CN115639572A - Satellite-borne laser radar for synchronously observing wind, temperature and aerosol - Google Patents
Satellite-borne laser radar for synchronously observing wind, temperature and aerosol Download PDFInfo
- Publication number
- CN115639572A CN115639572A CN202211139916.6A CN202211139916A CN115639572A CN 115639572 A CN115639572 A CN 115639572A CN 202211139916 A CN202211139916 A CN 202211139916A CN 115639572 A CN115639572 A CN 115639572A
- Authority
- CN
- China
- Prior art keywords
- laser
- unit
- aerosol
- signals
- temperature
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Classifications
-
- 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
Landscapes
- Optical Radar Systems And Details Thereof (AREA)
Abstract
A satellite-borne laser radar for synchronously observing wind, temperature and aerosol is characterized in that a laser emission unit emits single-frequency pulse laser to the atmosphere; the receiving telescope unit collects laser back scattering echoes and sends the laser back scattering echoes to the notch filter unit, aerosol signals are filtered out, atmospheric molecule Rayleigh scattering signals are reserved, echo filtering optical signals are formed, and the echo filtering optical signals are sent to the interferometer unit; the interferometer unit sequentially performs interference modulation on the sampled single-frequency pulse laser signals and the echo filtering optical signals to generate four paths of interference signals with the phase differences of 0 degrees, 90 degrees, 180 degrees and 270 degrees in sequence, the four paths of interference signals are respectively sent to the four signal detection units, the sampled laser optical signals and the echo filtering optical signals are sequentially detected, and the four paths of interference signals are sent to the processing inversion unit after photoelectric conversion and digitization are performed; the processing inversion unit utilizes the digital signals transmitted by the four signal detection units to invert the wind speed, the temperature and the aerosol extinction coefficient. The invention has the functions of measuring wind speed, temperature and aerosol through one satellite-borne laser radar device, and has high integration level and high cost-effectiveness ratio.
Description
Technical Field
The invention belongs to the technical field of atmospheric optical remote sensing, and relates to a device for realizing atmospheric wind speed, temperature and aerosol laser radar detection by combining a notch filter with a four-path interferometer.
Background
The detection of the wind speed, the temperature and the aerosol profile of the earth atmosphere has important value in the research and application fields of weather, climate, environment and the like. In order to perform the above-mentioned profile measurement, various laser radar detection techniques have been developed at home and abroad. Among the most common techniques are coherent wind lidar, direct wind lidar, rotating raman lidar, micro-pulse millimeter-scattering lidar, high spectral resolution lidar and the like.
The coherent detection laser radar can only be used for detecting the atmospheric wind speed with higher aerosol content, and the measurement height in the earth atmosphere is generally not more than 3km. The receiving aperture is limited by the coherent condition and is not suitable to be large, so the detection capability is improved mainly by increasing the laser single pulse energy in the remote or satellite-borne application. The direct detection laser radar generally measures the wind speed through the transmission energy change of a high spectral resolution optical element, if an FP etalon and a Fizeau interferometer are adopted, the problems of low energy utilization rate, poor field adaptability and the like exist, the improvement of comprehensive performance is not facilitated, and if an iodine molecular filter is adopted, the precision is low and the direct detection laser radar is only used for 532nm. In addition, the conventional coherent detection technology and the conventional direct detection technology do not have the capability of synchronously detecting the temperature and the aerosol.
The rotating Raman laser radar and the Raman laser radar are generally used for detecting the temperature profile of the foundation and aerosol, and are difficult to be used for satellite-borne detection and have no anemometry capability due to extremely small scattering signals. The micropulse millimeter scattering laser radar is generally used for aerosol detection, and the extinction coefficient precision of the micropulse millimeter scattering laser radar is lower than that of a rotary Raman laser radar and a Raman laser radar. The high spectral resolution laser radar generally improves the aerosol detection accuracy by separating molecular Rayleigh scattering signals and aerosol meter scattering signals, the accuracy of the high spectral resolution laser radar is equivalent to that of a rotary Raman laser radar and a Raman laser radar, but the high spectral resolution laser radar can be used for satellite-borne measurement but cannot synchronously measure wind speed and temperature due to strong signal intensity.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the satellite-borne laser radar detection device with the notch filter combined with the four-path interferometer is provided, wind speed detection can be achieved by measuring the frequency shift quantity of laser radar echo light, temperature measurement can be achieved by measuring the broadening of Rayleigh scattering echoes, and high-precision measurement of aerosol extinction coefficients can be achieved by separating molecular scattering signals and aerosol signals through contrast.
The technical solution of the invention is as follows: the utility model provides a satellite-borne wind, temperature, aerosol synchronous observation laser radar, includes laser emission unit, receives telescope unit, notch filter unit, interferometer unit, four signal detection units, handles inversion unit and laser sampling unit, wherein:
a laser emitting unit: the single-frequency pulse laser is used for emitting single-frequency pulse laser into the atmosphere;
a receiving telescope unit: the device is used for collecting laser back scattering echoes and sending the laser back scattering echoes to the notch filter unit;
a notch filter unit: the device is used for filtering aerosol signals in laser backscattering echoes and reserving atmospheric molecule Rayleigh scattering signals to form echo filtering signals and send the echo filtering signals to the interferometer unit;
a laser sampling unit: the single-frequency pulse laser sampling device is used for sampling single-frequency pulse laser emitted by the laser emitting unit and sending the single-frequency pulse laser as reference laser to the interferometer unit;
an interferometer unit: respectively processing the reference laser sent by the laser sampling unit and the laser back scattering echo light sent by the notch filter unit according to the sequence; firstly, the reference laser is subjected to interference modulation, and the generated optical path difference is delta in sequence 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 The four paths of interference signals of +3 lambda/4 are respectively sent to the four signal detection units; then, the laser back scattering echo light is subjected to interference modulation to generate optical path differences of delta in sequence 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 The four paths of interference signals of +3 lambda/4 are respectively sent to the four signal detection units;
a signal detection unit: the device is used for detecting optical signals contained in interference signals, carrying out photoelectric conversion and digitization and then sending the optical signals into a processing inversion unit;
processing an inversion unit: and the wind speed, the temperature and the aerosol extinction coefficient are inverted by using the digital signals transmitted by the four signal detection units.
Preferably, the processing and inverting unit inverts the wind speed v, specifically:
wherein c is the speed of light, v is the speed of wind,
for the laser back scattering echo light interference phase difference,
to refer to the interference phase difference, σ, of the laser light 0 For emitting laser wave number, Δ 0 Is the reference optical path difference.
Preferably, the processing and inverting unit inverts the temperature T, specifically:
in the formula,. DELTA. 0 Q is an inversion constant, V (r) is a value at a distance r obtained by the following equation,
wherein, I 1 、I 2 、I 3 、I 4 Respectively, the detection signals output by the signal detection unit, the corresponding optical path differences are respectively delta 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 And +3 lambda/4, wherein lambda is the wavelength of the single-frequency pulse laser.
Preferably, the processing inversion unit inverts the aerosol extinction coefficient, specifically:
in the formula I m (r)＝I 0 (r)，I 0 (r) is the intensity of the incident light, beta, obtained at a distance r m (r) is the backscattering coefficient of atmospheric molecules at a distance r, I 0 (r) is calculated by the following formulaIn the end of the above-mentioned process,
wherein, I 1 、I 2 、I 3 、I 4 Respectively, the detection signals output by the signal detection unit, the corresponding optical path differences are respectively delta 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 And +3 lambda/4, wherein lambda is the wavelength of the single-frequency pulse laser.
Preferably, the single-frequency pulse laser satisfies the following conditions: the single wavelength selection range is 0.3-2.2 μm, and the relative line width is less than or equal to 2 x 10 -7 λ, relative stability of wavelength less than or equal to 1 × 10 -6 The pulse width is less than or equal to 5 microseconds, the repetition frequency is less than or equal to 40kHz, and the single pulse energy is more than or equal to 1 muJ.
Preferably, the receiving telescope unit adopts a transmission lens or a reflection lens, the transmittance of the receiving telescope unit to the laser wavelength emitted by the laser emitting unit is more than or equal to 0.5, the effective caliber is more than or equal to 50mm, and the receiving field of view is more than or equal to 50 μ rad.
Preferably, the notch filter unit is an optical element or a combination of these elements having a capability of suppressing the lasing wavelength but transmitting adjacent wavelengths, including but not limited to FP etalons, molecular absorption cells, michelson interferometers.
Preferably, the notch filter unit has a suppression capability of more than 10 times of the laser wavelength signal emitted by the laser emission unit, and has a suppression bandwidth of 0.4 to 3 × 10 -6 λ。
Preferably, the interferometer unit is a michelson interferometer or a mach-zehnder interferometer.
Preferably, the four signal detection units adopt analog detection or photon detection devices with time resolution and photoelectric conversion capability, including but not limited to PMT, APD, G-APD or PIN.
Compared with the prior art, the invention has the advantages that:
(1) The satellite-borne laser radar device has the functions of measuring wind speed, temperature and aerosol, and is high in integration level and high in cost efficiency;
(2) The temperature is measured through the elastic scattering echo signals, the signal intensity is 2-3 orders of magnitude higher than that of the rotating Raman detection, and the satellite-borne load scale can be effectively compressed;
(3) The invention is not limited by coherent conditions, can improve the detection capability by increasing the caliber, and is beneficial to reducing the energy requirement on the laser and increasing the system reliability.
Drawings
Fig. 1 is a block diagram of the principle of the lidar of the present invention.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings.
As shown in FIG. 1, the laser radar of the invention mainly comprises a laser transmitting unit 1, a receiving telescope unit 2, a notch filter unit 3, an interferometer unit 4, four signal detection units 5-8, a processing inversion unit 9 and a laser sampling unit 10. The laser emission unit 1 is used for emitting single-frequency pulse laser to the atmosphere, the laser sampling unit 10 is used for taking out part of emitted laser as reference laser, the receiving telescope unit 2 is used for collecting laser backward scattering echoes, the relay optical units (the notch filter unit 3 and the interferometer unit 4) are used for optically separating the echoes, the notch filter unit 3 is mainly used for filtering aerosol signals in the echoes and reserving atmospheric molecule Rayleigh scattering signals, and the four-path interferometer (the interferometer unit 4) sequentially performs interference modulation on the reference laser and the echoes to generate optical path difference delta sequentially 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 +3 λ/4 four-way interference signal (where Δ 0 Reference optical path difference), the four signal detection units 5-8 are responsible for detecting the optical signals separated by the interferometer unit 4 and generating digitized data, and the processing and inverting unit 9 is responsible for calibrating the data and inverting the required information such as wind speed, temperature and aerosol extinction coefficient.
The single-frequency pulse laser emitted by the laser emitting unit 1 has a single wavelength selection range of 0.3-2.2 μm and a relative line width of less than or equal to 2 multiplied by 10 -7 Relative stability of wavelength less than or equal to 1 × 10 -6 The pulse width is less than or equal to 5 mu s,The repetition frequency is less than or equal to 40kHz, and the single pulse energy is more than or equal to 1 muJ.
The receiving telescope unit 2 can be a transmission lens or a reflection lens in form, the transmittance of the laser wavelength emitted by the laser emitting unit 1 is more than or equal to 0.5, the effective caliber is more than or equal to 50mm, and the receiving field of view is more than or equal to 50 μ rad.
The notch filter unit 3 is mainly used to filter the laser wavelength signal emitted from the laser emission unit 1 so that the signal of the wavelength cannot enter the interferometer unit 4, and the suppression capability of the laser wavelength signal emitted from the laser emission unit 1 after passing through the notch filter exceeds 10 times. The notch filter unit 3 may be an optical element having a laser emission wavelength suppression capability, such as an FP etalon, a molecular absorption cell, a michelson interferometer, or a combination of these elements.
The interferometer unit 4 modulates the reference laser and the echo light in time sequence to form four paths of signals respectively, wherein the former is used for calculating the wavelength during emission, and the latter is used for calculating the wavelength lambda and the modulation contrast V of the echo. The interferometer unit 4 has interference optical path differences of Δ 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 And +3 lambda/4. The interferometer unit 4 may be in the form of a michelson interferometer, a mach-zehnder interferometer, or the like. Wherein Δ 0 The specific value range is 0.5 delta for the reference optical path difference related to the wavelength lambda and the range of the atmospheric temperature T to be measured opt ～1.5Δ opt . Wherein, delta opt The calculation formula is that the unit is m:
a 1 ＝-1.007710316073537×10 9
b 1 ＝2.387652330524953×10 7
c 1 ＝4.669103274194003×10 4
a 2 ＝-9.943932650209543
b 2 ＝0.051216711849456
c 2 ＝-7.167196097489528×10 -5
the four signal detection units 5 to 8 respectively correspond to the 4 paths of interference light signals output by the interferometer unit 4, respectively detect the respective 4 paths of interference output light of the reference laser and the echo laser according to the time sequence, respectively perform photoelectric conversion and analog-to-digital conversion on the respective 4 paths of interference output light of the reference laser and the echo laser according to the time sequence to generate digital signals, and then send the digital signals to the processing and inverting unit 9. The four signal detection units 5 to 8 can be analog detection or photon detection devices with time resolution and photoelectric conversion capabilities, such as PMT, APD, G-APD, PIN and the like.
The specific measurement process is as follows:
(1) The laser transmitting unit 1 transmits laser to the atmosphere, and the backscattered laser scattered by the atmosphere enters the notch filter unit 3 after being collected by the receiving telescope unit 2;
(2) The backscattered laser passing through the notch filter unit 3 is filtered to remove the scattered signals and then enters the interferometer unit 4;
(3) The backscattered laser light passing through the interferometer unit 4 is divided into 4 interference light signals (4 interference optical path differences are Δ 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 +3 λ/4, λ being the working wavelength of the emitted laser), respectively enter the first signal detection unit 5, the second signal detection unit 6, the third signal detection unit 7 and the fourth signal detection unit 8;
(4) The laser sampling unit 10 takes out a small portion of the emitted laser light as reference laser light to be introduced into the interferometer unit 4. The reference laser beam passing through the interferometer unit 4 is divided into 4 interference optical signals (4 interference optical path differences are increased according to lambda/4), and the interference optical signals enter the first signal detection unit 5, the second signal detection unit 6, the third signal detection unit 7 and the fourth signal detection unit 8 respectively.
(5) The first signal detection unit 5, the second signal detection unit 6, the third signal detection unit 7 and the fourth signal detection unit 8 respectively complete photoelectric conversion and digitization on optical signals, and the digital signals are transmitted to the processing inversion unit 9;
(6) The processing and inverting unit 9 performs calibration and inversion on the digital signals input by the signal detection units 5 to 8 to obtain wind speed, temperature and aerosol extinction coefficient data. The specific treatment method comprises the following steps:
the detection signals output by the signal detection units 5 to 8 are respectively expressed as: i is 1 、I 2 、I 3 、I 4 Corresponding optical path differences are respectively delta 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 +3 λ/4. The sampled reference laser and echo laser enter the interferometer at different times and are detected, and no coherent relation occurs. Through the four output channels, the respective light intensity, phase and modulation degree of the two lasers are calculated in sequence, and the wind speed is inverted by subtracting the phase of the reference laser from the measured phase of the echo laser.
The incident light intensity I is calculated 0 Modulation degree V and interference phase difference
The following were used:
then, the frequency shift is calculated from the phase difference between the echo laser and the reference laser.
When the laser radar works, the reference laser and the echo laser enter the interferometer unit 4 in time sequence. Therefore, the reference laser signals are firstly received by the detection units 5 to 8, and the interference phase difference calculated by the reference laser is expressed as
Then, the echo laser light scattered and returned from the distance r reaches the detection units 5 to 8, and the echo laser light interference phase difference is expressed as shown in the formula (1-1)
Then the frequency shift of the laser echo relative to the emitted laser at distance r is:
where Δ f is the relative frequency shift, σ 0 For emitting laser wave number (1/lambda), delta 0 The reference optical path difference is obtained.
And then calculating the wind speed during atmospheric detection by the frequency shift.
The calculation formula of the wind speed is as follows:
wherein c is the speed of light and v is the speed of wind.
The atmospheric temperature is calculated from the modulation contrast.
The calculation formula of the temperature is as follows:
in the formula, Q is an inversion constant and can be obtained from calibration. V (r) is the result of V at distance r in equation (1-1).
The above formula can be referred to Wang Li, zhao Baochang, inbin, etc., the selection principle [ J ] of the reference optical path difference in the wind field detection interferometer, photonics, 2006,35 (8), 1254-1258.
The intensity of the incident light I obtained at the distance r according to the formula (1-1) 0 (r) is the rayleigh backscatter signal of atmospheric molecules, which can be expressed as:
I m (r)＝I 0 (r) (1-5)
in the laser radar echo signal, the atmospheric molecular echo signal is expressed as:
in the formula, c A The lidar system constants are related to emission energy, optical efficiency, electronic efficiency and the like, and are generally obtained by system calibration.β m (r) is the atmospheric molecular backscattering coefficient at distance r.
Then the extinction coefficient can be obtained from the molecular rayleigh backscatter signal by the formula:
where dr is the differential over r.
The formula can be seen in Liu Bingyi, zhuang Quanfeng, qin Shengguang and the like, and the research [ J ], infrared and laser engineering, 2017,46 (4): 0411001-1-13 is based on the aerosol classification method of the high-spectral resolution laser radar.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. The utility model provides a satellite-borne wind, temperature, synchronous observation laser radar of aerosol which characterized in that includes: laser emission unit (1), receive telescope unit (2), notch filter unit (3), interferometer unit (4), four signal detection units (5 ~ 8), processing inversion unit (9) and laser sampling unit (10), wherein:
laser emitting unit (1): the single-frequency pulse laser is used for emitting single-frequency pulse laser to the atmosphere;
receiving telescope unit (2): the device is used for collecting laser backscattering echoes and sending the laser backscattering echoes to a notch filter unit (3);
notch filter unit (3): the aerosol signal filtering unit is used for filtering aerosol signals in laser backward scattering echoes and reserving atmospheric molecule Rayleigh scattering signals to form echo filtering signals and send the echo filtering signals to the interferometer unit (4);
laser sampling unit (10): the single-frequency pulse laser device is used for sampling single-frequency pulse laser emitted by the laser emission unit (1) and sending the single-frequency pulse laser as reference laser to the interferometer unit (4);
interferometer unit (4): respectively processing the reference laser sent by the laser sampling unit (10) and the laser back scattering echo light sent by the notch filter unit (3) according to the sequence; firstly, the reference laser is subjected to interference modulation to generate optical path difference in sequenceIs Δ 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 The four paths of interference signals of +3 lambda/4 are respectively sent to four signal detection units (5-8); then, the laser back scattering echo light is subjected to interference modulation to generate optical path differences of delta in sequence 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 The four paths of interference signals of +3 lambda/4 are respectively sent to four signal detection units (5-8);
signal detection units (5-8): the device is used for detecting optical signals contained in interference signals, carrying out photoelectric conversion and digitization and then sending the optical signals into a processing inversion unit (9);
processing the inversion unit (9): the wind speed, the temperature and the aerosol extinction coefficient are inverted by using digital signals transmitted by the four signal detection units (5-8).
2. The spaceborne wind, temperature and aerosol synchronous observation laser radar as claimed in claim 1, wherein: the processing inversion unit (9) inverts the wind speed v, and specifically comprises the following steps:
wherein c is the speed of light, v is the speed of wind,
for the laser back scattering echo light interference phase difference,
for reference to the interference phase difference, σ, of the laser light 0 For emitting laser wave number, Δ 0 The reference optical path difference is obtained.
3. The spaceborne wind, temperature and aerosol synchronous observation laser radar as claimed in claim 1, wherein: the processing inversion unit (9) inverts the temperature T, and specifically comprises the following steps:
in the formula,. DELTA. 0 Q is an inversion constant, V (r) is a value at a distance r obtained by the following equation,
wherein, I 1 、I 2 、I 3 、I 4 Respectively, the detection signals output by the signal detection units (5-8), the corresponding optical path differences are respectively delta 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 And +3 lambda/4, wherein lambda is the wavelength of the single-frequency pulse laser.
4. The spaceborne wind, temperature and aerosol synchronous observation laser radar as claimed in claim 1, wherein: the processing inversion unit (9) inverts the aerosol extinction coefficient, and specifically comprises the following steps:
in the formula I m (r)＝I 0 (r)，I 0 (r) incident light intensity, beta, obtained at a distance r m (r) is the backscattering coefficient of atmospheric molecules at a distance r, I 0 (r) is calculated by the following formula,
wherein, I 1 、I 2 、I 3 、I 4 Are respectively a signal ofThe detection signals output by the detection units (5-8) respectively have corresponding optical path differences of delta 0 、Δ 0 +λ/4、Δ 0 +λ/2、Δ 0 +3 λ/4, λ is the wavelength of the single-frequency pulse laser.
5. The satellite-borne wind, temperature and aerosol synchronous observation laser radar according to claim 1, characterized in that: the single-frequency pulse laser satisfies the following conditions: the single wavelength selection range is 0.3-2.2 μm, and the relative line width is less than or equal to 2 x 10 -7 Lambda, relative stability of wavelength less than or equal to 1 x 10 -6 The pulse width is less than or equal to 5 microseconds, the repetition frequency is less than or equal to 40kHz, and the single pulse energy is more than or equal to 1 microseconds.
6. The spaceborne wind, temperature and aerosol synchronous observation laser radar as claimed in claim 1, wherein: the receiving telescope unit (2) adopts a transmission lens or a reflection lens, the transmittance of the laser wavelength emitted by the laser emitting unit (1) is more than or equal to 0.5, the effective caliber is more than or equal to 50mm, and the receiving field of view is more than or equal to 50 μ rad.
7. The spaceborne wind, temperature and aerosol synchronous observation laser radar as claimed in claim 1, wherein: the notch filter unit (3) is an optical element or a combination of elements with the capability of suppressing laser emission wavelength and transmitting adjacent wavelengths, including but not limited to FP etalon, molecular absorption cell, michelson interferometer.
8. The spaceborne wind, temperature and aerosol synchronous observation laser radar as claimed in claim 7, wherein: the suppression capability of the notch filter unit (3) on laser wavelength signals emitted by the laser emission unit (1) exceeds 10 times, and the suppression bandwidth is 0.4-3 multiplied by 10 -6 λ。
9. The spaceborne wind, temperature and aerosol synchronous observation laser radar as claimed in claim 1, wherein: the interferometer unit (4) is a Michelson interferometer or a Mach-Zehnder interferometer.
10. The spaceborne wind, temperature and aerosol synchronous observation laser radar as claimed in claim 1, wherein: the four signal detection units (5-8) adopt analog detection or photon detection devices with time resolution and photoelectric conversion capacity, including but not limited to PMT, APD, G-APD or PIN.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211139916.6A CN115639572A (en) | 2022-09-19 | 2022-09-19 | Satellite-borne laser radar for synchronously observing wind, temperature and aerosol |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211139916.6A CN115639572A (en) | 2022-09-19 | 2022-09-19 | Satellite-borne laser radar for synchronously observing wind, temperature and aerosol |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN115639572A true CN115639572A (en) | 2023-01-24 |
Family
ID=84941621
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211139916.6A Pending CN115639572A (en) | 2022-09-19 | 2022-09-19 | Satellite-borne laser radar for synchronously observing wind, temperature and aerosol |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115639572A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117784101A (en) * | 2024-02-27 | 2024-03-29 | 武汉大学 | Satellite-borne atmospheric laser radar signal simulation method and system |
-
2022
- 2022-09-19 CN CN202211139916.6A patent/CN115639572A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117784101A (en) * | 2024-02-27 | 2024-03-29 | 武汉大学 | Satellite-borne atmospheric laser radar signal simulation method and system |
| CN117784101B (en) * | 2024-02-27 | 2024-05-10 | 武汉大学 | Satellite-borne atmospheric laser radar signal simulation method and system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101710178B (en) | Real-time calibration high spectral resolution lidar device | |
| CN109143263B (en) | Mixed type wind measurement laser radar | |
| CN107462900B (en) | Gas component detection laser radar based on wavelength tunable laser source | |
| US11397149B2 (en) | Laser radar system apparatus for multi-wavelength measurement of atmospheric carbon dioxide concentration and vertical aerosol profile | |
| CN103630908B (en) | Laser frequency spectrum Measurement and calibration method in molecular scattering anemometry laser radar | |
| CN103592261B (en) | All-optical fiber temperature offset-type gas sensor and compensation method thereof | |
| CN108303706B (en) | Aerosol optical parameter detection method and hyperspectral laser radar detection system | |
| CN102384799B (en) | Frequency sweeping and data processing method based on Brillouin distributed fiber sensing system correlation detection scheme | |
| US20210116311A1 (en) | Self-calibration detection device and temperature demodulation method oriented to fiber raman temperature sensing system | |
| CN105334519B (en) | More atmospheric parameters based on triple channel F-P etalons while detected with high accuracy laser radar system | |
| CN101833089B (en) | Doppler anemometry laser radar sensitivity calibrating system and method | |
| CN110441792B (en) | Rayleigh scattering laser radar system capable of measuring wind and temperature simultaneously and related calibration method | |
| CN104777487A (en) | Atmospheric aerosol optical property measuring method and laser radar system | |
| CN107015243B (en) | Atmospheric temperature measurement method based on Brillouin laser radar system | |
| CN102636459A (en) | Forward scattering and transmission combined visibility measuring instrument and measuring method thereof | |
| CN101819275A (en) | Doppler laser radar device for measuring multiple meterological parameters | |
| CN104677421A (en) | Optical fiber temperature and strain sensing device and method based on high spectral resolution technology | |
| CN107102173B (en) | Calibration device and method of chirped grating based on optical frequency domain reflection principle | |
| CN102486402A (en) | Method and system for measuring pulse laser energy | |
| CN115639572A (en) | Satellite-borne laser radar for synchronously observing wind, temperature and aerosol | |
| CN110823262A (en) | High-sensitivity fiber grating sensing method and system based on light quantum technology | |
| CN112859112B (en) | Wind temperature detection laser radar and method based on rotating Raman-Doppler mechanism | |
| CN209590271U (en) | A kind of measuring device of space length | |
| CN113654580B (en) | Optical frequency domain reflection system for simultaneously measuring temperature and strain | |
| CN102445285B (en) | Peak searching method of Brillouin optical time domain reflectometer (BOTDR) system |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination |