CN104730523A - Method for showing topographic information based on weather radar - Google Patents
Method for showing topographic information based on weather radar Download PDFInfo
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- CN104730523A CN104730523A CN201510095963.9A CN201510095963A CN104730523A CN 104730523 A CN104730523 A CN 104730523A CN 201510095963 A CN201510095963 A CN 201510095963A CN 104730523 A CN104730523 A CN 104730523A
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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
- G01S13/93—Radar or analogous systems specially adapted for specific applications for anti-collision purposes
- G01S13/933—Radar or analogous systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft
- G01S13/935—Radar or analogous systems specially adapted for specific applications for anti-collision purposes of aircraft or spacecraft for terrain-avoidance
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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
- G01S13/95—Radar or analogous systems specially adapted for specific applications for meteorological use
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- 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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- Radar, Positioning & Navigation (AREA)
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- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention relates to a method for showing topographic information based on a weather radar. The method comprises the following steps firstly, a pitching angle a of an airplane during the flight is obtained; secondly, a positive pitching angle redundancy b and a negative pitching angle redundancy c are set; thirdly, a scanning angle range which is bigger or equal to -a-c and smaller or equal to -a+b is selected in the pitching direction, the scanning angle range in the horizontal direction ranges from +90 degrees to -90 degrees, and therefore a space scanning area is formed; fourthly, scanning is carried out on the space scanning area by the radar, integration is carried out on topographic data, in closest distance to the airplane, of back wave information, superposition is carried out on topographic edge lines which are in closest distance to the airplane, and a topographic contour line which is used as a safe boundary for the airplane flight is formed. According to the method, a topographic warning line is showed, and under the conditions that the airplane is in a remote mountain area, position information is lost, and a topographic database is unusable, the necessary and threatening topographic information is provided.
Description
Technical field
The present invention relates to by the method for aircraft weather radar to topographic data processing and display, particularly relate to the method being obtained risk altitude terrain information by weather radar data for communication.
Background technology
At present, use weather radar to carry out the weather information of hazard recognition in civil aviation, meanwhile, weather radar possesses the pattern of landform detection.In practice, when weather radar is operated in Meteorological Models, usually can carries out landform clutter recognition, and terrain information is filtered out completely; And when weather radar is operated under topomap mode of operation, terrain information roughly can only demonstrate the distribution of landform, and the terrain information having threat can not be identified.
For the gound-mapping information that weather radar provides, as a reference, can not can only originate as the authentic communication of hazard recognition landform at present.And in fact, in the terrain information that weather radar obtains, be include judgement to threaten the information of landform, but be not fully utilized always.
Summary of the invention
The object of the invention is to propose the method based on weather radar display terrain information, by making full use of the data that weather radar obtains, identify the terrain information of threat, and shown by display system, strengthen the safety coefficient that aircraft prevents to collide, and strengthen the trust of pilot to aircraft.
For this reason, according to an aspect of the present invention, a kind of method based on weather radar display terrain information is provided, comprises the steps:
A () obtains the angle of pitch a of aloft aircraft;
B () arranges positive angle of pitch redundancy b, negative angle of pitch redundancy c;
C () chooses scan angle scope in pitch orientation for being more than or equal to-a-c and being less than or equal to-a+b, the scan angle scope on in-plane is between ± 90 degree, thus forms a spacescan region;
D () utilizes radar to scan described spacescan region, for the scan angle in each pitch orientation chosen, launch within the scope of the scan angle of in the in-plane direction ± 90 degree and receive echo, obtain distance corresponding to each scan angle planar closest to the terrain information of aircraft, and project in surface level, obtain the landform edge line corresponding to the scan angle in this pitch orientation, the landform edge line of the scan angle in different pitch orientation is superposed, the terrain profile Yan Hangkongqisudushiliangqianchuimian line near aircraft formed, as the secure border of aircraft flight.
According to a further aspect in the invention, a kind of method based on weather radar display terrain information is provided, comprises the steps:
A () uses height sensor, record the height H of aloft aircraft in space;
B (), with the surface level of aircraft place flying height H for benchmark, arrange upwards high redundancy H1, downwards high redundancy H2, the scan angle scope on in-plane is between ± 90 degree, thus forms a spacescan region;
C () chooses the terrain return data of weather radar at various height on H, obtain distance planar closest to the terrain information of aircraft, and project in surface level, obtain the landform edge line corresponding to this height, landform edge line corresponding to differing heights is superposed, form terrain profile Yan Hangkongqisudushiliangqianchuimian line, as the secure border of aircraft flight.According to any one or more in above-mentioned aspect, the present invention can comprise any one or more following preferred forms further.
In some preferred form, the method based on weather radar display terrain information according to the present invention also comprises the steps:
A distance redundancy X based on aircraft horizontal level is set, new terrain profile Yan Hangkongqisudushiliangqianchuimian line is drawn towards aircraft direction from described terrain profile Yan Hangkongqisudushiliangqianchuimian line, every bit on described new terrain profile Yan Hangkongqisudushiliangqianchuimian line is all X apart from the minimum distance of described terrain profile Yan Hangkongqisudushiliangqianchuimian line, using terrain profile Yan Hangkongqisudushiliangqianchuimian line new described in this as the secure border of aircraft flight.
In some preferred form, smooth curve matching is carried out to described terrain profile Yan Hangkongqisudushiliangqianchuimian line, and the smooth curve obtained after matching is as new terrain profile Yan Hangkongqisudushiliangqianchuimian line.The curve obtained thus can remove the rough burr of old terrain profile Yan Hangkongqisudushiliangqianchuimian line, thus makes new terrain profile Yan Hangkongqisudushiliangqianchuimian linear light sliding, more meets visual experience.More preferably, described smooth curve matching adopts fitting of a polynomial, and the smooth curve obtained is the curve of polynomial expression.Smooth curve due to polynomial expression has much good mathematical property, and such as arbitrary order derivative all exists, therefore smooth curve is taken as polynomial expression curve can advantageously in computer program for the calculating of curve and process.
In some preferred form, described distance redundancy X is set as that is determined a numerical value.This determines that numerical value directly can be selected according to flying experience in the past, also can give one artificially and determine numerical value.When required secure border is wider, then give the numerical value of a larger distance redundancy X artificially, when required secure border is narrower, then give the numerical value of a less distance redundancy X artificially.
In some preferred form, described distance redundancy X sets based on aircraft horizontal position error and unit response time.Reasonably can determine the concrete numerical value of distance redundancy X thus.
In some preferred form, described positive angle of pitch redundancy b and/or described negative angle of pitch redundancy c is that the precision of facing upward precision and/or the radar detection height of bowing according to landform high redundancy, radar is determined.Value like this, is conducive to the scanning of saving aircraft, process and storage resources, ensures that aircraft has the open degree of the angle of pitch that realistic flight needs simultaneously.More preferably, described positive angle of pitch redundancy b is taken as 0.01 degree, and described negative angle of pitch redundancy c is taken as 0.01 degree.When lacking more data information, directly can choose the numerical value that described positive angle of pitch redundancy b and described negative angle of pitch redundancy c is taken as 0.01 degree, ensureing the open degree of the angle of pitch that safer flight needs.
In some preferred form, terrain profile Yan Hangkongqisudushiliangqianchuimian line can show separately, also can show with meteorological layer information superposition.The display mode of landform outline line can be selected thus neatly.
In some preferred form, upwards high redundancy H1 or downward high redundancy H2 sets based on the height error of GPS height error, radio altitude error, atmosphere data.Reasonably can determine the concrete numerical value of upwards high redundancy H1 or downward high redundancy H2 thus.
The Advantageous Effects that can obtain based on the method for weather radar display terrain information according to the present invention at least comprises: (1) demonstrates the secure border of landform warning line as aircraft flight by the data that weather radar obtains, at aircraft in remote mountain area and when losing positional information in the disabled situation of topographic database, the necessary terrain information having threat can be provided; (2) do not have chlamydate region at topographic database, in the disabled situation of terrain information of topographic database, the landform warning line now provided by weather radar can provide real-time terrain data; (3) terrain information of weather radar scanning compares topographic database mesorelief information, and real-time is better, and the landform for flip-flop has better adaptability; (4) supplementing as TAWS (Terrain awareness and warning system: landform hint and caveat system), can strengthen the trust of pilot to aircraft.
In the technical scheme improved, distance redundancy X also can make new terrain profile Yan Hangkongqisudushiliangqianchuimian line compare original terrain profile Yan Hangkongqisudushiliangqianchuimian line, more near aircraft side and away from landform side, thus provide the higher landform warning line of safety coefficient as the new secure border of aircraft flight for aircraft flight, make aircraft flight safer.
Accompanying drawing explanation
Fig. 1 is the basic principle schematic according to the method based on weather radar display terrain information of the present invention;
Fig. 2 a to Fig. 2 b is that wherein Fig. 2 a mesorelief outline line shows separately, and Fig. 2 b mesorelief outline line and meteorological layer information superposition show according to the terrain profile Yan Hangkongqisudushiliangqianchuimian line schematic diagram on a display screen obtained based on the method for weather radar display terrain information of the present invention.
Embodiment
In order to illustrate better according to the method based on weather radar display terrain information of the present invention, be described in detail below in conjunction with accompanying drawing.
In the first embodiment of the present invention, in horizontal projection as shown in Figure 1, aircraft smooth flight is at certain altitude, and numeral 1 is the position in-flight of aircraft, and numeral 1 ' is aircraft flight direction.Utilize aspect sensor, obtain aircraft angle of pitch a now, such as adopt inertial navigation or boat appearance to obtain the angle of pitch a of aircraft.Subsequently, aircraft needs to scan its front space with certain pitching scan angle Tilt with airborne weather radar.In order to obtain the terrain information near aircraft altitude, needing weather radar to launch radar wave to horizontal direction, considering the width of wave beam and the precision of actual radar detection Terrain Elevation, unnecessary warning line may be caused to produce; In addition, consider the height error that the radian of the earth produces, the warning line that produce may be caused to lose.Suitable positive luffing angle redundancy b and negative luffing angle redundancy c is now set, determine the variation range of scan angle Tilt, scan angle scope in pitch orientation is for being more than or equal to-a-c (being less than zero) and being less than or equal to-a+b (being greater than zero), not shown in FIG., scan angle scope in horizontal direction is between ± 90 degree, thus forms a spacescan region.Described positive angle of pitch redundancy b and/or described negative angle of pitch redundancy c is that the precision of facing upward precision and/or the radar detection height of bowing according to landform high redundancy, radar is determined.Especially, when aircraft smooth flight, positive luffing angle redundancy b can be taken as 0.01 degree, and negative luffing angle redundancy c can be taken as 0.01 degree.Now, more specifically, when front needs the horizontal range of scanning to be more than or equal to 80 km, then the vertical range of positive luffing angle redundancy is 14 meters (=80000 × sin (0.01)), and the vertical range of negative luffing angle redundancy is (-14) rice.Certainly, in actual applications, the value of positive luffing angle redundancy b and negative luffing angle redundancy c all can change as required, such as positive luffing angle redundancy b can be taken as 10 degree, 5 degree, 2 degree, 1 degree, 0.5 degree, 0.2 degree, 0.1 degree, 0.05 degree, 0.02 degree, 0.01 degree, 0.005 degree, 0.001 degree etc., negative luffing angle redundancy c can be taken as 10 degree, 5 degree, 2 degree, 1 degree, 0.5 degree, 0.2 degree, 0.1 degree, 0.05 degree, 0.02 degree, 0.01 degree, 0.005 degree, 0.001 degree etc., the value of these positive/negative luffing angle redundancies all falls into protection scope of the present invention.More specifically, lift an example again, 0.05 degree can be taken as when choosing positive luffing angle redundancy b, when negative luffing angle redundancy c can be taken as 0.05 degree, when front needs the horizontal range of scanning to be more than or equal to 80 km, then the vertical range of positive luffing angle redundancy is 69.8 meters (=80000 × sin (0.05)), and the vertical range of negative luffing angle redundancy is (-69.8) rice.The computing method of the positive/negative luffing angle vertical range of other positive/negative luffing angle redundancies are identical.
Weather radar scans in above-mentioned pitch orientation and horizontal direction.When pitching scan angle is taken as 0 degree, scan angle scope in horizontal direction is between ± 90 degree, launch and receive echo, obtain distance corresponding to 0 degree of pitching scan angle planar closest to the terrain information of aircraft, and project in surface level, now projection obtains the landform edge line in front is broken line EAB, (broken line EAB is herein made up of straight-line segment EA and AB, to schematically show the inventive method easily, in practice, landform edge line is irregular curve).Similarly, angle is determined every one, it is such as 0.01 degree for positive/negative luffing angle redundancy, then can choose 0.0001 degree, 0.0002 degree, 0.0005 degree, 0.001 degree, determine that (angle cited by these is an example to angle for one in 0.002 degree or 0.005 degree etc., this determines that angle also can be other angles less than 0.01), can progressively increase or reduce this and determine that the pitching scan angle Tilt in the p-a-c of angle to-a+b carries out a flat scanning, scan angle scope in horizontal direction is between ± 90 degree, launch and receive echo, obtain distance corresponding to pitching scan angle Tilt planar closest to the terrain information of aircraft, and project in surface level, thus obtain landform edge line corresponding to this pitching scan angle Tilt.After the pitching scan angle Tilt of the scope of the p-a-c to-a+b of weather radar of aircraft is scanned, the landform edge line of the scan angle in different pitch orientation can be superposed, the terrain profile Yan Hangkongqisudushiliangqianchuimian line near aircraft formed, can as the secure border of aircraft flight.More preferably, smooth curve matching can be carried out to described terrain profile Yan Hangkongqisudushiliangqianchuimian line, such as use polynomial expression to carry out matching to curve, and the smooth curve obtained after matching be as new terrain profile Yan Hangkongqisudushiliangqianchuimian line, thus there is better visual experience.Now integrating the front terrain profile Yan Hangkongqisudushiliangqianchuimian line obtained is broken line MFG (broken line MFG is herein made up of straight-line segment MF and FG, is to schematically show the inventive method easily, and in practice, terrain profile Yan Hangkongqisudushiliangqianchuimian line is irregular curve).In three dimensions, in fact this terrain profile Yan Hangkongqisudushiliangqianchuimian line is exactly the edge line by aircraft side on topographic projection figure in this altitude range.
More preferably, a distance redundancy X based on aircraft horizontal level can be set, new terrain profile Yan Hangkongqisudushiliangqianchuimian line is drawn towards aircraft direction from aforesaid terrain profile Yan Hangkongqisudushiliangqianchuimian line (i.e. broken line MFG), new terrain profile Yan Hangkongqisudushiliangqianchuimian line (i.e. broken line TUV, broken line TUV is herein made up of straight-line segment TU and UV, to schematically show the inventive method easily, in practice, terrain profile Yan Hangkongqisudushiliangqianchuimian line is irregular curve) on every bit be all X apart from the minimum distance of aforementioned terrain profile Yan Hangkongqisudushiliangqianchuimian line, using this new terrain profile Yan Hangkongqisudushiliangqianchuimian line as the secure border of aircraft flight.Distance redundancy X makes new terrain profile Yan Hangkongqisudushiliangqianchuimian line compare original formline, more near aircraft side and away from landform side, thus provide the higher landform warning line of safety coefficient as the new secure border of aircraft flight for aircraft flight, make aircraft flight safer.Specifically, the distance redundancy of terrain profile Yan Hangkongqisudushiliangqianchuimian line is a redundancy based on the unit response time, can by assessing practical response time to the test of airline operation person, and obtaining a response distance by the speed of this response time and aircraft, distance redundancy X can meet the requirement of unit reaction distance.In practice, distance redundancy X can be set as that is determined a numerical value.This determines that numerical value directly can be selected according to flying experience in the past, also can give one artificially and determine numerical value.When required secure border is wider, then give the numerical value of a larger distance redundancy X artificially, when required secure border is narrower, then give the numerical value of a less distance redundancy X artificially.
More preferably, as shown in Figure 2 a, the terrain profile Yan Hangkongqisudushiliangqianchuimian line 2 in display screen 4 can show separately, also can with meteorological map data mining platform 3 Overlapping display, as shown in Figure 2 b.The display mode of landform outline line can be selected thus neatly.
In the second embodiment of the present invention, in horizontal projection as shown in Figure 1, aircraft smooth flight is at certain altitude, and numeral 1 is the position in-flight of aircraft, and numeral 1 ' is aircraft flight direction.Aircraft utilization height sensor, records the height H of aloft aircraft in space.Upwards high redundancy H1 or downwards high redundancy H2 set based on the height error of GPS height error, radio altitude error, atmosphere data, by setting upwards high redundancy H1 or the high redundancy H2 impact that can effectively avoid the precision problem caused due to error to produce downwards.The span of the height A ltitude obtained thus is: H-H2 < Altitude < H+H1.
Choose the terrain return data of weather radar at various height on Altitude, obtain distance planar closest to the terrain information of aircraft, and project in surface level, the landform edge line obtained corresponding to this height is broken line EAB.Similarly, height spacing is determined every one, one of such as choosing in 1 meter, 2 meters, 5 meters, 10 meters, 20 meters or 50 meters etc. determines height spacing, can progressively increase or reduce this and determine that height spacing is to the terrain return data on the height A ltitude in H-H2 to H+H1, and project in surface level, and obtain landform edge line corresponding to this height A ltitude.After the height A ltitude of weather radar to the scope of H-H2 to H+H1 of aircraft chooses, the landform edge line corresponding to differing heights is superposed, form terrain profile Yan Hangkongqisudushiliangqianchuimian line, as the secure border of aircraft flight.
Especially, upwards high redundancy H1 or downward high redundancy H2 can be taken as 30 meters or 100 feet.
More preferably, smooth curve matching can be carried out to described terrain profile Yan Hangkongqisudushiliangqianchuimian line, such as use polynomial expression to carry out matching to curve, and the smooth curve obtained after matching be as new terrain profile Yan Hangkongqisudushiliangqianchuimian line, thus there is better visual experience.Now integrating the front terrain profile Yan Hangkongqisudushiliangqianchuimian line obtained is broken line MFG (broken line MFG is herein made up of straight-line segment MF and FG, is to schematically show the inventive method easily, and in practice, terrain profile Yan Hangkongqisudushiliangqianchuimian line is irregular curve).In three dimensions, in fact this terrain profile Yan Hangkongqisudushiliangqianchuimian line is exactly the edge line by aircraft side on topographic projection figure in this altitude range.
More preferably, a distance redundancy X based on aircraft horizontal level can be set, new terrain profile Yan Hangkongqisudushiliangqianchuimian line is drawn towards aircraft direction from aforesaid terrain profile Yan Hangkongqisudushiliangqianchuimian line (i.e. broken line MFG), new terrain profile Yan Hangkongqisudushiliangqianchuimian line (i.e. broken line TUV, broken line TUV is herein made up of straight-line segment TU and UV, to schematically show the inventive method easily, in practice, terrain profile Yan Hangkongqisudushiliangqianchuimian line is irregular curve) on every bit be all X apart from the minimum distance of aforementioned terrain profile Yan Hangkongqisudushiliangqianchuimian line, using this new terrain profile Yan Hangkongqisudushiliangqianchuimian line as the secure border of aircraft flight.Distance redundancy X makes new terrain profile Yan Hangkongqisudushiliangqianchuimian line compare original formline, more near aircraft side and away from landform side, thus provide the higher landform warning line of safety coefficient as the new secure border of aircraft flight for aircraft flight, make aircraft flight safer.Specifically, the distance redundancy of terrain profile Yan Hangkongqisudushiliangqianchuimian line is a redundancy based on the unit response time, can by assessing practical response time to the test of airline operation person, and obtaining a response distance by the speed of this response time and aircraft, distance redundancy X can meet the requirement of unit reaction distance.In practice, distance redundancy X can be set as that is determined a numerical value.This determines that numerical value directly can be selected according to flying experience in the past, also can give one artificially and determine numerical value.When required secure border is wider, then give the numerical value of a larger distance redundancy X artificially, when required secure border is narrower, then give the numerical value of a less distance redundancy X artificially.
More preferably, as shown in Figure 2 a, the terrain profile Yan Hangkongqisudushiliangqianchuimian line 2 in display screen 4 can show separately, also can with meteorological map data mining platform 3 Overlapping display, as shown in Figure 2 b.The display mode of landform outline line can be selected thus neatly.
By reference to the accompanying drawings embodiments of the present invention are explained in detail above, but the present invention is not limited to above-mentioned embodiment, in the ken that art those of ordinary skill possesses, various change can also be made under the prerequisite not departing from present inventive concept.
Claims (17)
1., based on a method for weather radar display terrain information, it is characterized in that, comprise the steps:
A () obtains the angle of pitch a of aloft aircraft;
B () arranges positive angle of pitch redundancy b, negative angle of pitch redundancy c;
C () chooses scan angle scope in pitch orientation for being more than or equal to-a-c and being less than or equal to-a+b, the scan angle scope on in-plane is between ± 90 degree, thus forms a spacescan region;
D () utilizes radar to scan described spacescan region, for the scan angle in each pitch orientation chosen, launch within the scope of the scan angle of in the in-plane direction ± 90 degree and receive echo, obtain distance corresponding to each scan angle planar closest to the terrain information of aircraft, and project in surface level, obtain the landform edge line corresponding to the scan angle in this pitch orientation, the landform edge line of the scan angle in different pitch orientation is superposed, the terrain profile Yan Hangkongqisudushiliangqianchuimian line near aircraft formed, as the secure border of aircraft flight.
2., as claimed in claim 1 based on the method for weather radar display terrain information, it is characterized in that, also comprise the steps:
E () arranges a distance redundancy X based on aircraft horizontal level, new terrain profile Yan Hangkongqisudushiliangqianchuimian line is obtained towards aircraft direction from described terrain profile Yan Hangkongqisudushiliangqianchuimian line, every bit on described new terrain profile Yan Hangkongqisudushiliangqianchuimian line is all X apart from the minimum distance of described terrain profile Yan Hangkongqisudushiliangqianchuimian line, using terrain profile Yan Hangkongqisudushiliangqianchuimian line new described in this as the secure border of aircraft flight.
3., as claimed in claim 1 or 2 based on the method for weather radar display terrain information, smooth curve matching is carried out to described terrain profile Yan Hangkongqisudushiliangqianchuimian line, and the smooth curve obtained after matching is as new terrain profile Yan Hangkongqisudushiliangqianchuimian line.
4., as claimed in claim 3 based on the method for weather radar display terrain information, described smooth curve matching adopts fitting of a polynomial, and the smooth curve obtained is the curve of polynomial expression.
5. as claimed in claim 3 based on the method for weather radar display terrain information, it is characterized in that, described positive angle of pitch redundancy b and/or described negative angle of pitch redundancy c is that the precision of facing upward precision and/or the radar detection height of bowing according to landform high redundancy, radar is determined.
6., as claimed in claim 3 based on the method for weather radar display terrain information, it is characterized in that, described positive angle of pitch redundancy b is taken as 0.01 degree, and described negative angle of pitch redundancy c is taken as 0.01 degree.
7. as claimed in claim 2 based on the method for weather radar display terrain information, it is characterized in that, described distance redundancy X is set as that is determined a numerical value.
8. as claimed in claim 2 based on the method for weather radar display terrain information, it is characterized in that, described distance redundancy X sets based on aircraft horizontal position error and unit response time.
9., as claimed in claim 3 based on the method for weather radar display terrain information, it is characterized in that, described terrain profile Yan Hangkongqisudushiliangqianchuimian line shows separately or shows with meteorological layer information superposition.
10., based on a method for weather radar display terrain information, it is characterized in that, comprise the steps:
A () uses height sensor, record the height H of aloft aircraft in space;
B (), with the surface level of aircraft place flying height H for benchmark, arrange upwards high redundancy H1, downwards high redundancy H2, the scan angle scope on in-plane is between ± 90 degree, thus forms a spacescan region;
C () meets for height A ltitude: H-H2 < Altitude < H+H1, choose the terrain return data of weather radar at various height on Altitude, obtain distance planar closest to the terrain information of aircraft, and project in surface level, obtain the landform edge line corresponding to this height, landform edge line corresponding to differing heights is superposed, forms terrain profile Yan Hangkongqisudushiliangqianchuimian line, as the secure border of aircraft flight.
11., as claimed in claim 9 based on the method for weather radar display terrain information, is characterized in that, also comprise the steps:
D () arranges a distance redundancy X based on aircraft horizontal level, new terrain profile Yan Hangkongqisudushiliangqianchuimian line is drawn towards aircraft direction from described terrain profile Yan Hangkongqisudushiliangqianchuimian line, every bit on described new terrain profile Yan Hangkongqisudushiliangqianchuimian line is all X apart from the minimum distance of described terrain profile Yan Hangkongqisudushiliangqianchuimian line, using terrain profile Yan Hangkongqisudushiliangqianchuimian line new described in this as the secure border of aircraft flight.
12. as described in claim 9 or 10 based on weather radar display terrain information method, smooth curve matching is carried out to described terrain profile Yan Hangkongqisudushiliangqianchuimian line, and the smooth curve obtained after matching is as new terrain profile Yan Hangkongqisudushiliangqianchuimian line.
13. as claimed in claim 11 based on the method for weather radar display terrain information, and described smooth curve matching adopts fitting of a polynomial, and the smooth curve obtained is the curve of polynomial expression.
14. as described in claim 10 or 11 based on weather radar display terrain information method, it is characterized in that, described upwards high redundancy H1 or downwards high redundancy H2 set based on the height error of GPS height error, radio altitude error and/or atmosphere data.
15. as described in claim 10 or 11 based on weather radar display terrain information method, it is characterized in that, described distance redundancy X be set as that is determined a numerical value.
16., as claimed in claim 10 based on the method for weather radar display terrain information, is characterized in that, described distance redundancy X sets based on aircraft horizontal position error and unit response time.
17. as claimed in claim 11 based on the method for weather radar display terrain information, and it is characterized in that, described terrain profile Yan Hangkongqisudushiliangqianchuimian line shows separately or shows with meteorological layer information superposition.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104730523B (en) | 2017-09-15 |
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