CN210220830U - Ground rocket operation automation equipment of artificial influence weather - Google Patents
Ground rocket operation automation equipment of artificial influence weather Download PDFInfo
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- CN210220830U CN210220830U CN201920984937.5U CN201920984937U CN210220830U CN 210220830 U CN210220830 U CN 210220830U CN 201920984937 U CN201920984937 U CN 201920984937U CN 210220830 U CN210220830 U CN 210220830U
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Abstract
The utility model relates to an artificial rainfall hail suppression technical field discloses an artificial influence weather's ground rocket operation automation equipment. The rotating cloud platform and the dual-wavelength high-altitude detection laser radar are arranged on the top of the cylinder, whether target cloud layers such as black clouds or hail clouds exist in airspaces in all directions can be detected in a rotating mode, and the rocket is automatically launched towards the target cloud layers and safely ignited and launched by arranging the forward and reverse rotating motor, the gear transmission mechanism, the sleeve and the weather modification rocket.
Description
Technical Field
The utility model belongs to the technical field of artificial rainfall hail suppression, specifically relate to a ground rocket operation automation equipment of artificial influence weather.
Background
The artificial weather-influencing rocket is a hail-suppression rain-increasing projection device widely used in artificial weather-influencing operation, namely, a catalyst (such as sulfonated silver, mesoacetaldehyde and the like) is sent into a target cloud layer by the rocket for spreading during shadow operation, so that the physical structure change of the cloud is influenced, the purposes of increasing snow and eliminating hail are achieved, and the artificial weather-influencing rocket is a tool for improving the natural environment of human beings. In actual figure operation, an existing ground rocket operation system is usually matched with a weather monitoring system for use, but because the moving speed of the Wuyun or hail clouds is high, the target searching and indicating precision of the existing weather monitoring system cannot meet the launching requirement, an operator is often required to determine the launching direction and opportunity through visual or experience, and therefore the problems that the operation efficiency is low, the ammunition consumption is large, and the operation effect is unsatisfactory exist.
SUMMERY OF THE UTILITY MODEL
In order to solve the problems of low operation efficiency, large ammunition consumption and unsatisfactory operation effect of the existing ground rocket operation system, the utility model aims to provide a ground rocket operation automation device with weather artificial influence.
The utility model discloses the technical scheme who adopts does:
a ground rocket operation automation device for artificially influencing weather comprises a base, a cylinder, a sleeve, a forward and reverse rotation motor, a driving gear, a driven gear, a rotating holder, a dual-wavelength high-altitude detection laser radar, an artificially influencing weather rocket and a control box;
the cylinder is vertically fixed at the center of the top surface of the base, the sleeve is sleeved on the periphery of the lower part of the cylinder in a sliding manner, the forward and reverse rotating motor is fixed on the top surface of the base, the output end of the forward and reverse rotating motor is connected with the driving gear, the driven gear shaft is connected with the bottom of the sleeve and is meshed with the driving gear, and the gear transmission ratio of the driving gear to the driven gear is greater than 1;
the rotating tripod head is installed at the top of the cylinder, the dual-wavelength high-altitude detection laser radar is installed on the rotating part of the rotating tripod head, and the weather modification rocket is obliquely installed on the periphery of the top of the sleeve, wherein a rocket launching controller is configured on the weather modification rocket;
the control box is fixed on the top surface of the base and is provided with a control module, a storage module, a GPRS communication module and a satellite positioning module, wherein the control module is respectively in communication connection with the storage module, the GPRS communication module, the satellite positioning module, the forward and reverse rotating motor, the rotating holder, the dual-wavelength high-altitude detection laser radar and a controlled end of the rocket launching controller.
Optimally, the number of the weather modification rockets is even and the rockets are evenly divided into two groups, wherein the two groups of rockets are symmetrically arranged on two opposite sides of the sleeve in a combined mode.
Further optimally, the inclined installation angle of the weather modification rockets is 50-80 degrees, and the inclined installation angles of two different groups of weather modification rockets are different.
Preferably, the periphery of the middle part of the sleeve is fixedly provided with a fireproof cover which is used for covering the base, the positive and negative rotation motor, the driving gear, the driven gear and the control box in a clearance mode, and the fireproof cover is made of a non-metal material.
Further preferably, a heat insulation layer is arranged on the inner bottom surface of the fireproof cover.
Preferably, a dustproof cover used for covering the top end face of the sleeve in a clearance mode is fixedly arranged on the periphery of the middle of the cylinder.
Preferably, the control module is in communication connection with the rotating holder and/or the dual-wavelength high-altitude detection laser radar through a cable, wherein the cable penetrates through the base and the inner through hole of the cylinder.
Preferably, the control module is in communication connection with the rocket launching controller through a wireless module, wherein the wireless module comprises a WiFi wireless module, a Bluetooth wireless module and/or a ZigBee wireless module.
Specifically, the control module adopts a microcontroller chip of the model STM32F103 series and a peripheral circuit thereof.
Specifically, the satellite positioning module adopts a Beidou/GPS dual-system wireless positioning module with the model number of UM 220-III.
The utility model has the advantages that:
(1) the invention provides a novel ground rocket operation automation device suitable for weather modification operation, namely, on one hand, whether target cloud layers such as dark clouds or hail clouds exist in airspaces of all directions can be rotationally detected by configuring a rotating holder and a dual-wavelength high-altitude detection laser radar at the top of a cylinder, on the other hand, by configuring a forward and reverse rotating motor, a gear transmission mechanism, a sleeve and an artificial weather influence rocket, when finding the target cloud layer, the rocket is automatically launched towards the target cloud layer, safe ignition and safe launching are carried out, compared with the traditional rocket launching system, the launching direction and the launching time are determined without an operator through eyes or experience in the whole process, the shadow work efficiency can be effectively improved, the ammunition consumption is reduced, the shadow work effect is improved, and the actual application requirements are met;
(2) the ground rocket operation automation device also has the advantages of good rocket rotation balance, fire and dust prevention, concise appearance, high automation degree, simple structure and the like, and is convenient for practical popularization and application.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
Fig. 1 is a schematic view of a front view structure of the ground rocket work automation device provided by the present invention.
Fig. 2 is a schematic structural diagram of a control system in an automatic ground rocket operation device according to the present invention.
In the above drawings: 1-a base; 2-column; 201-a dust cover; 3-a sleeve; 301-fire protection covers; 4-a positive and negative rotation motor; 501-a driving gear; 502-driven gear; 6-rotating the pan-tilt; 7-double wavelength high altitude detection laser radar; 8-artificial weather rocket; 9-control box.
Detailed Description
The invention will be further described with reference to the accompanying drawings and specific embodiments. It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. Specific structural and functional details disclosed herein are merely illustrative of example embodiments of the invention. The present invention may, however, be embodied in many alternate forms and should not be construed as limited to the embodiments set forth herein.
It will be understood that, although the terms first, second, etc. may be used herein to describe various elements, these elements should not be limited by these terms. These terms are only used to distinguish one element from another. For example, a first element could be termed a second element, and, similarly, a second element could be termed a first element, without departing from the scope of example embodiments of the present invention.
It should be understood that, for the term "and/or" as may appear herein, it is merely an associative relationship that describes an associated object, meaning that three relationships may exist, e.g., a and/or B may mean: a exists alone, B exists alone, and A and B exist at the same time; for the term "/and" as may appear herein, which describes another associative object relationship, it means that two relationships may exist, e.g., a/and B, may mean: a exists independently, and A and B exist independently; in addition, for the character "/" that may appear herein, it generally means that the former and latter associated objects are in an "or" relationship.
It will be understood that when an element is referred to herein as being "connected," "connected," or "coupled" to another element, it can be directly connected or coupled to the other element or intervening elements may be present. Conversely, if a unit is referred to herein as being "directly connected" or "directly coupled" to another unit, it is intended that no intervening units are present. In addition, other words used to describe the relationship between elements should be interpreted in a similar manner (e.g., "between … …" versus "directly between … …", "adjacent" versus "directly adjacent", etc.).
It is to be understood that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments of the invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises," "comprising," "includes" and/or "including," when used herein, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, numbers, steps, operations, elements, components, and/or groups thereof.
It should also be noted that, in some alternative implementations, the functions/acts noted may occur out of the order noted in the figures. For example, two figures shown in succession may, in fact, be executed substantially concurrently, or the figures may sometimes be executed in the reverse order, depending upon the functionality/acts involved.
It should be understood that specific details are provided in the following description to facilitate a thorough understanding of example embodiments. However, it will be understood by those of ordinary skill in the art that the example embodiments may be practiced without these specific details. For example, systems may be shown in block diagrams in order not to obscure the examples in unnecessary detail. In other instances, well-known processes, structures and techniques may be shown without unnecessary detail in order to avoid obscuring example embodiments.
Example one
As shown in fig. 1-2, the ground rocket operation automation device for artificially influencing weather provided in this embodiment includes a base 1, a cylinder 2, a sleeve 3, a forward and reverse rotation motor 4, a driving gear 501, a driven gear 502, a rotating pan-tilt 6, a dual-wavelength high-altitude detection laser radar 7, an artificially influencing weather rocket 8, and a control box 9; the cylinder 2 is vertically fixed at the center of the top surface of the base 1, the sleeve 3 is slidably sleeved on the periphery of the lower part of the cylinder 2, the forward and reverse rotating motor 4 is fixed on the top surface of the base 1, the output end of the forward and reverse rotating motor is connected with the driving gear 501, the driven gear 502 is connected with the bottom of the sleeve 3 in a shaft mode and meshed with the driving gear 501, and the gear transmission ratio of the driving gear 501 to the driven gear 502 is larger than 1; the rotating tripod head 6 is arranged at the top of the cylinder 2, the dual-wavelength high altitude detection laser radar 7 is arranged on the rotating part of the rotating tripod head 6, and the weather modification rocket 8 is obliquely arranged on the periphery of the top of the sleeve 3, wherein a rocket launching controller is configured on the weather modification rocket 8; the control box 9 is fixed on the top surface of the base 1 and is provided with a control module, a storage module, a GPRS communication module and a satellite positioning module, wherein the control module is respectively in communication connection with the storage module, the GPRS communication module, the satellite positioning module, the forward and reverse rotating motor 4, the rotating holder 6, the dual-wavelength high-altitude detection laser radar 7 and a controlled end of the rocket launching controller.
As shown in fig. 1 to 2, in the specific structure of the ground rocket work automation device, the base 1 is used for conveniently mounting the whole device on other equipment, such as a walking vehicle. The cylinder 2 is used for providing a rotation center and supporting the rotating holder 6 and the radar. The sleeve 3 is driven by the forward and reverse rotation motor 4 and the gear transmission mechanism composed of the driving gear 501 and the driven gear 502 to rotate clockwise or counterclockwise around a rotation center so as to adjust the launching orientation of the weather modification rocket 8, and the specific sliding fit structure of the sleeve and the cylinder 2 can be realized by adopting an existing bearing structure but is not limited to the existing bearing structure. In addition, the gear transmission ratio of the driving gear 501 to the driven gear 502 is larger than 1, so that the launching direction of the weather modification rocket 8 can be adjusted with high precision.
The rotating tripod head 6 is configured to drive the dual-wavelength high-altitude detection laser radar 7 to periodically rotate under the control of the control module, so as to detect whether a target cloud layer such as a dark cloud or a hail cloud exists in an airspace in each azimuth, where the rotation period may be very slow, for example, 15 minutes for one week, so that there is enough time to obtain a detection result, and in addition, it may be implemented by, but not limited to, an existing horizontal rotating tripod head structure, for example, an omni-directional tripod head that can rotate 360 degrees. The dual-wavelength high-altitude detection laser radar 7 is used for detecting and finding a target cloud layer by adopting two echo mechanisms of Rayleigh scattering and resonance fluorescence, transmitting a detection result to the control module, and can be realized by adopting the existing meteorological radar equipment, for example, the dual-wavelength meteorological radar with the dual detection wavelengths of 30mm and 100mm respectively. The artificial weather-affecting rocket 8 is used for sending the internally-packaged catalyst (such as sulfonated silver, metaldehyde and the like) into a target cloud layer for spreading, affecting the physical structure change of the cloud, and achieving the purposes of increasing snow and eliminating hail, wherein the rocket launching controller is used for igniting and launching the artificial weather-affecting rocket 8 under the control of the control module; in addition, both the weather modification rocket 8 and the rocket launching controller can be realized by adopting the existing design structure, for example, the rocket launching controller adopts a programmable logic controller.
The control box 9 is used for bearing and protecting the control module, the storage module, the GPRS communication module and the satellite positioning module. In the control box 9, the satellite positioning module is used for communicating with a positioning satellite to obtain satellite positioning data of the whole device, and the satellite positioning module can be but is not limited to a big dipper/GPS dual-system wireless positioning module with the model number UM220-III, so that two satellite positioning systems can be compatible. The GPRS communication module is used for performing remote communication with a remote control center, for example, but not limited to, receiving the figure job task information sent by the remote control center or feeding back the figure job process information. The control module is used for starting the rotating tripod head 6 and the dual-wavelength high-altitude detection laser radar 7 to detect a target cloud layer in each azimuth airspace on the basis of the conventional program on one hand after receiving the figure operation task information; on the other hand, when a target cloud layer is found according to a detection result transmitted by the dual-wavelength high-altitude detection laser radar 7, recording the current position of the target cloud layer, and according to the current satellite positioning data and a rocket artificial influence weather operation point safety range diagram in the artifact operation task information, estimating whether the rocket can safely fall into the rocket artificial influence weather operation point safety range diagram after the rocket is launched (the estimation method is conventional geometric operation), if so, permitting the rocket to launch: and starting the forward and reverse rotation motor 4 to enable the launching azimuth of the weather modification rocket 8 to face a target cloud layer, then sending a launching instruction to the rocket launching controller to finish rocket launching, and if not, forbidding rocket launching. As shown in fig. 2, specifically, the control module may be, but is not limited to, a microcontroller chip of model STM32F103 series and its peripheral circuits. The memory module may be, but is not limited to, a memory module for storing the aforementioned required process data and operation programs, etc. In addition, a power supply device, such as a battery, for supplying power to other devices may be provided in the control box 9.
Therefore, based on the detailed structural description of the ground rocket operation automation device, on one hand, whether target cloud layers such as black clouds or hail clouds exist in airspaces in all directions can be detected in a rotating mode by arranging the rotating cloud platform and the dual-wavelength high-altitude detection laser radar on the top of the cylinder, on the other hand, weather rockets can be automatically launched towards the target cloud layers by arranging the forward and reverse rotating motor, the gear transmission mechanism, the sleeve and the artificial influence rocket, when the target cloud layers are found, the rocket launching directions can be automatically enabled to face the target cloud layers, safe ignition and safe launching are conducted, compared with a traditional rocket launching system, an operator does not need to determine the launching directions and opportunities through eyes or experience in the whole process, the human shadow operation efficiency can be effectively improved, the ammunition consumption is reduced, the human shadow operation effect is improved, and.
Preferably, the weather modification rockets 8 are even in number and are equally divided into two groups, wherein the two groups of rockets are symmetrically coupled to opposite sides of the sleeve 3. As shown in fig. 1, a plurality of weather modification rockets 8 can be arranged to realize multi-target launching or repeated launching and ensure balance of the rotation process, and besides two sets of two-united rockets as shown in fig. 1, the weather modification rockets can also be configured into two sets of four-united rockets, two sets of six-united rockets or two sets of eight-united rockets. Further optimally, the inclined installation angle of the weather modification rockets 8 is 50-80 degrees, and the inclined installation angles of two different groups of weather modification rockets 8 are different. Because the rockets have different inclined installation angles, the inclined rocket with the best alignment effect can be selected for launching according to the distance from the target cloud layer, so that the ammunition consumption is further reduced, and the figure operation effect is improved.
Preferably, the middle periphery of the sleeve 3 is fixedly provided with a fireproof cover 301 for covering the base 1, the forward and reverse rotating motor 4, the driving gear 501, the driven gear 502 and the control box 9 in a clearance manner, wherein the fireproof cover 301 is made of a non-metal material. As shown in fig. 1, by providing the fire-proof cover 301, it is possible to prevent the base 1, the forward/reverse rotation motor 4, the driving gear 501, the driven gear 502, the control box 9, and the like from being damaged by rocket launching flames, and at the same time, by designing the fire-proof cover 301 to be a non-metal structure (for example, a high-temperature resistant glass structure), it is possible to avoid adverse effects on telecommunication due to electromagnetic shielding, and ensure their normal operation. Further optimally, a heat insulation layer is arranged on the inner bottom surface of the fireproof cover 301, so that a certain effect of preventing electrical equipment from aging can be achieved, and the service lives of the forward and reverse rotating motor 4 and the control box 9 are ensured.
Preferably, a dust cover 201 for covering the top end face of the sleeve 3 with a gap is fixedly arranged on the periphery of the middle part of the cylinder 2. As shown in fig. 1, by providing the dust cover 201, external dust can be prevented from entering a gap between the cylinder 2 and the sleeve 3, and normal rotation of the sleeve 3 is ensured.
Preferably, the control module is in communication connection with the rotating holder 6 and/or the dual-wavelength high-altitude detection laser radar 7 through a cable, wherein the cable penetrates through the base 1 and the inner through hole of the cylinder 2. Through aforementioned design, can simplify and walk the line, do benefit to the simplification of whole device. Furthermore, the electrical wires required for the power supply may also be passed through the inner through holes of the base 1 and the cylinder 2.
Preferably, the control module is communicatively connected to the rocket launch controller via a wireless module, wherein the wireless module may include, but is not limited to, a WiFi wireless module, a bluetooth wireless module, and/or a ZigBee wireless module. Through aforementioned design, can further simplify and walk the line, do benefit to the simplification of whole device.
To sum up, adopt the artifical ground rocket operation automation equipment who influences weather that this embodiment provided, have following technological effect:
(1) the embodiment provides a novel ground rocket operation automation device suitable for weather modification operation, namely, on one hand, whether target cloud layers such as black cloud or hail cloud exist in airspaces in all directions can be rotationally detected by configuring a rotating holder and a dual-wavelength high-altitude detection laser radar at the top of a cylinder, and on the other hand, by configuring a forward and reverse rotating motor, a gear transmission mechanism, a sleeve and a weather modification rocket, when the target cloud layers are found, the rocket can be automatically launched towards the target cloud layers in the launching direction and safely launched, so that compared with a traditional rocket launching system, an operator does not need to determine the launching direction and opportunity by means of vision or experience in the whole process, the shadow operation efficiency can be effectively improved, the ammunition consumption is reduced, the shadow operation effect is improved, and the actual application requirements are met;
(2) the ground rocket operation automation device also has the advantages of good rocket rotation balance, fire and dust prevention, concise appearance, high automation degree, simple structure and the like, and is convenient for practical popularization and application.
The various embodiments described above are merely illustrative, and may or may not be physically separate, as they relate to elements illustrated as separate components; if reference is made to a component displayed as a unit, it may or may not be a physical unit, and may be located in one place or distributed over a plurality of network units. Some or all of the units can be selected according to actual needs to achieve the purpose of the solution of the embodiment. One of ordinary skill in the art can understand and implement it without inventive effort.
The above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: modifications of the technical solutions described in the embodiments or equivalent replacements of some technical features may still be made. Such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Finally, it should be noted that the present invention is not limited to the above-mentioned alternative embodiments, and that various other forms of products can be obtained by anyone in light of the present invention. The above detailed description should not be taken as limiting the scope of the invention, which is defined in the following claims, and which can be used to interpret the claims.
Claims (10)
1. The utility model provides an artificial influence weather's ground rocket operation automation equipment which characterized in that: the device comprises a base (1), a cylinder (2), a sleeve (3), a forward and reverse rotating motor (4), a driving gear (501), a driven gear (502), a rotating holder (6), a dual-wavelength high-altitude detection laser radar (7), an artificial weather influence rocket (8) and a control box (9);
the cylinder (2) is vertically fixed at the center of the top surface of the base (1), the sleeve (3) is sleeved on the periphery of the lower part of the cylinder (2) in a sliding manner, the forward and reverse rotating motor (4) is fixed on the top surface of the base (1) and the output end of the forward and reverse rotating motor is connected with the driving gear (501), the driven gear (502) is connected with the bottom of the sleeve (3) in a shaft manner and is meshed with the driving gear (501), and the gear transmission ratio of the driving gear (501) to the driven gear (502) is greater than 1;
the rotating tripod head (6) is installed at the top of the cylinder (2), the dual-wavelength high altitude detection laser radar (7) is installed on a rotating part of the rotating tripod head (6), the weather modification rocket (8) is obliquely installed on the periphery of the top of the sleeve (3), and a rocket launching controller is configured on the weather modification rocket (8);
the control box (9) is fixed on the top surface of the base (1) and is provided with a control module, a storage module, a GPRS communication module and a satellite positioning module, wherein the control module is respectively in communication connection with the storage module, the GPRS communication module, the satellite positioning module, the forward and reverse rotating motor (4), the rotating holder (6), the dual-wavelength high-altitude detection laser radar (7) and a controlled end of the rocket launching controller.
2. A weather-altering ground rocket work automation device as set forth in claim 1, wherein: the number of the weather modification rockets (8) is even and the rockets are divided into two groups on average, wherein the two groups of rockets are symmetrically arranged on two opposite sides of the sleeve (3).
3. A weather-altering ground rocket work automation device as set forth in claim 2, wherein: the inclined installation angle of the weather modification rockets (8) is 50-80 degrees, and the inclined installation angles of two different weather modification rockets (8) are different.
4. A weather-altering ground rocket work automation device as set forth in claim 1, wherein: the fixed fire prevention that is equipped with on the middle part periphery of sleeve (3) and is used for the clearance to cover base (1), positive reverse motor (4) driving gear (501), driven gear (502) and control box (9) covers (301), wherein, fire prevention covers (301) and is made by non-metallic material.
5. A weather-altering ground rocket work automation device as set forth in claim 4, wherein: and a heat insulation layer is arranged on the inner bottom surface of the fireproof cover (301).
6. A weather-altering ground rocket work automation device as set forth in claim 1, wherein: and a dust cover (201) for covering the top end face of the sleeve (3) with a gap is fixedly arranged on the periphery of the middle part of the cylinder (2).
7. A weather-altering ground rocket work automation device as set forth in claim 1, wherein: the control module is in communication connection with the rotating holder (6) and/or the dual-wavelength high-altitude detection laser radar (7) through a cable, wherein the cable penetrates through the base (1) and the inner through hole of the cylinder (2).
8. A weather-altering ground rocket work automation device as set forth in claim 1, wherein: the control module is in communication connection with the rocket launching controller through a wireless module, wherein the wireless module comprises a WiFi wireless module, a Bluetooth wireless module and/or a ZigBee wireless module.
9. A weather-altering ground rocket work automation device as set forth in claim 1, wherein: the control module adopts a microcontroller chip of STM32F103 series and a peripheral circuit thereof.
10. A weather-altering ground rocket work automation device as set forth in claim 1, wherein: the satellite positioning module adopts a Beidou/GPS dual-system wireless positioning module with the model number of UM 220-III.
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| CN201920984937.5U CN210220830U (en) | 2019-06-27 | 2019-06-27 | Ground rocket operation automation equipment of artificial influence weather |
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| CN201920984937.5U CN210220830U (en) | 2019-06-27 | 2019-06-27 | Ground rocket operation automation equipment of artificial influence weather |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113093142A (en) * | 2021-04-12 | 2021-07-09 | 天津市人工影响天气办公室 | Hail suppression effect evaluation method |
| CN117898156A (en) * | 2024-03-07 | 2024-04-19 | 成都润联科技开发有限公司 | Artificial weather intervention system based on unmanned aerial vehicle |
-
2019
- 2019-06-27 CN CN201920984937.5U patent/CN210220830U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113093142A (en) * | 2021-04-12 | 2021-07-09 | 天津市人工影响天气办公室 | Hail suppression effect evaluation method |
| CN117898156A (en) * | 2024-03-07 | 2024-04-19 | 成都润联科技开发有限公司 | Artificial weather intervention system based on unmanned aerial vehicle |
| CN117898156B (en) * | 2024-03-07 | 2024-05-31 | 成都润联科技开发有限公司 | Artificial weather intervention system based on unmanned aerial vehicle |
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| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A Ground Rocket Operation Automation Device for Artificial Weather Modification Effective date of registration: 20230516 Granted publication date: 20200331 Pledgee: Chengdu SME financing Company Limited by Guarantee Pledgor: CHENGDU RUNLIAN TECHNOLOGY DEVELOPMENT Co.,Ltd. Registration number: Y2023980040706 |
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