CN115333596B - Satellite communication system for aircraft and antenna array selection method - Google Patents

Satellite communication system for aircraft and antenna array selection method Download PDF

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Publication number
CN115333596B
CN115333596B CN202211252280.6A CN202211252280A CN115333596B CN 115333596 B CN115333596 B CN 115333596B CN 202211252280 A CN202211252280 A CN 202211252280A CN 115333596 B CN115333596 B CN 115333596B
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aircraft
antenna array
satellite
antenna
coordinate system
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CN115333596A (en
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张春水
李昕
吴志勇
于跃
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Huanyu Jiacheng Technology Beijing Co ltd
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Huanyu Jiacheng Technology Beijing Co ltd
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    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/02—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas
    • H04B7/04—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas
    • H04B7/06—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the transmitting station
    • H04B7/0602—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the transmitting station using antenna switching
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/02—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas
    • H04B7/04—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas
    • H04B7/08—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the receiving station
    • H04B7/0802—Diversity systems; Multi-antenna system, i.e. transmission or reception using multiple antennas using two or more spaced independent antennas at the receiving station using antenna selection
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/18502—Airborne stations

Abstract

The invention relates to the field of satellite communication, and provides a satellite communication system for an aircraft and an antenna array selection method, wherein the method comprises the following steps: monitoring whether complete antenna selection input parameters are acquired; calculating vector data of a connecting line between the aircraft and the satellite by using the antenna selection input parameters; calculating the included angle between the orientation of each antenna array and the connecting line; determining the antenna array with the minimum included angle as the optimal antenna array of the current calculation period; judging whether the optimal antenna arrays of a plurality of continuous calculation periods are the same antenna array or not; judging whether the difference value of the included angle of the optimal antenna array and the included angle of the currently started antenna array is larger than a set threshold value or not; and when the difference value between the included angle of the optimal antenna array and the included angle of the currently started antenna array is larger than a set threshold value, starting the optimal antenna array.

Description

Satellite communication system for aircraft and antenna array selection method
Technical Field
The invention relates to the field of satellite communication, in particular to a satellite communication system for an aircraft and an antenna array selection method.
Background
In order to cope with changes in the attitude and direction of the aircraft, a plurality of array antennas at different angles are usually mounted on the aircraft. Besides the antenna array, the communication system is also provided with modules such as frequency conversion, power amplification, baseband processing and the like, so as to realize signal receiving and transmitting. The receiving and the transmitting are array antennas, the zero-setting anti-interference processing can be utilized for receiving satellite signals, the pressure-resistant type forced interference is realized, the reliability of received signals is improved, the beam forming can be realized by utilizing the array antennas for transmitting signals, the EIRP value of the transmission is effectively improved, and therefore the data transmission rate can be effectively improved. By adopting the plurality of array antennas, satellite communication can be realized from all directions after the attitude of the carrier is changed, and the communication blind area of the carrier is effectively reduced.
During the flight, the quality of signals received and transmitted by each array antenna is dynamically changed, and if all the array antennas are started at the full time, resources are obviously wasted, so that the antenna arrays are required to be dynamically switched according to the condition of the aircraft. In the prior art, an optimal antenna array is determined and switched according to the signal quality of each antenna array in real time. However, in practical situations, the attitude of the aircraft changes frequently, for example, the aircraft itself rotates to change the orientation of the antenna array, and the switching after the judgment according to the signal quality has hysteresis, and in this way, all the antenna arrays must be activated sequentially or simultaneously to calculate the corresponding signal quality, which still wastes resources.
Disclosure of Invention
In view of the above, the present invention provides an antenna array selection method for an aircraft, wherein a plurality of antenna arrays are arranged on the aircraft in different orientations, and only one antenna array is in an active state at a time, the method comprising:
monitoring whether complete antenna selection input parameters are acquired, wherein the antenna selection input parameters comprise aircraft initial position information, aircraft current attitude information and satellite position information;
when complete antenna selection input parameters can be obtained, calculating vector data of a connecting line between the aircraft and the satellite by using the antenna selection input parameters;
calculating included angles between the orientations of the antenna arrays and the connecting line according to vector data of antenna normals of the antenna arrays, which are oriented to different antenna arrays, on the aircraft and vector data of the aircraft and the connecting line;
determining an antenna array with the minimum included angle as an optimal antenna array of the current calculation period;
judging whether the optimal antenna arrays of a plurality of continuous calculation periods are the same antenna array or not;
when the optimal antenna arrays of a plurality of continuous calculation periods are the same antenna array, judging whether the difference value between the included angle of the optimal antenna array and the included angle of the currently started antenna array is larger than a set threshold value;
and when the difference value between the included angle of the optimal antenna array and the included angle of the currently started antenna array is larger than a set threshold value, starting the optimal antenna array.
Optionally, there are 3 antenna arrays, evenly arranged around the aircraft.
Optionally, the aircraft initial position information comprises shot to
Figure 981015DEST_PATH_IMAGE001
Latitude of geocentric
Figure 35559DEST_PATH_IMAGE002
Longitude, longitude
Figure 465403DEST_PATH_IMAGE003
Elevation
Figure 113553DEST_PATH_IMAGE004
(ii) a The current position information of the aircraft is coordinate information of the aircraft in a launching inertial coordinate system; the current attitude information of the aircraft is an attitude angle of the aircraft relative to a launching inertial system; the satellite position information comprises position information of the satellite in a geocentric fixed spherical coordinate system.
Optionally, calculating vector data of a connection line between the aircraft and the satellite by using the antenna selection input parameter specifically includes:
converting the position of the satellite under the earth center spherical surface fixed coordinate system into the position under the earth center rectangular coordinate system;
converting the position under the geocentric rectangular coordinate system into a transmitting coordinate system, and further calculating the position of the satellite relative to the transmitting coordinate system;
converting the position of the satellite relative to the launching system into the position of the satellite in the launching inertial coordinate system;
converting the position of the satellite in the launching inertial coordinate system into an aircraft coordinate system, and further calculating the position of the satellite relative to the aircraft coordinate system;
and calculating vector data of a connecting line between the aircraft and the satellite by using the position of the satellite relative to the aircraft coordinate system and the position of the aircraft in the aircraft coordinate system.
Optionally, the following calculation method is adopted to convert the position of the satellite in the geocentric sphere fixed coordinate system into the position in the geocentric rectangular coordinate system:
Figure 919835DEST_PATH_IMAGE005
，
Figure 953519DEST_PATH_IMAGE006
，
Figure 819844DEST_PATH_IMAGE007
，
wherein
Figure 814345DEST_PATH_IMAGE008
The distance between the earth center and the ground,
Figure 299684DEST_PATH_IMAGE009
Is the latitude of the geocentric region,
Figure 63240DEST_PATH_IMAGE010
Is the longitude of the earth's center, and is,
Figure 100467DEST_PATH_IMAGE011
、
Figure 211292DEST_PATH_IMAGE012
、
Figure 359376DEST_PATH_IMAGE013
is a three-dimensional coordinate under the geocentric rectangular coordinate system.
Optionally, the position of the satellite relative to the transmission system is calculated by the following calculation method:
Figure 118385DEST_PATH_IMAGE014
wherein
Figure 326512DEST_PATH_IMAGE015
、
Figure 295605DEST_PATH_IMAGE016
、
Figure 372015DEST_PATH_IMAGE017
Are the three-dimensional coordinates of the satellite relative to the transmission system,
Figure 110164DEST_PATH_IMAGE011
、
Figure 489192DEST_PATH_IMAGE012
、
Figure 820948DEST_PATH_IMAGE013
is a three-dimensional coordinate of the satellite under the earth center rectangular coordinate system,
Figure 310835DEST_PATH_IMAGE018
is a transformation matrix set according to direction, latitude and longitude in the earth.
Optionally, the position of the satellite relative to the transmission system is converted into the position of the satellite in the transmission inertial coordinate system by adopting the following calculation method:
Figure 795168DEST_PATH_IMAGE019
wherein
Figure 79519DEST_PATH_IMAGE020
、
Figure 23204DEST_PATH_IMAGE021
、
Figure 192148DEST_PATH_IMAGE022
Three-dimensional coordinates of the satellite in the transmit inertial frame,
Figure 904890DEST_PATH_IMAGE015
、
Figure 625721DEST_PATH_IMAGE016
、
Figure 915757DEST_PATH_IMAGE017
are the three-dimensional coordinates of the satellite relative to the transmission system,
Figure 747447DEST_PATH_IMAGE023
is a transformation matrix set according to the rotational angular velocity, time of flight, direction and geodetic latitude of the earth.
Optionally, the position of the satellite relative to the aircraft coordinate system is calculated using the following calculation:
Figure 455640DEST_PATH_IMAGE024
wherein
Figure 347372DEST_PATH_IMAGE025
、
Figure 70DEST_PATH_IMAGE026
、
Figure 258620DEST_PATH_IMAGE027
Are the three-dimensional coordinates of the satellite relative to the aircraft coordinate system,
Figure 945953DEST_PATH_IMAGE020
、
Figure 8587DEST_PATH_IMAGE021
、
Figure 23948DEST_PATH_IMAGE022
three-dimensional coordinates of the satellite in the transmit inertial frame,
Figure 197440DEST_PATH_IMAGE028
、
Figure 863914DEST_PATH_IMAGE029
、
Figure 97449DEST_PATH_IMAGE030
is three-dimensional coordinate information of the aircraft in a transmitting inertial coordinate system,
Figure 724739DEST_PATH_IMAGE031
the transformation matrix is set for the attitude angle of the aircraft relative to the launching inertial system according to the current attitude information of the aircraft.
Optionally, when the complete antenna selection input parameters cannot be acquired, sequentially setting each antenna array to be in an enabled state and communicating with the satellite, calculating a signal-to-noise ratio according to the received signals, determining the antenna array with the highest signal-to-noise ratio as an optimal antenna array, and keeping enabling the optimal antenna array until the complete antenna selection input parameters can be acquired.
The invention provides a satellite communication system for an aircraft, comprising: a communication host and a plurality of antenna array front ends, wherein
The front end of the antenna array is provided with a plurality of array elements and low-noise amplifier receiving channels which are connected with the array elements in a one-to-one manner; the communication host is provided with a baseband processing module, a power amplifier module and a down-conversion module, the baseband processing module is used for executing the antenna array selection method for the aircraft, and an antenna array front end is communicated as an enabled antenna array front end by controlling the power amplifier module and the down-conversion module, so that the communication with a satellite is carried out through the array elements in the enabled antenna array front end.
According to the satellite communication system for the aircraft and the antenna array selection method provided by the embodiment of the invention, the vector data of the connection line between the aircraft and the satellite is calculated by obtaining the antenna selection input parameters, the included angle between the normal of each antenna array interface and the direction of the satellite is calculated according to the vector data of the normal of the antenna, and the front end of the optimal antenna array is further determined according to the included angle value, so that the communication system does not need to start all the antenna arrays sequentially or simultaneously, only needs to periodically calculate the value of the included angle, and can directly start the optimal antenna array when the switching condition is met, thereby ensuring that the signal quality meets the communication requirement and having strong real-time performance. Meanwhile, the operation of calculating the included angle is executed periodically, and the antenna array switching action is executed according to the calculation results of a plurality of continuous periods and the comparison with the currently-started antenna array, so that the influence of frequent or unnecessary execution of the switching action on normal communication is avoided.
The communication system provided by the invention has the advantages that the low noise is arranged at the front end of the antenna, so that the insertion loss caused by a long cable and a switch is reduced, and the noise coefficient of the whole receiving machine is favorably reduced; at the front end of the ungated array antenna, the low-noise amplifier is not fed, so that the isolation between the antenna arrays is very high, ungated array signals cannot be introduced into the normal working antenna array, no superposition interference is caused, and the anti-interference effect is effectively guaranteed; the transmitting antennas can share the transmitting power amplifier, the utilization rate of power amplifier resources is high, the power amplifier and the low-noise amplifier are not in a space, and the receiving and transmitting isolation degree is effectively improved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the prior art descriptions will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural diagram of a satellite communication system for an aircraft according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of the front end of an antenna array in an embodiment of the invention;
FIG. 3 is a schematic diagram of a communication host according to an embodiment of the present invention;
FIG. 4 is a schematic diagram of an aircraft equipped with multiple antenna array front ends in an embodiment of the invention;
FIG. 5 is a flow chart of an antenna array selection method for an aircraft according to an embodiment of the invention;
FIG. 6 is a schematic diagram of a vector in an embodiment of the invention;
fig. 7 is a schematic diagram of an antenna normal in an embodiment of the invention.
Detailed Description
The technical solutions of the present invention will be described clearly and completely with reference to the accompanying drawings, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In addition, the technical features involved in the different embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Fig. 1 shows a satellite communication system for an aircraft, which includes a communication host 1 and a plurality of antenna array front ends 2, and further as shown in fig. 2, a plurality of array elements 21 are provided in the antenna array front ends 2, and low-noise receiving channels 22 are connected to the plurality of array elements one-to-one, in this embodiment, there are specifically 3 antenna array front ends 2, and there are 7 array elements 21 and 7 low-noise receiving channels 22 in each antenna array front end 2.
The array element 21 of this embodiment is a passive antenna array element, and has two interfaces, namely receiving and transmitting. A low-noise receiving channel is arranged on a receiving interface of each array element 21, a transmitting interface is directly connected with a cable, and the front end of the antenna array is composed of the array elements 21, the low-noise receiving channel 22 and the structural members of the related cables.
As shown in fig. 3, the communication host 1 is provided with a baseband processing module 11, a power amplifier module 12 and a down-conversion module 13.
Regarding receiving satellite signals, a down-conversion module 13 gates a receiving link of each antenna array front end 2 through a switch to obtain all receiving channels of the desired gating antenna array front end 2, a radio frequency down-conversion processing channel with the same number as that of array elements in a single array is arranged in the down-conversion module 13, the obtained receiving channels are all subjected to down-conversion processing, and after frequency conversion, intermediate frequency signals are transmitted to a baseband processing module 11;
regarding transmitting signals to the satellite, the power amplifier module 12 divides the radio frequency signals sent by the baseband processing module 11 into power amplifier channels with the same number as the array elements 21, and then switches and selects to connect all the power amplifier channels with the array elements 21 of the gating antenna array front end 2.
In a conventional satellite communication system with multiple array antennas, a passive antenna mode is usually adopted at the front end of an antenna array, and each transmit-receive antenna element is connected to a processor through two cables, or radio frequency processing and power amplification are both placed at the front end of the antenna array. By adopting a passive mode, the noise coefficient is deteriorated, the isolation between the front ends of the array antennas is not high, the receiving anti-interference effect is deteriorated, and by adopting a second mode, the layout of the front ends of the array antennas is crowded, the power amplifier resources are wasted, the receiving and transmitting isolation is poor, and the transmitting signals can influence a receiving end.
In the embodiment, the low-noise amplifier is positioned at the front end of the antenna, so that the insertion loss caused by a long cable and a switch is reduced, and the noise coefficient of the whole receiving machine is favorably reduced; at the front end of the ungated array antenna, the low-noise amplifier is not fed, so that the isolation between the antenna arrays is very high, ungated array signals cannot be introduced into the normal working antenna array, no superposition interference is caused, and the anti-interference effect is effectively guaranteed; the transmitting antennas can share the transmitting power amplifier, the utilization rate of power amplifier resources is high, the power amplifier and the low-noise amplifier are not in a space, and the receiving and transmitting isolation degree is effectively improved.
In the present embodiment, the antenna arrays are multiple and are disposed on the aircraft in different orientations, and only one antenna array is in an active state at the same time, as shown in fig. 4, in this embodiment, the aircraft 00 is a column, 3 antenna array front ends 2 are disposed on the column in different orientations in a surrounding manner, all the array elements 21 in the same antenna array front end 2 are disposed on a plane, and a dotted line shown in the figure is a normal line of each antenna array front end 2 (a virtual line perpendicular to a plane where the array elements 21 are located, which is referred to as an antenna aperture plane method for short).
The included angle between the normal line of the antenna aperture surface of each array antenna, the central point of the antenna aperture surface and the satellite connecting line can be calculated through the geographic position information of the satellite, the position coordinates of each antenna mounted on the aircraft, the initial geographic position of the aircraft, and the real-time geographic position and attitude of the aircraft. The smaller this angle, the better the antenna position. And then, by combining the signal strength and the signal quality of the satellite signals tracked by the receiving channels of each array antenna, the optimal antenna can be selected to communicate with the satellite.
The present embodiment provides an antenna array selection method for an aircraft, which is performed by an arithmetic device, such as a baseband processing module 11, provided in a communication system on the aircraft. The optimal antenna array is determined by executing an antenna array selection method, and then the power amplification module 12 and the down-conversion module 13 are controlled to be communicated with one antenna array front end 2 based on the calculation result to serve as the enabled antenna array front end, so that the communication with the satellite is carried out through the array elements in the enabled antenna array front end.
As shown in fig. 5, the antenna array selection method for an aircraft includes the following steps:
s1, monitoring whether complete antenna selection input parameters are acquired, wherein the antenna selection input parameters comprise aircraft initial position information, aircraft current attitude information and satellite position information. The step is complete, namely all parameters can be acquired, the scheme has high requirement on communication reliability, the step S2 is executed only when all antenna selection input parameters can be acquired, and the step S8 is executed if one or more parameters are lacked, so that accurate calculation cannot be carried out.
And S2, calculating vector data of a connecting line between the aircraft and the satellite by using the antenna selection input parameters. As shown in FIG. 6, in this step, the vector of the connection line between the aircraft O and the satellite S needs to be calculated
Figure 577289DEST_PATH_IMAGE032
There are many ways to calculate this data, and a suitable algorithm is designed according to the kind of input parameters selected.
And S3, calculating the included angle between the orientation of each antenna array and the connecting line according to the vector data of the antenna normal lines of each antenna array oriented to different directions on the aircraft and the vector data of the aircraft and the connecting line. In the specific embodiment shown in fig. 6, the aircraft has 3 antenna arrays with vector data for their normals of 3 antennas
Figure 973635DEST_PATH_IMAGE033
、
Figure 378072DEST_PATH_IMAGE034
And
Figure 118757DEST_PATH_IMAGE035
as shown in fig. 7, the antenna normal vector is predetermined based on the antenna array assembly position and angle in the aircraft coordinate system.
And S4, determining the antenna array with the minimum included angle as the optimal antenna array of the current calculation period. This step can be expressed as
Figure 899631DEST_PATH_IMAGE036
，
Figure 884905DEST_PATH_IMAGE037
The angle is the minimum included angle, and the angle is the minimum included angle,
Figure 601188DEST_PATH_IMAGE038
is the normal vector of the kth antenna.
And S5, judging whether the optimal antenna arrays of a plurality of continuous calculation periods are the same antenna array or not. Specifically, the method is periodically executed during the flight, for example, the calculation period is set to 10ms-100ms. In the case of frequent change of the attitude of the aircraft, the optimal antenna arrays calculated before and after may be different, and in the actual situation, data communication is performed between the aircraft and the satellite at any time, and if the antenna is switched every time a different result is calculated, the communication efficiency is reduced. The optimal antenna array number calculated over a plurality of calculation cycles, for example, 4, and the first 3 calculation cycles (the first 3 times of performing the method) will be temporarily stored. When the same result is obtained in 4 successive calculation cycles, the next judgment is carried out.
S6 is executed when the optimal antenna arrays of a plurality of continuous calculation cycles are the same antenna array, otherwise, the step S1 is returned to;
s6, judging the included angle of the optimal antenna array and the current startingWhether the difference of the included angles of the antenna arrays is larger than a set threshold value or not. Provided that the optimal antenna array determined through the preamble step is not currently enabled, the vector data of the normal is used here for ease of description
Figure 203070DEST_PATH_IMAGE033
、
Figure 646690DEST_PATH_IMAGE034
And
Figure 17629DEST_PATH_IMAGE035
three antennas are shown, assuming that currently
Figure 763868DEST_PATH_IMAGE034
The corresponding array is in an enabled state and the vector
Figure 728413DEST_PATH_IMAGE032
Is at an included angle of
Figure 585510DEST_PATH_IMAGE039
At this time, it calculates
Figure 545376DEST_PATH_IMAGE033
The corresponding array is an optimal antenna array, which is associated with the vector
Figure 634422DEST_PATH_IMAGE032
Is at an included angle of
Figure 679738DEST_PATH_IMAGE040
Where calculations are required
Figure 481472DEST_PATH_IMAGE041
Whether greater than a threshold (e.g., 1 deg.).
And (5) executing the step (S7) when the difference value between the included angle of the optimal antenna array and the included angle of the currently started antenna array is larger than a set threshold, otherwise, returning to the step (S1).
And S7, enabling the optimal antenna array. The action of switching the front end of the antenna array is really executed after the judgment of the steps S4-S6 meets the condition. In practical applications, it is necessary to perform antenna switching operation when data transmission between the system and the satellite is idle, so as to avoid data loss.
And S8, sequentially setting each antenna array to be in an enabled state, communicating with a satellite, calculating a signal-to-noise ratio according to the received signals, determining the antenna array with the highest signal-to-noise ratio as an optimal antenna array, and keeping enabling the optimal antenna array until complete antenna selection input parameters can be obtained.
According to the antenna array selection method provided by the embodiment of the invention, the vector data of the connecting line between the aircraft and the satellite is calculated by obtaining the antenna selection input parameters, the included angle between the normal of each antenna array and the direction of the satellite is calculated according to the vector data of the normal of the antenna, and the front end of the optimal antenna array is further determined according to the included angle value, so that a communication system does not need to start all antenna arrays sequentially or simultaneously, only needs to periodically calculate the value of the included angle, and can directly start the optimal antenna array when the switching condition is met, thereby ensuring that the signal quality meets the communication requirement and having strong real-time performance. Meanwhile, the operation of calculating the included angle is executed periodically, and the antenna array switching action is executed according to the calculation results of a plurality of continuous periods and the comparison with the currently-started antenna array, so that the influence of frequent or unnecessary execution of the switching action on normal communication is avoided.
The present application provides a calculation vector
Figure 561424DEST_PATH_IMAGE032
In this embodiment, the aircraft initial position information includes the heading
Figure 915045DEST_PATH_IMAGE001
Latitude of geocentric
Figure 572291DEST_PATH_IMAGE002
Longitude, longitude
Figure 302350DEST_PATH_IMAGE003
Elevation of
Figure 236808DEST_PATH_IMAGE004
(ii) a The current position information of the aircraft is the coordinate information of the aircraft under a transmitting inertial coordinate system (the lower position of the transmitting inertial coordinate system)
Figure 636696DEST_PATH_IMAGE028
、
Figure 656605DEST_PATH_IMAGE029
、
Figure 550874DEST_PATH_IMAGE030
) (ii) a The current attitude information of the aircraft is the relative launch inertial system attitude angle of the aircraft (the relative launch inertial system attitude angle of the aircraft)
Figure 339838DEST_PATH_IMAGE042
、
Figure 300841DEST_PATH_IMAGE043
、
Figure 683412DEST_PATH_IMAGE044
) (ii) a The satellite position information comprises position information of the satellite in a geocentric fixed spherical coordinate system
Figure 489694DEST_PATH_IMAGE008
、
Figure 398744DEST_PATH_IMAGE009
、
Figure 389702DEST_PATH_IMAGE010
(geocentric distance, geocentric latitude, geocentric longitude).
Further, step S2 specifically includes:
s21, converting the position of the satellite under the earth center spherical surface fixed coordinate system into the position under the earth center rectangular coordinate system, and concretely adopting the following mode:
Figure 384203DEST_PATH_IMAGE005
，
Figure 869542DEST_PATH_IMAGE006
，
Figure 633099DEST_PATH_IMAGE045
，
wherein
Figure 670325DEST_PATH_IMAGE008
、
Figure 775291DEST_PATH_IMAGE009
、
Figure 923376DEST_PATH_IMAGE010
The position of the satellite in the earth center fixedly connected with a spherical coordinate system is the earth center distance, the earth center latitude and the earth center longitude respectively,
Figure 807018DEST_PATH_IMAGE011
、
Figure 156091DEST_PATH_IMAGE012
、
Figure 859605DEST_PATH_IMAGE013
the three-dimensional coordinates of the satellite under the geocentric rectangular coordinate system are obtained.
And S22, converting the position under the geocentric rectangular coordinate system into a transmitting coordinate system, and further calculating the position of the satellite relative to the transmitting coordinate system. Specifically, the following method can be adopted:
Figure 936014DEST_PATH_IMAGE014
wherein
Figure 674163DEST_PATH_IMAGE015
、
Figure 53192DEST_PATH_IMAGE016
、
Figure 384947DEST_PATH_IMAGE017
Are the three-dimensional coordinates of the satellite relative to the transmission system,
Figure 874834DEST_PATH_IMAGE011
、
Figure 467489DEST_PATH_IMAGE012
、
Figure 643518DEST_PATH_IMAGE013
is a three-dimensional coordinate of the satellite under the earth center rectangular coordinate system,
Figure 587203DEST_PATH_IMAGE018
is a transformation matrix set according to direction, latitude and longitude in the earth.
Figure 880781DEST_PATH_IMAGE046
,
Figure 468889DEST_PATH_IMAGE047
，
Figure 924141DEST_PATH_IMAGE048
，
Figure 479756DEST_PATH_IMAGE049
，
Figure 311446DEST_PATH_IMAGE050
The latitude of the earth is the latitude of the earth,
Figure 144273DEST_PATH_IMAGE051
，
Figure 645792DEST_PATH_IMAGE052
is a half shaft of the earth's length,
Figure 564070DEST_PATH_IMAGE053
is the earth minor axis.
And S23, converting the position of the satellite relative to the transmitting system into the position of the satellite in the transmitting inertial coordinate system. Specifically, the following method can be adopted:
Figure 199450DEST_PATH_IMAGE054
wherein
Figure 250233DEST_PATH_IMAGE020
、
Figure 312867DEST_PATH_IMAGE021
、
Figure 328227DEST_PATH_IMAGE022
Three-dimensional coordinates of the satellite in the transmit inertial frame,
Figure 767299DEST_PATH_IMAGE015
、
Figure 309138DEST_PATH_IMAGE016
、
Figure 667307DEST_PATH_IMAGE017
are the three-dimensional coordinates of the satellite relative to the transmission system,
Figure 294598DEST_PATH_IMAGE023
the transformation matrix is set according to the rotation angular velocity, flight time, direction and ground latitude of the earth.
Figure 271781DEST_PATH_IMAGE055
Figure 543494DEST_PATH_IMAGE056
Figure 947930DEST_PATH_IMAGE057
Figure 688615DEST_PATH_IMAGE058
Figure 203910DEST_PATH_IMAGE059
Figure 720342DEST_PATH_IMAGE060
Figure 171046DEST_PATH_IMAGE061
Figure 772929DEST_PATH_IMAGE062
Figure 91915DEST_PATH_IMAGE063
Figure 587487DEST_PATH_IMAGE064
Figure 333726DEST_PATH_IMAGE065
Is the rotational angular velocity of the earth and takes the value as
Figure 891747DEST_PATH_IMAGE066
And is the time of flight.
And S24, converting the position of the satellite in the emission inertial coordinate system into an aircraft coordinate system, and further calculating the position of the satellite relative to the aircraft coordinate system. Specifically, the following method can be adopted:
Figure 155369DEST_PATH_IMAGE067
wherein
Figure 115235DEST_PATH_IMAGE025
、
Figure 921123DEST_PATH_IMAGE026
、
Figure 232019DEST_PATH_IMAGE027
Are the three-dimensional coordinates of the satellite relative to the aircraft coordinate system,
Figure 158386DEST_PATH_IMAGE020
、
Figure 848125DEST_PATH_IMAGE021
、
Figure 467325DEST_PATH_IMAGE022
three-dimensional coordinates of the satellite in the transmit inertial frame,
Figure 999938DEST_PATH_IMAGE028
、
Figure 589051DEST_PATH_IMAGE029
、
Figure 523509DEST_PATH_IMAGE030
is three-dimensional coordinate information of the aircraft in a transmitting inertial coordinate system,
Figure 188976DEST_PATH_IMAGE031
the transformation matrix is set for the attitude angle of the aircraft relative to the launching inertial system according to the current attitude information of the aircraft.
Figure 208885DEST_PATH_IMAGE068
Figure 211476DEST_PATH_IMAGE069
And S25, calculating vector data of a connecting line between the aircraft and the satellite by using the position of the satellite relative to the aircraft coordinate system and the position of the aircraft in the aircraft coordinate system. Namely use of
Figure 892118DEST_PATH_IMAGE025
、
Figure 853121DEST_PATH_IMAGE026
、
Figure 94747DEST_PATH_IMAGE027
And
Figure 776395DEST_PATH_IMAGE028
、
Figure 951024DEST_PATH_IMAGE029
、
Figure 551770DEST_PATH_IMAGE030
calculating vectors
Figure 936484DEST_PATH_IMAGE032
。
As will be appreciated by one skilled in the art, embodiments of the present invention may be provided as a method, system, or computer program product. Accordingly, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product embodied on one or more computer-usable storage media (including, but not limited to, disk storage, CD-ROM, optical storage, and the like) having computer-usable program code embodied therein.
The present invention is described with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It will be understood that each flow and/or block of the flow diagrams and/or block diagrams, and combinations of flows and/or blocks in the flow diagrams and/or block diagrams, can be implemented by computer program instructions. These computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, embedded processor, or other programmable data processing apparatus to produce a machine, such that the instructions, which execute via the processor of the computer or other programmable data processing apparatus, create means for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be stored in a computer-readable memory that can direct a computer or other programmable data processing apparatus to function in a particular manner, such that the instructions stored in the computer-readable memory produce an article of manufacture including instruction means which implement the function specified in the flowchart flow or flows and/or block diagram block or blocks.
These computer program instructions may also be loaded onto a computer or other programmable data processing apparatus to cause a series of operational steps to be performed on the computer or other programmable apparatus to produce a computer implemented process such that the instructions which execute on the computer or other programmable apparatus provide steps for implementing the functions specified in the flowchart flow or flows and/or block diagram block or blocks.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications therefrom are within the scope of the invention.

Claims (7)

1. An antenna array selection method for an aircraft, wherein a plurality of antenna arrays are arranged on the aircraft in different orientations, only one antenna array is in an active state at a time, and all elements in the same antenna array are arranged on the same plane, the method comprising:
monitoring whether complete antenna selection input parameters are acquired, wherein the antenna selection input parameters comprise aircraft initial position information, aircraft current attitude information and satellite position information, and the aircraft initial position information comprises shooting direction
Figure 205989DEST_PATH_IMAGE001
Latitude of geocentric
Figure 996090DEST_PATH_IMAGE002
Longitude, longitude
Figure 406212DEST_PATH_IMAGE003
Elevation of
Figure 877644DEST_PATH_IMAGE004
The current position information of the aircraft is coordinate information of the aircraft under a launching inertial coordinate system, the current attitude information of the aircraft is an attitude angle of the aircraft relative to the launching inertial system, and the satellite position information comprises position information of a satellite in a geocentric fixed spherical coordinate system;
when the complete antenna selection input parameters can be acquired, calculating vector data of a connection line between the aircraft and the satellite by using the antenna selection input parameters, specifically, converting the position of the satellite under a geocentric sphere fixed coordinate system into the position under a geocentric rectangular coordinate system, converting the position under the geocentric rectangular coordinate system into a transmitting coordinate system, further calculating the position of the satellite relative to the transmitting system, converting the position of the satellite relative to the transmitting system into the position of the satellite in a transmitting inertial coordinate system, converting the position of the satellite in the transmitting inertial coordinate system into an aircraft coordinate system, further calculating the position of the satellite relative to the aircraft coordinate system, and calculating the vector data of the connection line between the aircraft and the satellite by using the position of the satellite relative to the aircraft coordinate system and the position of the aircraft under the aircraft coordinate system, wherein the position of the satellite relative to the aircraft coordinate system is calculated by adopting the following calculation methods:
Figure DEST_PATH_IMAGE005
wherein
Figure 604292DEST_PATH_IMAGE006
、
Figure 565295DEST_PATH_IMAGE007
、
Figure 275762DEST_PATH_IMAGE008
Are the three-dimensional coordinates of the satellite relative to the aircraft coordinate system,
Figure 962003DEST_PATH_IMAGE009
、
Figure 402211DEST_PATH_IMAGE010
、
Figure 143902DEST_PATH_IMAGE011
three-dimensional coordinates of the satellite in the transmit inertial frame,
Figure 403982DEST_PATH_IMAGE012
、
Figure 217218DEST_PATH_IMAGE013
、
Figure 370987DEST_PATH_IMAGE014
is three-dimensional coordinate information of the aircraft in a transmitting inertial coordinate system,
Figure 673793DEST_PATH_IMAGE015
according to the current attitude information of the aircraftA transformation matrix for the attitude angle setting of the aircraft relative to the launch inertial system,
Figure 296535DEST_PATH_IMAGE016
Figure DEST_PATH_IMAGE017
、
Figure 867456DEST_PATH_IMAGE018
、
Figure 954361DEST_PATH_IMAGE019
launching an inertial system attitude angle for the aircraft relative to one another;
calculating included angles between the orientations of the antenna arrays and the connecting line according to vector data of antenna normals of the antenna arrays, which are oriented to different antenna arrays, on an aircraft and vector data of the aircraft and the connecting line, wherein the antenna normals refer to lines perpendicular to a plane where the array elements are located;
determining an antenna array with the minimum included angle as an optimal antenna array of the current calculation period;
judging whether the optimal antenna arrays of a plurality of continuous calculation periods are the same antenna array or not;
when the optimal antenna arrays of a plurality of continuous calculation periods are the same antenna array, judging whether the difference value between the included angle of the optimal antenna array and the included angle of the currently started antenna array is larger than a set threshold value;
and when the difference value between the included angle of the optimal antenna array and the included angle of the currently started antenna array is larger than a set threshold value, starting the optimal antenna array.
2. The method as claimed in claim 1, wherein there are at least 3 antenna arrays.
3. The antenna array selection method for the aircraft as claimed in claim 1, wherein the following calculation is used to convert the position of the satellite under the earth-centered spherical fixed coordinate system into the position under the earth-centered rectangular coordinate system:
Figure 428067DEST_PATH_IMAGE020
，
Figure 538106DEST_PATH_IMAGE021
，
Figure 489881DEST_PATH_IMAGE022
，
wherein
Figure 696872DEST_PATH_IMAGE023
Is the distance from the earth's center,
Figure 200534DEST_PATH_IMAGE024
Is the latitude of the geocentric region,
Figure 922503DEST_PATH_IMAGE025
Is the longitude of the earth's center, and is,
Figure 553335DEST_PATH_IMAGE026
、
Figure 614832DEST_PATH_IMAGE027
、
Figure 430341DEST_PATH_IMAGE028
is a three-dimensional coordinate under the geocentric rectangular coordinate system.
4. The antenna array selection method for an aircraft according to claim 1, wherein the position of the satellite with respect to the transmission system is calculated as follows:
Figure 125DEST_PATH_IMAGE029
wherein
Figure 559283DEST_PATH_IMAGE030
、
Figure 147390DEST_PATH_IMAGE031
、
Figure 337063DEST_PATH_IMAGE032
Are the three-dimensional coordinates of the satellite relative to the transmission system,
Figure 768044DEST_PATH_IMAGE026
、
Figure 989947DEST_PATH_IMAGE027
、
Figure 822774DEST_PATH_IMAGE028
is a three-dimensional coordinate of the satellite under the earth center rectangular coordinate system,
Figure 855452DEST_PATH_IMAGE033
is a transformation matrix set according to direction, latitude and longitude in the earth.
5. The antenna array selection method for an aircraft according to claim 1, wherein the position of the satellite relative to the launch frame is converted to the position of the satellite in the launch inertial frame by the following calculation:
Figure 976991DEST_PATH_IMAGE034
wherein
Figure 612372DEST_PATH_IMAGE009
、
Figure 191383DEST_PATH_IMAGE010
、
Figure 519596DEST_PATH_IMAGE011
Three-dimensional coordinates of the satellite in the transmit inertial frame,
Figure 534957DEST_PATH_IMAGE030
、
Figure 442870DEST_PATH_IMAGE031
、
Figure 984710DEST_PATH_IMAGE032
are the three-dimensional coordinates of the satellite relative to the transmission system,
Figure 874037DEST_PATH_IMAGE035
is a transformation matrix set according to the rotational angular velocity, time of flight, direction and geodetic latitude of the earth.
6. The method for selecting an antenna array for an aircraft according to any one of claims 1 to 5, wherein when the complete antenna selection input parameters cannot be acquired, the antenna arrays are sequentially set to an activated state and communicate with a satellite, the signal-to-noise ratio is calculated according to the received signals, the antenna array with the highest signal-to-noise ratio is determined as the optimal antenna array, and the optimal antenna array is kept activated until the complete antenna selection input parameters can be acquired.
7. A satellite communication system for an aircraft, comprising: a communication host and a plurality of antenna array front ends, wherein
The front end of the antenna array is provided with a plurality of array elements and low-noise amplifier receiving channels which are connected with the array elements in a one-to-one manner;
the communication host is provided with a baseband processing module, a power amplifier module and a down-conversion module, wherein the baseband processing module is used for executing the antenna array selection method for the aircraft according to any one of claims 1 to 6, and the power amplifier module and the down-conversion module are controlled to be communicated with an antenna array front end to be used as an enabled antenna array front end, so that the communication with a satellite is carried out through an array element in the enabled antenna array front end.
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