CN208805572U - A kind of radar target recognition equipment - Google Patents
A kind of radar target recognition equipment Download PDFInfo
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- CN208805572U CN208805572U CN201821496931.5U CN201821496931U CN208805572U CN 208805572 U CN208805572 U CN 208805572U CN 201821496931 U CN201821496931 U CN 201821496931U CN 208805572 U CN208805572 U CN 208805572U
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Abstract
The utility model relates to Air Vehicle Detection technical fields, disclose a kind of radar target recognition equipment.It is created by the utility model, it can provide a kind of laser radar system that can carry out target identification to concealed aircraft based on Raman scattering principle, the pulse laser of specific wavelength can be emitted to airspace to be measured by laser radar, and receive the Raman scattering light from airspace to be measured, then pass through photoelectric conversion and spectral matching factor, the Raman spectrum of available reflection airspace chemical component to be measured, subsequently when finding to contain strong carbon dioxide and steam ingredient in the Raman spectrum, can further suspected target quickly be scanned and be tracked using pitching driving mechanism and horizontal drive mechanism driving laser radar, identify whether suspected target is doubtful aircraft finally by conventional rate characteristics analysis, and then a kind of ancillary equipment can be provided to existing radar system, the stealthy mechanism of existing stealth aircraft is broken through from principle, Promote the development of Defence business.
Description
Technical field
The utility model belongs to Air Vehicle Detection technical field, and in particular to a kind of radar target recognition equipment.
Background technique
Explorer vehicle is the original intention for designing radar.Past, the detection for aircraft such as various aircrafts, rocket, guided missiles
Radio radar is relied primarily on, such as millimeter wave and microwave radar.The advantages of these radars, penetration power was strong it is obvious that power is big, no
By Influence of cloud, therefore detection range is remote.However, with the development of electromagnetic countermeasure technology and the development of new material, radio thunder
Up to increasingly by various limitations, for example Active Radar station is easy to stick one's chin out to become the target preferentially attacked, by force
Electromagnetic interference may make a piece of snow noise of radar screen and fail.More seriously, what the western countries such as U.S. developed is hidden
Shape aircraft, such as B-2 bomber, radar cross section is dropped to about the 1% of conventional airplane, infrared letter by F-35 fighter plane etc.
Number it is reduced to about the 10% of conventional airplane, this will be a serious challenge to the radar system in China.
For normal radar when detecting target, what is utilized is all the direct echo-signal of target itself.Infrared detector can be with
The presence of target is perceived by the temperature difference to target temperature and background.In view of these situations, the stealthy side of present aircraft
Method, mainly utilize two o'clock: 1. reduce radar cross section, for example design special shape and reduce backwards to echo-signal, in machine
Body coats absorbing material, absorbs the electromagnetic wave from microwave to light wave；2. reducing the infrared signal of wake flow, for example wake flow is carried out pre-
First cool down, air jet pipe is hidden in machine back, it is heat-insulated etc. to engine jet pipe.However these stealth technologies also have lacking for itself
Point.
It is well known that engine will generate wake flow when jet aircraft flight, unless engine does not work, then flying
Row device also just loses power.The characteristics of aircraft wake, in addition to high temperature, the characteristics of there are also high pressures, high speed, chemical composition also with
Greatly, main component is the carbon dioxide and steam and a part of burning particles object of high concentration to atmosphere difference.As long as having determined
The presence of wake flow, can find the track of aircraft, to be tracked, guided or even be smashed target.The purpose of the present invention is just
It is to detect the wake flow of this high temperature, high pressure, high speed, and pass through the Raman scattering detection of turbulent flow and particulate matter strong in wake flow
Its chemical composition, so that it is determined that it exists and spatial position.
It is used for the technology of Atmospheric Survey about Raman scattering, there are many processing methods to be reported, such as
Detection of the CN200910237425 for atmospheric temperature, multifunction of the CN200710018406 about atmospheric environment detection system
Design, measurement of the CN201310057961 for aerosol, measurement etc. of the CN201210322203 about steam in cloud and mist.But
It is that the equipment that Raman scattering is applied to Air Vehicle Detection or system are reported not yet, therefore the purpose of the present invention is to provide one
Kind can carry out the laser radar apparatus of target identification based on Raman scattering principle to concealed aircraft.
Utility model content
In order to solve the problems, such as that existing normal radar is difficult to that concealed aircraft is effectively detected and identified, this is practical new
Type is designed to provide a kind of novel radar target recognition equipment.
The technology employed by the present utility model is
A kind of radar target recognition equipment, including host computer, Raman spectrometer, laser radar, support frame, pedestal, pitching
Driving mechanism and horizontal drive mechanism；
The laser radar includes shell and is built in the intracorporal laser of the shell, dichroscope, plano-concave lens, card
Fill in Green's telescope, photoelectric sensor and bandpass filter, wherein the laser, the dichroscope, the plano-concave lens
With the Cassegrain telescope from rear to preceding successively arranged for interval, the dichroscope turns forward 45 degree of settings, described flat
Concavees lens are located at the dead astern of the primary mirror central openings of the Cassegrain telescope and confocal with the Cassegrain telescope,
The photosurface of the photoelectric sensor is located at the underface of the dichroscope, the input terminal communication connection of the bandpass filter
The output end of the photoelectric sensor；
Support frame as described above and the pedestal are sequentially located at the underface of the shell, wherein the top of support frame as described above is logical
Cross and extend transversely through the trunnion axis of the housing central section and connect with the housing into rotation, the bottom of support frame as described above by vertical axis with
The base rotation connection；
The pitching driving mechanism is mounted in the internal cavities of support frame as described above, and the trunnion axis that is sequentially connected, can
By driving the trunnion axis rotating manner that the shell is driven to do pitching movement, the horizontal drive mechanism in vertical direction
It is mounted in the internal cavities of the pedestal, and the vertical axis that is sequentially connected, it can be by driving the vertical axis rotating manner
Support frame as described above is driven to horizontally rotate；
The output end of the host computer communicates to connect the laser, the pitching driving mechanism and the horizontal drive respectively
The controlled end of motivation structure, the input terminal of the host computer communicate to connect the output end of the Raman spectrometer, the Raman spectrum
The input terminal of instrument communicates to connect the output end of the bandpass filter.
Optimization, further include the display for communicating to connect the host computer.
Optimization, the pitching driving mechanism includes pitching driving motor, pitching reduction gearbox, the first synchronous pulley, synchronization
Band and the second synchronous pulley, wherein the controlled end of the pitching driving motor communicates to connect the output end of the host computer, described
For the rotation output end of pitching driving motor by pitching reduction gearbox transmission connection first synchronous pulley, described first is same
It walks belt wheel and second synchronous pulley, the coaxially connected level of the second synchronous pulley is connected by the toothed belt transmission
Axis.
Specifically, support frame as described above is made of horizontal supporting portion and two supporting legs, wherein in the horizontal supporting portion
The pitching driving motor and the pitching reduction gearbox are installed in portion's cavity, pacified in the wherein internal cavities of a supporting leg
Fill the toothed belt transmission structure being made of first synchronous pulley, the synchronous belt and second synchronous pulley.
Optimization, the horizontal drive mechanism includes horizontal drive motor, horizontal reduction gearbox, the first transmission gear, second
Transmission gear and vertical axle bed, wherein the controlled end of the horizontal drive motor communicates to connect the output end of the host computer, institute
It states the rotation output end of horizontal drive motor to be sequentially connected first transmission gear by the horizontal reduction gearbox, described first
Transmission gear is engaged with second transmission gear, the coaxially connected vertical axis of the second transmission gear, the vertical axis
Bottom nesting be mounted in the vertical axle bed.
Specifically, the horizontal reduction gearbox uses right-angle reduction case.
Specifically, the laser is that can launch YAG laser of the wavelength between 1000~1100nm.
Specifically, the bore of the Cassegrain telescope is not less than 30cm.
The utility model has the following beneficial effects:
(1) the invention provide it is a kind of based on Raman scattering principle can to concealed aircraft carry out target identification swash
Optical detection and ranging system can emit the pulse laser of specific wavelength to airspace to be measured by laser radar, and receive and come from sky to be measured
Then the Raman scattering light in domain passes through photoelectric conversion and spectral matching factor, the drawing of available reflection airspace chemical component to be measured
Graceful spectrum can be utilized further subsequently when finding to contain strong carbon dioxide and steam ingredient in the Raman spectrum
Pitching driving mechanism and horizontal drive mechanism driving laser radar are quickly scanned and are tracked to suspected target, finally by normal
The rate characteristics of rule are analyzed to identify whether suspected target is doubtful aircraft, and then can provide one kind to existing radar system
Ancillary equipment breaks through the stealthy mechanism of existing stealth aircraft from principle, promotes the development of Defence business；
(2) the radar target recognition equipment also has many advantages, such as that structure is simple, integrated and high degree of automation, is convenient for
Practical application and popularization.
Detailed description of the invention
In order to illustrate the embodiment of the utility model or the technical proposal in the existing technology more clearly, below will be to embodiment
Or attached drawing needed to be used in the description of the prior art is briefly described, it should be apparent that, the accompanying drawings in the following description is only
It is some embodiments of the utility model, for those of ordinary skill in the art, in the premise not made the creative labor
Under, it is also possible to obtain other drawings based on these drawings.
Fig. 1 is the system structure diagram of radar target recognition equipment provided by the utility model.
Fig. 2 is the schematic diagram of internal structure of laser radar provided by the utility model.
Fig. 3 is the assembly structure diagram of laser radar provided by the utility model, support frame and pedestal.
In above-mentioned attached drawing: 1- host computer；2- Raman spectrometer；3- laser radar；301- shell；302- laser；303-
Dichroscope；304- plano-concave lens；305- Cassegrain telescope；306- photoelectric sensor；307- bandpass filter；308- water
Flat axis；4- support frame；401- horizontal supporting portion；402- supporting leg；5- pedestal；6- pitching driving mechanism；601- pitching driving motor；
602- pitching reduction gearbox；The first synchronous pulley of 603-；604- synchronous belt；The second synchronous pulley of 605-；7- horizontal drive mechanism；
701- horizontal drive motor；The horizontal reduction gearbox of 702-；The first transmission gear of 703-；The second transmission gear of 704-；705- vertical axis
Seat.
Specific embodiment
With reference to the accompanying drawing and specific embodiment is further elaborated the utility model.It should be noted that right
It is used to help understand the utility model in the explanation of these way of example, but does not constitute the restriction to the utility model.
The terms "and/or", only a kind of incidence relation for describing affiliated partner, indicates that there may be three kinds of passes
System, for example, A and/or B, can indicate: individualism A, individualism B exist simultaneously tri- kinds of situations of A and B, the terms
"/and " it is to describe another affiliated partner relationship, indicate may exist two kinds of relationships, for example, A/ and B, can indicate: individually depositing
In A, two kinds of situations of individualism A and B, in addition, character "/" herein, typicallying represent forward-backward correlation object is a kind of "or" pass
System.
Embodiment one
As shown in Figures 1 to 3, the radar target recognition equipment provided in this embodiment, including host computer 1, Raman spectrum
Instrument 2, laser radar 3, support frame 4, pedestal 5, pitching driving mechanism 6 and horizontal drive mechanism 7；The laser radar 3 includes shell
Body 301 and the laser 302 being built in the shell 301, dichroscope 303, plano-concave lens 304, Cassegrain look in the distance
Mirror 305, photoelectric sensor 306 and bandpass filter 307, wherein the laser 302, the dichroscope 303, described flat
From rear to preceding successively arranged for interval, the dichroscope 303 turns forward for concavees lens 304 and the Cassegrain telescope 305
45 degree setting, the plano-concave lens 304 be located at the dead astern of the primary mirror central openings of the Cassegrain telescope 305 and with institute
State that Cassegrain telescope 305 is confocal, the photosurface of the photoelectric sensor 306 is located at the underface of the dichroscope 303,
The input terminal of the bandpass filter 307 communicates to connect the output end of the photoelectric sensor 306.
Support frame as described above 4 and the pedestal 5 are sequentially located at the underface of the shell 301, wherein support frame as described above 4
Top is rotatablely connected by the trunnion axis 308 and the shell 301 for extending transversely through 301 middle part of shell, support frame as described above 4
Bottom is rotatablely connected by vertical axis and the pedestal 5；The inside that the pitching driving mechanism 6 is mounted on support frame as described above 4 is empty
In chamber, and the trunnion axis 308 that is sequentially connected, it can be by driving 308 rotating manner of trunnion axis that the shell 301 is driven to exist
Pitching movement is done in vertical direction, the horizontal drive mechanism 7 is mounted in the internal cavities of the pedestal 5, and is sequentially connected
The vertical axis, can be by driving the vertical axis rotating manner that support frame as described above 4 is driven to horizontally rotate；The host computer 1
Output end communicates to connect the controlled end of the laser 302, the pitching driving mechanism 6 and the horizontal drive mechanism 7 respectively,
The input terminal of the host computer 1 communicates to connect the output end of the Raman spectrometer 2, and the input terminal of the Raman spectrometer 2 is logical
Letter connects the output end of the bandpass filter 307.
As shown in Figures 1 to 3, in the specific structure of the radar target recognition equipment, the laser radar 3 is used in institute
The pulse laser for launching specific wavelength under the control of host computer 1 to airspace to be measured is stated, and receives the Raman from airspace to be measured
Scattering light can obtain the detection electric signal that can be used in Raman spectrum analysis finally by photoelectric conversion and bandpass filtering.Institute
Stating Raman spectrometer 2 is existing spectral analysis apparatus, for carrying out according to existing analysis program to filtered detection electric signal
Spectral matching factor obtains and can reflect the Raman spectrum of airspace chemical component to be measured, and the Raman spectrum is sent to described upper
Machine 1.The host computer 1 be used to judge according to conventional recognition methods (such as data comparison mode etc.) in the Raman spectrum whether
Containing strong carbon dioxide and steam ingredient, if then controlling the pitching driving mechanism 6 and the horizontal drive mechanism 7,
The laser radar 3 is driven to carry out pitch angle and azimuthal adjusting, so that suspected target is quickly scanned and is tracked, and
Identify whether suspected target is that (working method of aforementioned host computer 1 is doubtful aircraft by conventional rate characteristics analysis
The normal working practices of existing radar equipment, the software program being related to can refer to existing relative program and routinely designed
It obtains).Support frame as described above 4 and the pedestal 5 are used to support the laser radar 3, wherein the built-in use in support frame as described above 4
It is built-in for driving institute in the pedestal 5 in the pitching driving mechanism 6 for driving the laser radar 3 to carry out pitch angle adjusting
State the horizontal drive mechanism 7 that laser radar 3 carries out azimuth adjustment.
In the specific structure of the laser radar 3, the shell 301 is for the electronic device or light inside insulation blocking
Learn device.The laser 302 is used to launch under the control of the host computer 1 pulse laser (its control of specific wavelength
Program, which can refer to existing program and carry out routinely design, to be obtained), can preferably launch wavelength between 1000~1100nm it
Between YAG laser (i.e. Nd.YAG laser, be originated from Neodymium-doped Yttrium Aluminium Garnet；Nd:
Y3Al5O12, or Chinese are referred to as yag crystal, use yag crystal for its activated material, brilliant intracorporal Nd
Atom content is 0.6~1.1%, belongs to Solid State Laser, can excitation pulse laser or continous way laser, the laser of transmitting is infrared ray
Wavelength 1.064um).303 one side of dichroscope is used to transmit the pulse laser of specific wavelength, on the other hand for that will return
(due to because of steam, carbon dioxide and other tails in the Raman diffused light line reflection penetrated to the photosurface of the photoelectric sensor 306
The frequency of Raman scattering light caused by stream substance has a frequency shifts relative to incident laser, therefore can be almost complete
Portion's reflection).The plano-concave lens 304 is for dissipating pulse laser and convergence Raman scattering light.The Cassegrain telescope
305 launch for aiming at airspace to be measured and collimating pulse laser, and convergence receives the Raman scattering light returned,
Bore is preferably not less than 30cm.The photoelectric sensor 306 is used for when Raman scattering light is irradiated on its photosurface, is generated
Corresponding detection electric signal.The bandpass filter 307 is further filtered out for being filtered to the detection electric signal because of it
Its bias light and the electric signal generated.
From there through the detailed description of aforementioned radar target recognition equipment, can be sent out by laser radar 3 to airspace to be measured
The pulse laser of specific wavelength is penetrated, and receives the Raman scattering light from airspace to be measured, then passes through photoelectric conversion and spectrum
Identification, the Raman spectrum of available reflection airspace chemical component to be measured are subsequently strong when finding to contain in the Raman spectrum
Carbon dioxide and steam ingredient when, further can drive laser radar using pitching driving mechanism 6 and horizontal drive mechanism 7
3 carry out pitch angle and azimuthal adjusting, so that suspected target is quickly scanned and tracked, finally by conventional speed
Characteristic analysis identifies whether suspected target is doubtful aircraft, and then the stealthy of existing stealth aircraft can be broken through from principle
Mechanism provides a kind of ancillary equipment for existing radar system, promotes the development of Defence business.
Optimization, further include the display 8 for communicating to connect the host computer 1.As illustrated in fig. 1 and 2, the display 8 is used
Detection recognition result immediately is shown in output, facilitates human-computer interaction.
Optimization, the pitching driving mechanism 6 includes pitching driving motor 601, pitching reduction gearbox 602, the first synchronous belt
Wheel 603, synchronous belt 604 and the second synchronous pulley 605, wherein described in the controlled end communication connection of the pitching driving motor 601
The rotation output end of the output end of host computer 1, the pitching driving motor 601 is sequentially connected by the pitching reduction gearbox 602
First synchronous pulley 603, first synchronous pulley 603 are sequentially connected described second synchronous by the synchronous belt 604
Belt wheel 605, the coaxially connected trunnion axis 308 of the second synchronous pulley 605.As shown in Figure 1, passing through aforementioned pitching driving machine
Structure can drive the laser radar 3 to carry out the adjusting of pitch angle, and practical adjustable range can be between -10~30 degree.Tool
Body, as shown in figs. 1 and 3, support frame as described above 4 is made of horizontal supporting portion 401 and two supporting legs 402, wherein in the level
The pitching driving motor 601 and the pitching reduction gearbox 602 are installed, wherein an institute in the internal cavities of support portion 401
It states in the internal cavities of supporting leg 402 and installs by first synchronous pulley 603, the synchronous belt 604 and second synchronous belt
The toothed belt transmission structure that wheel 605 is constituted.
Optimization, the horizontal drive mechanism 7 includes horizontal drive motor 701, horizontal reduction gearbox 702, the first driving cog
Take turns the 703, second transmission gear 704 and vertical axle bed 705, wherein the controlled end of the horizontal drive motor 701 communicates to connect institute
The output end of host computer 1 is stated, the rotation output end of the horizontal drive motor 701 is connected by the horizontal transmission of reduction gearbox 702
First transmission gear 703 is connect, first transmission gear 703 is engaged with second transmission gear 704, and described second passes
The coaxially connected vertical axis of moving gear 704, the bottom nesting of the vertical axis are mounted in the vertical axle bed 705.Such as Fig. 1
It is shown, by aforementioned levels driving mechanism, the laser radar 3 can be driven to carry out the adjustable of 360 degree of azimuth, meet full side
Track demand in the airspace of position.Specifically, the horizontal reduction gearbox 702 preferably uses right-angle reduction case, it can be in favor of at the bottom
Horizontal drive mechanism 7 described in compact Layout is carried out in seat 5.
To sum up, it using radar target recognition equipment provided by the present embodiment, has the following technical effect that
(1) a kind of laser that can carry out target identification to concealed aircraft based on Raman scattering principle is present embodiments provided
Radar system can emit the pulse laser of specific wavelength to airspace to be measured by laser radar, and receive and come from airspace to be measured
Raman scattering light, then by photoelectric conversion and spectral matching factor, the Raman of available reflection airspace chemical component to be measured
Spectrum can be further using bowing subsequently when finding to contain strong carbon dioxide and steam ingredient in the Raman spectrum
Face upward driving mechanism and horizontal drive mechanism driving laser radar carry out pitch angle and azimuthal adjusting, so as to suspected target into
Row quickly scanning and tracking, identifies whether suspected target is doubtful aircraft finally by conventional rate characteristics analysis, into
And the stealthy mechanism of existing stealth aircraft can be broken through from principle, a kind of ancillary equipment is provided for existing radar system, is promoted
The development of Defence business；
(2) the radar target recognition equipment also has many advantages, such as that structure is simple, integrated and high degree of automation, is convenient for
Practical application and popularization.
The utility model is not limited to above-mentioned optional embodiment, anyone can obtain under the enlightenment of the utility model
Other various forms of products out.Above-mentioned specific embodiment should not be understood the limitation of the pairs of protection scope of the utility model,
The protection scope of the utility model should be subject to be defined in claims, and specification can be used for explaining that right is wanted
Seek book.
Claims (8)
1. a kind of radar target recognition equipment, it is characterised in that: including host computer (1), Raman spectrometer (2), laser radar
(3), support frame (4), pedestal (5), pitching driving mechanism (6) and horizontal drive mechanism (7)；
The laser radar (3) includes shell (301) and the laser (302), the dichroic that are built in the shell (301)
Mirror (303), plano-concave lens (304), Cassegrain telescope (305), photoelectric sensor (306) and bandpass filter (307),
In, the laser (302), the dichroscope (303), the plano-concave lens (304) and the Cassegrain telescope
(305) from rear to preceding successively arranged for interval, the dichroscope (303) turns forward 45 degree of settings, the plano-concave lens (304)
Positioned at the primary mirror central openings of the Cassegrain telescope (305) dead astern and with the Cassegrain telescope (305)
Confocal, the photosurface of the photoelectric sensor (306) is located at the underface of the dichroscope (303), the bandpass filter
(307) input terminal communicates to connect the output end of the photoelectric sensor (306)；
Support frame as described above (4) and the pedestal (5) are sequentially located at the underface of the shell (301), wherein support frame as described above
(4) top is by extending transversely through trunnion axis (308) and the shell (301) rotation connection in the middle part of the shell (301), institute
The bottom for stating support frame (4) is rotatablely connected by vertical axis and the pedestal (5)；
The pitching driving mechanism (6) is mounted in the internal cavities of support frame as described above (4), and the trunnion axis that is sequentially connected
It (308), can be by driving trunnion axis (308) rotating manner that the shell (301) is driven to do pitching fortune in vertical direction
Dynamic, the horizontal drive mechanism (7) is mounted in the internal cavities of the pedestal (5), and the vertical axis that is sequentially connected, and can lead to
The vertical axis rotating manner of overdriving drives support frame as described above (4) to horizontally rotate；
The output end of the host computer (1) communicates to connect the laser (302), the pitching driving mechanism (6) and institute respectively
The controlled end of horizontal drive mechanism (7) is stated, the input terminal of the host computer (1) communicates to connect the defeated of the Raman spectrometer (2)
Outlet, the input terminal of the Raman spectrometer (2) communicate to connect the output end of the bandpass filter (307).
2. a kind of radar target recognition equipment as described in claim 1, it is characterised in that: further include that communication connection is described upper
The display (8) of machine (1).
3. a kind of radar target recognition equipment as described in claim 1, it is characterised in that: pitching driving mechanism (6) packet
Include pitching driving motor (601), pitching reduction gearbox (602), the first synchronous pulley (603), synchronous belt (604) and the second synchronous belt
It takes turns (605), wherein the controlled end of the pitching driving motor (601) communicates to connect the output end of the host computer (1), described
The rotation output end of pitching driving motor (601) passes through the pitching reduction gearbox (602) transmission connection first synchronous pulley
(603), first synchronous pulley (603) passes through the synchronous belt (604) transmission connection second synchronous pulley (605),
The coaxially connected trunnion axis (308) of second synchronous pulley (605).
4. a kind of radar target recognition equipment as claimed in claim 3, it is characterised in that: support frame as described above (4) is propped up by level
Support part (401) and two supporting legs (402) are constituted, wherein are bowed described in installation in the internal cavities of the horizontal supporting portion (401)
Driving motor (601) and the pitching reduction gearbox (602) are faced upward, is installed in the internal cavities of a supporting leg (402) wherein
The synchronous belt being made of first synchronous pulley (603), the synchronous belt (604) and second synchronous pulley (605) passes
Dynamic structure.
5. a kind of radar target recognition equipment as described in claim 1, it is characterised in that: horizontal drive mechanism (7) packet
Include horizontal drive motor (701), horizontal reduction gearbox (702), the first transmission gear (703), the second transmission gear (704) and vertical
Axle bed (705), wherein the controlled end of the horizontal drive motor (701) communicates to connect the output end of the host computer (1), institute
The rotation output end for stating horizontal drive motor (701) passes through horizontal reduction gearbox (702) transmission connection first driving cog
It takes turns (703), first transmission gear (703) is engaged with second transmission gear (704), second transmission gear
(704) the coaxially connected vertical axis, the bottom nesting of the vertical axis are mounted in the vertical axle bed (705).
6. a kind of radar target recognition equipment as claimed in claim 5, it is characterised in that: the horizontal reduction gearbox (702) is adopted
With right-angle reduction case.
7. a kind of radar target recognition equipment as described in claim 1, it is characterised in that: the laser (302) is that can send out
Project YAG laser of the wavelength between 1000~1100nm.
8. a kind of radar target recognition equipment as described in claim 1, it is characterised in that: the Cassegrain telescope
(305) bore is not less than 30cm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821496931.5U CN208805572U (en) | 2018-09-13 | 2018-09-13 | A kind of radar target recognition equipment |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821496931.5U CN208805572U (en) | 2018-09-13 | 2018-09-13 | A kind of radar target recognition equipment |
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| CN208805572U true CN208805572U (en) | 2019-04-30 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111736161A (en) * | 2020-08-25 | 2020-10-02 | 中国人民解放军国防科技大学 | Static stealth target revealing method based on coherent laser radar |
| WO2022204909A1 (en) * | 2021-03-30 | 2022-10-06 | 深圳市大疆创新科技有限公司 | Microwave radar and mobile platform |
-
2018
- 2018-09-13 CN CN201821496931.5U patent/CN208805572U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111736161A (en) * | 2020-08-25 | 2020-10-02 | 中国人民解放军国防科技大学 | Static stealth target revealing method based on coherent laser radar |
| CN111736161B (en) * | 2020-08-25 | 2020-11-20 | 中国人民解放军国防科技大学 | Static stealth target revealing method based on coherent laser radar |
| WO2022204909A1 (en) * | 2021-03-30 | 2022-10-06 | 深圳市大疆创新科技有限公司 | Microwave radar and mobile platform |
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| GR01 | Patent grant | ||
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20190430 Termination date: 20210913 |