CN107328361B - System and method for measuring and calculating base station antenna parameters - Google Patents
System and method for measuring and calculating base station antenna parameters Download PDFInfo
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- G—PHYSICS
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- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
- G01B11/00—Measuring arrangements characterised by the use of optical techniques
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
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Abstract
The invention provides a base station sky parameter measuring and calculating system which comprises a positioning module, a control module, a mode switching module, a communication module and an identification measuring and calculating module, wherein the control module acquires the position of a target base station through the communication module and controls an aircraft to travel to the position of the target base station by means of the positioning module, the mode switching module has two working modes of identification/verification, when the mode switching module is set to be the identification mode, the identification measuring and calculating module acquires and calculates the sky parameter of the target base station, and when the mode switching module is set to be the verification mode, the identification measuring and calculating module transmits the acquired and calculated sky parameter to a background. The system and the method for measuring and calculating the base station ceiling parameters realize automatic acquisition and measurement of the base station ceiling parameters, can replace manual operation, improve the operation efficiency, reduce the difference of manual measurement and reduce the operation cost and risk.
Description
Technical Field
The present invention relates to the field of wireless communications technologies, and in particular, to a system and a method for measuring and calculating a base station antenna parameter.
Background
The base station antenna information is one of important indexes of mobile communication wireless side network optimization, and directly affects the communication quality, so that the optimization adjustment of the base station antenna information is most complex and frequent. The optimization adjustment work of the base station antenna mainly comprises adjustment of three dimensions of antenna height, direction angle and pitch angle. The height and pitch angle influence the coverage distance of signals of a base station cell, and the direction angle influences the coverage direction of a main signal lobe. After the base station is connected to the network, because of the outdoor environment factors and the untimely parameter updating or adjustment errors after the maintenance personnel adjust, the actual weather information is inconsistent with the on-network record, and the accuracy of the wireless network planning and the communication user experience are affected.
In actual work, the base station antenna information can only be measured by manual station climbing generally, and a plurality of defects exist: first, there is a risk of overhead operation and a risk of antenna radiation; secondly, the cost is high, and every time a tower worker climbs a tower, a company pays 200 yuan/time of tower climbing fee; thirdly, the workload is large, the manual operation efficiency is low, the number of the tower climbing measurement of a skilled tower worker is only about 4-6 per day, the number of the base stations of the whole network is huge, and the number of the antenna running on the network reaches 5 digits only by one operator in Suzhou; fourth, measurement variability is large, and there is often a large measurement variability for the same day by turrets of different proficiency.
Besides manual measurement, the scheme of using an antenna sensor exists at present, but the sensor is required to be installed in the early stage and a monitoring network is required to be deployed, and the later maintenance cost and the complexity are high; there is also a scheme of estimating the pitch angle by using ticket data and the base station antenna height, but the ticket data relates to user privacy, and there is a great limitation in practical application.
Therefore, a novel system and a novel method for measuring and calculating the base station antenna parameters are continued to solve the problems.
Disclosure of Invention
The invention aims to provide a system and a method for measuring and calculating the base station antenna parameters, which are used for solving the problem that the conventional base station antenna parameters are difficult to measure and calculate.
In order to solve the technical problems, the invention provides a base station antenna parameter measuring and calculating system, which comprises a positioning module, a control module, a mode switching module, a communication module and an identification measuring and calculating module, wherein the control module acquires the position of a target base station through the communication module and controls an aircraft to travel to the position of the target base station by means of the positioning module, the mode switching module has two working modes of identification/verification, when the mode switching module is set to be in the identification mode, the identification measuring and calculating module acquires and calculates the antenna parameter of the target base station, and when the mode switching module is set to be in the verification mode, the identification measuring and calculating module verifies the antenna of the target base station and transmits the parameter to a background.
Optionally, the identifying and measuring module comprises an identifying sub-module, a measuring sub-module and a storage sub-module, the identifying sub-module identifies the sky, the measuring sub-module calculates the pitch angle of the sky according to the sky information identified by the identifying sub-module, and the storage sub-module stores the sky information and the calculation result.
Optionally, the recognition and measurement module further includes a camera shooting sub-module and a ranging sub-module, the camera shooting sub-module transmits the photographed sky photograph to the recognition sub-module for recognition, and the ranging sub-module measures the distance between the aircraft and the front of the sky and transmits the distance to the storage sub-module.
Optionally, the positioning module comprises a GPS sub-module, an optical flow sensor, an air pressure sensor and an ultrasonic sensor, wherein the GPS sub-module performs coarse positioning on the horizontal position of the aircraft, the air pressure sensor performs coarse control on the hovering height of the aircraft, the optical flow sensor performs precise control on the hovering horizontal position of the aircraft, and the ultrasonic sensor realizes precise control and obstacle avoidance on the aircraft.
Optionally, the base station antenna parameter measurement and calculation system further includes a timer, and the timer is connected with the mode switching module and the control module.
The invention also provides a method for measuring and calculating the base station antenna parameters, which comprises the following steps:
the communication module transmits the position of the target base station to the control module, and the control module controls the aircraft to travel to the target position through the positioning module;
the mode switching module is set to be an identification mode, and the identification and measurement module collects and measures the antenna parameters of the target base station;
the mode switching module is set to be a verification mode, and the identification measuring and calculating module verifies the antenna surface of the target base station and transmits parameters to the background.
Optionally, the process of verifying the antenna surface of the target base station by the identification and measurement module is as follows: if the identification measuring and calculating module identifies the front face of the sky in the identification mode, the identification measuring and calculating module identifies the side face of the sky in the verification mode for verification; on the contrary, if the recognition measuring and calculating module recognizes the side face of the sky in the recognition mode, the recognition measuring and calculating module recognizes the front face of the sky in the verification mode to verify
Optionally, the process of collecting and measuring the antenna parameters by the identification measuring module is as follows: the shooting submodule shoots a sky photo; the recognition sub-module performs image recognition on the photographed top photo, and when the center image of the top photo is recognized to meet the design condition, the measuring and calculating sub-module measures the size of the top; the distance measuring submodule measures the distance between the aircraft and the front surface of the sky so that the measuring and calculating submodule measures the real size of the side surface of the sky and verifies whether the real size is consistent with the size of a known sky product; and the measuring and calculating submodule calculates the pitch angle of the sky according to the size of the sky.
Optionally, the process of identifying the side of the sky and measuring and calculating the pitch angle is as follows: the center of the photo is rectangular; the color value of the rectangular inner area is within the designed range; measuring the distance from the aircraft to the sky side by the measuring submodule, and calculating the actual length and width of the sky side according to the rectangular length and width identified by the photo, wherein the length and width or the length-width ratio of the sky side is consistent with the size data of one of the sky sides operated by the existing network; calculating an included angle alpha between the long side of the rectangle and the horizontal, wherein if alpha is more than 90 degrees, the side surface is positioned on the left side of the front surface of the sky, and if alpha is less than 90 degrees, the side surface is positioned on the right side of the front surface of the sky; and calculating the pitch angle beta= |90-alpha|.
Optionally, the process of identifying the front of the sky comprises the following steps: the center of the photo is isosceles trapezoid; the color value of the inner area of the isosceles trapezoid is within the design range; a black feeder line joint exists outside the lower bottom of the isosceles trapezoid.
The system and the method for measuring and calculating the base station ceiling parameters realize automatic acquisition and measurement of the base station ceiling parameters, can replace manual operation, improve the operation efficiency, reduce the difference of manual measurement and reduce the operation cost and risk.
Drawings
FIG. 1 is a schematic diagram of a system for measuring and calculating parameters of a base station antenna according to an embodiment of the present invention;
fig. 2 is a flowchart of a method for measuring and calculating a base station antenna parameter according to an embodiment of the present invention.
Detailed Description
The system and the method for measuring and calculating the base station antenna parameters are further described in detail below with reference to the accompanying drawings and the specific embodiments. Advantages and features of the invention will become more apparent from the following description and from the claims. It should be noted that the drawings are in a very simplified form and are all to a non-precise scale, merely for convenience and clarity in aiding in the description of embodiments of the invention.
The inventor of the present application has invented a system and a method for measuring and calculating the antenna parameters of the base station through long-term study and experiment, which solves the above problems.
The system comprises a positioning module, a control module, a mode switching module, a communication module and an identification and measurement module, wherein the control module acquires the position of a target base station through the communication module and controls the aircraft to travel to the position of the target base station by means of the positioning module, the mode switching module has two working modes of identification/verification, when the mode switching module is set to the identification mode, the identification and measurement module collects and measures the antenna parameters of the target base station, and when the mode switching module is set to the verification mode, the identification and measurement module transmits the collected and measured antenna parameters to a background.
As shown in fig. 1, the base station antenna parameter measuring and calculating system comprises a positioning module, an identification measuring and calculating module (comprising an identification sub-module, a measuring sub-module, a storage sub-module, a ranging sub-module and a camera sub-module), a mode switching module, a control module, a communication module and a timer.
The control module acquires the position of the target base station through the communication module, and the aircraft advances to the target position by means of the positioning module; the mode switching module controls the working mode (identification/verification) of the base station antenna parameter measuring and calculating system, and the identification sub-module sends a level value corresponding to 0/1 to the mode switching module to switch the mode to identification/verification.
The identification sub-module is used for carrying out image identification of a rectangle or an isosceles trapezoid on the photo shot by the shooting sub-module in an identification mode and a verification mode, and when the fact that the center of the photo meets the rectangle of a pixel condition, a length-width dimension or an aspect ratio is identified, the detection sub-module is triggered to carry out pitch angle measurement and calculation. After the recognition processing of each recognition sub-module is finished, the control module is directly informed or indirectly informed to change the flight attitude of the aircraft through the mode switching module.
The measuring and calculating submodule can calculate the included angle between the long side and the horizontal according to the pixel positions of any two points of the long side of the rectangle on the side of the identified sky, so that the pitch angle of the sky (the default aircraft keeps horizontal when hovering shooting) is calculated. The measuring and calculating submodule can restore the real length and width dimensions of the side face of the sky according to the length and width of the rectangle on the identification photo and the distance between the sky and the front face measured by the ranging submodule, and verify whether the dimensions of the side face of the sky are consistent with those of the known sky product.
The storage sub-module is used for storing the pitch angle, the length and width dimensions and the corresponding side photos of the sky measured by the measuring sub-module, the ranging sub-module measures the distance from the aircraft to the currently opposite sky and stores the distance into the storage sub-module, the background transmits the known sky dimensions of the current net to the storage sub-module through the communication module, and the positioning module transmits the flying height and the heading of the aircraft when the sky is identified to the storage module, wherein the flying height and the heading correspond to the height and the azimuth of the sky respectively.
When the mode identification module is in an identification mode, the control module controls the aircraft to shoot along the vertical S-shaped flight in the surrounding area of the base station antenna; in the verification mode, the control module controls the aircraft to measure the distance according to the background setting and the distance measuring submodule, and fly along a right angle in the horizontal direction: when the front face of the sky is identified to be verified, after the aircraft turns clockwise/anticlockwise by 90 degrees, the aircraft linearly flies for 3 times of the width of the front face of the sky, then turns anticlockwise/clockwise by 90 degrees, and the distance is measured by a distance measuring submodule in a linear flight mode; when the left side surface of the front surface of the sky is identified to be required to verify the front surface, the aircraft turns to 90 degrees anticlockwise, the distance is 3 times of the width of the side surface of the sky in a straight line flight, then turns to 90 degrees clockwise, and the distance is measured by a distance measuring submodule in the straight line flight; when the right side surface of the front surface of the sky is identified to be required to be verified, the aircraft turns 90 degrees clockwise, the distance is 3 times of the width of the side surface of the sky in a straight line flight, then turns 90 degrees anticlockwise, and the distance is measured by a distance measuring submodule in the straight line flight.
When the mode identification module is in an identification mode, the control module controls the aircraft to hover until the timer counts down to 0, and then the camera shooting sub-module shoots the sky; in the recognition mode, if the recognition sub-module does not recognize the sky, when the aircraft needs to resume flying along the vertical S-shaped route from the hovering state, the recognition sub-module is relied on to send a signal to the control module; if the recognition sub-module recognizes the sky in the recognition mode or does not recognize the sky in the verification mode, the recognition sub-module sends a signal to the mode switching module, and the mode switching module informs the control module of changing the flight attitude.
The distance measuring sub-module is located right above the camera of the camera sub-module, the distance between the distance measuring sub-module and the camera sub-module is smaller than 1/2 of the width of the side face of the sky, and therefore when the front face or the side face of the sky exists in the center of a photo, the measured distance cannot exceed the range of the current plane of the sky, the distance measuring sub-module preferably adopts infrared distance measurement, the refractive index is smaller, and the distance measurement is stable.
The positioning module comprises a GPS sub-module, an air pressure sensor, an optical flow sensor and an ultrasonic sensor, wherein the GPS sub-module realizes the rough positioning of the horizontal position of the aircraft, the air pressure sensor realizes the rough control of the hovering height, the optical flow sensor realizes the precise control of the hovering horizontal position, and the ultrasonic sensor realizes the precise control of the flying height and obstacle avoidance.
Correspondingly, the invention also discloses a method for measuring and calculating the base station sky parameters, which is carried out by adopting the system for measuring and calculating the base station sky parameters and comprises the following steps:
step 1: the communication module transmits the position of the target base station to the control module, and the control module controls the aircraft to travel to the target position through the positioning module;
step 2: setting the mode switching module as an identification mode, and collecting and calculating the antenna parameters of the target position by the identification and calculation module;
step 3: the mode switching module is set to be a verification mode, and the identification and measurement module transmits the acquired and measured weather parameters to the background.
Specifically, please refer to fig. 2:
step 11: the control module receives information of the background about the flight range through the communication module, wherein the information comprises the height, longitude and latitude and manually set flight scanning shooting range stored in a database of the antenna to be tested, and the information can quickly fly to the initial position near the antenna.
Step 21: in the recognition mode, the timer 180 resets the countdown to start.
Step 22: the aircraft flies along a vertical S-shaped path.
Step 23: whether the timer counts down to 0: if the count down time is 0, the timer triggers the module to hover, and the step 24 is carried out; if the count down has not been reached to 0, step 22 is continued.
Step 24: the aircraft hovers, and the shooting submodule shoots a picture and transmits the picture to the identification submodule for identification processing.
Step 25: the recognition submodule judges whether a rectangular region with pixels in a certain range exists in the center of the photo: if so, whether the aircraft is in an identification mode or a verification mode, then the process proceeds to step 251 to continue the identification process; if not, go to step 26 to continue the determination.
The subsequent processing involved in steps 251 to 254 for identifying the existence of a rectangle in the photo center may be specifically described as the following:
step 251: the ranging sub-module determines a horizontal straight line distance of the aircraft to the currently identified sky side. And the calculating submodule calculates the length, width and length-width ratio of the rectangle.
Step 252: comparing whether the length-width dimension or the length-width ratio is consistent with the dimension of the known antenna surface of the current net: if so, go to step 253; if not, go back to step 21 and look for the sky again.
Step 253: the measuring and calculating submodule calculates an included angle alpha with the horizontal according to the long side of the rectangle, and judges which side face of the rectangle is the sky according to whether the alpha is larger than 90 degrees.
Step 254: the measurement submodule calculates a pitch angle beta= |90-alpha|. The detecting sub-module stores the pitch angle into the storage sub-module, the identifying sub-module stores the corresponding sky side photo into the storage sub-module, and the positioning module stores the altitude and heading of the aircraft into the storage sub-module.
Step 255: after finishing the identification processing of the photo center trapezium, judging whether the current aircraft is in a verification mode or not: if yes, go to step 31; if not, the process is ready to go to the authentication mode, i.e., step 256 is entered.
Step 256: the recognition submodule sends a signal to the mode switching module to be converted into a verification mode.
Step 257: judging whether the rectangle which is recognized is the right side of the front of the sky or not: if so, go to step 258; otherwise, go to step 259.
Step 258: and the control module controls the aircraft to turn 90 degrees clockwise and to fly straight for 3 times of the distance of the lateral surface width of the sky by the indication of the mode switching module, and then turns 90 degrees anticlockwise and to fly straight for measuring the distance by a distance measuring submodule.
Step 259: and the control module controls the aircraft to turn 90 degrees anticlockwise and to fly 3 times the distance of the width of the side face of the sky in a straight line, then turn 90 degrees clockwise and fly one distance measuring submodule in a straight line to measure the distance.
Step 2510: the aircraft flies to the front of the sky, and the control module controls the aircraft to hover. The camera sub-module takes a picture, passes it to the recognition sub-module for recognition processing and proceeds to step 26.
Step 26: judging whether pixels exist in the center of the photo within a certain range: isosceles trapezoid area with black feeder joint outside bottom edge: if so, whether the aircraft is in the identification mode or the verification mode, the process proceeds to step 261 to continue the identification process; if not, go to step 21 where the reset timer 180 counts down again.
Step 261: the ranging sub-module determines a horizontal straight line distance of the aircraft to the currently identified sky front.
Step 262: after the identification processing of the isosceles trapezoid in the center of the photo is completed, judging whether the current aircraft is in a verification mode or not: if yes, go to step 31; if not, the process proceeds to step 263 in preparation for the transfer to the authentication mode.
In the identification mode of steps 263 to 265, after identifying the isosceles trapezoid on the front of the sky, the flight control process of converting to the verification mode may be specifically described as the following process:
step 263: the recognition sub-module sends a signal to the mode switching module to be converted into a verification mode.
Step 264: and after the control module controls the clockwise/anticlockwise steering degree of the aircraft, the control module controls the distance of 3 times of the width of the front face of the linear flight sky, and then the control module turns anticlockwise/clockwise for 90 degrees, and the linear flight ranging submodule measures the distance.
Step 265: the aircraft flies to one side of the sky, and the control module controls the aircraft to hover. The photographing sub-module takes a picture, passes to the recognition sub-module for recognition processing, and proceeds to step 25.
Step 31: the pitch angle, the height and the heading in the storage sub-module 230 are transmitted to the background through the communication module, and the pitch angle, the height and the direction angle of the antenna are corresponding.
Step 32: and (3) aiming at the end of the complete process of identifying and measuring one antenna, the aircraft receives a background instruction to return or the mode switching module is converted into an identifying mode through the communication module to start the operation of identifying and measuring the next antenna.
The base station sky parameter measuring and calculating system firstly scans and shoots the surrounding area of the base station sky under the identification mode and carries out image processing until the sky is identified, then the base station sky parameter measuring and calculating system is switched into the verification mode to confirm the sky. And in the process of identification and verification, measuring and calculating the pitch angle of the antenna, recording the height and azimuth angle of the antenna, and completing automatic acquisition and measurement of the antenna parameters of the base station.
The base station antenna parameter measuring and calculating system is used for identifying and verifying the base station antenna, and the base station antenna parameter measuring and calculating system is used for identifying and verifying the front face and the side face of the antenna respectively. That is, if the front face of the antenna is identified in the identification mode, the verification is performed by means of the side face of the antenna in the verification mode; on the contrary, if the side of the top surface is recognized in the recognition mode, the verification is performed by means of the front surface of the recognition top surface in the verification mode.
The measurement of the antenna pitch angle of the base station is based on the identification of the antenna side, namely, the measurement of the pitch angle is carried out as long as the antenna side is identified in the identification mode or the verification mode.
The process of the base station antenna parameter measuring and calculating system for identifying the antenna side face and measuring and calculating the pitch angle comprises the following steps: identifying whether a rectangle exists in the center of the photo; whether the color value of the rectangular inner area is within the designed range; measuring the distance from the aircraft to the side by the measuring submodule, and then calculating whether the actual length and width of the side, the length and width or the length-width ratio are consistent with the size data of one of the sky sides in the operation of the existing network according to the rectangular length and width identified by the picture; calculating an included angle alpha between a straight line of a rectangular long side and the horizontal, wherein if alpha is more than 90 degrees, the side surface is positioned on the left side of the front face of the top, otherwise, if alpha is less than 90 degrees, the side surface is positioned on the right side of the front face of the top; calculate pitch angle β= |90- α|. If there is a rectangle satisfying all the above conditions, it is judged that the ceiling side face is recognized. After the pitch angle measurement is completed, the pitch angle, the corresponding weather side photo, the aircraft height and the heading are stored in the storage submodule, and the identification submodule sends a level signal to the mode switching module to switch the flight mode.
The color value of the rectangular internal area adopts RGB color standard, and the color value of the rectangular internal area needs to meet the requirements of R65-95, G65-95 and B55-105.
The process of identifying the front face of the antenna by the base station antenna parameter measuring and calculating system comprises the following steps: identifying whether an isosceles trapezoid exists in the center of the photo; whether the color value of the inner area of the isosceles trapezoid is within the designed range; whether a black feeder joint exists outside the bottom of the isosceles trapezoid or not. If the isosceles trapezoid with all three conditions met exists, judging that the front of the sky is identified, performing infrared ranging, sending a level signal to a mode switching module, and switching the flight mode.
The color value of the inner area of the isosceles trapezoid adopts RGB color standard, and the color value of the inner area of the isosceles trapezoid is required to meet the requirements of R65-95, G65-95 and B55-105.
The base station antenna parameter measuring and calculating system can fly to the periphery of the antenna rapidly in an identification mode, and then the cycle of flying, hovering, shooting and identification is repeated continuously along a vertical S-shaped route in a certain area, until the presence of the top/side of the center of the taken photograph is recognized, and then switches to the authentication mode.
The base station antenna parameter measuring and calculating system scans and shoots the surrounding area of the antenna in an identification mode, and the scanning range determines the GPS longitude and latitude, altitude and azimuth angle of the antenna recorded in a resource management system of an operator and the starting position and the ending position of vertical and horizontal scanning shooting which are manually set are transmitted to the flight control module through the communication module by virtue of the background. The interval of scanning shooting is controlled by the countdown of a timer, and after the identification processing is finished, if the sky is not identified, the timer is reset by sending an instruction, and the countdown is restarted; if the sky is identified, the verification mode is shifted to.
In summary, the system and the method for measuring and calculating the base station ceiling parameters provided by the invention realize automatic collection and measurement of the base station ceiling parameters, can replace manual operation, improve the operation efficiency, reduce the difference of manual measurement, and reduce the operation cost and risk.
The above description is only illustrative of the preferred embodiments of the present invention and is not intended to limit the scope of the present invention, and any alterations and modifications made by those skilled in the art based on the above disclosure shall fall within the scope of the appended claims.
Claims (5)
1. The system is characterized by comprising a positioning module, a control module, a mode switching module, a communication module and an identification measuring module, wherein the control module acquires the position of a target base station through the communication module and controls the aircraft to travel to the position of the target base station by means of the positioning module, the mode switching module is at least provided with two working modes of identification/verification, when the mode switching module is set to be in an identification mode, the identification measuring module collects and measures parameters of the antenna of the target base station, and when the mode switching module is set to be in a verification mode, the identification measuring module verifies the antenna of the target base station and transmits the parameters to a background; wherein,,
the recognition and measurement module comprises a recognition sub-module, a measurement sub-module, a storage sub-module, a camera shooting sub-module and a ranging sub-module, wherein the recognition sub-module recognizes the sky, the measurement sub-module calculates the pitch angle of the sky according to the sky information recognized by the recognition sub-module, the storage sub-module stores the sky information and the calculation result, the camera shooting sub-module transmits the photographed sky photo to the recognition sub-module for recognition, and the ranging sub-module measures the distance between the aircraft and the front of the sky and transmits the distance to the storage sub-module;
the process of verifying the antenna surface of the target base station by the identification and measurement module comprises the following steps: if the identification measuring and calculating module identifies the front face of the sky in the identification mode, the identification measuring and calculating module identifies the side face of the sky in the verification mode for verification; otherwise, if the recognition measuring and calculating module recognizes the side face of the sky in the recognition mode, the recognition measuring and calculating module recognizes the front face of the sky in the verification mode for verification;
the process of collecting and measuring the antenna parameters by the identification measuring and calculating module is as follows: the shooting submodule shoots a sky photo; the recognition sub-module performs image recognition on the photographed top photo, and when the center image of the top photo is recognized to meet the design condition, the measuring and calculating sub-module measures the size of the top; the distance measuring submodule measures the distance between the aircraft and the front surface of the sky so that the measuring and calculating submodule measures the real size of the side surface of the sky and verifies whether the real size is consistent with the size of a known sky product; the measuring and calculating submodule calculates the pitch angle of the sky according to the size of the sky;
the process of identifying the side face of the sky and measuring and calculating the pitch angle comprises the following steps: the center of the photo is rectangular; the color value of the rectangular inner area is within the designed range; the distance measuring sub-module measures the distance from the aircraft to the sky side, calculates the actual length and width of the sky side according to the rectangular length and width identified by the photo, and the length and width or the length-width ratio of the sky side is consistent with the size data of one of the sky sides operated by the existing network; calculating an included angle alpha between the long side of the rectangle and the horizontal, wherein if alpha is more than 90 degrees, the side surface is positioned on the left side of the front surface of the sky, and if alpha is less than 90 degrees, the side surface is positioned on the right side of the front surface of the sky; and calculating the pitch angle beta= |90-alpha|.
2. The base station antenna parameter measurement and calculation system of claim 1, wherein the positioning module comprises a GPS sub-module, an optical flow sensor, an air pressure sensor and an ultrasonic sensor, the GPS sub-module performs horizontal position coarse positioning on the aircraft, the air pressure sensor performs coarse control on the hovering height of the aircraft, the optical flow sensor performs precise control on the hovering horizontal position of the aircraft, and the ultrasonic sensor realizes precise control and obstacle avoidance on the aircraft.
3. The base station antenna parameter measurement system of claim 1, further comprising a timer, the timer connecting the mode switching module and the control module.
4. A method for measuring and calculating the antenna parameters of a base station comprises the following steps:
the communication module transmits the position of the target base station to the control module, and the control module controls the aircraft to travel to the target position through the positioning module;
the mode switching module is set to be an identification mode, and the identification measuring and calculating module collects and calculates parameters of the sky surface of the target base station;
the mode switching module is set to be a verification mode, and the identification measuring and calculating module verifies the antenna surface of the target base station and transmits parameters to the background;
the process of verifying the antenna surface of the target base station by the identification and measurement module comprises the following steps: if the identification measuring and calculating module identifies the front face of the sky in the identification mode, the identification measuring and calculating module identifies the side face of the sky in the verification mode for verification; otherwise, if the recognition measuring and calculating module recognizes the side face of the sky in the recognition mode, the recognition measuring and calculating module recognizes the front face of the sky in the verification mode for verification;
the process of parameter acquisition and calculation of the sky by the identification and calculation module is as follows: the shooting submodule shoots a sky photo; the recognition sub-module performs image recognition on the photographed top photo, and when the center image of the top photo is recognized to meet the design condition, the measuring and calculating sub-module measures the size of the top; the distance measuring submodule measures the distance between the aircraft and the front surface of the sky so that the measuring and calculating submodule measures the real size of the side surface of the sky and verifies whether the real size is consistent with the size of a known sky product; the measuring and calculating submodule calculates the pitch angle of the sky according to the size of the sky; the process of identifying the side face of the sky and measuring and calculating the pitch angle comprises the following steps: the center of the photo is rectangular; the color value of the rectangular inner area is within the designed range; the distance measuring sub-module measures the distance from the aircraft to the sky side, calculates the actual length and width of the sky side according to the rectangular length and width identified by the photo, and the length and width or the length-width ratio of the sky side is consistent with the size data of one of the sky sides operated by the existing network; calculating an included angle alpha between the long side of the rectangle and the horizontal, wherein if alpha is more than 90 degrees, the side surface is positioned on the left side of the front surface of the sky, and if alpha is less than 90 degrees, the side surface is positioned on the right side of the front surface of the sky; and calculating the pitch angle beta= |90-alpha|.
5. The method for measuring and calculating parameters of a base station according to claim 4, wherein the process of identifying the front of the antenna is: the center of the photo is isosceles trapezoid; the color value of the inner area of the isosceles trapezoid is within the design range; a black feeder line joint exists outside the lower bottom of the isosceles trapezoid.
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