CN110780292A - Airborne airplane bump detector and method thereof - Google Patents

Airborne airplane bump detector and method thereof Download PDF

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Publication number
CN110780292A
CN110780292A CN201911073804.3A CN201911073804A CN110780292A CN 110780292 A CN110780292 A CN 110780292A CN 201911073804 A CN201911073804 A CN 201911073804A CN 110780292 A CN110780292 A CN 110780292A
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information
airplane
bump
index
pitch
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林嘉希
王叶
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Nanjing University of Aeronautics and Astronautics
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/02—Systems using reflection of radio waves, e.g. primary radar systems; Analogous systems
    • G01S13/06—Systems determining position data of a target
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
    • G01S13/88—Radar or analogous systems specially adapted for specific applications
    • G01S13/95—Radar or analogous systems specially adapted for specific applications for meteorological use
    • G01S13/953—Radar or analogous systems specially adapted for specific applications for meteorological use mounted on aircraft
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
    • Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
    • Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • General Physics & Mathematics (AREA)
  • Electromagnetism (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar Systems Or Details Thereof (AREA)

Abstract

The invention discloses an airborne airplane bump detector which comprises a bump information receiving system, a bump data processing system and a bump early warning display system, wherein the bump information receiving system is connected with an airborne radar and is used for receiving real-time airplane position information, flight data and meteorological information detected by the airborne radar; the bumping data processing system receives the data provided by the information receiving system and calculates the obtained regional bumping intensity information; the pitch early warning display system compares the airplane position information with the intensity information and sends out a forecast through the early warning system; the method adopts real-time data measured by the meteorological radar and a more accurate dutton index to predict, and the obtained result has higher reliability. The airborne wind shear alarm improves the capability of the airplane for forecasting the jolt, reduces the time required by a ground controller for forecasting the pilot, and has wide application prospect.

Description

Airborne airplane bump detector and method thereof
Technical Field
The invention relates to the technical field of airplane safety, in particular to an airborne airplane bump detector and a method thereof.
Background
Aircraft jounce is the result of an aircraft encountering turbulence. When the airplane generates left-right shaking, pitching, up-down throwing and local shaking under the local uniform aerodynamic impact after the airflow is disturbed, the airplane is difficult to operate, and the instrument is inaccurate. When the airplane encounters extremely strong jolt, each part of the airplane may deform or be damaged due to large load change, and the airplane can be disassembled in severe cases, so that a major safety accident occurs.
The cause of pitch has been studied a lot since the last 50 s. Since then, methods of diagnosing and prognosing thrashing are continually developed and improved. The development of a small and medium-scale numerical prediction mode with higher space-time resolution enables objective and quantitative diagnosis and prediction to be possible. At present, the main means for forecasting the turbulence is to utilize a numerical model product and adopt a corresponding turbulence forecasting index to diagnose and forecast the turbulence, so as to reflect the turbulence intensity and enable a pilot to react and make adjustments as soon as possible.
Disclosure of Invention
The invention aims to provide an airborne airplane bump detector and a method thereof, which solve the problem that the prediction of a fixed route by only adopting historical data in a bump occurrence area through airplane report statistics can not be carried out in time when an airplane enters a bump multi-occurrence area to send out early warning. The invention adopts the Dutton bump index with better forecasting effect to calculate the bump index of the airplane in the flying process at every moment and give real-time early warning.
In order to achieve the purpose, the invention adopts the following technical scheme:
an airborne airplane bump detector comprises a bump information receiving system, a bump data processing system and a bump early warning display system,
the bumping information receiving system is connected with the airborne radar and is used for receiving real-time airplane position information, flight data and meteorological information detected by the airborne radar;
the bumping data processing system receives the data provided by the information receiving system and calculates the obtained regional bumping intensity information;
and the pitch early warning display system compares the airplane position information with the intensity information and sends out a forecast through the early warning system.
Furthermore, the bumpy information receiving system stores the received data information in the cloud in real time so that the bumpy data processing system can extract the data information and update the information of the bumpy area at any time.
An airborne aircraft bump detection method comprising the steps of:
s1, the pitching information receiving system receives real-time airplane position information, flight data and meteorological information detected by the airborne radar;
s2, calculating the bumping intensity of the area at the moment by using a dutton index through the bumping data processing system according to the received meteorological information;
and S3, comparing the position information of the airplane with the position information of the pitch index area obtained in the step S2, and when the airplane enters the predicted pitch area, the pitch early warning display system carries out corresponding pitch intensity prediction.
Further, the position information includes longitude x, latitude y and height h; the flight data comprises information such as airplane model, flight time, flight path and the like; the meteorological information includes radial wind u and latitudinal wind v.
Further, the airborne radar is an airborne radar located at the nose, and the detected weather information is weather information within a certain distance in front of the airplane.
Further, in step S2, the received weather information uses a dutton index to calculate and output a thrashing index, and the specific steps include:
s21, calculating horizontal wind shear S H：
Figure BDA0002261758310000021
Horizontal wind shear is used to measure the variation of wind speed over a horizontal range,
wherein the content of the first and second substances,
Figure BDA0002261758310000022
for the variation of the weftwise wind in the longitudinal direction,
Figure BDA0002261758310000023
the variation condition of the warp wind along the latitude direction;
s22, calculating the verticalityShear of direct wind S v：
Figure BDA0002261758310000024
Vertical wind shear is used to measure the variation of wind speed with altitude,
the method comprises the following steps that du and dv are change values of wind fields on adjacent altitude layers, and delta h is a potential difference between the altitude h where an airplane is located and the adjacent altitude layers;
s23, calculating a dutton bump index:
the Dutton toss index E is an empirical index obtained from nonlinear regression analysis of turbulence reports and turbulence indices for various weather scales, and is expressed as:
E＝1.25×S H+0.25×S v 2+10.5
wherein 10.5 is an empirical constant;
s24, determining the bump strength according to the bump index:
a slightly turbulent or bumpless condition when the value of the Dutton bump index is less than 30; moderate jounce when the value of the Dutton jounce index is less than 35 and greater than 30; severe jounce when the value of the Dutton jounce index is 35 or higher; severe jounce is observed when the value of the Dutton jounce index is equal to or greater than 40.
Furthermore, when the area where the airplane enters has heavy turbulence, the turbulence is displayed on the display screen and forecasts the area to the pilot, when the area where the airplane enters has moderate turbulence, only the turbulence is displayed on the display screen, and when the area where the airplane enters has a light turbulence or no turbulence state, the turbulence is not required to be displayed or forecasted.
Furthermore, the bumpy information receiving system stores the received data information in the cloud in real time so that the bumpy data processing system can extract the data information and update the information of the bumpy area at any time.
Compared with the prior art, the invention has the following beneficial effects:
the method adopts real-time data measured by the meteorological radar and a more accurate dutton index to predict, and the obtained result has higher reliability. The airborne wind shear alarm improves the capability of the airplane for forecasting the jolt, reduces the time required by a ground controller for forecasting the pilot, and has wide application prospect.
Drawings
FIG. 1 is a flow chart of the operation of the present invention;
FIG. 2 is the distribution diagram of the mean wind field doutton index per 200hPa day in the China region (100-150E, 15-60N) in example 1.
Detailed Description
The invention is described in detail below with reference to the drawings and the detailed description, which are given by way of example only for the purpose of illustrating the invention and are not meant to limit the scope of the invention.
In the invention, the civil airborne weather radar generally refers to an airborne radar for measuring cloud, rain, wind and other weather elements in the atmosphere by means of a radio remote sensing technology, and because the area where an airplane is about to enter needs to be predicted, the data to be received mainly comes from the data measured by the weather radar positioned at the nose.
The principle of the invention is as follows: turbulence generated by horizontal wind shear and vertical wind shear in high altitude is an important factor for causing high altitude flight bump, so that the Dutton empirical index which simultaneously considers the horizontal wind shear and the vertical wind shear is selected, and the high altitude flight bump has good indication capability.
Example 1
The airborne airplane bump detector comprises a bump information receiving system, a bump data processing system and a bump early warning display system, wherein the bump information receiving system is connected with an airborne radar and is used for receiving real-time airplane position information, flight data and meteorological information detected by the airborne radar; preferably, the bumping information receiving system stores the received data information in a cloud end in real time so that the bumping data processing system can extract the data information and update information of a bumping area at any time; the bumping data processing system receives the data provided by the information receiving system and calculates the obtained regional bumping intensity information; and the pitch early warning display system compares the airplane position information with the intensity information and sends out a forecast through the early warning system.
Example 2
An airborne aircraft bump detection method comprising the steps of:
s1, the pitch information receiving system receives real-time airplane position information (longitude x, latitude y and height h), flight data (airplane model, flight time and flight path) and meteorological information (radial wind u and latitudinal wind v) detected by an airborne radar; further, the airborne radar is an airborne radar located at the nose, and the detected weather information is weather information within a certain distance in front of the airplane.
S2, calculating the bumping intensity of the area at the moment by using a dutton index through the bumping data processing system according to the received meteorological information;
the method comprises the following specific steps:
s21, calculating horizontal wind shear S H：
Figure BDA0002261758310000041
Horizontal wind shear is used to measure the variation of wind speed over a horizontal range,
wherein the content of the first and second substances,
Figure BDA0002261758310000042
for the variation of the weftwise wind in the longitudinal direction,
Figure BDA0002261758310000043
the variation condition of the warp wind along the latitude direction;
s22, calculating vertical wind shear S v：
Figure BDA0002261758310000044
Vertical wind shear is used to measure the variation of wind speed with altitude,
the method comprises the following steps that du and dv are change values of wind fields on adjacent altitude layers, and delta h is a potential difference between the altitude h where an airplane is located and the adjacent altitude layers;
s23, calculating a dutton bump index:
the Dutton toss index E is an empirical index obtained from nonlinear regression analysis of turbulence reports and turbulence indices for various weather scales, and is expressed as:
E＝1.25×S H+0.25×S v 2+10.5
wherein 10.5 is an empirical constant;
s24, determining the bump strength according to the bump index:
severe turbulence when the value of the Dutton jounce index is equal to or greater than 35; moderate jounce when the value of the Dutton jounce index is less than 35 and greater than 30; a slightly turbulent or bumpless condition when the value of the Dutton bump index is less than 30;
s3, comparing the position information of the airplane with the position information of the pitch index area obtained in the step S2, and when the airplane enters the predicted pitch area, the pitch early warning display system carries out corresponding pitch intensity prediction;
specifically, when the area entered by the airplane has heavy turbulence, the turbulence is displayed on the display screen and forecasts to the pilot, when the area entered by the airplane has moderate turbulence, the turbulence is only displayed on the display screen, and when the area entered by the airplane has a light turbulence or no-turbulence state, the turbulence is not required to be displayed or forecasted.
Example 3
According to the daily average wind field data of 200hPa height layers in China regions (100-150 degrees E, 15-60 degrees N) measured by an airborne radar, a daily bumpiness index distribution diagram is drawn and is shown in figure 2, and when an aircraft enters the regions, a detector can give out corresponding warning.
As shown in fig. 2, point a is measured at 115 ° east longitude and 40 ° north latitude 200hpa high altitude, radial wind is 34.9 meters per second, and latitudinal wind is 10.45 meters per second, i.e., x equals 115, y equals 40, u equals 34.9, and v equals 10.45. Calculating to obtain horizontal wind shear Vertical wind cutting
Figure BDA0002261758310000052
Then, E is 1.25 XS H+0.25×S v 2+10.5 ═ 55.585. Values greater than 40 are attributed to severe jolts。
In the same way, the point B is measured at 200hpa high altitude with east longitude 120 ° and north latitude 50.25 °, radial wind is 66.32 m/s, and latitudinal wind is 14.33 m/s, i.e. x is 120, y is 50.25, u is 66.32, and v is 14.33. Calculating to obtain horizontal wind shear S H33.039, vertical wind shear becomes S v＝8.995e -4Then, E — 33.039 is calculated. Values above 30 and below 35 are moderate jounces.
The above description is only of the preferred embodiments of the present invention, and it should be noted that: it will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the principles of the invention and these are intended to be within the scope of the invention.

Claims (7)

1. An airborne airplane bump detector is characterized by comprising a bump information receiving system, a bump data processing system and a bump early warning display system,
the bumping information receiving system is connected with the airborne radar and is used for receiving real-time airplane position information, flight data and meteorological information detected by the airborne radar;
the bumping data processing system receives the data provided by the information receiving system and calculates the obtained regional bumping intensity information;
and the pitch early warning display system compares the airplane position information with the intensity information and sends out a forecast through the early warning system.
2. The airborne aircraft pitch finder of claim, wherein the pitch information receiving system stores the received data information in real time in the cloud so that the pitch data processing system can extract the data information and update the pitch area information at any time.
3. An airborne aircraft bump detection method is characterized by comprising the following steps:
s1, the pitching information receiving system receives real-time airplane position information, flight data and meteorological information detected by the airborne radar;
s2, calculating the bumping intensity of the area at the moment by using a dutton index through the bumping data processing system according to the received meteorological information;
and S3, comparing the position information of the airplane with the position information of the pitch index area obtained in the step S2, and when the airplane enters the predicted pitch area, the pitch early warning display system carries out corresponding pitch intensity prediction.
The position information comprises longitude x, latitude y and height h; the flight data comprises information such as airplane model, flight time, flight path and the like; the meteorological information includes radial wind u and latitudinal wind v.
4. The method of claim 3, wherein the airborne radar is an airborne radar located at the nose, and the detected weather information is weather information within a certain distance in front of the aircraft.
5. The method for detecting airborne aircraft pitch according to claim 3, wherein in step S2, the received meteorological information uses a dutton index to calculate and output a pitch index, and the specific steps include:
s21, calculating horizontal wind shear S H：
Figure FDA0002261758300000011
Horizontal wind shear is used to measure the variation of wind speed over a horizontal range,
wherein the content of the first and second substances,
Figure FDA0002261758300000012
for the variation of the weftwise wind in the longitudinal direction,
Figure FDA0002261758300000013
the variation condition of the warp wind along the latitude direction;
s22, calculating vertical wind shear S v：
Figure FDA0002261758300000014
Vertical wind shear is used to measure the variation of wind speed with altitude,
the method comprises the following steps that du and dv are change values of wind fields on adjacent altitude layers, and delta h is a potential difference between the altitude h where an airplane is located and the adjacent altitude layers;
s23, calculating a dutton bump index:
the Dutton toss index E is an empirical index obtained from nonlinear regression analysis of turbulence reports and turbulence indices for various weather scales, and is expressed as:
E＝1.25×S H+0.25×S v 2+10.5
wherein 10.5 is an empirical constant;
s24, determining the bump strength according to the bump index:
a slightly turbulent or bumpless condition when the value of the Dutton bump index is less than 30; moderate jounce when the value of the Dutton jounce index is less than 35 and greater than 30; severe jounce when the value of the Dutton jounce index is 35 or higher; severe jounce is observed when the value of the Dutton jounce index is equal to or greater than 40.
6. The method as claimed in claim 3, wherein when the area entered by the airplane has a heavy turbulence, it is displayed on the display screen and forecasted to the pilot, when the area entered by the airplane has a medium turbulence, it is only displayed on the display screen, and when the area entered by the airplane has a light turbulence or no turbulence, it is not necessary to display or forecast.
7. The method as claimed in claim 6, wherein the pitch information receiving system stores the received data information in real time in the cloud so that the pitch data processing system can extract the data information and update the pitch area information at any time.
CN201911073804.3A 2019-11-06 2019-11-06 Airborne airplane bump detector and method thereof Pending CN110780292A (en)

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Application publication date: 20200211