CN103808318A - Real-time plane taxiing position positioning system and control method - Google Patents
Real-time plane taxiing position positioning system and control method Download PDFInfo
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- CN103808318A CN103808318A CN201410045064.3A CN201410045064A CN103808318A CN 103808318 A CN103808318 A CN 103808318A CN 201410045064 A CN201410045064 A CN 201410045064A CN 103808318 A CN103808318 A CN 103808318A
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Abstract
The invention provides a real-time plane taxiing position positioning system and a control method. The system comprises a plurality of embedded sensors, a plurality of data collection terminals and an analysis control terminal, wherein each embedded sensor is connected with one data collection terminal; the data collection terminals are connected with the analysis control terminal mounted on a control center in a wireless manner; each embedded sensor comprises a columnar shell, a controller for a single chip microcomputer, at least one vibration sensor, a plurality of limiters, a lithium battery, a lower fixing base and an upper detachable cover plate; each limiter comprises a fixing sleeve, a stretchable limiting rod, a high-strength spring, at least one fixed limiting pin, at least one stretchable limiting pin and a limiting sleeve. According to the real-time plane taxiing position positioning system and the control method provided by the invention, a plane taxiing position on an airport pavement can be dynamically monitored in real time. The real-time plane taxiing position positioning system and the control method have the advantages of security, reliability, simplicity and convenience in construction, and simplicity and convenience in implementation; the service life of the system is long.
Description
Technical field
The invention belongs to airport engineering technical field, particularly relate to a kind of aircraft taxi position real-time positioning system and control method.
Background technology
Data shows according to statistics, and the high-incidence season of airline carriers of passengers accident mainly concentrates on and takes off, starts to climb and the approach stage.Under the inclement weathers such as dense fog, heavy rain, heavy snow, On The Deterioration of Visibility Over, managerial personnel cannot observe directly aircraft taxi position from control tower, and pilot also cannot observe the position of other aircraft simultaneously, so just very easily causes passenger plane security incident.Because airline carriers of passengers accident can directly affect the safe operation on airport and passenger's life security, so enjoy the concern of airdrome control department all the time.
Although can determine in real time by GPS locator meams at present the sliding position of aircraft, under inclement weather, very easily there is the inaccurate problem in location, therefore still leave potential safety hazard.The applicant once submitted " Flying Area in Airport panorama management system " by name and " a kind of airport pavement plate residual life assessment system and control evaluation method " two patented claims to 2012 and 2013 Patent Offices of Nian Xianhouxiang State Intellectual Property Office for this reason, this technical scheme gathers aircraft taxi image analysis of aircraft sliding position by camera is installed in movement area, locate problem inaccurate and that cause although solved to a certain extent GPS, but still the unresolved poor problem of image identification degree causing because of low visibility under inclement weather.Therefore, how to locate in real time aircraft taxi position and become the problem that airport engineering field needs further research.
Based on above-mentioned analysis, research and develop a kind of aircraft taxi position real-time positioning system and control method, under adverse weather condition, pass through recording channel surface vibration, intuitively, judge reliably, exactly aircraft taxi position, reduce airfield pavement operational management risk with this, there is important theory significance and practice significance.
Summary of the invention
In order to address the above problem, the object of the present invention is to provide one safe and reliable, there is aircraft taxi position real-time positioning system and the control method of easy construction, long service life.
In order to achieve the above object, aircraft taxi provided by the invention position real-time positioning system comprises multiple buried sensors, multiple data collection station and an analysis and Control terminal, each buried sensor is connected with a data collection station, and data collection station is connected with the analysis and Control terminal that is arranged on control center by wireless mode; Buried sensor comprises cylindrical shell, singlechip controller, at least one vibration transducer, multiple stop, lithium battery, bottom firm banking and top dismountable cover plate; Wherein singlechip controller is arranged at cylindrical shell internal upper part, and is connected with vibration transducer and lithium battery, simultaneously be arranged at airfield pavement outside data collection station and the power supply in Cao Mian district be electrically connected; Lithium battery is arranged at bottom in cylindrical shell; Vibration transducer and stop are disposed on the outer circumference surface of cylindrical shell removably; The bottom surface of cylindrical shell is fixed on the surface of bottom firm banking; Top dismountable cover plate is arranged on cylindrical shell end face removably; Described stop comprises fixed muffle, Extendible spacing bar, high strong spring, at least one fixing spacer pin, at least one Extendible spacing pin and a spacing collar; Wherein one end of fixed muffle sealing, this blind end external stability is on cylindrical shell; One end of Extendible spacing bar is inserted in the inside of fixed muffle; The two ends of high strong spring are separately fixed on fixed muffle on blind end inside surface and Extendible spacing bar inner face; Fixing spacer pin is arranged at the outside surface middle part of fixed muffle; Extendible spacing pin is arranged at Extendible spacing bar middle part outside, and inside that can indentation Extendible spacing bar; On one side of spacing collar, be formed with opening, it is enclosed within fixed muffle and Extendible spacing bar outside between fixing spacer pin and Extendible spacing pin removably.
Described data collection station is the single-chip microcomputer being connected with buried sensor by data line, is provided with the computing machine that aircraft taxi position control routine analyzer is installed in it in analysis and Control terminal.
The quantity of described stop is 4, between adjacent stop at a distance of 90 °.
On described singlechip controller, also leave multiple for the spare interface of vibration transducer is set.
The control method of aircraft taxi provided by the invention position real-time positioning system comprises the following step carrying out in order:
1) the S1 stage of system power-on self-test; In this stage, first system carries out the power-on self-test of hardware, and aircraft taxi position control routine analyzer on startup analysis control terminal Computer, whether working properly to judge the buried sensor that each data collection station connected, if had extremely, self check again after hand inspection, if shown normally, enters the S2 stage;
2) the S2 stage of idle pulley; In this stage, wait pending next step operation;
3) judge whether to click S3 stage of the real-time navigation button in aircraft taxi position; In this stage, system will judge that whether user clicks " locate the in real time aircraft taxi position " button on analysis and Control terminal Computer display screen, if judged result is "Yes", enters the S4 stage; Otherwise turn back to the porch in S2 stage;
4) carry out S4 stage of surface vibration signals collecting; In this stage, the vibration signal that the vibration signal that computing machine in analysis and Control terminal 3 collects buried sensor internal vibration sensor embedding to dynamic acquisition airfield runway, taxiway and tarmac area filter motor-car cause, then demonstrate on display screen with graphics mode by the vibrative position of aircraft taxi excited vibrational sensor, thereby position and the moving direction of orienting airfield runway, taxiway and tarmac area aircraft, then enter the S5 stage;
5) judge the S5 stage whether vibration signals collecting finishes; In this stage, system will judge that whether user clicks " gather and the finish " button on analysis and Control terminal Computer display screen, if judged result is "Yes", finishes gatherer process, otherwise turns back to the porch in S4 stage.
Aircraft taxi provided by the invention position real-time positioning system and control method tool have the following advantages: 1) easy construction: only need on road face, hole and cutting, whole process is consuming time short, and can utilize suspends completely intermittently carries out.2) safe and reliable: after road face reparation construction finishes, on road face, without any breakage and legacy, can not bring hidden danger to takeoff and landing.3) data acquisition reliable results: sensor setting can directly be obtained to the data in aircraft and runway contact process on aircraft wheel path, more reliable with respect to traditional test method results.4) change easy: if sensor breaks down, only need original sensor to take out, and reinstall.5) long service life: power supply is arranged on to Cao Mian district, runway both sides, can effectively improves the serviceable life of sensor, prevent the internal battery charge storage ability sensor failure causing that declines.
Accompanying drawing explanation
Fig. 1 is aircraft taxi provided by the invention position real-time positioning system composition schematic diagram.
Fig. 2 is buried sensor construction vertical view in the real-time positioning system of aircraft taxi provided by the invention position.
Fig. 3 is buried sensor construction elevation drawing in the real-time positioning system of aircraft taxi provided by the invention position.
Fig. 4 is buried sensor upper limit device original state schematic diagram in the real-time positioning system of aircraft taxi provided by the invention position.
Fig. 5 is buried sensor upper limit device working state schematic representation in the real-time positioning system of aircraft taxi provided by the invention position.
Fig. 6 is the control method process flow diagram of aircraft taxi provided by the invention position real-time positioning system.
Embodiment
Below in conjunction with the drawings and specific embodiments, aircraft taxi provided by the invention position real-time positioning system and control method are elaborated.
As Figure 1-Figure 5, aircraft taxi provided by the invention position real-time positioning system comprises multiple buried sensors 1, multiple data collection station 2 and an analysis and Control terminal 3, each buried sensor 1 is connected with a data collection station 2, and data collection station 2 is connected with the analysis and Control terminal 3 that is arranged on control center by wireless mode; Buried sensor 1 comprises cylindrical shell 4, singlechip controller 5, at least one vibration transducer 6, multiple stop 7, lithium battery 8, bottom firm banking 9 and top dismountable cover plate 10; Wherein singlechip controller 5 is arranged at cylindrical shell 4 internal upper parts, and is electrically connected with vibration transducer 6 and lithium battery 8, simultaneously be arranged at airfield pavement outside data collection station 2 and the power supply in Cao Mian district be electrically connected; Lithium battery 8 is arranged at the interior bottom of cylindrical shell 4; Vibration transducer 6 and stop 7 are disposed on the outer circumference surface of cylindrical shell 4 removably; The bottom surface of cylindrical shell 4 is fixed on the surface of bottom firm banking 9; Top dismountable cover plate 10 is arranged on cylindrical shell 4 end faces removably; Described stop 7 comprises fixed muffle 11, Extendible spacing bar 12, high strong spring 13, at least one fixing spacer pin 14, at least one Extendible spacing pin 15 and a spacing collar 16; Wherein one end of fixed muffle 11 sealing, this blind end external stability is on cylindrical shell 4; One end of Extendible spacing bar 12 is inserted in the inside of fixed muffle 11; The two ends of high strong spring 13 are separately fixed on fixed muffle 11 on blind end inside surface and Extendible spacing bar 12 inner faces; Fixing spacer pin 14 is arranged at the outside surface middle part of fixed muffle 11; Extendible spacing pin 15 is arranged at Extendible spacing bar 12 middle parts outsides, and inside that can indentation Extendible spacing bar 12; On one side of spacing collar 16, be formed with opening, it is enclosed within fixed muffle 11 and Extendible spacing bar 12 outsides between fixing spacer pin 14 and Extendible spacing pin 15 removably.
The single-chip microcomputer of described data collection station 2 for being connected with buried sensor 1 by data line, is provided with the computing machine that aircraft taxi position control routine analyzer is installed in it in analysis and Control terminal 3.
The quantity of described stop 7 is 4, between adjacent stop 7, at a distance of 90 °, whole buried sensor 1 firmly can be fixed on like this in the ground of airfield pavement below.
On described singlechip controller 5, also leave multiple for the spare interface of vibration transducer 6 is set.
Now the implementation method of above-mentioned aircraft taxi position real-time positioning system is described below:
1) vibration transducer 6 and stop 7 are arranged on cylindrical shell 4, and whether test is working properly;
2) on the assigned address of airfield runway, taxiway and center line both sides, hardstand aircraft wheel path, drill airfield pavement downwards to basal layer, form the column road face boring that and the degree of depth identical with buried sensor 4 maximum gauges is greater than buried sensor 4 height 5cm, then face boring in Cong Gai road goes out a joint-cutting that 2cm is wide, 5cm is dark to outer runway transverse cuts, until reach Cao Mian district outside airfield pavement, thus road face boring Yu Caomian district is communicated with;
3) on above-mentioned road face drill hole inner wall, highly radially outwards get out according to arranging of stop 7 circular hole that multiple and degree of depth corresponding with multiple stops 7 positions respectively, diameter conform to;
4) pull down top dismountable cover plate 10, and Extendible spacing pin 15 is compressed into Extendible spacing bar 12 inside, then the inner end of Extendible spacing bar 12 is inserted in fixed muffle 11, compress thus high strong spring 13, state now as shown in Figure 4, is arranged at bottom firm banking 9 on the basal layer surface in face boring afterwards;
5) circular hole on Yi Ge road face drill hole inner wall is aimed in the outer end of each Extendible spacing bar 12, then pull out Extendible spacing bar 12, after Extendible spacing pin 15 shifts out fixed muffle 11, it will outwards eject to Extendible spacing bar 12 outsides, the outer end of Extendible spacing bar 12 will extend in above-mentioned circular hole simultaneously, then spacing collar 16 is enclosed within to fixed muffle 11 and Extendible spacing bar 12 outsides between fixing spacer pin 14 and Extendible spacing pin 15 from opening part, thus the relative position between fixed muffle 11 and Extendible spacing bar 12 is fixed, change with the position that prevents Extendible spacing pin 15, state now as shown in Figure 5,
6) data line being connected with singlechip controller 5 and power lead are connected on top dismountable cover plate 10;
7) adopt the material identical with airfield pavement that the position in above-mentioned road face boring cylindrical shell 4 outsides is filled up, until reach the tip position of cylindrical shell 4, then top dismountable cover plate 10 is arranged on cylindrical shell 4, and data line and power lead are arranged in joint-cutting, then road face boring top is all sealed;
8) data line and power lead are caused to Cao Mian district outside airfield pavement along joint-cutting, and be connected with data collection station 2 and power supply;
9) by step 2) the joint-cutting sealing that forms;
10) in actual motion, data collection station 2 is by the signal that on buried Real-time Collection sensor 1, vibration transducer 6 gathers and transmits, radio to afterwards analysis and Control terminal 3, to monitor the vibration causing after aircraft landing on airfield pavement, thus real-time aircraft taxi positional information.
In addition, occur damaging if work progress causes above-mentioned vibration transducer 6, or the situation of abnormal signal occurs and while needing repairing in use procedure, can be in former bore position redrilling, buried sensor 1 is taken out to repeating step 1 after replacing damage parts) to step 9).
As shown in Figure 6, the control method of aircraft taxi provided by the invention position real-time positioning system comprises the following step carrying out in order:
1) the S1 stage of system power-on self-test; In this stage, first system carries out the power-on self-test of hardware, and aircraft taxi position control routine analyzer on startup analysis control terminal 3 Computers, whether working properly to judge the buried sensor 1 that each data collection station 2 connected, if had extremely, self check again after hand inspection, if shown normally, enters the S2 stage;
2) the S2 stage of idle pulley; In this stage, wait pending next step operation;
3) judge whether to click S3 stage of the real-time navigation button in aircraft taxi position; In this stage, system will judge that whether user clicks " locate the in real time aircraft taxi position " button on analysis and Control terminal 3 Computer display screens, if judged result is "Yes", enters the S4 stage; Otherwise turn back to the porch in S2 stage;
4) carry out S4 stage of surface vibration signals collecting; In this stage, the vibration signal that the vibration signal that computing machine in analysis and Control terminal 3 collects buried sensor embedding to dynamic acquisition airfield runway, taxiway and tarmac area 1 internal vibration sensor 6 filter motor-car cause, then demonstrate on display screen with graphics mode by aircraft taxi excited vibrational sensor 6 vibrative positions, thereby position and the moving direction of orienting airfield runway, taxiway and tarmac area aircraft, then enter the S5 stage;
5) judge the S5 stage whether vibration signals collecting finishes; In this stage, system will judge that whether user clicks " gather and the finish " button on analysis and Control terminal 3 Computer display screens, if judged result is "Yes", finishes gatherer process, otherwise turns back to the porch in S4 stage.
Claims (5)
1. an aircraft taxi position real-time positioning system, it is characterized in that: it comprises multiple buried sensors (1), multiple data collection station (2) and an analysis and Control terminal (3), each buried sensor (1) is connected with a data collection station (2), and data collection station (2) is connected with the analysis and Control terminal (3) that is arranged on control center by wireless mode; Buried sensor (1) comprises cylindrical shell (4), singlechip controller (5), at least one vibration transducer (6), multiple stop (7), lithium battery (8), bottom firm banking (9) and top dismountable cover plate (10); Wherein singlechip controller (5) is arranged at cylindrical shell (4) internal upper part, and is electrically connected with vibration transducer (6) and lithium battery (8), simultaneously be arranged at airfield pavement outside data collection station (2) and the power supply in Cao Mian district be electrically connected; Lithium battery (8) is arranged at the interior bottom of cylindrical shell (4); Vibration transducer (6) and stop (7) are disposed on the outer circumference surface of cylindrical shell (4) removably; The bottom surface of cylindrical shell (4) is fixed on the surface of bottom firm banking (9); Top dismountable cover plate (10) is arranged on cylindrical shell (4) end face removably; Described stop (7) comprises fixed muffle (11), Extendible spacing bar (12), high strong spring (13), at least one fixing spacer pin (14), at least one Extendible spacing pin (15) and a spacing collar (16); Wherein one end of fixed muffle (11) sealing, this blind end external stability is on cylindrical shell (4); One end of Extendible spacing bar (12) is inserted in the inside of fixed muffle (11); The two ends of high strong spring (13) are separately fixed on the upper blind end inside surface of fixed muffle (11) and Extendible spacing bar (12) inner face; Fixing spacer pin (14) is arranged at the outside surface middle part of fixed muffle (11); Extendible spacing pin (15) is arranged at Extendible spacing bar (12) middle part outside, and inside that can indentation Extendible spacing bar (12); On one side of spacing collar (16), be formed with opening, it is enclosed within the fixed muffle (11) and Extendible spacing bar (12) outside that are positioned between fixing spacer pin (14) and Extendible spacing pin (15) removably.
2. aircraft taxi according to claim 1 position real-time positioning system, it is characterized in that: the single-chip microcomputer of described data collection station (2) for being connected with buried sensor (1) by data line, analysis and Control terminal is provided with the computing machine that aircraft taxi position control routine analyzer is installed in it in (3).
3. aircraft taxi according to claim 1 position real-time positioning system, is characterized in that: the quantity of described stop (7) is 4, between adjacent stop (7) at a distance of 90 °.
4. aircraft taxi according to claim 1 position real-time positioning system, is characterized in that: on described singlechip controller (5), also leave multiple for the spare interface of vibration transducer (6) is set.
5. a control method for aircraft taxi as claimed in claim 1 position real-time positioning system, is characterized in that: described control method comprises the following step carrying out in order:
1) the S1 stage of system power-on self-test; In this stage, first system carries out the power-on self-test of hardware, and aircraft taxi position control routine analyzer on startup analysis control terminal (3) Computer, whether working properly to judge the buried sensor (1) that each data collection station (2) connected, if had extremely, self check again after hand inspection, if shown normally, enters the S2 stage;
2) the S2 stage of idle pulley; In this stage, wait pending next step operation;
3) judge whether to click S3 stage of the real-time navigation button in aircraft taxi position; In this stage, system will judge that whether user clicks " locate the in real time aircraft taxi position " button on analysis and Control terminal (3) Computer display screen, if judged result is "Yes", enters the S4 stage; Otherwise turn back to the porch in S2 stage;
4) carry out S4 stage of surface vibration signals collecting; In this stage, the vibration signal that the vibration signal that computing machine in analysis and Control terminal (3) collects buried sensor (1) internal vibration sensor (6) embedding to dynamic acquisition airfield runway, taxiway and tarmac area filter motor-car cause, then demonstrate on display screen with graphics mode by the vibrative position of aircraft taxi excited vibrational sensor (6), thereby position and the moving direction of orienting airfield runway, taxiway and tarmac area aircraft, then enter the S5 stage;
5) judge the S5 stage whether vibration signals collecting finishes; In this stage, system will judge that whether user clicks " gather and the finish " button on analysis and Control terminal (3) Computer display screen, if judged result is "Yes", finishes gatherer process, otherwise turns back to the porch in S4 stage.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104071351A (en) * | 2014-06-20 | 2014-10-01 | 中国民航大学 | Monitoring system for taking off and landing of plane on airport runway |
| CN104890889A (en) * | 2015-05-13 | 2015-09-09 | 深圳一电科技有限公司 | Control method of aircraft and aircraft |
| CN114858327A (en) * | 2022-03-15 | 2022-08-05 | 同济大学 | Airplane wheel track identification method based on soil pressure gauge |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030182076A1 (en) * | 2002-03-12 | 2003-09-25 | American Gnc Corporation | Gravity-reference vision system |
| CN101850849A (en) * | 2010-05-18 | 2010-10-06 | 清华大学 | Positioning system and positioning method for take-off deviation of airplane |
| US20110257818A1 (en) * | 2010-04-16 | 2011-10-20 | The Boeing Company | Dynamically Monitoring Airborne Turbulence |
| CN102360218A (en) * | 2011-10-14 | 2012-02-22 | 天津大学 | ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and flight control system for unmanned helicopter |
| CN103076502A (en) * | 2012-12-20 | 2013-05-01 | 北京交通大学 | System and method for collecting remote and synchronous measuring data of moving object target |
| US20130317736A1 (en) * | 2012-05-22 | 2013-11-28 | Steven J. Fernandes | System and method to determine an initial insurance policy benefit based on telematics data collected by a smartphone |
-
2014
- 2014-02-07 CN CN201410045064.3A patent/CN103808318B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030182076A1 (en) * | 2002-03-12 | 2003-09-25 | American Gnc Corporation | Gravity-reference vision system |
| US20110257818A1 (en) * | 2010-04-16 | 2011-10-20 | The Boeing Company | Dynamically Monitoring Airborne Turbulence |
| CN101850849A (en) * | 2010-05-18 | 2010-10-06 | 清华大学 | Positioning system and positioning method for take-off deviation of airplane |
| CN102360218A (en) * | 2011-10-14 | 2012-02-22 | 天津大学 | ARM (advanced RISC (reduced instruction set computer) machines) and FPGA (field-programmable gate array) based navigation and flight control system for unmanned helicopter |
| US20130317736A1 (en) * | 2012-05-22 | 2013-11-28 | Steven J. Fernandes | System and method to determine an initial insurance policy benefit based on telematics data collected by a smartphone |
| CN103076502A (en) * | 2012-12-20 | 2013-05-01 | 北京交通大学 | System and method for collecting remote and synchronous measuring data of moving object target |
Non-Patent Citations (2)
| Title |
|---|
| 王立冬等: "《多传感器定位误差对跟踪性能影响的研究 》", 《火力与指挥控制》 * |
| 马建仓等: "《飞机状态监测无线传感器网络系统》", 《测控技术》 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104071351A (en) * | 2014-06-20 | 2014-10-01 | 中国民航大学 | Monitoring system for taking off and landing of plane on airport runway |
| CN104071351B (en) * | 2014-06-20 | 2016-05-04 | 中国民航大学 | A kind of airfield runway takeoff and landing monitoring system |
| CN104890889A (en) * | 2015-05-13 | 2015-09-09 | 深圳一电科技有限公司 | Control method of aircraft and aircraft |
| CN104890889B (en) * | 2015-05-13 | 2017-02-22 | 深圳一电航空技术有限公司 | Control method of aircraft and aircraft |
| CN114858327A (en) * | 2022-03-15 | 2022-08-05 | 同济大学 | Airplane wheel track identification method based on soil pressure gauge |
| CN114858327B (en) * | 2022-03-15 | 2023-02-17 | 同济大学 | Airplane wheel track identification method based on soil pressure gauge |
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