CN106530838A - Aircraft flight path jump removing method - Google Patents
Aircraft flight path jump removing method Download PDFInfo
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- CN106530838A CN106530838A CN201610931969.XA CN201610931969A CN106530838A CN 106530838 A CN106530838 A CN 106530838A CN 201610931969 A CN201610931969 A CN 201610931969A CN 106530838 A CN106530838 A CN 106530838A
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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]
- G08G5/0004—Transmission of traffic-related information to or from an aircraft
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Abstract
The invention discloses an aircraft flight path jump removing method, which comprises the following steps: constructing a cubic polynomial fitting algorithm in corresponding type and at non-fixed time intervals, and calculating predicted values corresponding to altitude, angle, ground velocity and vertical velocity and storing the predicted values; when receiving latitude and longitude values, and if the number of latitude and longitude elements in a set within a time range 1 minute before the current time is smaller than 3, not carrying out calculating and quitting; or otherwise, comparing the longitude and latitude at the current time with longitude and latitude at a previous time point and longitude and latitude at a time point before the previous time point: calculating predicted distance and actual distance, and comparing the difference between the predicted distance and the actual distance and larger one of the predicted distance and the actual distance to obtain data credibility weight; and if the data credibility weight is smaller than 1, regarding the data as credibility data and storing the data. The method can solve the problem of longitude and latitude or height positioning jump, so that real-time positioning data is allowed to be more accurate, and the flight path of an aircraft is allowed to be displayed with smoother data.
Description
Technical field
The present invention relates to a kind of method that aircraft flight profiles saltus step is removed, belongs to aircraft flight profiles optimization method
Technical field.
Background technology
The problems such as along with constantly developing for China Aviation cause, spatial domain, flow, also constantly projects, flight delay,
Flow-control causes passenger, and complaints are heard everywhere.The appearance of this new techniques of ADS-B, automatically slave phase can close airborne equipment acquisition ginseng
Number to the information such as other aircrafts or earth station's broadcast position of aircraft, height, speed, course, identifier, so that controller is to flying
Machine monitoring state.
As ADS-B application popularization rates on aircraft increase, the feasible of position of aircraft monitoring is carried out by ADS-B
Property is also more and more stronger；But as ADS-B transmitting boundaries are limited, and clock is difficult to synchronous cause data between data receiver base station
Randomness, ADS-B issue data presence itself it is wrong the problems such as, the track of the ADS-B initial datas structure for causing to receive
There is saltus step, track disappearance.Based on the above-mentioned state of the art, it is necessary to which design provides what a kind of aircraft flight profiles saltus step was removed
Method, to solve the above problems, makes real time positioning data more accurate, and with the flight rail of smoother data exhibiting airborne vehicle
Mark.
The content of the invention
The present invention is exactly in view of the shortcomings of the prior art, there is provided the side that a kind of aircraft flight profiles saltus step is removed
Method, is solved the problems, such as to position longitude and latitude or height saltus step, makes real time positioning data more accurate, and navigated with smoother data exhibiting
The flight path of pocket.
For solving the above problems, the technical solution used in the present invention is as follows：
A kind of method that aircraft flight profiles saltus step is removed, comprises the following steps：
S1, receiving longitude and latitude, height above sea level, angle, ground velocity, vertical speedWhen, represented with t and connect
The timestamp of the data is received, by the set of metadata record to nearest three minute data of correspondenceIn；
S2, receivingDuring value, the on-fixed time interval of corresponding types is built
Cubic polynomial fitting algorithm operand；For entering row interpolation to each time interval of one-dimensional time series data,
So as to reach the purpose of data prediction in the short time；
S3, obtainCorresponding predictive value：
And willStored as actual value；
S4, receivingDuring value, ifIn number of elements before current time in the range of 1 minute be less than 3, then
Do not calculated and jumped out；Otherwise, by current time longitude and latitudeLongitude and latitude with a upper time point respectively, on
The longitude and latitude of a upper time pointCompare, comparison process is comprised the following steps：
S41, definition two functions B and K, wherein, B represents the earth spherical distance asked between two longitudes and latitudes, and K is represented and asked two
The earth spherical distance flown between airborne vehicle ground velocity：
S42, the actual range for obtaining current location and the first two position location according to the function B of definition：
S43, because the timestamp of velocity vector and position vector asynchronous, need to obtain current location time point (t3), front
Predetermined speed of two position time points (t1, t2)：
S44, the function K of foundation definition obtain the Prediction distance between two time points：
S45, set degree of error as, Prediction distance with the difference of actual range is, among Prediction distance and both actual ranges
The greater be, willWithEvaluation is compared, data reliability weight is drawn：
ObtainThe latitude and longitude value being as currently receivedCredibility, if<1, then willIt is regarded as trust data to enter
Row storage.
As the improvement of above-mentioned technical proposal, in step S45, degree of errorIt is set to 3.
Compared with prior art, the implementation result of the present invention is as follows for the present invention：
The method that a kind of aircraft flight profiles saltus step of the present invention is removed, is found by the observation to historical data：
, there is small probability, the prolonged situation to a fixed position saltus step on a large scale, the number in the longitude and latitude that ADS-B is issued
According to present it is regular, at interval of two anchor points to a fixed position hopping once；Based on above-mentioned saltus step rule, and according to
The rule of status values in longitude and latitude, height above sea level, angle, ground velocity, vertical speed is only issued every time according to ADS-B, and is calculated
The method that the aircraft flight profiles saltus step of the present invention is removed is obtained, the problem of positioning longitude and latitude or height saltus step is can solve the problem that,
Make real time positioning data more accurate, and with the flight path of smoother data exhibiting airborne vehicle.
Specific embodiment
Below in conjunction with specific embodiments illustrating present disclosure.
Through the observation to historical data, the longitude and latitude that ADS-B is issued, exist small probability, it is prolonged solid to one
The situation of fixed position saltus step on a large scale.
The data present it is regular, at interval of two anchor points to a fixed position hopping once, and due to
ADS-B only issues status values every time, a value such as in longitude and latitude, height above sea level, angle, ground velocity, vertical speed.
Based on above-mentioned rule and rule, the method that a kind of aircraft flight profiles saltus step that the present embodiment is provided is removed,
Including step in detail below：
1st, receiving longitude and latitude, height above sea level, angle, ground velocity, vertical speedWhen,
T represents the timestamp for receiving the data, by the set of metadata record to nearest three minute data of correspondenceIn.
ReceivingDuring value, build between the on-fixed time of corresponding types
Every cubic polynomial fitting algorithm operand；
For entering row interpolation to each time interval of one-dimensional time series data, so as to reach the prediction of data in the short time
Purpose.
3rd, obtainCorresponding predictive value：
And willStored as actual value.
4th, receivingDuring value, ifIn before current time in the range of 1 minute number of elements be less than 3, then do not enter
Row is calculated and is jumped out；
Otherwise, willRespectively withCompare, process is as follows：
（1）Two functions are defined,The earth spherical distance between two longitudes and latitudes is sought in expression,Two airborne vehicles are sought in expression
The earth spherical distance flown between ground velocity：
（2）Obtain the actual range of current location and the first two position location：
（3）Because velocity vector is with the timestamp of position vector and asynchronous, need to obtain current location time point (t3), front two
The predetermined speed of individual position time point (t1, t2)：
（4）Obtain the Prediction distance between two time points：
（5）If degree of error is, Prediction distance is compared with actual range, by the difference of two distances and Prediction distance with it is actual away from
The greater among the two is compared evaluation, draws data reliability weight：
Due to data longitude and latitude saltus step scope it is larger, generally more than hundred kilometers, and airline carriers of passengers flight speed 1 minute is general not
More than 60 kilometers, so can be byIt is set to higher value, it is to avoid incite somebody to action correct due to what the inexactness of velocity fitting prediction was brought
The problem that longitude and latitude degrees of data is excluded,It is traditionally arranged to be 3；
ObtainThe latitude and longitude value being as currently receivedCredibility, if<1, then willIt is regarded as trust data to enter
Row storage.
Above content is detailed description made for the present invention in conjunction with specific embodiments, it is impossible to assert that the present invention is only embodied as
It is limited to these explanations.For those skilled in the art, without departing from the inventive concept of the premise,
Some simple deduction or replace can also be made, the scope of protection of the invention should be all considered as belonging to.
Claims (2)
1. a kind of method that aircraft flight profiles saltus step is removed, is characterized in that, comprise the following steps：
S1, receiving longitude and latitude, height above sea level, angle, ground velocity, vertical speedWhen, reception is represented with t
The timestamp of the data, by the set of metadata record to nearest three minute data of correspondenceIn；
S2, receivingDuring value, the on-fixed time interval of corresponding types is built
Cubic polynomial fitting algorithm operand；For entering row interpolation to each time interval of one-dimensional time series data, so as to
Reach the purpose of data prediction in the short time；
S3, obtainCorresponding predictive value：
And willStored as actual value；
S4, receivingDuring value, ifIn number of elements before current time in the range of 1 minute be less than 3, then not
Calculated and jumped out；Otherwise, by current time longitude and latitudeLongitude and latitude with a upper time point respectively, upper one
The longitude and latitude of individual time pointCompare, comparison process is comprised the following steps：
S41, definition two functions B and K, wherein, B represents the earth spherical distance asked between two longitudes and latitudes, and K is represented and asked two
The earth spherical distance flown between airborne vehicle ground velocity：
S42, the actual range for obtaining current location and the first two position location according to the function B of definition：
S43, because the timestamp of velocity vector and position vector asynchronous, need to obtain current location time point (t3), front
Predetermined speed of two position time points (t1, t2)：
S44, the function K of foundation definition obtain the Prediction distance between two time points：
S45, set degree of error as, Prediction distance with the difference of actual range is, among Prediction distance and both actual ranges
The greater be, willWithEvaluation is compared, data reliability weight is drawn：
ObtainThe latitude and longitude value being as currently receivedCredibility, if<1, then willIt is regarded as trust data to enter
Row storage.
2. the method that a kind of aircraft flight profiles saltus step as claimed in claim 1 is removed, is characterized in that, in the step
In S45, degree of errorIt is set to 3.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN110017838A (en) * | 2019-02-13 | 2019-07-16 | 浩亚信息科技有限公司 | Schedule flight trajectory predictions method, equipment, medium and system |
| CN111968413A (en) * | 2020-08-26 | 2020-11-20 | 成都民航空管科技发展有限公司 | Flight plan synchronization method for regional control center and terminal area ATC system |
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| CN110017838A (en) * | 2019-02-13 | 2019-07-16 | 浩亚信息科技有限公司 | Schedule flight trajectory predictions method, equipment, medium and system |
| CN111968413A (en) * | 2020-08-26 | 2020-11-20 | 成都民航空管科技发展有限公司 | Flight plan synchronization method for regional control center and terminal area ATC system |
| CN111968413B (en) * | 2020-08-26 | 2021-09-24 | 成都民航空管科技发展有限公司 | Flight plan synchronization method for regional control center and terminal area ATC system |
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| CN106530838B (en) | 2019-04-09 |
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Address after: 230001 Anhui City, Hefei Province, No. 4 Suzhou Road, Xin building, room 3009 Applicant after: Flying friend Technology Co., Ltd. Address before: 230001 Anhui City, Hefei Province, No. 4 Suzhou Road, Xin building, room 3009 Applicant before: Hefei Feiyou Network Technology Co., Ltd. |
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Address after: Room 813, Kechuang building, 860 Wangjiang West Road, hi tech Zone, Hefei City, Anhui Province Patentee after: VARIFLIGHT TECHNOLOGY Co.,Ltd. Address before: 3009, room 4, Xin Xin building, No. 230001, Suzhou Road, Hefei, Anhui Patentee before: VARIFLIGHT TECHNOLOGY Co.,Ltd. |