CN109102720A - A kind of ILS safe operation state verification, reliability judgment means and method - Google Patents
A kind of ILS safe operation state verification, reliability judgment means and method Download PDFInfo
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- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/02—Automatic approach or landing aids, i.e. systems in which flight data of incoming planes are processed to provide landing data
- G08G5/025—Navigation or guidance aids
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- G—PHYSICS
- G08—SIGNALLING
- G08G—TRAFFIC CONTROL SYSTEMS
- G08G5/00—Traffic control systems for aircraft, e.g. air-traffic control [ATC]
- G08G5/0017—Arrangements for implementing traffic-related aircraft activities, e.g. arrangements for generating, displaying, acquiring or managing traffic information
- G08G5/0026—Arrangements for implementing traffic-related aircraft activities, e.g. arrangements for generating, displaying, acquiring or managing traffic information located on the ground
Abstract
The present invention relates to the evaluation areas of navigation system safe operation, especially a kind of ILS safe operation state verification, ILS reliability judgment means and method.ADS-B data reception module in the present invention is exported for receiving the ADS-B signal of aircraft, and by optical fiber link；The course ILS and glide path computing module, for receiving the ADS-B signal of the optical fiber link output；And according to ADS-B signal, calculate closely into flight path data, and according to closely obtaining closely into flight path data into navigation channel DDM data；Terminal display module, for being closely respectively formed glide path figure and course figure into navigation channel DDM data according to described.
Description
Technical field
The present invention relates to the evaluation areas of navigation system safe operation, especially a kind of ILS safe operation state verification, can
By property judgment means and method.
Background technique
Currently, executed in flight it is accurate closely into landing period, will receive when ground unit to instrument-landing-system (ILS,
Instrument Landing System) jitter situation feedback, aircraft occur near procedure it is non-it is mandatory under
Drop.There are two types of the reason of phenomenon: a kind of may be that the flying height of aircraft is higher than blind landing glide path, result in aircraft under big
Drop rate chases after glide path, caused by such case is mainly aircraft group operation error；Alternatively possible is blind landing signal station specific
Time or specific position are interfered, and being also not excluded for blind landing signal itself failure leads to jitter, such case master
Caused by if navigation signal fails.
After occurring the similar time, common processing method is by local Supervision Bureau's organization and administration office, local airport, sky
The relevant departments such as pipe, airline carry out field research, from unit operation, navigational facility state etc. it is many-sided to the event into
Row analysis and investigation.It checks navigation equipment, assesses electromagnetic environment or school flies mode every technology relevant to accident of guidance station
Index is analyzed, therefore, it is determined that the occurrence cause of event.
Since relatively winged higher cost (closing airspace) and airport carry out relatively winged number limitation, the school winged time is too short, week
Phase is long, causes the daily maintenance of the navigation equipment on each airport and problem investigation more difficult.Positioned at the instrument-landing-system of airfield runway
Aircraft landing guidance of the aircraft when visual condition is short of is carry, so safety responsibility is great, the stabilization and measurement of the equipment
The protection of precision is even more important.
ADS-B covers the big portion's airfield runway in China comprehensively at present, so can be obtained in real time using ADS-B speed winged
Machine is being guided the key messages such as position, height, speed, course when landing by ILS.Real-time, the precision of ADS-B is high, supervises
Strong depending on ability, each rack-mounted aircraft for having ADS-B equipment all can serve as school and fly aircraft, can be right by receiving ADS-B data
The operating status of ILS is verified and is assessed.Navigation equipment verification based on ADS-B is relied primarily in high-precision, high reliability
Monitoring data, can realize the corresponding verifying of navigation equipment if every airplane is all become school and flies aircraft.
Summary of the invention
The technical problems to be solved by the present invention are: in view of the problems of the existing technology, providing a kind of ILS safe operation
State verification device and method.Its receive aircraft closely into when ADS-B real time data, parsing obtains horizontal flight information and vertical flies
Row information；Further, a kind of ILS reliability judgment method and device are provided, a large amount of historical statistical data comparative analyses are passed through
The guidance sign mutation at one moment, real-time verification ILS signal reliability.
The technical solution adopted by the invention is as follows:
A kind of instrument-landing-system safe operation state verification device includes:
ADS-B data reception module is exported for receiving the ADS-B signal of aircraft, and by optical fiber link；
The course ILS and glide path computing module, for receiving the ADS-B signal of the optical fiber link output；And according to
ADS-B signal calculates closely into flight path data, and according to closely obtaining closely into flight path data into navigation channel DDM data；
Terminal display module, for being closely respectively formed glide path figure and localizer figure into navigation channel DDM data according to described.
Further, the course ILS and glide path computing module include data resolution module, filtering module, calculate mould
Block, data memory module and record playback module；Wherein,
Data resolution module, for reading the ADS-B data being transferred to by optical fiber link in real time and by record playback
The history ADS-B data of module playback, parse aircraft trace data；
Filtering module, non-near in the flight path data for being exported to data resolution module into aircraft trace data and
False aircraft trace data are filtered, and are extracted closely into flight path data；
Computing module, for according to closely into the calculating of flight path data closely into navigation channel DDM data；Closely into navigation channel DDM data
Including described closely into the corresponding localizer DDM value of deviation of flight path data and runway centerline and closely into flight path
Data and the corresponding glide path DDM value of the deviation of 3 ° of approach centerlines.
Further, the ADS-B data reception module includes ADS-B receiver, ADS-B antenna；Wherein ADS-B is received
Machine is exported for receiving the ADS-B signal of aircraft by ADS-B antenna, and by optical fiber link.
Further, the course ILS and glide path computing module further include data memory module；Data memory module,
For storing history ADS-B data, history closely into flight path data and history closely into navigation channel DDM data；History is closely into boat
Road DDM data include history localizer DDM data and history glide path DDM data；Wherein history ADS-B data are the optical fiber
Link exports and passes through the data that record playback module is stored in data memory module；History is closely filtering into flight path data
Module is stored in the data of memory module after calculating；History is closely to be stored in storage after computing module calculates into navigation channel DDM data
The data of module.
Further, the terminal display module form glide path figure and course figure be according to computing module output it is close into
The localizer DDM data and average heading that navigation channel DDM data and the history of data memory module are closely formed into navigation channel DDM data
Road DDM data, the glide path DDM number closely closely formed into navigation channel DDM data and the history of data memory module into navigation channel DDM data
Accordingly and average glide path DDM data, the course figure of the glide path figure to form 2 dimensions and 2 dimensions is respectively corresponded.
Further, the terminal display module further includes that 3 dimension flight path figures are shown；Wherein 3 dimension flight path figures are
According to the nearly history stored into flight path data and data memory module of filtering module output closely into flight path data meter
Calculate gained.
ILS reliability judgment means based on the verifying device further include guidance sign mutation detection, and guidance signal is prominent
Become detection, for respectively corresponding the course with history based on closely into localizer DDM value in the DDM data of navigation channel and glide path DDM value
The road DDM and glide path DDM of history, which subtracts each other, to take absolute value, the corresponding absolute value of the bias δ found out with history localizer DDMl, and go through
The absolute value of the bias δ of history glide path DDMgIf δl>UlAnd/or δg>Ug, then localizer DDM value and glide path DDM value are corresponding at this time
Tracing point position, as sign mutation position can determine whether that ILS reliability goes wrong if sign mutation position can reappear；
Otherwise, judge ILS reliability no problem at this time；δl>UlIndicate that aircraft horizontal direction at this position deviates closely into localizer, δg>
Ug, indicate vertical direction glide-slope deviation of the aircraft at this position.
Include: based on the verification method for verifying device
ADS-B data reception module receives the ADS-B signal of aircraft, and is exported by optical fiber link；
The course ILS and glide path computing module receive the ADS-B signal of the optical fiber link output；And believed according to ADS-B
Number, it calculates closely into flight path data, and obtain closely into navigation channel DDM data；
Terminal display module is closely respectively formed glide path figure and localizer figure into navigation channel DDM data according to described.
ILS reliability judgment method based on the verification method further include: based on closely into localizer in the DDM data of navigation channel
DDM value and glide path DDM value, respectively correspond to subtract each other with the glide path DDM of the localizer DDM of history and history and take absolute value, right
The absolute value of the bias δ with history localizer DDM should be found outlAnd the absolute value of the bias δ of history glide path DDMgIf δl>UlAnd/or
δg>Ug, then localizer DDM value and the corresponding tracing point position of glide path DDM value, as sign mutation position at this time, if signal is prominent
Displacement is set and can be reappeared, then can determine whether that ILS reliability goes wrong；Otherwise, judge ILS reliability no problem at this time；δl>UlIt indicates
Aircraft horizontal direction at this position deviates closely into localizer, δg>Ug, under indicating that vertical direction of the aircraft at this position deviates
Slideway.
In conclusion by adopting the above-described technical solution, the beneficial effects of the present invention are:
Using ADS-B technology, by receiving and handling ADS-B broadcast message, the flight for being ready to carry out arrival procedure is flown
Row vertical flight track and horizontal flight track are recorded and analyzed and are formed glide path figure and localizer figure, can assist realizing
The reliability verification of real-time ILS and the historical data of big data statistically analyze, by the statistical analysis of long-time big data quantity
The horizontal and vertical planing surface of flight when aircraft is guided by ILS is marched into the arena situation, can directly assess ILS equipment with navigation channel DDM data
To the guidance accuracy etc. of aircraft landing guidance.The guidance sign mutation at a certain moment can be found out and carry out initial stage tune simultaneously
It looks into, provides a real time monitoring for airport equipment safe operation, the winged decision implement in school provides science data foundation, to assess
The reliability and stability of ILS equipment, until analytical equipment trouble-shoots go out ILS there are the problem of.
Detailed description of the invention
Examples of the present invention will be described by way of reference to the accompanying drawings, in which:
Fig. 1 invention's principle block diagram.
Fig. 2 is computing module functional block diagram.
Specific embodiment
All features disclosed in this specification or disclosed all methods or in the process the step of, in addition to mutually exclusive
Feature and/or step other than, can combine in any way.
Any feature disclosed in this specification unless specifically stated can be equivalent or with similar purpose by other
Alternative features are replaced.That is, unless specifically stated, each feature is an example in a series of equivalent or similar characteristics
?.
Working principle of the present invention: such as Fig. 1, ADS-B data reception module of the present invention receives the ADS-B signal of aircraft, and leads to
Cross optical fiber link output；Then the course ILS and glide path computing module receive the ADS-B signal of the optical fiber link output；And
It according to ADS-B signal, calculates closely into flight path data, and obtains closely into navigation channel DDM data；Final terminal display module according to
It is described to be closely respectively formed glide path figure and localizer figure into navigation channel DDM data and form three-dimensional flight track datagram.
Present invention composition:
One, the present invention includes ADS-B data reception module, the course ILS and glide path computing module and terminal display module.
1.ADS-B data reception module includes Anneta module, ADS-B receiver and optical fiber link transmission module；
Wherein, Anneta module is used to receive the ADS-B signal of aircraft；
ADS-B receiver is for acquiring ADS-B signal；
Optical fiber link transmission module is for the real-time number between ADS-B receiver and the course ILS and glide path computing module
According to transmission.
2. it includes data resolution module, record playback module, filter module that the course ILS and glide path, which calculate reason module,
Block, computing module and data memory module；The all modules that the course ILS and glide path calculate reason module, which pass through to have, to be calculated
It programs and realizes with the processor of data processing function.
Wherein, data resolution module, for reading the ADS-B data being transferred to by optical fiber link in real time and passing through record
The history ADS-B data of playback module playback, parse aircraft trace data (including: longitude and latitude, height and speed)；Specific solution
Analysis process is that (data format is " EUROCONTROL ASTERIX according to report name according to ADS-B data format
Categoy021 EUROCONTROL monitor the 12nd part of data exchange standard file: ADS-B object message transmission " format into
Row, parses aircraft trace data (including: longitude and latitude, height and speed)；
Filtering module, non-near in the flight path data for being exported to data resolution module into aircraft trace data and
False aircraft trace data are filtered, and are extracted closely into flight path data；Concrete methods of realizing: by judging flying height
Whether taper off trend simultaneously with flying speed, reject the flight path data of non-decreasing trend, only retains flying for the condition that meets
Row data are closely into flight path data；
Computing module, for according to closely into the calculating of flight path data closely into navigation channel DDM data；Closely into navigation channel DDM data
Including described closely into the corresponding localizer DDM value of deviation of flight path data and runway centerline and closely into flight path
Data and the corresponding glide path DDM value of the deviation of 3 ° of approach centerlines.
The data that record playback module is transmitted for recording ADS-B receiver in real time by optical fiber link, and can be at any time
Selection history ADS-B data, which carry out being played back to data resolution module, to be handled；
Data memory module, for storing history ADS-B data, history closely into flight path data and history closely into boat
Road DDM data；History includes closely history localizer DDM data and history glide path DDM data into navigation channel DDM data；Wherein go through
History ADS-B data are the data that the optical fiber link exported and passed through that record playback module is stored in data memory module；History
It is closely that the data of memory module are stored in after filtering module calculates into flight path data；History is closely meter into navigation channel DDM data
Calculate the data that memory module is stored in after module calculates.
Wherein, it is described closely into flight path data and runway centerline the corresponding localizer DDM value of deviation and closely into
Flight path data and the corresponding glide path DDM value of the deviation of 3 ° of approach centerlines.Specific calculating process is:
(1) calculate it is optimal closely into track: first receive seclected time period it is close into flight path data (assuming that having received N altogether
Data), then sort from small to large to all track points of this N flight path by height value, formed one it is new it is close into
Flight path data are filtered data using EKF (Extended Kalman filter) filter, obtain one it is optimal close
Into flight path data, and by every N-1 data point carry out data pick-up obtain it is final optimal closely into track data.
(2) it calculates closely into navigation channel DDM value: each data is calculated by the nearly latitude and longitude value into flight path after extracting
The bias angle theta of point and airfield runway center line, and the left side of regulation deviation from runway centerline is positive, the right is negative, and algorithm is realized such as
Under:
1) the equation L:y=kx+b of runway centerline is established, is reference with earth coordinates, k is for runway centerline and just
The tangent value of northern angle, deviation constant b=y0-kx0,(x0,y0) be course antenna latitude and longitude coordinates；
2) calculate closely into flight path point A (x, y) and runway centerline L distance d, and with course antenna distance r,
In
3) bias angle theta of track points and runway centerline is calculatedlocWith the bias angle theta with 3 ° of glissadesglid.If track points A is located at
The left side θ of runway centerlineloc=arcsin (d/r), otherwise θloc=-arcsin (d/r),Wherein h is height value of the aircraft at tracing point A.
4) localizer DDM value 7ocDDM=θ is calculatedloc*0.155/θ0.155, wherein θ0.155It is in runway threshold one side 105m
The DDM at place is 0.155 ± 20%, with the line at course antenna array center and the angle of runway centerline；
5) glide path DDM value DlidDDM=θ is calculatedglid*0.175*/0.7；
5) or 6) 6) based on calculating value, it is averaging, obtains corresponding to described closely into flight path data and runway centerline
The corresponding localizer mean value DDM of deviation and closely into the corresponding glide path of deviation of flight path data and 3 ° of approach centerlines
Mean value DDM.
3. terminal display module includes that 3 dimension display track modules show that flight path data, 2 dimension display localizer modules are aobvious
Show that localizer DDM data and average heading road DDM data, 2 dimension display glide path modules show glide path DDM data and comment
Valence glide path DDM data；
The 3 dimension display track module closely ties up perspective view into flight path 3 for showing in GIS map；Affiliated 2 dimension boat
It is used to show 2 dimension figures of localizer DDM data to road module；Affiliated 2 dimension glide path module is for showing glide path DDM data
2 dimension figures.
Two, specific embodiment:
Concrete operations process and the system Authentication method of a kind of ILS safe operation state verification appraisal procedure as shown in Figure 1,
Specific step is as follows:
(1) ADS-B data receiver: a Best Point is chosen near airports and places ADS-B receiving antenna, and is connected to
ADS-B receiver, the advantage of ADS-B receiver are that ADS-B receiver is only received from aircraft ADS-B data-signal, no
Signal is externally sent, therefore interference is not generated to the wireless communication signals of aircraft or airport, does not influence flight normal operation.
(2) ADS-B data are transmitted: the possible relative distance in position due to placing ADS-B receiver is distant, lead to
Optical fiber link transmission ADS-B data are crossed to enhance the real-time of data processing, and improve the correctness and safety of data.
(3) data ADS-B data record: are transferred to the course ILS and glide path by optical fiber link in ADS-B receiver
When computing module, system is stored in the ADS-B data record transmitted in storage equipment, in case subsequent playback and analysis make
With.
(4) ADS-B data readback: phase can be carried out to the ADS-B data of track record by the playback to historical data
Localizer road and glide path DDM value are filtered and are calculated in the parsing of pass.
(5) data parse: data item parsing is carried out to received data, it is corresponding to parse often referring to ADS-B format standard
One data item forms flight path data and transfers next processing module.
(6) data filtering: data filtering module be in order to extract aircraft closely into flight path data, discard non-near into shape
The flight path data of the target data of state, extraction calculate course and glidepath data for computing module and are directly used in three-dimensional
It closely shows, while is saved in storage equipment in case as history closely into track data into track state.
(7) course ILS and glide path calculate: the course ILS and glide path calculated result include localizer DDM, glide path
DDM, localizer mean value DDM and glide path mean value DDM, circular step are as shown in the figure.
Three, the present invention can also assist realizing real-time ILS reliability judgement.
Design process are as follows: closely into the horizontal flight information (latitude and longitude value) in landing path data and hung down by calculating aircraft
Row information (height value) corresponding localizer DDM and glide path DDM is flown nonstop to, the localizer DDM and history with history are respectively corresponded
Glide path DDM subtract each other and take absolute value, the corresponding absolute value of the bias δ found out with history localizer DDMlAnd history glide path DDM
Absolute value of the bias δgIf δl>UlAnd/or δg>Ug, then localizer DDM value and the corresponding track point of glide path DDM value at this time
It sets, as sign mutation position, if sign mutation position can reappear, can determine whether that ILS reliability goes wrong；Otherwise, judge
ILS reliability no problem at this time；δl>UlIndicate that aircraft horizontal direction at this position deviates closely into localizer, δg>Ug, indicate to fly
Vertical direction glide-slope deviation of the machine at this position；, wherein UlAnd UgRespectively navigation channel line maximum deflection amplitude and glissade
Maximum deflection amplitude, value are the boat of " air navigation radio aids part 1: instrument-landing-system (ILS) technical requirements "
Defined maximum deflection amplitude in road structure and structure of glide path.
The invention is not limited to specific embodiments above-mentioned.The present invention, which expands to, any in the present specification to be disclosed
New feature or any new combination, and disclose any new method or process the step of or any new combination.
Claims (9)
1. a kind of ILS is safely operated state verification device, characterized by comprising:
ADS-B data reception module is exported for receiving the ADS-B signal of aircraft, and by optical fiber link；
The course ILS and glide path computing module, for receiving the ADS-B signal of the optical fiber link output；And believed according to ADS-B
Number, it calculates closely into flight path data, and according to closely obtaining closely into flight path data into navigation channel DDM data；
Terminal display module, for being closely respectively formed glide path figure and course figure into navigation channel DDM data according to described.
2. verifying device according to claim 1, it is characterised in that the course ILS and glide path computing module include number
According to parsing module, filtering module, computing module, data memory module and record playback module；Wherein,
Data resolution module, for reading the ADS-B data being transferred to by optical fiber link in real time and by record playback module
The history ADS-B data of playback, parse aircraft trace data；
Filtering module, it is non-near into aircraft trace data and falseness in the flight path data for being exported to data resolution module
Aircraft trace data are filtered, and are extracted closely into flight path data；
Computing module, for according to closely into the calculating of flight path data closely into navigation channel DDM data；Closely include into navigation channel DDM data
It is described closely into the corresponding localizer DDM value of deviation of flight path data and runway centerline and closely into flight path data
And the corresponding glide path DDM value of the deviation of 3 ° of approach centerlines.
3. verifying device according to claim 2, it is characterised in that the course ILS and glide path computing module further include
Data memory module；Data memory module, for storing history ADS-B data, history closely into flight path data and history
Closely into navigation channel DDM data；History includes closely history localizer DDM data and history glide path DDM data into navigation channel DDM data；
Wherein history ADS-B data are the numbers that the optical fiber link exported and passed through that record playback module is stored in data memory module
According to；History is closely that the data of memory module are stored in after filtering module calculates into flight path data；History is closely into navigation channel DDM number
According to being to be stored in the data of memory module after computing module calculates.
4. verifying device according to claim 2, it is characterised in that the terminal display module forms glide path figure and boat
To figure be according to computing module export it is close into navigation channel DDM data and the history of data memory module closely into navigation channel DDM data shape
At localizer DDM data and average heading road DDM data, it is closely close with the history of data memory module into navigation channel DDM data
The glide path DDM data and average glide path DDM data formed into navigation channel DDM data, respectively correspond the glide path to form 2 dimensions
The course figure of figure and 2 dimensions.
5. according to claim 1 to verifying device described in one of 4, it is characterised in that the terminal display module further includes 3 dimensions
Flight path figure is shown；Wherein 3 dimension flight path figures are close the depositing into flight path data with data according to filtering module output
The history for storing up module storage closely calculates gained into flight path data.
6. verifying device according to claim 5, it is characterised in that the ADS-B data reception module includes that ADS-B connects
Receipts machine, ADS-B antenna；Wherein ADS-B receiver for receiving the ADS-B signal of aircraft by ADS-B antenna, and passes through light
Fine link output.
7. the ILS reliability judgment means based on claim 1,2,3,4 or the 6 verifying devices, it is characterised in that further include
Sign mutation detection module is guided, it is right respectively for being based on closely into localizer DDM value in the DDM data of navigation channel and glide path DDM value
It should subtract each other with the localizer DDM of history and the glide path DDM of history and take absolute value, correspondence finds out inclined with history localizer DDM
Poor absolute value δlAnd the absolute value of the bias δ of history glide path DDMgIf δl>UlAnd/or δg>Ug, then at this time localizer DDM value and
The corresponding tracing point position of glide path DDM value, as sign mutation position can determine whether ILS if sign mutation position can reappear
Reliability goes wrong；Otherwise, judge ILS reliability no problem at this time；Wherein, δl>UlIndicate aircraft level side at this position
To deviation closely into localizer, δg>Ug, indicate vertical direction glide-slope deviation of the aircraft at this position.
8. the verification method based on claim 1,2,3,4 or the 6 verifying devices, characterized by comprising:
ADS-B data reception module receives the ADS-B signal of aircraft, and is exported by optical fiber link；
The course ILS and glide path computing module receive the ADS-B signal of the optical fiber link output；And according to ADS-B signal, meter
It calculates closely into flight path data, and obtains closely into navigation channel DDM data；
Terminal display module is closely respectively formed glide path figure and course figure into navigation channel DDM data according to described.
9. the ILS reliability judgment method based on verification method described in claim 8, it is characterised in that further include:
Based on closely into localizer DDM value in the DDM data of navigation channel and glide path DDM value, respectively correspond with the localizer DDM of history and
The glide path DDM of history, which subtracts each other, to take absolute value, the corresponding absolute value of the bias δ found out with history localizer DDMlAnd history glides
The absolute value of the bias δ of road DDMgIf δl>UlAnd/or δg>Ug, then localizer DDM value and the corresponding track of glide path DDM value at this time
Point position, as sign mutation position can determine whether that ILS reliability goes wrong if sign mutation position can reappear；Otherwise,
Judge ILS reliability no problem at this time；Wherein, δl>UlIndicate that aircraft horizontal direction at this position deviates closely into localizer, δg>
Ug, indicate vertical direction glide-slope deviation of the aircraft at this position.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111477036A (en) * | 2020-04-08 | 2020-07-31 | 中国电子科技集团公司第二十八研究所 | Method for detecting aircraft height abnormity of air traffic control automation system |
| CN111824453A (en) * | 2020-06-08 | 2020-10-27 | 中国民用航空中南地区空中交通管理局 | Method and system for contrastively analyzing flight verification results of instrument landing system equipment |
| CN112230587A (en) * | 2020-10-29 | 2021-01-15 | 中国民用航空总局第二研究所 | Instrument landing system same-frequency different-call operation monitoring system and method |
| CN113205706A (en) * | 2021-04-22 | 2021-08-03 | 九州云(北京)科技发展有限公司 | ILS signal quality monitoring method based on flight QAR data |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4454496A (en) * | 1980-10-30 | 1984-06-12 | Mcdonald Douglas Corporation | Conformal head-up display |
| JP2003085699A (en) * | 2001-09-06 | 2003-03-20 | Electronic Navigation Research Institute | Glide path approach course prediction method for ils due to snowing and apparatus therefor |
| CN102426426A (en) * | 2011-12-15 | 2012-04-25 | 北京航空航天大学 | Aviation navigation signal simulation system applied to flight check |
| CN105116781A (en) * | 2014-03-27 | 2015-12-02 | 霍尼韦尔国际公司 | Independent instrument landing system monitor |
| CN106156467A (en) * | 2015-04-13 | 2016-11-23 | 上海宝信软件股份有限公司 | Lower whorl shelves time detecting method and system on aircraft based on ADSB |
| CN106546245A (en) * | 2016-10-30 | 2017-03-29 | 北京工业大学 | Aircraft trace based on ADS B datas is inferred and smoothing method |
| CN107421565A (en) * | 2017-07-25 | 2017-12-01 | 中国民航大学 | A kind of instrument-landing-system glissade check system based on unmanned plane |
-
2018
- 2018-04-11 CN CN201810321592.5A patent/CN109102720B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4454496A (en) * | 1980-10-30 | 1984-06-12 | Mcdonald Douglas Corporation | Conformal head-up display |
| JP2003085699A (en) * | 2001-09-06 | 2003-03-20 | Electronic Navigation Research Institute | Glide path approach course prediction method for ils due to snowing and apparatus therefor |
| CN102426426A (en) * | 2011-12-15 | 2012-04-25 | 北京航空航天大学 | Aviation navigation signal simulation system applied to flight check |
| CN105116781A (en) * | 2014-03-27 | 2015-12-02 | 霍尼韦尔国际公司 | Independent instrument landing system monitor |
| CN106156467A (en) * | 2015-04-13 | 2016-11-23 | 上海宝信软件股份有限公司 | Lower whorl shelves time detecting method and system on aircraft based on ADSB |
| CN106546245A (en) * | 2016-10-30 | 2017-03-29 | 北京工业大学 | Aircraft trace based on ADS B datas is inferred and smoothing method |
| CN107421565A (en) * | 2017-07-25 | 2017-12-01 | 中国民航大学 | A kind of instrument-landing-system glissade check system based on unmanned plane |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111477036A (en) * | 2020-04-08 | 2020-07-31 | 中国电子科技集团公司第二十八研究所 | Method for detecting aircraft height abnormity of air traffic control automation system |
| CN111477036B (en) * | 2020-04-08 | 2021-01-29 | 中国电子科技集团公司第二十八研究所 | Method for detecting aircraft height abnormity of air traffic control automation system |
| CN111824453A (en) * | 2020-06-08 | 2020-10-27 | 中国民用航空中南地区空中交通管理局 | Method and system for contrastively analyzing flight verification results of instrument landing system equipment |
| CN112230587A (en) * | 2020-10-29 | 2021-01-15 | 中国民用航空总局第二研究所 | Instrument landing system same-frequency different-call operation monitoring system and method |
| CN112230587B (en) * | 2020-10-29 | 2021-08-10 | 中国民用航空总局第二研究所 | Instrument landing system same-frequency different-call operation monitoring system and method |
| CN113205706A (en) * | 2021-04-22 | 2021-08-03 | 九州云(北京)科技发展有限公司 | ILS signal quality monitoring method based on flight QAR data |
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