CN210269905U - Airborne wind speed measurement laser radar system - Google Patents
Airborne wind speed measurement laser radar system Download PDFInfo
- Publication number
- CN210269905U CN210269905U CN201921191188.7U CN201921191188U CN210269905U CN 210269905 U CN210269905 U CN 210269905U CN 201921191188 U CN201921191188 U CN 201921191188U CN 210269905 U CN210269905 U CN 210269905U
- Authority
- CN
- China
- Prior art keywords
- optical fiber
- optical
- output end
- amplifier
- narrow
- 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.)
- Expired - Fee Related
Links
- 238000005259 measurement Methods 0.000 title claims abstract description 23
- 239000013307 optical fiber Substances 0.000 claims abstract description 133
- 230000003287 optical effect Effects 0.000 claims abstract description 99
- 238000012545 processing Methods 0.000 claims abstract description 39
- 239000004065 semiconductor Substances 0.000 claims abstract description 22
- 239000000835 fiber Substances 0.000 claims description 10
- 230000010287 polarization Effects 0.000 claims description 7
- 238000005253 cladding Methods 0.000 claims description 6
- 230000004927 fusion Effects 0.000 claims description 4
- 238000006243 chemical reaction Methods 0.000 claims description 3
- 238000001514 detection method Methods 0.000 claims description 3
- 239000007787 solid Substances 0.000 claims description 3
- 230000001360 synchronised effect Effects 0.000 claims description 3
- 238000003466 welding Methods 0.000 claims description 3
- 230000008901 benefit Effects 0.000 abstract description 6
- 238000013461 design Methods 0.000 abstract description 5
- 238000005070 sampling Methods 0.000 description 7
- 238000001228 spectrum Methods 0.000 description 7
- 238000000034 method Methods 0.000 description 5
- 239000000443 aerosol Substances 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000009825 accumulation Methods 0.000 description 3
- 230000010355 oscillation Effects 0.000 description 3
- 230000008859 change Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000004044 response Effects 0.000 description 2
- 229920006395 saturated elastomer Polymers 0.000 description 2
- 238000007476 Maximum Likelihood Methods 0.000 description 1
- 210000001015 abdomen Anatomy 0.000 description 1
- 230000003321 amplification Effects 0.000 description 1
- 239000005427 atmospheric aerosol Substances 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000009529 body temperature measurement Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000003199 nucleic acid amplification method Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000003595 spectral effect Effects 0.000 description 1
- 239000005437 stratosphere Substances 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
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
The utility model relates to an airborne wind speed measurement laser radar system, which comprises a narrow linewidth laser pulse light source module, a radar transmitting and receiving optical antenna module and a signal receiving and processing module; the narrow-linewidth laser pulse light source module comprises a narrow-linewidth seed light source, an optical fiber preamplifier, an acousto-optic modulator, a C-waveband boosting semiconductor optical amplifier and an optical fiber main amplifier; the radar transceiving optical antenna module is connected with a narrow-linewidth laser pulse light source module and comprises an optical fiber circulator, an optical switch and an optical antenna; the signal receiving and processing module is respectively connected with the narrow-linewidth laser pulse light source module and the radar transceiving optical antenna module; the signal receiving and processing module comprises an optical fiber adjustable attenuator, an optical fiber beam combiner, a balanced photoelectric detector, a signal processing circuit and an embedded computer. The utility model has the advantages of reasonable design, it is reliable and stable to use, can provide real-time wind speed data for machine carries atmospheric data computer, improves the aircraft performance, guarantee flight safety.
Description
Technical Field
The utility model belongs to the technical field of laser radar surveys, specific theory relates to an airborne wind speed measurement laser radar system.
Background
If the aircraft encounters strong airflow in the flying process, great threat can be caused to the flying safety, and forward atmospheric turbulence and transverse shear wind are one of the main reasons for causing flying air-crash accidents. Therefore, real-time measurement of atmospheric wind field and airflow changes during the flight of an aircraft is an important task requirement during the flight.
The equipment for measuring wind speed installed on an aircraft can be divided into two modes of fixed-point measurement and remote measurement for measuring distance. In the fixed-point wind speed measuring equipment, the traditional airborne wind speed measuring equipment is an airspeed head, and the pressure change caused by dynamic pressure of the air speed measuring equipment cannot be accurately measured in the stratosphere low-air-density low-dynamic flying environment. Although the embedded atmospheric data system adopted by the novel fighter plane can replace the traditional airspeed head, the measuring range and the precision of the pressure sensor of the high-altitude low-speed aircraft cannot meet the requirements. The hot-wire type and hot-film type anemometers mainly calculate the wind speed by detecting the heat-sensitive temperature dissipation and heat energy transfer rate exposed in the fluid, but the two types of anemometers are limited by single-end input signal saturation, the measuring range of the wind speed is not high, and certain response time is required for temperature measurement. Although the micro-pressure sensor has the advantages of high sensitivity, light weight, corrosion resistance and the like, the material has the problem of temperature drift, the calibration is needed during continuous working, and the speed measurement precision is not high. The ultrasonic velocimeter measures the propagation time of ultrasonic waves in a certain direction based on the Doppler effect of relative motion, can obtain the propagation speed of downwind or upwind, and has high precision, but because the transmitting and receiving devices of sound waves have a blocking effect on wind in the atmosphere, large errors are easily caused particularly when the wind and the sound waves are transmitted and received in the same direction, and the ultrasonic velocimeter has a complex structure and is not easy to realize on a floating platform. Fixed point anemometry devices also have the common disadvantage that the airflow is subject to variations due to the aircraft profile, requiring calibration for a particular aircraft profile and device installation location.
The typical representation of the wind speed telemetering equipment is a laser wind measuring radar, and the wind speed telemetering equipment has the advantages of high precision, quick response, wide coverage range, no influence of a carrying platform on a measuring result and the like. There are currently examples reported in the united states, japan, france, and other countries that use airborne lidar to remotely measure aircraft wind speed.
Disclosure of Invention
To the problem among the above-mentioned background art, the utility model provides a structural design is reasonable, uses reliable and stable, can provide real-time wind speed data for machine carries atmospheric data computer, improves the aircraft performance, and guarantee flight safety's machine carries wind speed and measures laser radar system.
The technical scheme of the utility model as follows:
the airborne wind speed measuring laser radar system comprises a narrow-linewidth laser pulse light source module, a radar transceiving optical antenna module and a signal receiving and processing module; the narrow-linewidth laser pulse light source module comprises a narrow-linewidth seed light source, an optical fiber preamplifier, an acousto-optic modulator, a C-waveband boosting semiconductor optical amplifier and an optical fiber main amplifier; the output end of the narrow-linewidth seed light source is connected with the input end of the optical fiber preamplifier; the output end of the optical fiber preamplifier is connected with the input end of the acousto-optic modulator; the output end of the acousto-optic modulator is connected with the input end of the C-band boosting semiconductor optical amplifier; the output end of the C-band boosting semiconductor optical amplifier is connected with the input end of the optical fiber main amplifier; the radar transceiving optical antenna module is connected with the narrow-linewidth laser pulse light source module and comprises an optical fiber circulator, an optical switch and an optical antenna; the input end of the optical fiber circulator is connected with the output end of the optical fiber main amplifier; the input end of the optical switch is connected with one output end of the optical fiber circulator through an optical fiber, and the output end of the optical switch is connected with the optical antenna; the signal receiving and processing module is respectively connected with the narrow linewidth laser pulse light source module and the radar transceiving optical antenna module; the signal receiving and processing module comprises an optical fiber adjustable attenuator, an optical fiber beam combiner, a balanced photoelectric detector, a signal processing circuit and an embedded computer; the input end of the optical fiber adjustable attenuator is connected with the other output end of the optical fiber preamplifier; the input end of the optical fiber beam combiner is respectively connected with the other output end of the optical fiber circulator and the output end of the optical fiber adjustable attenuator; the input end of the balance photoelectric detector is connected with the output end of the optical fiber beam combiner; the input end of the signal processing circuit is connected with the output end of the balanced photoelectric detector, and the output end of the signal processing circuit is connected to the embedded computer.
The airborne wind speed measurement laser radar system, wherein: the narrow linewidth seed light source can adopt any one of a single-frequency narrow linewidth semiconductor laser, a DBR/DFB optical fiber laser and a solid laser which output continuous laser in a 1.5 mu m waveband.
The airborne wind speed measurement laser radar system, wherein: the optical fiber pre-amplifier adopts a single-mode polarization-maintaining optical fiber amplifier or a double-cladding single-mode polarization-maintaining optical fiber amplifier, and further adopts a multistage optical fiber amplifier formed by combining the single-mode polarization-maintaining optical fiber amplifier and the double-cladding single-mode polarization-maintaining optical fiber amplifier.
The airborne wind speed measurement laser radar system, wherein: the C-band boosting semiconductor optical amplifier is a pigtail with a polarization maintaining fiber and adopts an electric pulse pump synchronous with input pulse light; the optical fiber main amplifier is a double-cladding polarization-maintaining optical fiber amplifier.
The airborne wind speed measurement laser radar system, wherein: the optical switch can adopt any one of a mechanical optical switch with a polarization-maintaining fiber pigtail, a mems optical switch and a magneto-optical switch; and the optical fiber connection between the optical switch and the optical fiber circulator adopts a fusion welding mode.
The airborne wind speed measurement laser radar system, wherein: the optical antennas are three optical antennas with the same structure, and all adopt single-chip aspheric mirrors, the light-passing aperture of each aspheric mirror is 50mm, and the focal length of each aspheric mirror is 180 mm; the three optical antennas point to different directions, output light beams are focused to the positions 200 meters ahead of the three optical antennas, and the Rayleigh length of a focused light spot is 30 meters.
The airborne wind speed measurement laser radar system, wherein: and two input ends of the optical fiber beam combiner are connected with the other output end of the optical fiber circulator and the output end of the optical fiber adjustable attenuator by adopting an optical fiber flange plate.
The airborne wind speed measurement laser radar system, wherein: the balanced photoelectric detector adopts a balanced photoelectric detector with the model number of PDB 460C-AC; the balanced photoelectric detector with the model number PDB460C-AC is provided with two optical input interfaces and a radio frequency signal output interface; the two optical input interfaces of the balanced photoelectric detector with the model number of PDB460C-AC are both FC structural interfaces; the radio frequency signal output interface of the balanced photoelectric detector with the model number of PDB460C-AC is an SMA structure interface.
The airborne wind speed measurement laser radar system, wherein: the output end of the optical fiber combiner is directly inserted into an FC structural interface of the balanced photoelectric detector with the model number of PDB460C-AC by adopting an FC/APC joint; in the FC structural interface of the balanced photoelectric detector with the model of PDB460C-AC, light beams are emitted from optical fibers and irradiate onto the photosensitive surface of the balanced photoelectric detector with the model of PDB460C-AC to realize light detection; the balanced photoelectric detector with the model number of PDB460C-AC outputs the electric signal after photoelectric conversion to the signal processing circuit through an SMA structure interface.
The airborne wind speed measurement laser radar system, wherein: the input end of the signal processing circuit is connected with the SMA structure interface of the balanced photoelectric detector with the model number of PDB460C-AC through a coaxial cable, and the output end of the signal processing circuit is connected to the embedded computer through a network cable.
Has the advantages that:
the laser radar system for measuring airborne wind speed has simple and reasonable structural design, amplifies pulse light by using the semiconductor pulse light amplifier, increases the modulation depth of the pulse, can solve the problem of pulse leakage by using only one acousto-optic modulator in the system, reduces the volume of the laser and reduces the cost; meanwhile, pulse laser is emitted, a light beam is focused to a position hundreds of meters ahead through an optical antenna to form a Rayleigh length region, and a system only receives and processes atmospheric aerosol backscatter signals in the laser beam of the region; the advantage of high peak power of the pulse laser is fully utilized to obtain a strong echo signal, and the method is suitable for being used in an environment with high air aerosol density being thin.
Drawings
FIG. 1 is a schematic diagram of the structure of the airborne wind speed measurement laser radar system of the present invention;
fig. 2 is a diagram of the directional pattern of the distribution of the optical antenna of the airborne wind speed measurement laser radar system of the present invention.
Detailed Description
As shown in fig. 1 and 2, the utility model discloses airborne wind speed measurement laser radar system, including narrow linewidth laser pulse light source module 1, radar receiving and dispatching optical antenna module 2 and signal reception processing module 3
The narrow-linewidth laser pulse light source module 1 comprises a narrow-linewidth seed light source 11, an optical fiber preamplifier 12, an acousto-optic modulator 13, a C-band boost semiconductor optical amplifier 14 and an optical fiber main amplifier 15.
The narrow-linewidth seed light source 11, the optical fiber preamplifier 12, the acousto-optic modulator 13, the C-band boosting semiconductor optical amplifier 14 and the optical fiber main amplifier 15 are connected in a locking mode after being inserted into an optical fiber flange plate through respective own optical fiber FC/APC joints.
The output end of the narrow-linewidth seed light source 11 is connected with the input end of the optical fiber preamplifier 12; wherein, the narrow linewidth seed light source 11 can adopt any one of a single-frequency narrow linewidth semiconductor laser, a DBR/DFB fiber laser and a solid laser which output continuous laser in a 1.5 μm waveband; the spectral line width of the narrow-line-width seed light source 11 is less than 15kHz, the polarization state is linear polarization, the single-mode polarization-maintaining optical fiber outputs light, and the output light power is 1-100 mW.
The output end of the optical fiber preamplifier 12 is connected with the input end of an acousto-optic modulator 13; the optical fiber preamplifier 12 uses a single-mode polarization-maintaining optical fiber amplifier or a double-clad single-mode polarization-maintaining optical fiber amplifier, or a multi-stage optical fiber amplifier formed by combining the single-mode polarization-maintaining optical fiber amplifier and the double-clad single-mode polarization-maintaining optical fiber amplifier.
The output end of the acousto-optic modulator 13 is connected with the input end of a C-band boosting semiconductor optical amplifier 14; the modulation pulse rising edge of the acousto-optic modulator 13 is less than 100ns, the frequency is shifted up by 80MHz, the light beam output by the fiber preamplifier 12 is modulated into pulse light with the full width of 500ns, and the pulse repetition frequency is 10 kHz.
The output end of the C-band boosting semiconductor optical amplifier 14 is connected with the input end of an optical fiber main amplifier 15; the C-band boosting semiconductor optical amplifier 14 is a pigtail with a polarization maintaining fiber, and is pumped by an electric pulse synchronized with the input pulse light.
The fiber main amplifier 15 is a double-clad polarization maintaining fiber amplifier.
The optical fiber preamplifier 12 receives linearly polarized continuous laser output by the narrow-linewidth seed light source 11, the optical fiber preamplifier 12 processes a light beam and transmits the processed light beam to the acousto-optic modulator 13, the acousto-optic modulator 13 modulates the light beam output by the optical fiber preamplifier 12 into pulsed light, the acousto-optic modulator 13 transmits the modulated pulsed light to the C-band boost semiconductor optical amplifier 14, the C-band boost semiconductor optical amplifier 14 further amplifies and modulates the light pulse, the C-band boost semiconductor optical amplifier 14 transmits the further amplified and modulated light pulse to the optical fiber main amplifier 15, and the optical fiber main amplifier 15 amplifies and outputs the power of the pulsed light.
The radar transceiving optical antenna module 2 is connected to the narrow linewidth laser pulse light source module 1, and includes an optical fiber circulator 21, an optical switch 22, and an optical antenna 23.
The input end of the optical fiber circulator 21 is connected with the output end of the optical fiber main amplifier 15; wherein, the input end optical fiber of the optical fiber circulator 21 and the output end optical fiber of the optical fiber main amplifier 15 are welded together by an optical fiber fusion splicer.
The optical switch 22 has an input end and a plurality of output ends, the input end of the optical switch 22 is connected with one of the output ends of the optical fiber circulator 21 through an optical fiber, and the output end of the optical switch 22 is connected with three optical antennas 23; the optical switch 22 may be any one of a mechanical optical switch with a polarization maintaining fiber pigtail, a mems optical switch, and a magneto-optical switch; the optical switch 22 can switch the input light beam to any path for output through electric signal control, when the laser radar works, the light beam is switched in sequence and emitted from each output end of the optical switch 22 through the corresponding optical antenna 23, and then the operation is repeated in a circulating way; meanwhile, the optical fiber connection between the optical switch 22 and the optical fiber circulator 21 adopts a fusion welding mode, so that the interference of reflected light of the end face of the optical fiber with local oscillation light when a connector is adopted is avoided.
The three optical antennas 23 have the same structure, and all adopt a single-chip aspheric mirror, and the aperture of the aspheric mirror is 50mm, and the focal length is 180 mm; wherein, three optical antennas 23 point to different directions, and the output beam all focuses to 200 meters in front of each, and the rayleigh length of the focus facula is 30 meters.
The signal receiving and processing module 3 is respectively connected with the narrow-linewidth laser pulse light source module 1 and the radar transceiving optical antenna module 2, and the signal receiving and processing module 3 comprises an optical fiber adjustable attenuator 31, an optical fiber beam combiner 32, a balanced photoelectric detector 33, a signal processing circuit 34 and an embedded computer 35.
The optical fiber adjustable attenuator 31 is used to adjust the output local oscillation optical power of the optical fiber preamplifier 12, and its input end is connected to the other output end of the optical fiber preamplifier 12 of the narrow-linewidth laser pulse light source module 1.
The optical fiber combiner 32 adopts a 2 × 2 optical fiber combiner, and two input ends of the optical fiber combiner are respectively connected with the other output end of the optical fiber circulator 21 of the radar transceiving optical antenna module 2 and the output end of the optical fiber adjustable attenuator 31; two input ends of the optical fiber combiner 32 are connected with the other output end of the optical fiber circulator 21 and the output end of the optical fiber adjustable attenuator 31 by adopting an optical fiber flange.
The input end of the balanced photodetector 33 is connected to the two output ends of the optical fiber combiner 32. Wherein, the balanced photodetector 33 can adopt a model PDB460C-AC balanced photodetector manufactured by Thorlabs of America; the balanced photoelectric detector with the model number of PDB460C-AC is provided with two optical input interfaces and a radio frequency signal output interface; the two optical input interfaces of the balanced photoelectric detector with the model number of PDB460C-AC are both FC structural interfaces; the radio frequency signal output interface of the balanced photodetector with the model number of PDB460C-AC is an SMA structure interface. The output end of the optical fiber combiner 32 can be directly inserted into an FC structural interface of a balanced photoelectric detector with the model number PDB460C-AC by adopting an FC/APC joint; in the FC structural interface of the balanced photodetector model PDB460C-AC, a light beam is emitted from the optical fiber and irradiates the photosensitive surface of the balanced photodetector model PDB460C-AC to realize light detection. The PDB460C-AC balanced photodetector outputs the photoelectrically converted electrical signal to the signal processing circuit 34 through the SMA structure interface.
The input end of the signal processing circuit 34 (adopting an SMA structure interface) is connected with the output end of the balanced photodetector 33 (namely, the SMA structure interface of the balanced photodetector with model number PDB 460C-AC) through a coaxial cable, and the output end of the signal processing circuit 34 is connected to the embedded computer 35 through a network cable; wherein, the signal processing circuit 34 collects and processes the backscattering signals of aerosol particles in the rayleigh length region of the focused facula of the three optical antennas 23; the sampling frequency of the signal processing circuit 34 is 400MHz, the precision is 14bit, and the signal is processed by programming an FPGA (field programmable gate array).
For the echo signal received by each optical antenna 23, the single signal sampling time of the signal processing circuit 34 can be determined to be 500ns according to the pulse width of 500ns, and the number of single sampling points can be determined to be 200 points according to the sampling frequency of 400 MHz; zero filling is carried out on 200 point data sampled every time to 1024 points, a window function is added, fast Fourier transform is carried out, then a power spectrum is calculated, the frequency spectrum resolution after FFT transform is carried out is less than 0.4MHz, and the corresponding speed precision is less than 0.3 m/s; the speed measurement precision can be improved through a power spectrum accumulation algorithm, 5000 times of accumulation is carried out on the signal power spectrum measured by the single optical antenna 23, and finally the realized speed precision is less than 0.1 m/s.
The signal acquisition processing flow of the signal processing circuit 34 is as follows:
(1) according to the fact that the repetition frequency of laser pulse is 10KHz (or 5kHz, 8kHz and the like), the frequency of a trigger signal for signal acquisition is also 10KHz, and the time interval between two triggers is 100 mus;
(2) after receiving the trigger signal, the signal processing circuit 34 performs high-speed digital signal conversion on the analog signal and then collects the analog signal, wherein the number of sampling points is 200;
(3) after sampling is finished, zero padding is carried out on the sampled data to 1024 points, and then Fourier transformation is carried out; obtaining a power spectrum, accumulating the power spectrum, continuing to perform the next processing if the accumulated times reach the specified 5000 times, and otherwise continuing to wait for a trigger signal and repeatedly executing the steps (2) - (3);
(4) after the accumulation is finished, the subsequent processing is continued, the corresponding frequency is obtained for the power spectrum data accumulated before by adopting a maximum likelihood estimation algorithm, the corresponding radial wind speed is calculated, and the radial wind speed data is output to the embedded computer 35;
(5) the transmitting optical antenna 23 is switched, and steps (2) - (5) are repeatedly performed.
Because the balance photoelectric detector 33 is saturated by the optical signal due to the reflection of the end face of the optical fiber head and the reflection of the lens of the optical antenna 23, the saturated part of the signal is removed from the sampling point used for calculation, and the data collected each time is 200 points of data which is delayed for a certain time from the receipt of the trigger signal and is centered on the data at the 200-meter focusing point.
As shown in fig. 2, a right-hand coordinate system is established with the aircraft nose direction as the + X-axis direction and the aircraft belly direction as the + Z-axis direction; the three optical antennas 23 are uniformly distributed at intervals of 120 degrees along the circumference, have included angles of 15 degrees with the direction of the + X axis, and point to different directions.
Under the optical antenna arrangement condition shown in fig. 2, the embedded computer 35 receives the radial wind speeds in the pointing directions of the three optical antennas 23 sent by the signal processing circuit 34, respectively solves the wind speed components of the radial wind speeds on the coordinate axes of the airframe, and sums the scalar values on the coordinate axes to obtain the respective wind speed components of the airframe of the airplane in the direction of the X, Y, Z axis.
The working principle of the utility model is as follows:
the small-power laser output by the narrow-linewidth seed light source 11 is amplified through the optical fiber preamplifier 12, the optical fiber preamplifier 12 is divided into two paths to output, one path outputs light with small power as a local oscillation signal, the other path outputs light with most power which is modulated into pulse light by the acousto-optic modulator 13, a frequency shift of tens of megahertz is generated at the same time, the pulse light is amplified through the C-band boosting semiconductor optical amplifier 14, the pulse modulation depth is increased at the same time, and finally the laser is output after being subjected to power amplification through the optical fiber main amplifier 15; the output light beam enters from one input port of the optical fiber circulator 21, exits through two output ports, is switched in the direction of the light beam by the optical switch 22 and then is emitted through the three optical antennas 23 with different directions; each optical antenna 23 emits a focused measuring beam forward, and each optical antenna 23 focuses the emitted beams at the same distance, which is several hundreds of meters; an echo signal which is generated by Doppler frequency shift of laser scattered by aerosol in the atmosphere in a Rayleigh length area focused by the light beam returns along a transmitting light path, and the echo signal is output from the optical fiber circulator 21; the echo signals and the local oscillator light are combined by the 2 x 2 optical fiber beam combiner 32 and then enter the balanced photoelectric detector 33 to generate heterodyne signals which are sent to the signal processing circuit 34 to extract Doppler frequency, so that radial velocity information of each light beam is obtained; after the radial velocity of each light beam is measured, wind field information is calculated in the embedded computer 35 by a wind field inversion algorithm.
The utility model has the advantages of reasonable design, it is reliable and stable to use, can provide real-time wind speed data for machine carries atmospheric data computer, improves the aircraft performance, guarantee flight safety.
According to the technical scheme, pulsed light is used for focusing to measure the backscattering signals of the aerosol in the air, the radial wind speed in each direction is measured through different directions of the multiple optical antennas, the airborne wind speed measuring radar can be realized after the wind field inversion, and the airborne wind speed measuring radar is suitable for the application fields of vacuum speed measurement of aircrafts and the like.
According to the above embodiment, alright realize the utility model discloses well. It is worth explaining, under the prerequisite based on above-mentioned design principle, for solving same technical problem, even in some insubstantial changes or retouching that make on the basis of the structure disclosed in the utility model, if increase optical antenna quantity, change optical antenna and lead to changes such as light bore, focus different distances, the essence of the technical scheme who adopts still with the utility model discloses, so it also should be in the protection scope of the utility model.
Claims (10)
1. An airborne wind speed measurement laser radar system is characterized in that: the radar system comprises a narrow-linewidth laser pulse light source module, a radar transmitting and receiving optical antenna module and a signal receiving and processing module;
the narrow-linewidth laser pulse light source module comprises a narrow-linewidth seed light source, an optical fiber preamplifier, an acousto-optic modulator, a C-waveband boosting semiconductor optical amplifier and an optical fiber main amplifier; the output end of the narrow-linewidth seed light source is connected with the input end of the optical fiber preamplifier; the output end of the optical fiber preamplifier is connected with the input end of the acousto-optic modulator; the output end of the acousto-optic modulator is connected with the input end of the C-band boosting semiconductor optical amplifier; the output end of the C-band boosting semiconductor optical amplifier is connected with the input end of the optical fiber main amplifier;
the radar transceiving optical antenna module is connected with the narrow-linewidth laser pulse light source module and comprises an optical fiber circulator, an optical switch and an optical antenna; the input end of the optical fiber circulator is connected with the output end of the optical fiber main amplifier; the input end of the optical switch is connected with one output end of the optical fiber circulator through an optical fiber, and the output end of the optical switch is connected with the optical antenna;
the signal receiving and processing module is respectively connected with the narrow linewidth laser pulse light source module and the radar transceiving optical antenna module; the signal receiving and processing module comprises an optical fiber adjustable attenuator, an optical fiber beam combiner, a balanced photoelectric detector, a signal processing circuit and an embedded computer; the input end of the optical fiber adjustable attenuator is connected with the other output end of the optical fiber preamplifier; the input end of the optical fiber beam combiner is respectively connected with the other output end of the optical fiber circulator and the output end of the optical fiber adjustable attenuator; the input end of the balance photoelectric detector is connected with the output end of the optical fiber beam combiner; the input end of the signal processing circuit is connected with the output end of the balanced photoelectric detector, and the output end of the signal processing circuit is connected to the embedded computer.
2. The airborne anemometry lidar system of claim 1, wherein: the narrow linewidth seed light source can adopt any one of a single-frequency narrow linewidth semiconductor laser, a DBR/DFB optical fiber laser and a solid laser which output continuous laser in a 1.5 mu m waveband.
3. The airborne anemometry lidar system of claim 1, wherein: the optical fiber pre-amplifier adopts a single-mode polarization-maintaining optical fiber amplifier or a double-cladding single-mode polarization-maintaining optical fiber amplifier, and further adopts a multistage optical fiber amplifier formed by combining the single-mode polarization-maintaining optical fiber amplifier and the double-cladding single-mode polarization-maintaining optical fiber amplifier.
4. The airborne anemometry lidar system of claim 1, wherein: the C-band boosting semiconductor optical amplifier is a pigtail with a polarization maintaining fiber and adopts an electric pulse pump synchronous with input pulse light; the optical fiber main amplifier is a double-cladding polarization-maintaining optical fiber amplifier.
5. The airborne anemometry lidar system of claim 1, wherein: the optical switch can adopt any one of a mechanical optical switch with a polarization-maintaining fiber pigtail, a mems optical switch and a magneto-optical switch; and the optical fiber connection between the optical switch and the optical fiber circulator adopts a fusion welding mode.
6. The airborne anemometry lidar system of claim 1, wherein: the optical antennas are three optical antennas with the same structure, and all adopt single-chip aspheric mirrors, the light-passing aperture of each aspheric mirror is 50mm, and the focal length of each aspheric mirror is 180 mm; the three optical antennas point to different directions, output light beams are focused to the positions 200 meters ahead of the three optical antennas, and the Rayleigh length of a focused light spot is 30 meters.
7. The airborne anemometry lidar system of claim 1, wherein: and two input ends of the optical fiber beam combiner are connected with the other output end of the optical fiber circulator and the output end of the optical fiber adjustable attenuator by adopting an optical fiber flange plate.
8. The airborne anemometry lidar system of claim 1, wherein: the balanced photoelectric detector adopts a balanced photoelectric detector with the model number of PDB 460C-AC; the balanced photoelectric detector with the model number PDB460C-AC is provided with two optical input interfaces and a radio frequency signal output interface; the two optical input interfaces of the balanced photoelectric detector with the model number of PDB460C-AC are both FC structural interfaces; the radio frequency signal output interface of the balanced photoelectric detector with the model number of PDB460C-AC is an SMA structure interface.
9. The airborne anemometry lidar system of claim 8, wherein: the output end of the optical fiber combiner is directly inserted into an FC structural interface of the balanced photoelectric detector with the model number of PDB460C-AC by adopting an FC/APC joint; in the FC structural interface of the balanced photoelectric detector with the model of PDB460C-AC, light beams are emitted from optical fibers and irradiate onto the photosensitive surface of the balanced photoelectric detector with the model of PDB460C-AC to realize light detection; the balanced photoelectric detector with the model number of PDB460C-AC outputs the electric signal after photoelectric conversion to the signal processing circuit through an SMA structure interface.
10. The airborne anemometry lidar system of claim 8, wherein: the input end of the signal processing circuit is connected with the SMA structure interface of the balanced photoelectric detector with the model number of PDB460C-AC through a coaxial cable, and the output end of the signal processing circuit is connected to the embedded computer through a network cable.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2018211980505 | 2018-07-27 | ||
| CN201821198050 | 2018-07-27 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210269905U true CN210269905U (en) | 2020-04-07 |
Family
ID=70014469
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201921191188.7U Expired - Fee Related CN210269905U (en) | 2018-07-27 | 2019-07-26 | Airborne wind speed measurement laser radar system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210269905U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110261644A (en) * | 2018-07-27 | 2019-09-20 | 成都信息工程大学 | A kind of airborne measuring wind speed laser radar system |
| CN111211858A (en) * | 2020-04-22 | 2020-05-29 | 成都坤恒顺维科技股份有限公司 | C-band network transceiving system based on time division duplex |
| WO2023015589A1 (en) * | 2021-08-10 | 2023-02-16 | 南京牧镭激光科技有限公司 | Adaptive multi-channel wind measurement lidar system |
-
2019
- 2019-07-26 CN CN201921191188.7U patent/CN210269905U/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110261644A (en) * | 2018-07-27 | 2019-09-20 | 成都信息工程大学 | A kind of airborne measuring wind speed laser radar system |
| CN110261644B (en) * | 2018-07-27 | 2024-05-28 | 成都信息工程大学 | Airborne wind speed measurement laser radar system |
| CN111211858A (en) * | 2020-04-22 | 2020-05-29 | 成都坤恒顺维科技股份有限公司 | C-band network transceiving system based on time division duplex |
| WO2023015589A1 (en) * | 2021-08-10 | 2023-02-16 | 南京牧镭激光科技有限公司 | Adaptive multi-channel wind measurement lidar system |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN110261644B (en) | Airborne wind speed measurement laser radar system | |
| CN210269905U (en) | Airborne wind speed measurement laser radar system | |
| CN1316262C (en) | Detection method and laser radar of Raman-Mie scattering laser atmospheric signal | |
| CN110308454B (en) | Wind speed measurement system and method of quasi-non-blind-area Doppler coherent laser radar | |
| CN102692622B (en) | Laser detection method based on dense pulses | |
| CN109990843B (en) | Method and device for monitoring flight speed and environmental parameters of aircraft | |
| CN109164430A (en) | Utilize the system and method for return laser beam and laser spot detection target position and posture | |
| US9188677B2 (en) | Imaging doppler lidar for wind turbine wake profiling | |
| CN111398993B (en) | Non-blind area pulse coherent wind lidar system | |
| CN113391327A (en) | Doppler wind finding radar system and method based on continuous laser | |
| CN110161280B (en) | Hybrid detection Doppler laser radar wind speed measurement system and measurement method thereof | |
| CN113640813A (en) | Multi-beam single-photon detection laser radar | |
| CN110531378B (en) | Continuous wave laser coherent wind-finding radar system of wind turbine generator | |
| JP2022170737A (en) | Multi-wavelength Doppler lidar | |
| CN113640832A (en) | Multi-beam coherent detection laser radar | |
| CN203720351U (en) | Laser radar measuring instrument for measuring object angles and angular velocities accurately | |
| DK2795344T3 (en) | SINGLE LASER, FIBER BASED OPTICAL SENSOR AND REPLACEMENT SYSTEM AND METHOD OF MEASURING SPEED IN ATMOSPHERIC AIR FLOW | |
| CN215297681U (en) | Variable-focus high signal-to-noise ratio wind lidar system | |
| CN112764056B (en) | Composite detection laser wind measuring radar with high-low altitude remote detection capability | |
| Wang et al. | Design and calibration of a coherent wind measurement system with paraxial structure | |
| CN219435047U (en) | Pulse laser Doppler velocimeter for measuring low-altitude flying carrier speed | |
| Mylapore et al. | Development and wind tunnel testing of a novel 3D scanning lidar for global velocimetry | |
| CN218567610U (en) | Laser ranging system based on optical feedback semiconductor laser dynamics | |
| CN102508254B (en) | Square output laser beam projectile launching track test system | |
| CN114791606A (en) | Laser radar detection method and device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200407 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |