CN110764091B - A Radar Device for Detecting Clouds During Automatic Rainfall - Google Patents
A Radar Device for Detecting Clouds During Automatic Rainfall Download PDFInfo
- Publication number
- CN110764091B CN110764091B CN201911151507.6A CN201911151507A CN110764091B CN 110764091 B CN110764091 B CN 110764091B CN 201911151507 A CN201911151507 A CN 201911151507A CN 110764091 B CN110764091 B CN 110764091B
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- Prior art keywords
- space
- gear
- fixedly installed
- sliding
- rocket
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- 239000003507 refrigerant Substances 0.000 claims description 27
- 238000004804 winding Methods 0.000 claims description 18
- 238000002955 isolation Methods 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims 1
- 239000003795 chemical substances by application Substances 0.000 description 10
- 238000002485 combustion reaction Methods 0.000 description 10
- 230000002146 bilateral effect Effects 0.000 description 4
- 238000001556 precipitation Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 230000001502 supplementing effect Effects 0.000 description 1
Images
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S13/00—Systems using the reflection or reradiation of radio waves, e.g. radar systems; Analogous systems using reflection or reradiation of waves whose nature or wavelength is irrelevant or unspecified
- G01S13/88—Radar or analogous systems specially adapted for specific applications
- G01S13/95—Radar or analogous systems specially adapted for specific applications for meteorological use
-
- A—HUMAN NECESSITIES
- A01—AGRICULTURE; FORESTRY; ANIMAL HUSBANDRY; HUNTING; TRAPPING; FISHING
- A01G—HORTICULTURE; CULTIVATION OF VEGETABLES, FLOWERS, RICE, FRUIT, VINES, HOPS OR SEAWEED; FORESTRY; WATERING
- A01G15/00—Devices or methods for influencing weather conditions
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/01—Arrangements thereon for guidance or control
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01W—METEOROLOGY
- G01W1/00—Meteorology
- G01W1/08—Adaptations of balloons, missiles, or aircraft for meteorological purposes; Radiosondes
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02A—TECHNOLOGIES FOR ADAPTATION TO CLIMATE CHANGE
- Y02A90/00—Technologies having an indirect contribution to adaptation to climate change
- Y02A90/10—Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation
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- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Radar, Positioning & Navigation (AREA)
- Life Sciences & Earth Sciences (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Environmental Sciences (AREA)
- Atmospheric Sciences (AREA)
- Environmental & Geological Engineering (AREA)
- Combustion & Propulsion (AREA)
- Biodiversity & Conservation Biology (AREA)
- Electromagnetism (AREA)
- Chemical & Material Sciences (AREA)
- Ecology (AREA)
- Computer Networks & Wireless Communication (AREA)
- General Physics & Mathematics (AREA)
- Radar Systems Or Details Thereof (AREA)
Abstract
The invention discloses a radar device for detecting cloud layers in automatic rainfall, which comprises a machine body, wherein a spring is fixedly arranged between the lower side surface of a sliding block and the lower wall of a spring space, a first motor drives a positioning shaft to rotate, the positioning shaft drives a meshing gear to rotate, a hand lever is utilized to adjust the initial angle of a rocket before launching, the distance between the cloud layers suitable for artificial rainfall and the ground is measured by matching with a radar, the initial angle of the rocket during launching is calculated and adjusted to be the correct initial angle more accurately, the pushing direction of flame in the rocket after launching is controlled by utilizing a linkage design, so that the track is changed accurately, a launching part controls the retraction and release of a pulling line by a sliding strip contacting with insection, the rocket can better store power when sliding downwards, and the whole design has high automation, safe use and high practicability.
Description
Technical Field
The invention relates to the field of meteorology, in particular to a radar device for detecting cloud layers in automatic rainfall.
Background
Artificial precipitation, also known as artificial precipitation, refers to a process of artificially supplementing some necessary conditions for forming precipitation according to the principle of natural precipitation formation, promoting cloud drops to be rapidly condensed or collided and enlarged into rain drops to land.
Disclosure of Invention
The invention aims to provide a radar device for detecting cloud layers in automatic rainfall, which is used for overcoming the defects in the prior art.
According to the embodiment of the invention, the radar device for detecting cloud layers in automatic rainfall comprises a body, a spring space is arranged in the body, a transmitting component for transmitting is arranged in the spring space, the transmitting component comprises a sliding block which is slidably arranged in the spring space, a spring is fixedly arranged between the lower side surface of the sliding block and the lower wall of the spring space, a positioning space is arranged in the sliding block, the positioning space can temporarily clamp an object to be transmitted to position the object to be transmitted, the sliding block slides downwards to store force, the spring can drive the sliding block to transmit the object to be transmitted to the upper right side,
the device comprises a rocket body and a carrying part, wherein the rocket body is connected with the rocket body in a sliding mode, a refrigerant space for storing refrigerants is arranged in the rocket body, a pressurizing plate is arranged in the refrigerant space in a sliding mode, a nozzle is arranged between the right wall of the refrigerant space and the right side face of the rocket body in a communicating mode, a nozzle valve is fixedly arranged in the nozzle, the pressurizing plate is arranged in the refrigerant space in a sliding mode, the refrigerant space is launched into a proper cloud layer, the nozzle valve is opened, and the refrigerant in the refrigerant space is taken into the cloud layer by the pressurizing plate in a sliding mode to carry out artificial rainfall.
On the basis of the technical scheme, the launching component further comprises electrified magnets which are symmetrically and fixedly installed in the bottom wall of the positioning space, and permanent magnets are symmetrically and fixedly installed on the lower side surface of the rocket body.
On the basis of the technical scheme, a pulling space is arranged at the lower side of the spring space in the machine body, a first motor is fixedly arranged in the rear wall of the pulling space, a positioning shaft is fixedly arranged on an output shaft of the first motor, a meshing gear is fixedly arranged on the positioning shaft, a limiting wheel is fixedly arranged between the front wall and the rear wall of the pulling space, a third sliding space is arranged in the limiting wheel, two clamping blocks are symmetrically and slidably arranged in the third sliding space in a central mode, the inner sides of the clamping blocks are meshed with the meshing gear, a winding gear is rotatably arranged on the outer side of the limiting wheel in the front wall of the pulling space, a meshing space is communicated between the limiting wheel and the winding gear, one-way insections are arranged on the inner side of the winding gear, the clamping blocks can extend to be meshed with the winding gear, a pulling wire is wound on the outer side of the winding gear, and a steering wheel for steering the pulling wire is fixedly arranged, the other side of the traction line is fixedly connected with the sliding block.
On the basis of the technical scheme, the carrying component also comprises a combustion agent space which is arranged in the rocket body in a bilateral symmetry manner, the combustion agent space is fixedly installed by an isolation valve in a side wall in the middle, a steering space is arranged on the right side of the combustion agent space in the rocket body, a moving space is arranged on the right side of the steering space in the rocket body, the left side of the moving space is communicated with a first sliding space, a first slide rod is installed in the first sliding space in a sliding manner, a second sliding space is arranged on the right side of the moving space in a communicating manner, a second slide rod is installed in the second sliding space in a sliding manner, a threaded screw rod is rotatably installed on the lower side surface of the first slide rod, the threaded screw rod is fixedly connected with the second slide rod, and a first rotating shaft is rotatably installed on the right side of the threaded screw rod between the first slide rod and, a regulating rod is installed on the threaded screw in a threaded manner, a first gear is fixedly installed on the threaded screw and positioned on the lower side of the regulating rod, a second gear is fixedly installed on a first rotating shaft and meshed with the first gear, a second rotating shaft is fixedly installed on the bottom wall of a second sliding space and positioned on the right side of the second gear, a third gear is rotatably installed on the second rotating shaft and meshed with the second gear, a gear space is arranged in the rocket body and positioned on the right side of the moving space, the gear space is communicated with the first sliding space, a second motor is fixedly installed in the rear wall of the gear space, a driving shaft is fixedly installed on an output shaft of the second motor, a fifth gear is fixedly installed on the driving shaft, and a third rotating shaft is rotatably installed on the upper side of the driving shaft and positioned between the front wall and the rear wall of the gear space, a fourth gear is fixedly arranged on the third rotating shaft and is meshed with the first sliding rod, the fifth gear is meshed with the fourth gear, a helical gear space is arranged on the front side of the gear space, a first helical gear is fixedly arranged on the driving shaft in the helical gear space, a fourth rotating shaft is rotatably arranged between the top wall of the second sliding space and the lower wall of the helical gear space, a second bevel gear is fixedly arranged on the fourth rotating shaft in the bevel gear space and meshed with the first bevel gear, a sixth gear is fixedly arranged on the fourth rotating shaft in the second sliding space and meshed with the third gear, and a hydraulic cylinder is fixedly arranged in the lower side wall of the refrigerant space, a push rod is fixedly arranged on a piston of the hydraulic cylinder, and the push rod is fixedly connected with the pressurizing plate.
On the basis of the technical scheme, the lower side of the machine body is rotatably provided with the movable base, the radar suitable for the artificial rainfall cloud layer is fixedly arranged in the movable base, the movable base is internally provided with a steering space on the front side of the radar, a rocker is arranged between the front wall and the rear wall of the steering space in a threaded manner, and the rocker is in threaded connection with the machine body.
The invention has the beneficial effects that: the rocket launching device utilizes the hand-operated lever to adjust the initial angle of the rocket before launching, measures the distance between the cloud layer suitable for artificial rainfall and the ground by matching with the radar, calculates the initial angle when the rocket is launched, more accurately adjusts the initial angle to be correct, and utilizes the linkage design to control the pushing direction of flame in the rocket after launching, thereby accurately changing the track.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.
FIG. 1 is a schematic view of the overall structure of the present invention;
FIG. 2 is a cross-sectional view A-A of FIG. 1 in accordance with the present invention;
FIG. 3 is a cross-sectional view of B-B of FIG. 1 in accordance with the present invention;
fig. 4 is a partial enlarged view of C of fig. 1 according to the present invention.
Detailed Description
The invention will now be described in detail with reference to fig. 1-4, wherein for ease of description the orientations described hereinafter are now defined as follows: the up, down, left, right, front and rear directions described below correspond to the front, back, left, right, top and bottom directions of the view direction of fig. 1, fig. 1 is a front view of the apparatus of the present invention, and the directions shown in fig. 1 correspond to the front, back, left, right, top and bottom directions of the apparatus of the present invention.
Referring to fig. 1-4, a radar apparatus for detecting cloud cover during automatic rainfall according to an embodiment of the present invention includes a body 11, a spring space 12 is disposed in the body 11, a launching component 80 for launching is disposed in the spring space 12, the launching component 80 includes a sliding block 15 slidably mounted in the spring space 12, a spring 13 is fixedly mounted between a lower side surface of the sliding block 15 and a lower wall of the spring space 12, a positioning space 16 is disposed in the sliding block 15, the positioning space 16 can temporarily block an object to be launched to position the object, the sliding block 15 slides downwards to accumulate force, the spring 13 can drive the sliding block 15 to launch the object to be launched to the upper right side,
the artificial rainfall device is characterized in that a carrying component 81 used for absorbing cloud layers to carry out artificial rainfall is arranged in the body 11, the carrying component 81 comprises a rocket body 19 which is in sliding connection with the body 11, a refrigerant space 30 used for storing a refrigerant is arranged in the rocket body 19, a pressurizing plate 29 is arranged in the refrigerant space 30 in a sliding mode, a nozzle 31 is arranged between the right wall of the refrigerant space 30 and the right side face of the rocket body 19 in a communicating mode, a nozzle valve 32 is fixedly arranged in the nozzle 31, the pressurizing plate 29 is arranged in the refrigerant space 30 in a sliding mode and is launched into a proper cloud layer, the nozzle valve 32 is opened, and the pressurizing plate 29 slides rightwards to absorb the refrigerant in the refrigerant space 30 into the cloud layer to carry out artificial rainfall.
In addition, in one embodiment, the launching component 80 further comprises an electrified magnet 14 which is fixedly installed in the bottom wall of the positioning space 16 in a bilateral symmetry mode, permanent magnets 18 are fixedly installed on the lower side face of the rocket body 19 in a bilateral symmetry mode, when a rocket is installed, the electrified magnet 14 is electrified, the electrified magnet 14 attracts the permanent magnets 18, and the permanent magnets 18 drive the rocket body 19 to be fixed in the positioning space 16 to prepare for launching.
In addition, in one embodiment, a pulling space 55 is provided in the machine body 11 at the lower side of the spring space 12, a first motor 67 is fixedly installed in the rear wall of the pulling space 55, a positioning shaft 58 is fixedly installed on the output shaft of the first motor 67, an engaging gear 66 is fixedly installed on the positioning shaft 58, a limiting wheel 63 is fixedly installed between the front wall and the rear wall of the pulling space 55, a third sliding space 62 is provided in the limiting wheel 63, two clamping blocks 57 are centrally and symmetrically installed in the third sliding space 62 in a sliding manner, the inner sides of the clamping blocks 57 are engaged with the engaging gear 66, a winding gear 64 is rotatably installed in the front wall of the pulling space 55 at the outer side of the limiting wheel 63, an engaging space 65 is provided between the limiting wheel 63 and the winding gear 64 in a communicating manner, a unidirectional tooth pattern is provided in the inner side of the winding gear 64, and the clamping blocks 57 can extend to be engaged with, a traction wire is wound on the outer side of the winding gear 64, a steering wheel 60 used for steering the traction wire is fixedly installed on the right wall of the pulling space 55, the other side of the traction wire is fixedly connected with the sliding block 15, the rocket to be launched is fixed in the positioning space 16, the first motor 67 is started, the first motor 67 drives the positioning shaft 58 to rotate, the positioning shaft 58 drives the meshing gear 66 to rotate, the meshing gear 66 drives the clamping block 57 to move outwards to be meshed with the winding gear 64, the positioning shaft 58 rotates to drive the meshing gear 66, the clamping block 57 and the winding gear 64 to rotate to tension the traction wire, and the traction wire drives the sliding block 15 and the rocket to be launched to move downwards to store force.
In addition, in one embodiment, the carrying component 81 further includes a combustion agent space 42 disposed in the rocket body 19 in a bilateral symmetry manner, the combustion agent space 42 is fixedly installed with an isolation valve 69 in a side wall in the middle, a turning space 68 is disposed in the rocket body 19 on the right side of the combustion agent space 42, a moving space 39 is disposed in the rocket body 19 on the right side of the turning space 68, a first sliding space 28 is disposed in the moving space 39 in a communicating manner, a first sliding rod 24 is slidably installed in the first sliding space 28, a second sliding space 36 is disposed in the moving space 39 in a communicating manner, a second sliding rod 40 is slidably installed in the second sliding space 36, a threaded screw 21 is rotatably installed on the lower side surface of the first sliding rod 24, the threaded screw 21 is fixedly connected with the second sliding rod 40, a first rotating shaft 23 is rotatably installed between the first sliding rod 24 and the second sliding rod 40 on the right side of the threaded screw 21, the threaded screw 21 is provided with an adjusting rod 20 in a threaded manner, a first gear 41 is fixedly arranged on the threaded screw 21 and positioned below the adjusting rod 20, a second gear 38 is fixedly arranged on the first rotating shaft 23, the second gear 38 is meshed with the first gear 41, a second rotating shaft 37 is fixedly arranged on the bottom wall of the second sliding space 36 and positioned on the right side of the second gear 38, a third gear 35 is rotatably arranged on the second rotating shaft 37, the third gear 35 is meshed with the second gear 38, a gear space 27 is arranged on the right side of the moving space 39 in the rocket body 19, the gear space 27 is communicated with the first sliding space 28, a second motor 70 is fixedly arranged in the rear wall of the gear space 27, a driving shaft 48 is fixedly arranged on an output shaft of the second motor 70, and a fifth gear 47 is fixedly arranged on the driving shaft 48, a third rotating shaft 26 is rotatably mounted between the front wall and the rear wall of the gear space 27 at the upper side of the driving shaft 48, a fourth gear 25 is fixedly mounted on the third rotating shaft 26, the fourth gear 25 is engaged with the first sliding rod 24, the fifth gear 47 is engaged with the fourth gear 25, a helical gear space 50 is arranged at the front side of the gear space 27, a first helical gear 49 is fixedly mounted on the driving shaft 48 in the helical gear space 50, a fourth rotating shaft 52 is rotatably mounted between the top wall of the second sliding space 36 and the lower wall of the helical gear space 50, a second helical gear 51 is fixedly mounted on the fourth rotating shaft 52 in the helical gear space 50, the second helical gear 51 is engaged with the first helical gear 49, a sixth gear 53 is fixedly mounted on the fourth rotating shaft 52 in the second sliding space 36, and the sixth gear 53 is engaged with the third gear 35, a hydraulic cylinder 34 is fixedly installed in the lower side wall of the refrigerant space 30, a push rod 33 is fixedly installed on a piston of the hydraulic cylinder 34, the push rod 33 is fixedly connected with the pressurizing plate 29, when the rocket is to be launched, an isolation valve 69 and an igniter 43 are opened, the igniter 43 ignites the combustion agent flowing out of the combustion agent space 42, the generated flame and hot gas push the rocket to be launched upwards, a second motor 70 is started, the second motor 70 drives a driving shaft 48, a fifth gear 47 and a fourth gear 25 to rotate, the fourth gear 25 drives a first sliding rod 24, a threaded screw 21 and an adjusting rod 20 to slide rightwards, the adjusting rod 20 slides rightwards to increase air circulation, the flame accelerates the rocket helical gear, the driving shaft 48 rotates to drive a first helical gear 49, a second helical gear 51, a fourth rotating shaft 52, a sixth gear 53, a third gear 35, a second gear 38, a first gear 41 and a threaded screw 21 to rotate, the threaded screw 21 drives the adjusting rod 20 to move left and right to change the flame direction, so that the rocket direction is changed, when the rocket moves to a corresponding cloud layer, the hydraulic cylinder 34 and the nozzle valve 32 are started, the nozzle valve 32 pushes the push rod 33 and the pressurizing plate 29 to move right, and the refrigerant is sprayed out for artificial rainfall.
In addition, in one embodiment, a movable base 10 is rotatably installed on the lower side of the body 11, a radar 44 suitable for detecting artificial rainfall cloud is fixedly installed in the movable base 10, a steering space 46 is arranged in the movable base 10 and located on the front side of the radar 44, a rocker 45 is installed between the front wall and the rear wall of the steering space 46 in a threaded mode, the rocker 45 is in threaded connection with the body 11, the rocker 45 is rocked, and the launching direction of the body 11 and the rocket can be adjusted.
At the beginning: the electrified magnet 14 is electrified, the electrified magnet 14 attracts the permanent magnet 18 to fix the rocket in the positioning space 16, and the fixture block 57 is not meshed with the winding gear 64;
when in use: when the rocket is loaded, the electrified magnet 14 is electrified, the electrified magnet 14 attracts the permanent magnet 18, the permanent magnet 18 drives the rocket body 19 to be fixed in the positioning space 16 for launching, the rocket to be launched is fixed in the positioning space 16, the first motor 67 is started, the first motor 67 drives the positioning shaft 58 to rotate, the positioning shaft 58 drives the meshing gear 66 to rotate, the meshing gear 66 drives the fixture block 57 to move outwards to be meshed with the winding gear 64, the positioning shaft 58 rotates to drive the meshing gear 66, the fixture block 57 and the winding gear 64 to rotate to tension the pulling wire, the pulling wire drives the sliding block 15 and the rocket to be launched to move downwards to store force,
when the rocket is to be launched, the isolation valve 69 and the igniter 43 are opened, the igniter 43 ignites the combustion agent flowing out from the combustion agent space 42, the generated flame and hot air push the rocket to be launched upwards, the second motor 70 is started, the second motor 70 drives the driving shaft 48, the fifth gear 47 and the fourth gear 25 to rotate, the fourth gear 25 drives the first sliding rod 24, the threaded screw 21 and the adjusting rod 20 to slide rightwards, the adjusting rod 20 slides rightwards to increase air circulation, the flame is increased to accelerate the rocket, the driving shaft 48 rotates to drive the first helical gear 49, the second helical gear 51, the fourth rotating shaft 52, the sixth gear 53, the third gear 35, the second gear 38, the first gear 41 and the threaded screw 21 to rotate, the threaded screw 21 drives the adjusting rod 20 to move leftwards and rightwards to change the flame direction, so as to change the direction of the rocket, and when the rocket moves to a corresponding cloud layer, the hydraulic cylinder 34 and the, the nozzle valve 32 pushes the push rod 33 and the pressurizing plate 29 to move to the right, and the refrigerant is sprayed for artificial rainfall.
The invention has the beneficial effects that: the rocket launching device utilizes the hand-operated lever to adjust the initial angle of the rocket before launching, measures the distance between the cloud layer suitable for artificial rainfall and the ground by matching with the radar, calculates the initial angle when the rocket is launched, more accurately adjusts the initial angle to be correct, and utilizes the linkage design to control the pushing direction of flame in the rocket after launching, thereby accurately changing the track.
It will be apparent to those skilled in the art that various modifications may be made to the above embodiments without departing from the general spirit and concept of the invention. All falling within the scope of protection of the present invention. The protection scheme of the invention is subject to the appended claims.
Claims (2)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911151507.6A CN110764091B (en) | 2019-11-21 | 2019-11-21 | A Radar Device for Detecting Clouds During Automatic Rainfall |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911151507.6A CN110764091B (en) | 2019-11-21 | 2019-11-21 | A Radar Device for Detecting Clouds During Automatic Rainfall |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN110764091A CN110764091A (en) | 2020-02-07 |
| CN110764091B true CN110764091B (en) | 2020-05-01 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911151507.6A Expired - Fee Related CN110764091B (en) | 2019-11-21 | 2019-11-21 | A Radar Device for Detecting Clouds During Automatic Rainfall |
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| Country | Link |
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| CN (1) | CN110764091B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3326129A (en) * | 1965-09-01 | 1967-06-20 | Bert B Gould | Miniature disappearing projectile |
| CN101403595A (en) * | 2008-11-17 | 2009-04-08 | 长安汽车（集团）有限责任公司 | Safety type artificial rain bullet detonator |
| CN201302427Y (en) * | 2008-11-17 | 2009-09-02 | 长安汽车（集团）有限责任公司 | Secure man-made rail shell fusee |
| CN101726219A (en) * | 2009-12-03 | 2010-06-09 | 陕西中天火箭技术有限责任公司 | Multielement seeding combustion explosion type rainfall-increasing and anti-hail rocket |
| CN104412877A (en) * | 2013-09-10 | 2015-03-18 | 中国兵器科学研究院 | Full-automatic rocket system integrated with radar detection and integrated seeding |
| CN107278732A (en) * | 2016-04-11 | 2017-10-24 | 国家电网公司 | The overhead potential energy ejecting rain making method and system of mountain shape are relied on based on intelligent grid |
| CN107388893A (en) * | 2017-09-01 | 2017-11-24 | 西北工业大学 | A kind of pencil rocket bullet emitter |
| CN209230411U (en) * | 2018-11-12 | 2019-08-09 | 晁增元 | A kind of intelligence rocket launching gear of increasing rain artificially plays device |
-
2019
- 2019-11-21 CN CN201911151507.6A patent/CN110764091B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3326129A (en) * | 1965-09-01 | 1967-06-20 | Bert B Gould | Miniature disappearing projectile |
| CN101403595A (en) * | 2008-11-17 | 2009-04-08 | 长安汽车（集团）有限责任公司 | Safety type artificial rain bullet detonator |
| CN201302427Y (en) * | 2008-11-17 | 2009-09-02 | 长安汽车（集团）有限责任公司 | Secure man-made rail shell fusee |
| CN101726219A (en) * | 2009-12-03 | 2010-06-09 | 陕西中天火箭技术有限责任公司 | Multielement seeding combustion explosion type rainfall-increasing and anti-hail rocket |
| CN104412877A (en) * | 2013-09-10 | 2015-03-18 | 中国兵器科学研究院 | Full-automatic rocket system integrated with radar detection and integrated seeding |
| CN107278732A (en) * | 2016-04-11 | 2017-10-24 | 国家电网公司 | The overhead potential energy ejecting rain making method and system of mountain shape are relied on based on intelligent grid |
| CN107388893A (en) * | 2017-09-01 | 2017-11-24 | 西北工业大学 | A kind of pencil rocket bullet emitter |
| CN209230411U (en) * | 2018-11-12 | 2019-08-09 | 晁增元 | A kind of intelligence rocket launching gear of increasing rain artificially plays device |
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| CN110764091A (en) | 2020-02-07 |
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