein the first azimuth angle is an azimuth angle of the star antenna relative to true north.
And step S200, obtaining a magnetic declination of the satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is the azimuth angle of the satellite antenna relative to magnetic north.
In the angles calculated according to the star location information and the geographic position information, the first azimuth angle is the azimuth angle of the satellite aiming antenna relative to the true north, and due to the existence of the magnetic declination, if the satellite aiming is carried out according to the first azimuth angle, the problem of inaccurate satellite aiming can be caused.
In this step, after obtaining the first azimuth, the control device obtains a magnetic declination of the satellite antenna according to the geographical location information, and obtains a second azimuth which is an azimuth of the satellite antenna relative to magnetic north according to the magnetic declination and the first azimuth. The magnetic declination is an angle between magnetic north and true north, that is, an angle between north indicated by a south pointer and geographic north. Different regions have different declination angles, for example: in the east longitude region of 25 degrees, the magnetic declination is 1-2 degrees; in the area above 25 degrees of north latitude, the magnetic declination is more than 2 degrees; if in the low latitude areas of the west longitude, the declination is 5-20 degrees; the west longitude is more than 45 degrees, the magnetic declination is 25-50 degrees, and in China, the magnetic declination can reach 6 degrees at most under normal conditions, and is 2-3 degrees under general conditions. The first azimuth angle is compensated through the magnetic declination, the azimuth angle of the satellite antenna relative to the magnetic north, namely the second azimuth angle, can be obtained, the satellite is aimed according to the second azimuth angle, and the accuracy of the satellite can be effectively improved.
And step S300, acquiring a pitch axis installation error deflection angle and an antenna deflection feed angle of the satellite antenna, and obtaining a second pitch angle according to the pitch axis installation error deflection angle, the antenna deflection feed angle and the first pitch angle.
After the first pitch angle is obtained, considering that the deflection angle of the antenna can also have certain influence on the accuracy of the satellite, the control device also obtains the mounting error deflection angle of the pitch axis of the satellite antenna and the antenna deflection feed angle, obtains a second pitch angle according to the mounting error deflection angle of the pitch axis, the antenna deflection feed angle and the first pitch angle, and performs satellite alignment according to the second pitch angle, so that the accuracy of the satellite can be effectively improved.
And S400, taking the second azimuth angle, the second pitch angle and the polarization angle as corresponding satellite parameters of the satellite antenna.
After the control device calculates and obtains a second azimuth angle, a second pitch angle and a polarization angle, the second azimuth angle, the second pitch angle and the polarization angle are used as satellite alignment parameters corresponding to the satellite alignment antenna, and a user can perform satellite alignment operation according to the second azimuth angle, the second pitch angle and the polarization angle.
The embodiment provides a satellite alignment control method, when satellite alignment is performed, a magnetic declination angle is adopted to compensate an azimuth angle during satellite alignment, the azimuth angle relative to magnetic north can be obtained, the problem of inaccurate satellite alignment can be avoided by performing satellite alignment according to the azimuth angle relative to magnetic north, in addition, a pitch angle is compensated by combining declination angle information of a satellite antenna, the satellite alignment accuracy can be further improved, and therefore the working performance of satellite communication equipment is not influenced.
In one embodiment, the star position information of the target satellite comprises: satellite geostationary orbit radius and satellite longitude; the geographic position information of the satellite antenna comprises: antenna longitude and antenna latitude;
the method comprises the following steps of obtaining a first azimuth angle, a first pitch angle and a polarization angle according to star information and geographical position information, and comprises the following steps: calculating a first azimuth angle and a first polarization angle according to the satellite longitude, the antenna longitude and the antenna latitude; and calculating a first pitch angle according to the earth radius, the satellite geostationary orbit radius, the satellite longitude, the antenna longitude and the antenna latitude.
Specifically, the satellite geostationary orbit radius S _ R is 42164590 m, the earth radius E _ R is 6378160 m, the satellite longitude is λ S, the antenna longitude is λ a, the antenna latitude is Φ, and the difference in longitude between the satellite and the antenna is δ λ a- λ S.
The first azimuth calculation formula is:
the first pitch angle calculation formula is:
the calculation formula of the polarization angle is as follows:
in one embodiment, the geographic location information for the satellite antenna includes: antenna longitude, antenna latitude and antenna radial direction;
the step of obtaining the magnetic declination of the satellite antenna according to the geographical position information comprises the following steps: and calculating the magnetic declination of the satellite antenna through a world geomagnetic model according to the longitude, the latitude and the radial direction of the antenna.
Specifically, the longitude, latitude and radial direction of the antenna are set as r, λ and Φ, respectively, and the world geomagnetic model adopts WMM2015 world geomagnetic model (12-order spherical harmonic model):
wherein a is the radius of the earth (6371.2 km), t is the year,
and
is a gaussian coefficient related to time t; legendre function associated with m-th order Schmidt seminormalization
Is defined as:
the main magnetic field of the earth magnetism is BmRepresented by a negative gradient of the magnetic potential, then
The expression for each directional magnetic field component is:
magnetic field components in geodetic coordinates:
wherein φ 1 is the latitude under the geodetic coordinate.
The longitude under the geodetic coordinate system is equal to the longitude under the geocentric coordinate system, and then the declination calculation formula is as follows:
in one embodiment, the step of obtaining the second azimuth angle according to the declination and the first azimuth angle includes: and performing summation operation on the magnetic declination and the first azimuth angle, and taking the operation result as a second azimuth angle. Specifically, the calculation formula of the second azimuth angle is as follows: a2 ═ a1+ D.
In one embodiment, the step of obtaining the second pitch angle according to the pitch axis installation error deflection angle, the antenna deflection angle and the first pitch angle includes: summing the antenna offset angle and the first pitch angle to obtain a first operation result; and performing difference calculation on the first calculation result and the installation error deflection angle of the pitch axis to obtain a second calculation result, and taking the second calculation result as a second pitch angle. Specifically, if the antenna offset angle is set to be m, and the pitch axis installation error offset angle is set to be n, the second pitch angle calculation formula is as follows: t2 ═ T1+ m-n.
It should be understood that, although the steps in the flowchart of fig. 2 are shown in order as indicated by the arrows, the steps are not necessarily performed in order as indicated by the arrows. The steps are not performed in the exact order shown and described, and may be performed in other orders, unless explicitly stated otherwise. Moreover, at least a portion of the steps in fig. 2 may include multiple sub-steps or multiple stages that are not necessarily performed at the same time, but may be performed at different times, and the order of performance of the sub-steps or stages is not necessarily sequential, but may be performed in turn or alternately with other steps or at least a portion of the sub-steps or stages of other steps.
In one embodiment, as shown in fig. 3, there is provided a pair-star control apparatus, comprising: an information acquisition module 110 and an information processing module 120.
The information obtaining module 110 is configured to obtain star position information of the target satellite and geographic position information of the satellite antenna, and further obtain a pitch axis installation error drift angle and an antenna drift feed angle of the satellite antenna.
The information processing module 120 is configured to obtain a first azimuth, a first pitch angle, and a polarization angle according to the star information and the geographic position information, where the first azimuth is an azimuth of the satellite antenna relative to true north; the satellite antenna positioning system is also used for obtaining a magnetic declination angle of the satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination angle and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite antenna relative to magnetic north; and the second pitch angle is obtained according to the pitch axis installation error deflection angle, the antenna deflection angle and the first pitch angle, and the second azimuth angle, the second pitch angle and the polarization angle are used as satellite alignment parameters corresponding to the satellite alignment antenna.
For specific limitations of the star control device, reference may be made to the above limitations of the star control method, which are not described herein again. All or part of each module in the pair of satellite control devices can be realized by software, hardware and a combination thereof. The modules can be embedded in a hardware form or independent from a processor in the computer device, and can also be stored in a memory in the computer device in a software form, so that the processor can call and execute operations corresponding to the modules.
This embodiment provides a to star controlling means, when carrying out the alignment, adopt the magnetic declination to compensate the azimuth angle when the star, can obtain the azimuth angle for magnetic north, carry out the alignment according to the azimuth angle for magnetic north and can avoid appearing the inaccurate problem of alignment, in addition, combine to compensate the pitch angle to the declination information of star antenna, can further improve the accuracy of alignment to the star to guarantee that the working property of satellite communication equipment is not influenced.
In one embodiment, as shown in fig. 4, there is provided a pair-star control system, comprising: an antenna positioning device 210, a deflection angle obtaining device 220 and a satellite control device 230.
The antenna positioner 210 is used to measure the geographic location information of the opposite satellite antenna.
The deflection angle obtaining device 220 is used for obtaining a tilt angle of a pitch axis installation error of the satellite antenna and an antenna deflection angle.
The satellite control device 230 is configured to obtain satellite position information of the target satellite and geographic position information measured by the antenna positioning device 210, and obtain a pitch axis installation error drift angle and an antenna drift angle obtained by the drift angle obtaining device; obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star information and the geographic position information, wherein the first azimuth angle is an azimuth angle of the satellite antenna relative to true north; obtaining a magnetic declination of the satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite antenna relative to magnetic north; obtaining a second pitch angle according to the mounting error deflection angle of the pitch shaft, the antenna deflection angle and the first pitch angle; and taking the second azimuth angle, the second pitch angle and the polarization angle as corresponding satellite parameters of the satellite antenna.
Specifically, the antenna positioning device 210 may be a GPS positioning module or a beidou positioning module, as long as the module can acquire the geographic position information of the satellite antenna. The declination obtaining device 220 includes an electronic compass and an accelerometer, which may be a three-dimensional electronic compass and a three-axis accelerometer, and the three-dimensional electronic compass and the three-axis accelerometer are disposed on the feed source support of the opposite satellite antenna. It should be noted that, before the three-dimensional electronic compass is used, the azimuth axis needs to be manually rotated by 360 degrees, so that the influence of soft magnetism near the antenna on the three-dimensional electronic compass can be calibrated.
Further, the antenna offset angle corresponding to the antenna is a fixed value, and the antenna offset angles corresponding to different antennas may be the same or different, and the antenna offset angle may be obtained directly according to information such as the antenna type and the antenna number. When detecting the installation error deflection angle of the pitching axis, firstly, assuming that the installation error deflection angle of the pitching axis is zero, then, placing the antenna on a horizontal plane to align the satellite, and after determining the alignment of the satellite, if the equation: if the pitch angle is formed by detecting the elevation angle and the offset angle by the sensor, the mounting error offset angle of the pitch shaft is zero; if the difference value is not true, the difference value between the actual detection value of the sensor and the theoretical value is the installation error deflection angle of the pitching axis.
The embodiment provides a to star control system, when carrying out to the star, adopt the magnetic declination to compensate to the azimuth angle when the star, can obtain the azimuth angle for magnetic north, carry out to the star according to the azimuth angle for magnetic north and can avoid appearing the inaccurate problem of star to the star, in addition, combine to compensate to the pitch angle of star antenna's declination information, can further improve to the star accuracy to guarantee that the working property of satellite communication equipment is not influenced.
In one embodiment, referring to fig. 4, the pair of satellite control systems further includes: a satellite trim demodulator 240 for communicating with a target satellite;
the satellite alignment control device 230 is further configured to determine a satellite alignment completion condition of the satellite alignment antenna according to the communication signal change information of the satellite alignment satellite adjusting demodulator, and determine that satellite alignment of the satellite alignment antenna and the target satellite is completed when the communication signal strength reaches a preset strength threshold.
Specifically, the signal strength EN/b0 value of the satellite adjusting demodulator can be obtained during satellite alignment, fine adjustment is performed according to the size change trend of the signal strength EN/b0 value, and when the signal strength EN/b0 value is strongest (for example, exceeds a certain preset strength threshold), the satellite alignment effect on the satellite antenna and the target satellite is the best.
In the embodiment, the satellite adjusting demodulator is arranged, so that the satellite can be adjusted according to the signal intensity of the satellite adjusting demodulator, and the satellite accuracy is further improved.
In an embodiment, a satellite alignment terminal is provided, which may be but is not limited to various personal computers, notebook computers, smart phones, tablet computers and portable wearable devices, and is installed with a satellite alignment APP (Application), an interface of the satellite alignment APP is shown in fig. 5, the satellite alignment APP may calculate an azimuth angle, a pitch angle and a polarization angle of satellite alignment through the steps of the satellite alignment control method described in the above embodiments, and a user may perform satellite alignment according to data displayed by the satellite alignment terminal.
Specifically, as shown in fig. 6, which is a schematic diagram of a specific structure of the satellite alignment antenna, when a user aligns the satellite alignment antenna, first, according to a polarization angle displayed on the satellite alignment terminal, the user manually rotates a polarization pointer to a numerical value corresponding to a dial (circular polarization only needs to be left-handed or right-handed), and fastens the polarization axis 310; then, manually rotating the azimuth axis according to the azimuth axis pointer disc displayed on the opposite star terminal, and fastening the azimuth axis 320 when the antenna azimuth pointer and the opposite star azimuth pointer are superposed; then, manually rotating the pitch axis according to a pitch axis pointer disc displayed on the opposite star terminal, and fastening the pitch axis 330 when the antenna pitch angle pointer is superposed with the opposite star pitch angle pointer; and finally, finely adjusting the azimuth axis and the pitch axis of the antenna according to the variation trend of the satellite modulation and demodulation signal strength EN/b0 value displayed on the satellite terminal, and searching the strongest signal strength EN/b0 value. Through the steps, the satellite operation can be completed, and the satellite alignment efficiency can be improved to a certain extent through the adjustment mode.
This embodiment provides a to star terminal, should install to star APP to star terminal, the user can carry out to the star according to this data to star APP provides to make to star operation simple and convenient more.
In one embodiment, a computer device is provided, comprising a memory and a processor, the memory having a computer program stored therein, the processor implementing the following steps when executing the computer program: acquiring star position information of a target satellite and geographical position information of a star antenna, and obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star position information and the geographical position information, wherein the first azimuth angle is an azimuth angle of the star antenna relative to true north; obtaining a magnetic declination of the satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite antenna relative to magnetic north; acquiring a pitch axis installation error deflection angle and an antenna deflection feed angle of the satellite antenna, and obtaining a second pitch angle according to the pitch axis installation error deflection angle, the antenna deflection feed angle and the first pitch angle; and taking the second azimuth angle, the second pitch angle and the polarization angle as corresponding satellite parameters of the satellite antenna.
In one embodiment, the processor, when executing the computer program, further performs the steps of: calculating a first azimuth angle and a first polarization angle according to the satellite longitude, the antenna longitude and the antenna latitude; and calculating a first pitch angle according to the earth radius, the satellite geostationary orbit radius, the satellite longitude, the antenna longitude and the antenna latitude.
In one embodiment, the processor, when executing the computer program, further performs the steps of: and calculating the magnetic declination of the satellite antenna through a world geomagnetic model according to the longitude, the latitude and the radial direction of the antenna.
In one embodiment, the processor, when executing the computer program, further performs the steps of: and performing summation operation on the magnetic declination and the first azimuth angle, and taking the operation result as a second azimuth angle.
In one embodiment, the processor, when executing the computer program, further performs the steps of: summing the antenna offset angle and the first pitch angle to obtain a first operation result; and performing difference calculation on the first calculation result and the installation error deflection angle of the pitch axis to obtain a second calculation result, and taking the second calculation result as a second pitch angle.
In one embodiment, a computer-readable storage medium is provided, having a computer program stored thereon, which when executed by a processor, performs the steps of: acquiring star position information of a target satellite and geographical position information of a star antenna, and obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star position information and the geographical position information, wherein the first azimuth angle is an azimuth angle of the star antenna relative to true north; obtaining a magnetic declination of the satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite antenna relative to magnetic north; acquiring a pitch axis installation error deflection angle and an antenna deflection feed angle of the satellite antenna, and obtaining a second pitch angle according to the pitch axis installation error deflection angle, the antenna deflection feed angle and the first pitch angle; and taking the second azimuth angle, the second pitch angle and the polarization angle as corresponding satellite parameters of the satellite antenna.
In one embodiment, the computer program when executed by the processor further performs the steps of: calculating a first azimuth angle and a first polarization angle according to the satellite longitude, the antenna longitude and the antenna latitude; and calculating a first pitch angle according to the earth radius, the satellite geostationary orbit radius, the satellite longitude, the antenna longitude and the antenna latitude.
In one embodiment, the computer program when executed by the processor further performs the steps of: and calculating the magnetic declination of the satellite antenna through a world geomagnetic model according to the longitude, the latitude and the radial direction of the antenna.
In one embodiment, the computer program when executed by the processor further performs the steps of: and performing summation operation on the magnetic declination and the first azimuth angle, and taking the operation result as a second azimuth angle.
In one embodiment, the computer program when executed by the processor further performs the steps of: summing the antenna offset angle and the first pitch angle to obtain a first operation result; and performing difference calculation on the first calculation result and the installation error deflection angle of the pitch axis to obtain a second calculation result, and taking the second calculation result as a second pitch angle.
It will be understood by those skilled in the art that all or part of the processes of the methods of the embodiments described above can be implemented by hardware related to instructions of a computer program, which can be stored in a non-volatile computer-readable storage medium, and when executed, the computer program can include the processes of the embodiments of the methods described above. Any reference to memory, storage, database, or other medium used in the embodiments provided herein may include non-volatile and/or volatile memory, among others. Non-volatile memory can include read-only memory (ROM), Programmable ROM (PROM), Electrically Programmable ROM (EPROM), Electrically Erasable Programmable ROM (EEPROM), or flash memory. Volatile memory can include Random Access Memory (RAM) or external cache memory. By way of illustration and not limitation, RAM is available in a variety of forms such as Static RAM (SRAM), Dynamic RAM (DRAM), Synchronous DRAM (SDRAM), Double Data Rate SDRAM (DDRSDRAM), Enhanced SDRAM (ESDRAM), Synchronous Link DRAM (SLDRAM), Rambus Direct RAM (RDRAM), direct bus dynamic RAM (DRDRAM), and memory bus dynamic RAM (RDRAM).
The technical features of the embodiments described above may be arbitrarily combined, and for the sake of brevity, all possible combinations of the technical features in the embodiments described above are not described, but should be considered as being within the scope of the present specification as long as there is no contradiction between the combinations of the technical features.
The above-mentioned embodiments only express several embodiments of the present invention, and the description thereof is more specific and detailed, but not construed as limiting the scope of the invention. It should be noted that, for a person skilled in the art, several variations and modifications can be made without departing from the inventive concept, which falls within the scope of the present invention. Therefore, the protection scope of the present patent shall be subject to the appended claims.
Claims (10)
1. A method for controlling a satellite is characterized by comprising the following steps:
acquiring star position information of a target satellite and geographical position information of a star antenna, and obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star position information and the geographical position information, wherein the first azimuth angle is an azimuth angle of the star antenna relative to true north;
obtaining a magnetic declination of the satellite-to-satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite-to-satellite antenna relative to magnetic north;
acquiring a pitching axis installation error deflection angle and an antenna deflection feed angle of the satellite antenna, and obtaining a second pitch angle according to the pitching axis installation error deflection angle, the antenna deflection feed angle and the first pitch angle;
and taking the second azimuth angle, the second pitch angle and the polarization angle as the satellite alignment parameters corresponding to the satellite alignment antenna.
2. The method of claim 1, wherein the satellite position information of the target satellite comprises: satellite geostationary orbit radius and satellite longitude; the geographical position information of the opposite star antenna comprises: antenna longitude and antenna latitude;
the step of obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star information and the geographic position information comprises the following steps:
calculating a first azimuth angle and a first polarization angle according to the satellite longitude, the antenna longitude and the antenna latitude;
and calculating a first pitch angle according to the earth radius, the satellite geostationary orbit radius, the satellite longitude, the antenna longitude and the antenna latitude.
3. The method according to claim 1, wherein the geographic location information of the satellite antenna comprises: antenna longitude, antenna latitude and antenna radial direction;
the step of obtaining the magnetic declination of the opposite satellite antenna according to the geographical position information comprises the following steps:
and calculating the magnetic declination of the opposite satellite antenna through a world geomagnetic model according to the longitude, the latitude and the radial direction of the antenna.
4. The method for controlling a satellite according to claim 1, wherein the step of obtaining a second azimuth angle according to the declination and the first azimuth angle comprises:
and performing summation operation on the magnetic declination and the first azimuth angle, and taking an operation result as a second azimuth angle.
5. The method for controlling a satellite according to claim 1, wherein the step of obtaining a second pitch angle according to the pitch axis installation error bias angle, the antenna bias feed angle and the first pitch angle comprises:
summing the antenna offset angle and the first pitch angle to obtain a first operation result;
and performing difference calculation on the first calculation result and the installation error deflection angle of the pitch axis to obtain a second calculation result, and taking the second calculation result as a second pitch angle.
6. A pair-star control device, comprising:
the information acquisition module is used for acquiring the star position information of a target satellite and the geographic position information of a star antenna, and also used for acquiring the pitch axis installation error deflection angle and the antenna deflection angle of the star antenna;
the information processing module is used for obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star information and the geographic position information, wherein the first azimuth angle is an azimuth angle of the satellite antenna relative to true north; the satellite antenna system is also used for obtaining a magnetic declination of the satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite antenna relative to magnetic north; and the second azimuth angle, the second pitch angle and the polarization angle are used as the satellite alignment parameters corresponding to the satellite alignment antenna.
7. A pair-star control system, comprising:
the antenna positioning device is used for measuring the geographic position information of the opposite satellite antenna;
the deflection angle acquisition device is used for acquiring a pitching axis installation error deflection angle and an antenna deflection feed angle of the opposite star antenna;
the satellite alignment control device is used for acquiring the satellite position information of a target satellite and the geographic position information measured by the antenna positioning device, and acquiring the installation error declination of the pitching axis and the antenna declination angle acquired by the declination acquisition device; obtaining a first azimuth angle, a first pitch angle and a polarization angle according to the star information and the geographic position information, wherein the first azimuth angle is an azimuth angle of the satellite antenna relative to true north; obtaining a magnetic declination of the satellite-to-satellite antenna according to the geographical position information, and obtaining a second azimuth angle according to the magnetic declination and the first azimuth angle, wherein the second azimuth angle is an azimuth angle of the satellite-to-satellite antenna relative to magnetic north; obtaining a second pitch angle according to the installation error deflection angle of the pitch shaft, the antenna deflection angle and the first pitch angle; and taking the second azimuth angle, the second pitch angle and the polarization angle as the satellite alignment parameters corresponding to the satellite alignment antenna.
8. The pair-star control system according to claim 7, further comprising:
a satellite tuning demodulator for communicating with the target satellite;
the satellite alignment control device is further used for determining satellite alignment completion conditions of the satellite alignment antenna according to communication signal change information of the satellite adjustment demodulator during satellite alignment, and determining satellite alignment completion of the satellite alignment antenna and the target satellite when the communication signal strength reaches a preset strength threshold.
9. A computer device comprising a memory and a processor, the memory storing a computer program, characterized in that the processor, when executing the computer program, implements the steps of the method of controlling a satellite according to any one of claims 1 to 5.
10. A computer-readable storage medium, on which a computer program is stored, which, when being executed by a processor, carries out the steps of the method of controlling a satellite according to any one of claims 1 to 5.
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