CN109239012A - Utilize the system and test method of aircraft measurement underlying surface atmosphere astronomical refraction - Google Patents
Utilize the system and test method of aircraft measurement underlying surface atmosphere astronomical refraction Download PDFInfo
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- CN109239012A CN109239012A CN201810827413.5A CN201810827413A CN109239012A CN 109239012 A CN109239012 A CN 109239012A CN 201810827413 A CN201810827413 A CN 201810827413A CN 109239012 A CN109239012 A CN 109239012A
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- 238000005259 measurement Methods 0.000 title claims description 22
- 238000010998 test method Methods 0.000 title abstract description 8
- 238000000034 method Methods 0.000 claims abstract description 9
- 238000003384 imaging method Methods 0.000 claims description 21
- 230000003287 optical effect Effects 0.000 claims description 16
- NJPPVKZQTLUDBO-UHFFFAOYSA-N novaluron Chemical compound C1=C(Cl)C(OC(F)(F)C(OC(F)(F)F)F)=CC=C1NC(=O)NC(=O)C1=C(F)C=CC=C1F NJPPVKZQTLUDBO-UHFFFAOYSA-N 0.000 claims description 15
- 239000013307 optical fiber Substances 0.000 claims description 5
- 238000004737 colorimetric analysis Methods 0.000 claims description 4
- 230000008569 process Effects 0.000 abstract description 2
- 239000003381 stabilizer Substances 0.000 abstract 2
- 230000004075 alteration Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 238000013461 design Methods 0.000 description 2
- 238000001514 detection method Methods 0.000 description 2
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- 238000011160 research Methods 0.000 description 2
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
- G01N21/17—Systems in which incident light is modified in accordance with the properties of the material investigated
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/02—Aircraft not otherwise provided for characterised by special use
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
- G01N21/17—Systems in which incident light is modified in accordance with the properties of the material investigated
- G01N21/41—Refractivity; Phase-affecting properties, e.g. optical path length
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
- G01N21/17—Systems in which incident light is modified in accordance with the properties of the material investigated
- G01N2021/1793—Remote sensing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
- G01N21/17—Systems in which incident light is modified in accordance with the properties of the material investigated
- G01N21/41—Refractivity; Phase-affecting properties, e.g. optical path length
- G01N2021/4106—Atmospheric distortion; Turbulence
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Abstract
本发明公开了利用飞行器测量下垫面大气蒙气差的系统及测试方法，该系统包括飞行器，所述飞行器上设置有视轴稳定器，视轴稳定器上设置有底座，底座上安装有多个光源，多个光源包括至少两个第一波长的光源和至少一个第二波长的光源，多个光源的中心均在同一条直线上。该发明利用飞行器携不同波长的光源飞行到需要观测的点，通过第一波长和第二波长的蒙气色差，计算其他指定波长的蒙气差/蒙气色差。不需要测量光波路径上的温度、湿度和压强廓线，并且已知两波长蒙气色差计算其他波长蒙气差/蒙气色差的方法物理过程简单、时效性高，可解决复杂下垫面、低仰角场景的大气蒙气差/蒙气色差获取问题，且为复杂路径条件蒙气差/色差的建模提供数据支持。
The invention discloses a system and a test method for using an aircraft to measure the atmospheric difference of an underlying surface. The system includes an aircraft, the aircraft is provided with a boresight stabilizer, a base is arranged on the boresight stabilizer, and multiple a light source, the plurality of light sources include at least two light sources of the first wavelength and at least one light source of the second wavelength, and the centers of the plurality of light sources are all on the same straight line. The invention utilizes the aircraft to carry light sources of different wavelengths to the point to be observed, and calculates the airborne color difference/airborne color difference of other specified wavelengths through the airborne color difference of the first wavelength and the second wavelength. There is no need to measure the temperature, humidity and pressure profiles on the light wave path, and the method to calculate the other wavelengths of the airborne color difference is known, the physical process is simple, and the timeliness is high, which can solve the complex underlying surface, The problem of obtaining atmospheric haze/chromatic aberration in low-elevation scenes, and provides data support for the modeling of complex path conditions.
Description
Technical field
The present invention relates to mechanical and optical field, especially with aircraft measurement underlying surface atmosphere astronomical refraction system and
Test method.
Background technique
The method of the acquisition astronomical refraction of open report at present are as follows: the distribution of atmosphere height substantially conforms to plane when the elevation angle is higher
Parallel atmosphere is assumed；Under the conditions of it is assumed herein that: whole atmosphere astronomical refraction is according to Air Close To The Earth Surface temperature, humidity, pressure and observation
The elevation angle calculates；Oblique journey limited distance astronomical refraction can also pass through disclosed theoretical formula method but need to know the temperature on propagation path
Degree, humidity and pressure profile data, or it is right using the astronomical refraction that the atmospheric outline data on vertical-path calculate zenith direction
Assume to calculate the astronomical refraction for specifying the elevation angle in parallel according to plane afterwards.It is false in parallel according to plane when the elevation angle is higher, underlying surface is single
The precision that atmosphere astronomical refraction is calculated in design is enough；But when the elevation angle is lower, underlying surface is complicated, the height distribution of atmospheric parameter is no longer
It is parallel it is assumed that must have the temperature on light wave propagation path, humidity and pressure profile data to support at this time to meet plane.It measures low
The difficulty of the temperature humidity pressure profile of elevation angle Complex Underlying Surface scene is significantly larger than vertical-path scene；It is surveyed in laser radar
Influence away from low elevation angle astronomical refractions in fields such as, laser positionings be can not ignore, it is therefore desirable to which research obtains the new system of astronomical refraction
System and test method.
Summary of the invention
In order to overcome the above-mentioned prior art, for this purpose, the present invention, which provides, utilizes aircraft measurement underlying surface atmosphere astronomical refraction
System and test method.
To achieve the above object, the invention adopts the following technical scheme:
Using the system of aircraft measurement underlying surface atmosphere astronomical refraction, including aircraft, bottom is provided on the aircraft
, it is arranged on pedestal by multiple light sources, multiple light sources include the light source and at least one second wave length of at least two first wave length
Light source, the center of multiple light sources is on same straight line.
Specifically, being provided with 3 light sources on the aircraft, the light source of first wave length is two, the light of second wave length
Source is 1.
Specifically, being provided with the lower section of optic central extract device, optic central extract device in the middle part of the aircraft by rigid portion
Part is connect with pedestal, and system further includes that setting two-dimensional tracking platform on the ground, setting receive light on two-dimensional tracking platform
The optical measuring device of source signal.
Specifically, the optical measuring device includes the telescope, varifocal mirror, detection set gradually on imaging optical path
Device further includes the computer connecting with detector electric signal.
Specifically, the light source of two first wave length is placed equidistant in the two sides of the light source of second wave length.
Specifically, the line of light source center is perpendicular to the ground or parallel to the ground on the aircraft.
Specifically, the line at multiple light sources center is overlapped with pedestal middle line
Specifically, the light source is single mode optical fiber output.
Use the test method of the above-mentioned system using aircraft measurement underlying surface atmosphere astronomical refraction, including following step
Suddenly；
S1, the imaging to all light sources in detector carry out long exposure；
S2, by the imaging center line of the light source of multiple identical first wave length, form reference line, calculate the light of second wave length
Source imaging and the vertical range d of reference line calculate this apart from corresponding subtended angle according to telescope equivalent focal length f,
The angle is that illiteracy complexion corresponding to first wave length and second wave length is poor；
S3, optical band according to cover gas Colorimetry specified wavelength astronomical refraction formula
Wherein λ1、λ2It respectively indicates first wave length and second wave length, λ is the wavelength of specified wavelength light wave, Δ φ is first wave
Long and illiteracy complexion corresponding to second wave length is poor, φ is the corresponding astronomical refraction of wavelength X under the atmospheric conditions.
The present invention has the advantages that
(1) place that the present invention is observed using the light source flight that aircraft takes different wave length to needs, passes through first wave length
Poor with the illiteracy complexion of second wave length, the astronomical refraction/illiteracy complexion for calculating other specified wavelengths accordingly is poor.This method does not need measurement light
Temperature, humidity and pressure profile on wave path, and known two wavelength covers other wavelength astronomical refraction/illiteracy complexions of gas Colorimetry
The method physical process of difference is simple, timeliness is high, is able to solve atmosphere astronomical refraction/illiteracy gas of Complex Underlying Surface, low elevation angle scene
Color difference obtains problem, and master data support can be provided for the modeling of pahtfinder hard condition astronomical refraction/color difference.
(2) optic central extract device can reduce the influence shaken and generated on aircraft.
(3) when refractive index gradient has height to be distributed, occur since refractive index gradient height change can cause light beam to be directed toward
Deviation, wavelength difference deviation amount are also different.Therefore multiple light sources point-blank are not since wavelength difference imaging is at one
On straight line.At this point, be reference with the light sources of at least two first wave length imaging line, count the light source of second wave length at image position
It is poor to set the illiteracy complexion that two kinds of wavelength can be obtained with the irrelevance with reference to straight line；Obtain the illiteracy complexion of first wave length and second wave length
The atmospheric conditions that may know that measuring route after difference, can further calculate astronomical refraction/illiteracy gas of other specified wavelengths under this condition
Color difference.
(4) present invention uses three light sources, the light source of two first wave length and the light source of a second wave length, examines realizing
Cost of manufacture is saved in the case where surveying purpose and reduces the bearing capacity of gap device.
(5) three light sources are integrated on optic central extract device according to relative to ground level or vertical direction, in atmospheric conditions
Meet atmospheric light beam when plane is assumed in parallel and is directed toward deviation mainly in vertical direction；But the light under complicated atmospheric conditions
For beam in the horizontal direction there is also deviation, deviation amount is generally less than the deviation amount of vertical direction.Accordingly, our three light of decision design
Source position word order in the horizontal direction；If measured scene atmospheric conditions are especially complex to need to consider the inclined of vertical direction
Three light source orientations are revised as vertical direction by folding.
(6) when the systematic survey horizontal route astronomical refraction/color difference, hovering/be accommodated to designated place for aircraft can be straight
Astronomical refraction/the color difference for measuring path of interest is connect, since aircraft itself is self-powered, the system is especially suitable for land and sea junction
Equal personnel are difficult to the place development reached observation.Measurement method of the present invention is simple and clear, effective height, helps to carry out multiple
Atmosphere astronomical refraction changing rule research under miscellaneous atmospheric conditions.
Detailed description of the invention
Fig. 1 is schematic diagram of the present invention using the system of aircraft measurement underlying surface atmosphere astronomical refraction.
Fig. 2 is the schematic diagram of aircraft section in system.
Fig. 3 is the schematic layout pattern of three light sources on pedestal.
Fig. 4 is the schematic diagram of optical measuring device in the present invention.
Fig. 5 is light path schematic diagram of three light sources in solid space in the present invention.
Fig. 6 is the side view of Fig. 5.
The meaning of label symbol is as follows in figure:
1- aircraft 2- optic central extract device 3- rigid element 4- pedestal 41- pedestal middle line
5- light source 51- first light source 52- second light source 53- third light source
6- optical measuring device 61- telescope 62- varifocal mirror 63- detector 64- computer
7- two-dimensional tracking platform
81- first is imaged 82- second and 83- third imaging 84- reference line is imaged
Specific embodiment
As shown in Figs 1-4, a kind of system using aircraft measurement underlying surface atmosphere astronomical refraction, which includes aircraft
1, optic central extract device 2, rigid element 3, pedestal 4, light source 5, setting two-dimensional tracking platform 7 on the ground, setting two dimension with
The optical measuring device 6 of 5 signal of light source is received on track platform 7.The aircraft 1 uses unmanned vehicle 1.The optical measurement dress
To set 6 include the telescope 61 set gradually on imaging optical path, varifocal mirror 62, detector 63, is connect with 63 electric signal of detector
Computer 64.
Wherein aircraft 1 is used to carry the flight of light source 5 to specified position hovering or motor-driven.The optic central extract device 2 is set
It sets at the middle part of aircraft 1, the lower section of optic central extract device 2 is connect by rigid element 3 with pedestal 4, to control on pedestal 4
Light source 5 faces optical measuring device 6 always.The light source 5 of 3 single mode optical fibers output is mounted on pedestal by rigid optical fiber flange
On 4, realize that the output of light source 5 is protected at the center of flange, by machining accuracy using the mechanical engagement of unicast optical fiber and flange
The mounting flange center for demonstrate,proving three light sources 5 is located on pedestal middle line 41.3 light sources 5 include the light source 5 of two first wave length
The light source 5 (second light source 52) of (first light source 51, third light source 53) and a second wave length, first light source 51 and third light source
53 are placed equidistant in the two sides of second light source 52, and in measurement, three light sources 5 are lighted.Two-dimensional tracking platform 7 is used to control light
The direction of measuring device 6 is learned to guarantee that light source 5 is imaged on the field of view center of telescope 61.
Light source 5 is imaged on detector 63 after telescope 61, varifocal mirror 62, and detector 63 is mounted on 61 He of telescope
At the equivalent focal plane of varifocal mirror 62.To computer 64,64 real time processed images of computer obtain the imaging data real-time transmission of detector 63
The imaging position being imaged to three light sources 5 (is statistics three if measuring the astronomical refraction of horizontal direction in the difference of vertical direction
A 5 imaging position of light source difference in the horizontal direction).To ensure measurement accuracy, computer 64 is logical as earth station and aircraft 1
Letter, the 1 positional information calculation telescope 61 of aircraft passed back according to aircraft 1 is at a distance from light source 5, then according to object-image relation
Real-time control varifocal mirror 62 realizes that not defocus is imaged in light source 5 on detector 63, to guarantee imaging position detection accuracy and then protect
Card covers the computational accuracy of complexion difference.
The line at 5 center of light source is perpendicular to the ground or parallel to the ground on the aircraft 1.
Embodiment 2
Include the following steps the test method of the above-mentioned system using aircraft measurement underlying surface atmosphere astronomical refraction；
S1, the imaging to all light sources 5 in detector 63 carry out long exposure, cause imaging to be trembled at random to eliminate atmospheric turbulance
Dynamic interference, as seen in figs. 5-6, first light source 51, second light source 52, third light source 53 are corresponding on detector 63 to be imaged as the
One the 81, second imaging 82 of imaging, third imaging 83；
S2, the line of centres that the center of the first imaging 81 and second are imaged to 82, form reference line 84, calculate the second imaging
82 center and the vertical range d of reference line calculate this apart from corresponding subtended angle according to 61 equivalent focal length f of telescope,
The angle is that illiteracy complexion corresponding to first wave length and second wave length is poor；
S3, optical band according to cover gas Colorimetry specified wavelength astronomical refraction formula
Wherein λ1、λ2It respectively indicates first wave length and second wave length, λ is the wavelength of specified wavelength light wave, Δ φ is first wave
Long and illiteracy complexion corresponding to second wave length is poor, φ is the corresponding astronomical refraction of wavelength X under the atmospheric conditions.
The above is only the preferred embodiments of the invention, are not intended to limit the invention creation, all in the present invention
Made any modifications, equivalent replacements, and improvements etc., should be included in the guarantor of the invention within the spirit and principle of creation
Within the scope of shield.
Claims (9)
1. utilizing the system of aircraft measurement underlying surface atmosphere astronomical refraction, which is characterized in that including aircraft (1), the flight
It is provided with pedestal (4), is provided on pedestal (4) multiple light sources (5) on device (1), multiple light sources (5) include at least two first waves
The light source (5) of long light source (5) and at least one second wave length, the center of multiple light sources (5) is on same straight line.
2. the system according to claim 1 using aircraft measurement underlying surface atmosphere astronomical refraction, which is characterized in that described
3 light sources (5) are provided on aircraft (1), the light source (5) of first wave length is two, and the light source (5) of second wave length is 1.
3. the system according to claim 1 using aircraft measurement underlying surface atmosphere astronomical refraction, which is characterized in that described
The lower section of optic central extract device (2), optic central extract device (2) is provided in the middle part of aircraft (1) by rigid element (3) and pedestal
(4) it connects, system further includes that setting two-dimensional tracking platform (7) on the ground, setting receive light on two-dimensional tracking platform (7)
The optical measuring device (6) of source (5) signal.
4. the system according to claim 3 using aircraft measurement underlying surface atmosphere astronomical refraction, which is characterized in that described
Optical measuring device (6) includes the telescope (61), varifocal mirror (62), detector (63) set gradually on imaging optical path, also
Including the computer (64) being connect with detector (63) electric signal.
5. the system according to claim 2 using aircraft measurement underlying surface atmosphere astronomical refraction, which is characterized in that two
The light source (5) of first wave length is placed equidistant in the two sides of the light source (5) of second wave length.
6. the system according to claim 1 using aircraft measurement underlying surface atmosphere astronomical refraction, which is characterized in that described
The line at light source (5) center is perpendicular to the ground or parallel to the ground on aircraft (1).
7. the system according to claim 1 using aircraft measurement underlying surface atmosphere astronomical refraction, which is characterized in that multiple
The line at light source (5) center is overlapped with pedestal middle line (41).
8. the system according to claim 1 using aircraft measurement underlying surface atmosphere astronomical refraction, which is characterized in that described
Light source (5) is single mode optical fiber output.
9. using the test of the system of aircraft measurement underlying surface atmosphere astronomical refraction is utilized described in claim 1-8 any one
Method, which is characterized in that include the following steps；
S1, the imaging to all light sources (5) in detector (63) carry out long exposure；
S2, by the imaging center line of the light source (5) of multiple identical first wave length, formed reference line (84), calculate second wave length
Light source (5) imaging this is calculated apart from corresponding according to telescope (61) equivalent focal length f with the vertical range d of reference line (84)
Subtended angle,
The angle is that illiteracy complexion corresponding to first wave length and second wave length is poor；
S3, optical band according to cover gas Colorimetry specified wavelength astronomical refraction formula
Wherein λ1、λ2Respectively indicate first wave length and second wave length, λ be the wavelength of specified wavelength light wave, Δ φ be first wave length and
Illiteracy complexion corresponding to second wave length is poor, φ is the corresponding astronomical refraction of wavelength X under the atmospheric conditions.
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2018
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| US6229619B1 (en) * | 1996-02-12 | 2001-05-08 | Massachusetts Institute Of Technology | Compensation for measurement uncertainty due to atmospheric effects |
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