CN115987371B - Satellite loss identification method and device for satellite mobile terminal antenna - Google Patents
Satellite loss identification method and device for satellite mobile terminal antenna Download PDFInfo
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- 238000005096 rolling process Methods 0.000 claims abstract description 18
- 238000001514 detection method Methods 0.000 claims description 9
- 238000012360 testing method Methods 0.000 claims description 4
- 238000012423 maintenance Methods 0.000 abstract description 7
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- 238000009434 installation Methods 0.000 description 4
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02D—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN INFORMATION AND COMMUNICATION TECHNOLOGIES [ICT], I.E. INFORMATION AND COMMUNICATION TECHNOLOGIES AIMING AT THE REDUCTION OF THEIR OWN ENERGY USE
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- Y02D30/70—Reducing energy consumption in communication networks in wireless communication networks
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Abstract
The invention relates to the technical field of data processing, in particular to a satellite loss identification method and device of a satellite mobile terminal antenna, comprising the steps of searching origin positions of a polarization motor, a pitching motor, a rolling motor and a azimuth motor to obtain an actual angle of the antenna; acquiring longitude and latitude coordinates of a carrier, and calculating an antenna theoretical angle based on the longitude and latitude coordinates; controlling the rotation of a polarization motor, a pitching motor, a rolling motor and an azimuth motor based on the actual angle of the antenna, so that the error between the actual angle of the antenna and the theoretical angle of the antenna is 0; the azimuth motor starts to rotate from an initialization angle, and simultaneously the antenna surface is controlled to be kept at a preset pitching angle through the pitching motor, so that satellite signals are obtained; the antenna is shielded and detected based on satellite signals to obtain a radar chart analysis chart, and the problem that the existing antenna maintenance method is low in efficiency is solved.
Description
Technical Field
The invention relates to the technical field of data processing, in particular to a satellite loss identification method and device for a satellite mobile terminal antenna.
Background
When the satellite mobile terminal antenna is used on a ship, the satellite mobile terminal antenna can be influenced by various external factors:
1. a quay crane or a nearby vessel shielding effect;
2. the deck vibration caused by the running of the engine on the ship or the unstable installation of the antenna bracket causes the poor antenna tracking effect;
3. radar interference, masts or other obstruction effects exist around the ship's antennas.
These influencing factors can reduce the signal strength of the satellite antenna, so that the network quality is poor, and even satellite signal loss is caused under severe conditions, thereby seriously affecting the user bandwidth experience.
These complex environmental factors make the application of geostationary satellite antennas on ships very difficult to maintain.
The existing maintenance method is that engineering technicians can overhaul the antenna on the ship without knowing what factors cause signal loss, and the efficiency is low.
Disclosure of Invention
The invention aims to provide a satellite loss identification method and device for a satellite mobile terminal antenna, and aims to solve the problem that the existing antenna maintenance method is low in efficiency.
In order to achieve the above object, in a first aspect, the present invention provides a method for identifying satellite loss of a satellite mobile terminal antenna, comprising the following steps:
searching the original point positions of a polarization motor, a pitching motor, a rolling motor and an azimuth motor to obtain the actual angle of the antenna;
acquiring longitude and latitude coordinates of a carrier, and calculating an antenna theoretical angle based on the longitude and latitude coordinates and the longitude and latitude coordinates of a target satellite;
controlling the rotation of the polarization motor, the pitching motor, the rolling motor and the azimuth motor based on the actual angle of the antenna so that the error between the actual angle of the antenna and the theoretical angle of the antenna is 0;
the azimuth motor starts to rotate from an initialization angle, and simultaneously the antenna surface is controlled to be kept at a preset pitching angle through the pitching motor, so that satellite signals are obtained;
and carrying out shielding detection on the antenna based on the satellite signals to obtain a radar chart analysis chart.
Wherein the method further comprises:
and performing vibration test on the antenna to obtain a vibration variance value, and sending out a vibration alarm when the vibration variance value is larger than a vibration threshold value.
The method for carrying out shielding detection on the antenna based on the satellite signals to obtain a radar chart analysis chart comprises the following steps:
carrying out locking tracking on the satellite signals to obtain the current satellite signal intensity and azimuth angle;
and carrying out shielding detection on the antenna, and updating a signal intensity average value based on the current satellite signal intensity and the azimuth angle by adopting an array updating formula to obtain a radar chart analysis chart.
Wherein the array update formula is a weighted average algorithm.
Wherein, the azimuth angle of the azimuth motor ranges from 0 degrees to 359.99 degrees, and the control precision is 0.01 degrees.
Wherein the azimuth angle value is stored in a range of 0-359 degrees and the step is 1 degree.
The invention provides a satellite loss identification device of a satellite mobile terminal antenna, which comprises an antenna base bracket, an azimuth origin fixing piece, an antenna main control unit, a GPS module, a polarization motor, a pitching motor, a rolling motor, an azimuth motor, a polarization position sensor, a pitching position sensor, a rolling position sensor, an azimuth position sensor and an inertial navigation module;
the azimuth origin fixing sheet is fixedly connected with the antenna base bracket and is positioned at the top of the antenna base bracket; the azimuth position sensor is fixedly connected with the antenna azimuth base, and when the antenna azimuth rotates, the azimuth position sensor passes through the azimuth origin fixing sheet; the antenna main control unit is arranged on one side of the azimuth position sensor, and the GPS module, the polarization motor, the pitching motor, the rolling motor, the azimuth motor, the polarization position sensor, the pitching position sensor, the rolling position sensor, the azimuth position sensor and the inertial navigation module are all connected with the antenna main control unit.
According to the satellite loss identification method of the satellite mobile terminal antenna, the actual angle of the antenna is obtained by searching the original point positions of the polarization motor, the pitching motor, the rolling motor and the azimuth motor; acquiring longitude and latitude coordinates of a carrier, and calculating an antenna theoretical angle based on the longitude and latitude coordinates; controlling the rotation of the polarization motor, the pitching motor, the rolling motor and the azimuth motor based on the actual angle of the antenna so that the error between the actual angle of the antenna and the theoretical angle of the antenna is 0; the azimuth motor starts to rotate from an initialization angle, and simultaneously the antenna surface is controlled to be kept at a preset pitching angle through the pitching motor, so that satellite signals are obtained; and shielding detection is carried out on the antenna based on the satellite signals, a radar chart analysis chart is obtained, faults are analyzed by customer service personnel through the radar chart analysis chart, treatment comments such as replacement of antenna installation points, reinforcement of antenna supports and antenna maintenance are given to engineering technicians, the engineering technicians can conveniently go on the ship to maintain and solve the problem, and the problem that the efficiency of the existing antenna maintenance method is low is solved.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a flowchart of a satellite loss identification method of a satellite mobile terminal antenna provided by the invention.
Fig. 2 is a schematic diagram of a radar chart analysis chart.
Fig. 3 is a schematic structural diagram of a satellite loss identification device for a satellite mobile terminal antenna.
Fig. 4 is a schematic block diagram of a satellite loss identification device of a satellite mobile terminal antenna according to the present invention.
1-antenna base support, 2-direction origin stationary blade, 3-antenna master control unit, 4-GPS module, 5-polarization motor, 6-every single move motor, 7-roll motor, 8-position motor, 9-polarization position sensor, 10-every single move position sensor, 11-roll position sensor, 12-position sensor, 13-inertial navigation module.
Detailed Description
Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein like or similar reference numerals refer to like or similar elements or elements having like or similar functions throughout. The embodiments described below by referring to the drawings are illustrative and intended to explain the present invention and should not be construed as limiting the invention.
Referring to fig. 1 to 2, in a first aspect, the present invention provides a method for identifying satellite loss of a satellite mobile terminal antenna, comprising the following steps:
s1, finding the original point positions of a polarization motor 5, a pitching motor 6, a rolling motor 7 and an azimuth motor 8 to obtain the actual angles of the antennas;
specifically, when the antenna is powered on, an initialization program is started first, and the polarization motor 5, the pitch motor 6, the roll motor 7 and the azimuth motor 8 find the origin position. The azimuth base of the antenna is provided with an azimuth position sensor 12 serving as an azimuth rotation reference angle relative to the bow, the azimuth motor 8 drives the azimuth position sensor 12 to rotate to the position of an azimuth origin fixing sheet 2, the azimuth angle of the initialization motor is Aref, and the direction of the azimuth origin fixing sheet 2 is not fixed relative to the position of the bow heading when the antenna is installed, so that the antenna after loading needs to be calibrated.
S2, acquiring longitude and latitude coordinates of a carrier, and calculating an antenna theoretical angle based on the longitude and latitude coordinates and the longitude and latitude coordinates of a target satellite;
specifically, the waiting GPS module 4 obtains the geographical location information of the carrier, and calculates the theoretical antenna angle of the antenna at the current geographical location according to the latitude and longitude coordinates of the carrier and the latitude and longitude coordinates of the target satellite.
S3, controlling the polarization motor 5, the pitching motor 6, the rolling motor 7 and the azimuth motor 8 to rotate based on the actual angle of the antenna so that the error between the actual angle of the antenna and the theoretical angle of the antenna is 0;
specifically, the rotation angle range of the azimuth motor 8 can be infinitely rotated. The azimuth angle is in the range of 0-359.99 degrees, and the control precision is 0.01 degrees.
S4, the azimuth motor 8 starts to rotate from an initialization angle, and simultaneously the antenna surface is controlled to be kept at a preset pitching angle through the pitching motor 6, so that satellite signals are obtained;
specifically, a star finding scanning procedure is initiated. The azimuth motor 8 starts to rotate from the Aref angle of the azimuth origin fixing plate 2, the motor angle range is 0-360 degrees, when the angle exceeds 360 degrees, the original rotation direction is kept running continuously, the recording angle starts from 0, the current angle value is divided by 360 to obtain remainder through antenna controller software processing, and therefore the antenna azimuth is always in the range of 0-360 degrees when rotating. The pitching motor 6 controls the antenna surface to keep a theoretical pitching angle, and when the antenna surface rotates once in azimuth, the pitching motor 6 is adjusted to increase or decrease a stepping angle in the theoretical pitching angle to make fine adjustment until satellite signals are found and tracking is locked.
And S5, shielding detection is carried out on the antenna based on the satellite signals, and a radar chart analysis chart is obtained.
Specifically, the satellite signals are locked and tracked to obtain the current satellite signal intensity and azimuth angle; and carrying out shielding detection on the antenna, and updating a signal intensity average value based on the current satellite signal intensity and the azimuth angle by adopting an array updating formula to obtain a radar chart analysis chart. The array update formula is a weighted average algorithm.
After the antenna locks the satellite, the MCU of the main control circuit board acquires the current satellite signal intensity Pnow and the azimuth angle An in real time. The satellite signal strength detection may be via a DVB tuner, a beacon receiver, or a modem. The main control MCU updates and stores a signal intensity average value array Pavg [ An ] according to Pnow and An values, wherein the signal intensity average value array Pavg [ An ] is used for recording the signal intensity average value of each azimuth angle, the An value is rounded, the range is 0-359, and the step is 1 degree. The array Pavg [ An ] update formula adopts a weighted average algorithm: pavg [ An ] = k Pavg [ An ] + (1-k) Pnow, wherein k is a weight coefficient, and the setting range is 0-1.
And when the antenna is blocked in a large range and is completely out of lock, stopping updating the Pavg [ An ] array.
When the antenna is on line again, operation and maintenance personnel can acquire Pavg [ An ] array data through a background network, and a radar chart analysis chart is generated. As is evident from the graph below, there is a large area of complete shielding in the range of 60 deg. -90 deg. clockwise relative to the bow.
S6, vibration testing is conducted on the antenna to obtain a vibration variance value, and when the vibration variance value is larger than a vibration threshold value, a vibration alarm is sent out.
Specifically, an inertial navigation module 13 for stable tracking of an antenna is fixed on an antenna azimuth base, and an acceleration sensor and an MCU are contained in the inertial navigation module, so that acceleration transmitted by an external carrier can be collected in real time, and n acceleration values X are obtained in a unit time 1 ～X n Calculating the average value of Z-direction acceleration in the time periodThen the variance is obtained:
the magnitude of the value indirectly reflects the intensity of the vibration amplitude. And the variance data in each unit time is transmitted to the MCU processing unit of the main control circuit board for analysis, and when the variance value is larger than the set vibration threshold value, an alarm is started to prompt the vibration overrun of the installation point. The operation and maintenance personnel can feed back the numerical result to engineering technicians according to vibration warning, and the suggestions of reinforcing the antenna bracket or replacing the installation point position and the like are provided.
Referring to fig. 3 to 4, in a second aspect, the present invention provides a satellite loss identification device for a satellite mobile terminal antenna, including an antenna base bracket 1, an azimuth origin fixing plate 2, an antenna main control unit 3, a GPS module 4, a polarization motor 5, a pitch motor 6, a roll motor 7, an azimuth motor 8, a polarization position sensor 9, a pitch position sensor 10, a roll position sensor 11, an azimuth position sensor 12 and an inertial navigation module 13;
the azimuth origin fixing piece 2 is fixedly connected with the antenna base bracket 1 and is positioned at the top of the antenna base bracket 1; the azimuth position sensor 12 is fixedly connected with the antenna azimuth base, and when the antenna azimuth rotates, the azimuth position sensor 12 passes through the azimuth origin fixing piece 2; the antenna main control unit 3 is arranged at one side of the azimuth position sensor 12, and the GPS module 4, the polarization motor 5, the pitching motor 6, the rolling motor 7, the azimuth motor 8, the polarization position sensor 9, the pitching position sensor 10, the rolling position sensor 11, the azimuth position sensor 12 and the inertial navigation module 13 are all connected with the antenna main control unit 3.
In this embodiment, the antenna base support 1 provides mounting conditions for the antenna and the azimuth origin fixing piece 2, the antenna main control unit 3 controls the GPS module 4, the polarization motor 5, the elevation motor 6, the roll motor 7, the azimuth motor 8, the polarization position sensor 9, the elevation position sensor 10, the roll position sensor 11, the azimuth position sensor 12 and the inertial navigation module 13, the GPS module 4 is used for obtaining geographic position information of the carrier, the polarization motor 5, the elevation motor 6, the roll motor 7 and the azimuth motor 8 are used for adjusting angles of the antenna, the polarization position sensor 9, the elevation position sensor 10, the roll position sensor 11 and the azimuth position sensor 12 are used for respectively detecting rotation angles of the polarization motor 5, the elevation motor 6, the roll motor 7 and the azimuth motor 8, and the inertial navigation module 13 is used for performing vibration test on the antenna.
The foregoing disclosure is only illustrative of a preferred embodiment of a satellite loss identification method and apparatus for a satellite mobile terminal antenna, but it is not limited thereto, and those skilled in the art will appreciate that all or part of the procedures for implementing the foregoing embodiments are equivalent and still fall within the scope of the invention.
Claims (5)
1. The satellite loss identification method for the satellite mobile terminal antenna is characterized by comprising the following steps of:
searching the original point positions of a polarization motor, a pitching motor, a rolling motor and an azimuth motor to obtain the actual angle of the antenna;
acquiring longitude and latitude coordinates of a carrier, and calculating an antenna theoretical angle based on the longitude and latitude coordinates and the longitude and latitude of a target satellite;
controlling the rotation of the polarization motor, the pitching motor, the rolling motor and the azimuth motor based on the actual angle of the antenna so that the error between the actual angle of the antenna and the theoretical angle of the antenna is 0;
the azimuth motor starts to rotate from an initialization angle, and simultaneously the antenna surface is controlled to be kept at a preset pitching angle through the pitching motor, so that satellite signals are obtained, and the method comprises the following steps: starting a star finding scanning program, enabling an azimuth motor to start rotating from an Aref angle of an azimuth origin fixing plate, enabling the angle range of the azimuth motor to be 0-360 degrees, continuously keeping the original rotation direction to operate when the angle exceeds 360 degrees, starting recording the angle from 0, processing by antenna controller software, dividing the current angle value by 360 to obtain remainder, enabling a pitching motor to control an antenna surface to keep a theoretical pitching angle when the antenna azimuth rotates within the range of 0-360 degrees forever, adjusting the pitching motor to increase or decrease a stepping angle on the theoretical pitching angle for fine adjustment when the antenna surface rotates once in azimuth, until satellite signals are found, locking and tracking, and initializing the azimuth angle of the motor to be Aref;
shielding detection is carried out on the antenna based on the satellite signals to obtain a radar chart analysis chart, which comprises the following steps:
carrying out locking tracking on the satellite signals to obtain the current satellite signal intensity and azimuth angle;
and carrying out shielding detection on the antenna, and updating a signal intensity average value based on the current satellite signal intensity and the azimuth angle by adopting an array updating formula to obtain a radar chart analysis chart.
2. The method for identifying lost satellites of a satellite mobile terminal antenna according to claim 1 wherein,
the method further comprises the steps of:
and performing vibration test on the antenna to obtain a vibration variance value, and sending out a vibration alarm when the vibration variance value is larger than a vibration threshold value.
3. The method for identifying lost satellites of a satellite mobile terminal antenna according to claim 1 wherein,
the array update formula is a weighted average algorithm.
4. The method for identifying lost satellites of claim 3 wherein,
the azimuth angle of the azimuth motor ranges from 0 degrees to 359.99 degrees, and the control precision is 0.01 degrees.
5. A satellite loss identification device of a satellite mobile terminal antenna is applied to the satellite loss identification method of the satellite mobile terminal antenna according to claim 4, and is characterized in that,
the device comprises an antenna base bracket, an azimuth origin fixing sheet, an antenna main control unit, a GPS module, a polarization motor, a pitching motor, a roll motor, an azimuth motor, a polarization position sensor, a pitching position sensor, a roll position sensor, an azimuth position sensor and an inertial navigation module;
the azimuth origin fixing sheet is fixedly connected with the antenna base bracket and is positioned at the top of the antenna base bracket; the azimuth position sensor is fixedly connected with the antenna azimuth base, and when the antenna azimuth rotates, the azimuth position sensor passes through the azimuth origin fixing sheet; the antenna main control unit is arranged on one side of the azimuth position sensor, and the GPS module, the polarization motor, the pitching motor, the rolling motor, the azimuth motor, the polarization position sensor, the pitching position sensor, the rolling position sensor, the azimuth position sensor and the inertial navigation module are all connected with the antenna main control unit.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211548033.0A CN115987371B (en) | 2022-12-05 | 2022-12-05 | Satellite loss identification method and device for satellite mobile terminal antenna |
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| CN202211548033.0A CN115987371B (en) | 2022-12-05 | 2022-12-05 | Satellite loss identification method and device for satellite mobile terminal antenna |
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| CN115987371B true CN115987371B (en) | 2023-12-05 |
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