System and method for artificially influencing weather based on large unmanned aerial vehicle

Abstract

The invention provides an artificial weather influence system and method based on a large unmanned aerial vehicle, and relates to the technical field of artificial weather influence operation. The task management module is used for communication conversion, data processing and data interaction with a ground station, and the ground station and the task management module carry out information interaction through a communication link; the task load module is used for performing optical investigation and meteorological detection on external weather and sending investigation data and meteorological detection results to the task management module, and the task management module is further used for generating a first control signal based on the investigation data and the meteorological detection results; the response module is used for performing intervention operation based on the first control signal and sending intervention information to the task management module; and the power distribution module is used for supplying and distributing power to the task load module and the response module based on the second control signal of the task management module. The large unmanned aerial vehicle is adopted to construct a detection-intervention-monitoring dynamic closed-loop operation system, and the overall execution effect of task operation is improved.

Description

Technical Field

[0001] This application relates to the field of weather modification technology, and for example to a system and method for weather modification based on large unmanned aerial vehicles (UAVs). Background Technology

[0002] Weather modification refers to the use of technology to artificially influence the physical and chemical processes of the atmosphere in a region to mitigate and avoid natural disasters, utilizing climate resources to achieve operations such as rainfall, rain reduction, hail prevention, fog prevention, and frost prevention. Currently, most existing weather modification aircraft platforms are modified manned aircraft, requiring pilots to take off and operate. The areas where operations are conducted are often in areas with severe weather conditions, including clouds, strong winds, and severe convective weather, posing significant risks to flight safety. Furthermore, specific operations often require approaching and entering cloud layers, which can cause icing on the aircraft's wings and fuselage. Icing on the fuselage and wings can lead to catastrophic accidents such as wing breakage and engine failure, further increasing the risk of accidents. Traditional manned aircraft have virtually no effective anti-icing measures.

[0003] In related technologies, to ensure the safety of personnel, there are existing artificial weather modification platforms modified from small / lightweight drones. Most of these platforms are drone platforms weighing less than 300 kg. These drone platforms have solved the above-mentioned safety issues, but because the aircraft is small, has limited payload, limited power supply, and limited altitude, it can only carry a small amount of seeding payload for mission operations. At the same time, the limited altitude results in poor performance of mission operations based on the current artificial weather modification system in special scenarios such as meteorological observation and disaster early warning. Summary of the Invention

[0004] This application aims to provide a system and method for artificial weather modification based on large-scale unmanned aerial vehicles (UAVs).

[0005] According to one aspect of this application, a system for artificial weather modification based on large unmanned aerial vehicles (UAVs) is proposed, comprising: The task management module is used for communication conversion, data processing, and data interaction with the ground station. The ground station and the task management module interact with each other through a communication link. The mission payload module is used to perform optical reconnaissance and meteorological detection of external weather, and to send the reconnaissance data and meteorological detection results to the mission management module. The mission management module is also used to generate the first control signal based on the reconnaissance data and meteorological detection results. The response module is used to perform artificial weather modification intervention operations based on the first control signal and send the intervention information to the task management module; The power distribution module is used to supply power to the task load module and the response module based on the second control signal from the task management module.

[0006] According to one aspect of this application, a method for weather modification based on a large unmanned aerial vehicle (UAV) is proposed, comprising: sending a second control signal to a power distribution module to enable the power distribution module to supply power to a mission payload module and a response module; receiving reconnaissance data and meteorological detection results obtained and transmitted by the mission payload module through optical reconnaissance and meteorological detection of external weather; generating a first control signal based on the reconnaissance data and meteorological detection results to enable the response module to perform weather modification intervention operations based on the first control signal; receiving intervention information transmitted by the response module; and transmitting the reconnaissance data, meteorological detection results, and intervention information to a ground station.

[0007] According to one aspect of this application, an electronic device is provided, comprising: a processor; and a memory storing a computer program that, when executed by the processor, causes the processor to perform the method described above.

[0008] According to one aspect of this application, a non-transitory computer-readable medium is proposed, on which readable instructions are stored, which, when executed by a processor, cause the processor to perform the method described above.

[0009] It should be understood that the above general description and the following detailed description are merely exemplary and do not limit this application.

[0010] Beneficial effects: The embodiments provided in this application utilize large unmanned aerial vehicles (UAVs) as the operational platform, significantly improving operational safety and cost-effectiveness compared to traditional manned aircraft. Compared to small UAVs, they significantly enhance payload capacity, weather adaptability, flight ceiling, range, and flight time, enabling efficient and long-term operational coverage in more complex and severe weather environments, thus expanding the spatiotemporal boundaries of weather modification operations. Integrating multiple meteorological monitoring payloads, a dynamic closed-loop operational system of "detection-intervention-monitoring" is constructed. This system not only performs weather modification interventions but also monitors changes in meteorological parameters before, during, and after operations in real time and in situ, providing direct data support for scientifically evaluating operational effectiveness and dynamically optimizing operational plans. This greatly improves the accuracy and controllability of operations, thereby enhancing the overall execution effect of the mission. Attached Figure Description

[0011] To more clearly illustrate the technical solutions in the embodiments of this application, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings, without exceeding the scope of protection claimed by this application.

[0012] Figure 1This is a schematic diagram of the system connection provided in an embodiment of this application; Figure 2 A block diagram of a system for artificial weather modification based on large unmanned aerial vehicles (UAVs) provided for embodiments of this application; Figure 3 A schematic diagram illustrating the data and image transmission of the payload device provided in an embodiment of this application; Figure 4 A flowchart illustrating a method for artificial weather modification based on a large unmanned aerial vehicle (UAV) provided in this application embodiment; Figure 5 This is a schematic diagram of the structure of an electronic device provided in an embodiment of this application. Detailed Implementation

[0013] Exemplary embodiments will now be described more fully with reference to the accompanying drawings. However, these exemplary embodiments can be implemented in many forms and should not be construed as limited to the embodiments set forth herein; rather, they are provided so that this application will be thorough and complete, and will fully convey the concept of the exemplary embodiments to those skilled in the art. The same reference numerals in the drawings denote the same or similar parts, and therefore repeated descriptions of them will be omitted.

[0014] Furthermore, the described features, structures, or characteristics can be combined in any suitable manner in one or more embodiments. Numerous specific details are provided in the following description to give a thorough understanding of embodiments of this application. However, those skilled in the art will recognize that the technical solutions of this application can be practiced without one or more of the specific details, or other methods, components, apparatuses, steps, etc., can be employed. In other instances, well-known methods, apparatuses, implementations, or operations are not shown or described in detail to avoid obscuring various aspects of this application.

[0015] The block diagrams shown in the accompanying drawings are merely functional entities and do not necessarily correspond to physically independent entities. That is, these functional entities can be implemented in software, in one or more hardware modules or integrated circuits, or in different network and / or processor devices and / or microcontroller devices.

[0016] The flowcharts shown in the accompanying drawings are merely illustrative and do not necessarily include all content and operations / steps, nor do they necessarily have to be performed in the described order. For example, some operations / steps can be broken down, while others can be combined or partially combined; therefore, the actual execution order may change depending on the specific circumstances.

[0017] It should be understood that although the terms first, second, third, etc., may be used herein to describe various components, these components should not be limited by these terms. These terms are used to distinguish one component from another. Therefore, the first component discussed below may be referred to as the second component without departing from the teachings of this application. As used herein, the term "and / or" includes all combinations of any one and more of the associated listed items.

[0018] Figure 1 This is a schematic diagram of the system connection provided for an embodiment of this application. The system of this application is built on a large unmanned aerial vehicle (UAV), which is typically a UAV weighing 2 tons or more. Specifically, the system may include a mission management computer, a mission platform motor, an optoelectronic pod, a total water detector, a seeding controller, a flare catalyst, a flare bomb catalyst, a cloud particle spectrometer, a cloud particle imager, a precipitation particle imager, an anti-icing controller, a wing heating actuator, a communication link, a flight control computer, and an icing solver. The mission manager is used for information exchange between various payloads, the mission platform motor, the flight control computer, and the ground station receiver. The mission management computer and the ground station receiver are connected via a communication link, and can use RS-422 / RS422 (Recommended Standard 422) to transmit remote control and telemetry data and payload pass-through data, and use Synchronous Transmission using RS-422 (Synchronous RS-422) to transmit optoelectronic video and imager images. The mission platform's motor supplies power to various payloads in this application, as well as components such as the left wing root of large UAVs. The anti-icing controller can send control signals to these components to perform anti-icing operations.

[0019] For specific implementation details, please refer to the following examples.

[0020] Figure 2 A block diagram of a system for artificial weather modification based on large unmanned aerial vehicles (UAVs) provided for embodiments of this application. Figure 2 As shown, the system 20 includes: a task management module 201, a task load module 202, a response module 203, and a power distribution module 204.

[0021] The mission management module 201 is used for communication conversion, data processing, and data interaction with the ground station. The ground station and the mission management module interact with each other through a communication link. The mission payload module 202 is used for optical reconnaissance and meteorological detection of external weather, and sends the reconnaissance data and meteorological detection results to the mission management module 201. The mission management module 201 is also used to generate a first control signal based on the reconnaissance data and meteorological detection results. The response module 203 is used to perform artificial weather modification intervention operations based on the first control signal. The power distribution module 204 is used to supply and distribute power to the mission payload module 202 and the response module 203 based on the second control signal from the mission management module 201.

[0022] In this application, the task management module 201 can specifically be as follows: Figure 1 The task management computer shown can exchange information with the task payload module 202 and the response module 203. The exchange can be conducted via RS-422 or RS-485 (Recommended Standard 485). The task management module 201 can perform communication conversion, logical analysis, image processing, and other data processing on the received data, and then send the resulting data to the receiving end of the ground station.

[0023] The mission payload module 202 can be a module integrating various mission payloads of different types, such as optical reconnaissance of external weather and meteorological detection. The response module 203 can be an integrated module of equipment that performs actions such as seeding rain-promoting catalysts and de-icing based on actual detected data. The power distribution module 204 can receive the first control signal from the mission management module 201 to supply or distribute power to the mission payload module 202 and the response module 203. The ground station can aggregate data and send commands to the mission management module 201.

[0024] This application utilizes large unmanned aerial vehicles (UAVs) as the operational platform, significantly improving operational safety and cost-effectiveness compared to traditional manned aircraft. Compared to smaller UAVs, it significantly enhances payload capacity, weather adaptability, flight ceiling, range, and flight time, enabling efficient and long-term operational coverage in more complex and severe weather environments, thus expanding the spatiotemporal boundaries of weather modification operations. It integrates multiple meteorological monitoring payloads to construct a dynamic closed-loop operational system of "detection-intervention-monitoring." This system not only performs weather modification interventions but also monitors changes in meteorological parameters before, during, and after operations in real time and in situ. This provides direct data support for scientifically evaluating operational effectiveness and dynamically optimizing operational plans, greatly improving the accuracy and controllability of operations, thereby enhancing the overall execution effect of the mission.

[0025] According to some embodiments, reference Figure 2The mission payload module 202 includes: an optoelectronic pod 2021 for optical reconnaissance in visible and infrared modes and generating corresponding reconnaissance data; a total water detector 2022 for detecting the water content of clouds and fog in external weather to generate corresponding meteorological detection results; a cloud particle spectrometer 2023 for detecting the microscopic physical parameters of particles in clouds and precipitation in external weather to generate corresponding meteorological detection results; a cloud particle imager 2024 for real-time imaging of weather factors and particle distribution measurement in external weather to generate corresponding meteorological detection results; and a precipitation particle imager 2025 for detecting the descent parameters of precipitation particles in external weather to generate corresponding meteorological detection results.

[0026] The optoelectronic pod 2021 in this application serves as a mission payload and can perform optical reconnaissance in visible light and infrared modes. In actual missions, when encountering natural disasters, it can serve as a reconnaissance platform to provide disaster area information, provide technical support for emergency rescue and disaster relief, and transmit optoelectronic remote control and telemetry information (reconnaissance data) to the mission management module 201. It also transmits optoelectronic video data (reconnaissance data) via SDI (Serial Digital Interface).

[0027] In some implementations, the photoelectric pod 2021 can be understood as a high-altitude camera. In the absence of natural disasters, the system can be configured to perform other reconnaissance tasks based on user needs. Common needs, in addition to disaster emergency response, include geographic mapping, maritime patrol, and military applications.

[0028] The Total Water Detector 2022 serves as a mission payload to detect the water content of clouds and fog in the meteorological field, namely LWC (Liquid Water Content) and TWC (Total Water Content). It is particularly suitable for the accurate analysis of mixed phase clouds (where ice and water coexist). The measurement data (meteorological detection results) are transmitted to the mission management computer via serial communication for data processing and distribution.

[0029] The Cloud Particle Spectrometer 2023 serves as the mission payload, used to measure microscopic physical parameters such as the concentration, size distribution, phase (liquid or solid), and motion characteristics of particles in clouds and precipitation. Measurement data (meteorological observation results) are transmitted via serial communication to the mission management module 201 for data processing and distribution to the ground station, where operators can access the information.

[0030] In some implementations, the packet assembly and distribution of different data packets from different devices is part of the data processing of the task management module 201. Because data from large UAVs is transmitted to the ground station via the UAV data link, data from different payload devices cannot be directly accessed through the data link (since these devices do not follow the existing communication protocols of UAVs). It must be processed uniformly by the task management module 201 before being sent to the data link and transmitted to the ground station. Only then can the ground station software reconstruct the data and display it correctly.

[0031] As a mission payload, the Cloud Particle Imager 2024 uses linear photoelectric array detection imaging technology to mainly perform real-time imaging and particle size distribution measurement of cloud droplets, ice crystals, and precipitation particles. The measurement data (meteorological detection results) is transmitted to the mission management module 201 via serial communication for data processing and distribution. The image data is received by the serial port and then converted into a synchronous 422 signal for output.

[0032] In some implementations, image data undergoes a synchronization 422 conversion performed by the synchronization board of the task management module 201, and is then transmitted to the data link, which in turn transmits it to the ground station. Measurement data (meteorological detection results) consists of data packets generated during normal equipment operation (not images, and the data volume is small), while image data consists of images generated by the detector and has a large data volume. They are transmitted through different channels of the data link to ensure that they do not become entangled.

[0033] The Precipitation Particle Imager 2025 captures and analyzes parameters such as the morphology, size, concentration, and falling velocity of precipitation particles (raindrops, snow crystals, graupel, hail, etc.) in real time, providing microphysical data support for disaster early warning, weather modification, and climate research. Measurement data (meteorological detection results) are transmitted to the task management module 201 via serial communication for data processing and distribution. Image data is received via serial port and internally converted into a synchronous 422 signal for output. This is the second device with image detection capabilities.

[0034] This application integrates an optoelectronic pod (macroscopic visible / infrared imaging), a total water detector (quantitative analysis of total water content), and a series of particle spectrometers / imagers (microscopic particle morphology and distribution). This system achieves comprehensive, multi-level, synchronous perception of target weather systems, from macroscopic morphology and total water storage to microscopic particle phase, scale, and concentration. This overcomes the limitations of a single sensor perspective, providing an unprecedentedly complete data foundation for weather modification operations. The combination of cloud particle spectrometers, imagers, and precipitation particle imagers enables real-time acquisition of key microscopic physical parameters within clouds and precipitation, such as particle number concentration, particle size distribution, shape (e.g., ice dendrites, snowflakes, graupel), and descent velocity. This allows the system to directly "diagnose" cloud phases (ice clouds, water clouds, or mixed phases), precipitation types, and formation mechanisms, providing direct and precise physical evidence for the scientific selection of catalytic timing, location, and formulation, greatly enhancing the targeting and scientific rigor of operations.

[0035] According to some embodiments, reference Figure 2 The system 20 also includes a flight control computer 205, which sends flight parameter data to the mission management module 201; the mission management module 201 is also used to send load control commands to the flight control computer 205.

[0036] In this application, the mission payload requires flight parameter data, which is stored in the flight control computer 205. Therefore, the mission management module 201 needs to send payload control commands to the flight control computer 205 to obtain the flight parameter data. The flight control computer 205 transmits the aircraft's flight parameters to the mission management module 201, while the mission management module 201 also transmits some payload control commands from the aircraft platform to the flight control computer 205.

[0037] In some implementations, to better perform mission operations, it is sometimes necessary to adjust the flight attitude and route. This can be achieved by sending instructions from the mission management module 201 to the flight control computer 205. The ground station sends a command to open the mission management module 201 and grant it control over the flight control computer 205. Based on the mission payload feedback, the mission management module 201 determines whether the aircraft's heading or altitude needs to be changed. The mission management computer 205 generates flight control commands and sends them to the flight control computer 205 via a serial port channel, which then executes the commands.

[0038] This application sends payload control commands to the flight control computer through the mission management module. The system can dynamically adjust the UAV's flight path, attitude, or altitude based on real-time meteorological data (such as cloud clusters to be tracked or strong convective areas to be avoided). This transforms the UAV from a passive carrier platform into an intelligent operational entity that can proactively respond to mission requirements, forming a closed loop of "detection → decision-making → flight control → operation".

[0039] According to some embodiments, reference Figure 2 The system 20 also includes an icing solver 206, which is connected to the flight control computer 205 and is used to detect icing data of large UAVs; the mission management module 201 makes logical judgments on anti-icing and de-icing based on the icing data.

[0040] In this application, the icing solver 206 is an airborne icing detection and measurement device. It is typically not a single sensor, but an integrated system that may include an icing detector, an icing rate / thickness sensor, etc. The icing solver 206 is directly connected to the flight control computer 205, meaning that icing data is incorporated into the flight critical parameter system. The flight control computer 205 can acquire raw icing information for basic flight safety warnings or stability compensation.

[0041] Icing data detected by the icing solver 206, such as "open ice detected on the leading edge of the left wing, thickness 2mm, cumulative rate 0.5mm / min", is sent in real time to the mission management module 201 via the flight control computer 205 or via an independent communication link.

[0042] In some implementations, within the task management module 201, icing data can be fused with other multi-source information, such as meteorological data, flight data, and mission data. The task management module 201 can preset or perform real-time calculations on a set of anti-icing and de-icing logic judgment rules, make multi-level decisions based on the fused information, and generate corresponding control commands. In some implementations, this may include: Level 1 Response (Automatically Triggered Protection): Judgment: Icing has begun.

[0043] Command: Immediately activate the electrothermal anti-icing / de-icing system (such as heating of the wing leading edge, propeller, and sensors) via power distribution module 204.

[0044] Level 2 Response (Adjusting Flight Strategy): Judgment: The ice layer continues to accumulate and the de-icing system is ineffective, or it is predicted that the area will enter a strong icing zone.

[0045] Command: Send commands to flight control computer 205, suggesting or directly executing changes in altitude, adjustments in heading to escape the icing cloud area, or requesting to return to base.

[0046] Level 3 Response (Adjusting Task Strategy): Judgment: Icing conditions affect the operation of specific payloads (e.g., the optical window is covered by ice), but the flight platform is still safe.

[0047] Instructions: Adjust the operating mode of mission payload module 202 (e.g., retract the optoelectronic pod, suspend certain external detections), or replan the operational route to balance safety and mission completion.

[0048] Level IV Response (Comprehensive Emergency Decision-Making): Judgment: A comprehensive assessment is conducted by combining icing data, remaining battery power, and the criticality of the mission.

[0049] Command: Make the final decision on "continue operation", "abort mission and return to base" or "fly to alternate landing site", and coordinate the flight control, payload and response modules to execute the command.

[0050] This application utilizes an icing de-icing calculator to acquire the most accurate icing information in real time and in situ, enabling the system to "sense" and "assess" threat levels in icy environments, thereby proactively managing risks. This is a core prerequisite for the safe execution of cloud-penetrating operations by UAVs. The system no longer completely avoids cloud systems due to icing. Through the combination of automatic anti-icing and intelligent flight path adjustment, it can continue to perform operations near or within the target cloud layer within a controllable risk boundary, significantly expanding the effective operational window and space, and improving the mission success rate under complex weather conditions.

[0051] According to some embodiments, reference Figure 2 The response module 203 includes: a seeding controller 2031, which controls the seeding equipment on the large drone to seed the items to be seeded in the corresponding area; and an anti-icing controller 2032, which controls the actuator of the wing heating of the large drone to perform segmented control of the heating area of ​​the large drone.

[0052] In this application, the seeding controller 2031 is used to control the seeding equipment on the fuselage to operate. The seeding equipment and the items to be seeded (items to be seeded) may include a flare bar on the left wing, a flare bomb on the fuselage, and a flare bar on the right wing. The flare bar and flare bomb are rain-inducing catalysts. The seeding controller itself is monitored by a mission management computer. The time and location of seeding are determined by ground operators, who send commands to the mission management module 201. Upon receiving the command, the mission management module 201 controls the seeding controller 2031 in the response module 203, causing the seeding controller 2031 to control the seeding equipment at the corresponding location to perform seeding in the corresponding area. After seeding is completed, the mission management module 201 collects a completion signal and sends it back to the ground operators, thus forming a closed-loop control system.

[0053] The anti-icing controller 2032, together with the actuators for heating each wing, constitutes the entire UAV anti-icing system. According to flight dynamics and structural mechanics, icing on the wings and tail of an aircraft can easily cause wing breakage, leading to air crashes. Therefore, it is essential to install anti-icing actuators on the wings and tail. The anti-icing controller 2032 controls 11 heating zones on the wings and tail in segments. The controller itself is located inside the cabin. Segmented control uses 11 power switches to control each of the 11 heating zones. The anti-icing controller 2032 adjusts the operating timing and duration of each switch according to instructions and algorithms.

[0054] In some implementations, the heating area is divided into 11 segments, each controlled by an independent power switch. The anti-icing controller 2032 is responsible for coordinating the switching and operating times of different segments. The anti-icing controller 2032 is further controlled at a higher level by the task management module 201, which can receive commands from ground station operators. Each heating segment can be set with a minimum operating temperature (heating begins below this temperature) and a maximum operating temperature (heating stops upon reaching this temperature). Due to the limited power supply capacity of the UAV, it is impossible to simultaneously heat all segments at full power while other mission payloads are operating. Therefore, the anti-icing controller 2032 employs a time-sharing and priority-based approach, prioritizing heating areas with higher risk before heating areas with lower risk, prioritizing iced areas before heating uniced areas, and so on. Based on the icing situation, the anti-icing controller 2032 can provide feedback to the task management module 201, which may shut down other powered mission payloads to prioritize power supply to the anti-icing heating module.

[0055] The seeding controller in this application is no longer a simple switch, but can precisely control the seeding rate, seeding amount, and start / stop timing of the catalyst in a specific spatial area based on instructions from the task management module (such as signals generated based on cloud particle spectrometer and total water content data). This allows for precise delivery of the catalyst to areas in the cloud with high supercooled water content and strong dynamic lift, avoiding ineffective seeding and improving cloud water resource conversion efficiency. The anti-icing controller provides segmented control of the wing heating actuators. The system can heat the entire aircraft uniformly based on data on icing location, thickness, and type provided by the icing solver.

[0056] According to some embodiments, the task management module 201 analyzes the reconnaissance data and meteorological detection results, and selects the corresponding communication link based on the analysis results.

[0057] In this application, the task management module 201 receives data from the aforementioned different devices, and can distinguish the data according to the size of the data, and then match a suitable communication link.

[0058] In some implementations, an embedded spatiotemporal registration algorithm can be used to unify cloud top features in photoelectric images, microscopic parameters measured by meteorological probes, and the aircraft's attitude and position into a single spatiotemporal reference frame using high-precision GPS time and location information. Other correspondence methods can then be used to match communication links.

[0059] The system does not rely on a single, fixed communication link. Through dynamic selection, it can always use the most suitable pipeline based on the most pressing task requirements (whether it is real-time command or data integrity) and the actual communication environment. This significantly improves the success rate and timeliness of transmitting critical commands and alarm information, especially in complex terrain or harsh electromagnetic environments, avoiding overall task failure due to communication interruptions.

[0060] According to some embodiments, when the analysis result of the task management module 201 is a large amount of data, the communication link is determined to be a synchronous 422 transmission mode; when the analysis result of the task management module 201 is a small amount of data, the communication link is determined to be an RS-422 transmission mode.

[0061] The communication link serves as the ground station's communication device between the aircraft and the ground station. It connects to the mission management module 201 via RS-422 and synchronous 422 connections. The synchronous 422 method, due to its high transmission rate, is used to transmit large data sets such as video and detector images. Data distribution is managed by the mission management module 201. There is only one ground station, but because the communication protocols of different mission payloads are incompatible with the UAV's own communication protocol, the mission management computer needs to process the data before transmitting it to the data link. Otherwise, data from all payload devices would be mixed together, making it unrecognizable by the ground software. Furthermore, image data is very large and requires a dedicated data link channel; it cannot be mixed with non-image data, so it needs to be distributed. Therefore, image and non-image data need to be sent through separate channels. Data from different devices within the non-image data channel needs to be reassembled and sent time-divisionally; otherwise, the ground system cannot recognize it.

[0062] In some implementations, refer to Figure 3 The diagram illustrates the data and image transmission of the payload equipment. The payload equipment can send data (including images and non-images) to the mission management computer. The mission management computer can parse the instructions processed by the ground station backend, separate the data, and transmit it using the corresponding links. The ground station backend then receives the data. Additionally, the human-machine interface can be configured with various software programs for sending or receiving information / signals to or from the ground station backend.

[0063] The following describes an apparatus embodiment of this application, which can be used to perform the method embodiment of this application. For details not disclosed in the apparatus embodiment of this application, please refer to the method embodiment of this application.

[0064] Figure 4 The flowchart of the method for artificial weather modification based on a large unmanned aerial vehicle (UAV) provided in this application embodiment is applied to the task management module 201 described above. For example... Figure 4As shown, the method includes steps S400, S401, S402, S403 and S404.

[0065] In step S400, a second control signal is sent to the power distribution module so that the power distribution module supplies power to the task load module and the response module. In step S401, the reconnaissance data and meteorological detection results obtained and transmitted by the mission payload module through optical reconnaissance and meteorological detection of external weather are received; In step S402, a first control signal is generated based on the reconnaissance data and meteorological detection results, so that the response module can perform artificial weather modification intervention based on the first control signal; In step S403, intervention information sent by the response module is received; In step S404, the reconnaissance data, meteorological detection results, and intervention information are sent to the ground station.

[0066] The method performs similar functions to the system provided earlier. Other functions can be found in the previous descriptions and will not be repeated here.

[0067] Figure 5 This is a schematic diagram of the structure of the electronic device provided in the embodiments of this application, such as... Figure 5 As shown, the electronic device 500 of this embodiment may include a memory 501 and a processor 502.

[0068] The memory 501 stores a computer program, which, when executed by the processor 502, causes the processor 502 to perform the method described in the above embodiments.

[0069] The processor 502 and the memory 501 are connected, for example, via a bus.

[0070] Optionally, the electronic device 500 may also include a transceiver. It should be noted that in practical applications, the transceiver is not limited to one, and the structure of the electronic device 500 does not constitute a limitation on the embodiments of this application.

[0071] Processor 502 may be a CPU (Central Processing Unit), a general-purpose processor, a DSP (Digital Signal Processor), an ASIC (Application Specific Integrated Circuit), an FPGA (Field Programmable Gate Array), or other programmable logic devices, transistor logic devices, hardware components, or any combination thereof. It can implement or execute the various exemplary logic blocks, modules, and circuits described in conjunction with the disclosure of this application. Processor 502 may also be a combination that implements computational functions, such as including one or more microprocessor combinations, a combination of a DSP and a microprocessor, etc.

[0072] A bus can include a pathway for transmitting information between the aforementioned components. The bus can be a PCI (Peripheral Component Interconnect) bus or an EISA (Extended Industry Standard Architecture) bus, etc. Buses can be categorized as address buses, data buses, control buses, etc. For ease of illustration, only one thick line is used in the diagram, but this does not imply that there is only one bus or one type of bus.

[0073] The memory 501 can be ROM (Read Only Memory) or other types of static storage devices capable of storing static information and instructions, RAM (Random Access Memory) or other types of dynamic storage devices capable of storing information and instructions, or it can be EEPROM (Electrically Erasable Programmable Read Only Memory), CD. ROM (Compact Disc Read Only Memory) or other optical disc storage, optical disc storage (including compressed discs, laser discs, optical discs, digital universal discs, Blu-ray discs, etc.), disk storage media or other magnetic storage devices, or any other medium capable of carrying or storing desired program code in the form of instructions or data structures and accessible by a computer, but not limited thereto.

[0074] The memory 501 is used to store application code that executes the solution of this application, and its execution is controlled by the processor 502. The processor 502 is used to execute the application code stored in the memory 501 to implement the content shown in the foregoing method embodiments.

[0075] Electronic devices include, but are not limited to: mobile terminals such as mobile phones, laptops, digital radio receivers, PDAs (personal digital assistants), PADs (tablet computers), PMPs (portable multimedia players), and in-vehicle terminals (such as in-vehicle navigation terminals), as well as fixed terminals such as digital TVs and desktop computers. Servers can also be included. Figure 5 The electronic device shown is merely an example and should not impose any limitation on the functionality and scope of use of the embodiments of this application.

[0076] The electronic device in this embodiment can be used to execute the method of any of the above embodiments, and its implementation principle and technical effect are similar, so they will not be described again here.

[0077] This application also provides a non-transitory computer-readable storage medium storing computer-readable instructions thereon, which, when executed by a processor, cause the processor to perform the method as described in the above embodiments.

[0078] Those skilled in the art will understand that all or part of the steps of the above-described method embodiments can be implemented by hardware related to program instructions. The aforementioned program can be stored in a non-transitory computer-readable storage medium. When executed, the program performs the steps of the above-described method embodiments; and the aforementioned storage medium includes various media capable of storing program code, such as ROM, RAM, magnetic disks, or optical disks.

[0079] The embodiments of this application have been described in detail above. Specific examples have been used to illustrate the principles and implementation methods of this application. The descriptions of the embodiments above are only for the purpose of helping to understand the method and core ideas of this application. Furthermore, any changes or modifications made by those skilled in the art based on the ideas of this application, and on the specific implementation methods and application scope of this application, are all within the scope of protection of this application. Therefore, the content of this specification should not be construed as a limitation of this application.

Claims

1. A system for artificial weather modification based on large unmanned aerial vehicles (UAVs), characterized in that, include: The task management module is used for communication conversion, data processing, and data interaction with the ground station. The ground station and the task management module interact with each other through a communication link. The mission payload module is used to perform optical reconnaissance and meteorological detection of external weather, and to send the reconnaissance data and meteorological detection results to the mission management module. The mission management module is also used to generate a first control signal based on the reconnaissance data and the meteorological detection results. The response module is used to perform artificial weather modification intervention operations based on the first control signal and send the intervention information to the task management module; The power distribution module is used to supply power to the task load module and the response module based on the second control signal from the task management module.

2. The system according to claim 1, characterized in that, The mission payload module includes: The optoelectronic pod is used for optical reconnaissance in visible light and infrared modes and generates corresponding reconnaissance data; A total water detector is used to detect the water content of clouds and fog in the external weather to generate corresponding meteorological detection results; The cloud particle spectrometer is used to detect the microscopic physical parameters of particles in clouds and precipitation in the external weather, so as to generate corresponding meteorological detection results. A cloud particle imager is used to perform real-time imaging of weather factors and particle distribution measurement of the external weather to generate corresponding meteorological detection results. A precipitation particle imager is used to detect the falling parameters of precipitation particles in the external weather to generate corresponding meteorological detection results.

3. The system according to claim 1, characterized in that, It also includes a flight control computer, used to send flight parameter data to the mission management module; The task management module is also used to send payload control commands to the flight control computer.

4. The system according to claim 3, characterized in that, It also includes an icing solver, which is connected to the flight control computer and is used to detect the icing data of the large UAV; The task management module makes logical judgments on anti-icing and de-icing based on the icing data.

5. The system according to claim 1, characterized in that, The response module includes: A seeding controller controls the seeding equipment on the large drone to seed the items to be seeded in the corresponding area. The anti-icing controller controls the wing heating actuator of the large UAV to perform segmented control of the heating area of ​​the large UAV.

6. The system according to claim 1, characterized in that, The task management module analyzes the reconnaissance data and the meteorological detection results, and selects the corresponding communication link based on the analysis results.

7. The system according to claim 6, characterized in that, If the analysis result of the task management module is a large amount of data, it is determined that the communication link is in synchronous 422 transmission mode; If the analysis result of the task management module is a small amount of data, the communication link is determined to be an RS-422 transmission mode.

8. A method for artificial weather modification based on large unmanned aerial vehicles (UAVs), characterized in that, include: Send a second control signal to the power distribution module so that the power distribution module supplies power to the task load module and the response module; Receives and transmits reconnaissance data and meteorological detection results obtained and transmitted by the mission payload module through optical reconnaissance and meteorological detection of external weather; Based on the reconnaissance data and the meteorological detection results, a first control signal is generated so that the response module can perform artificial weather intervention operations based on the first control signal; Receive intervention information sent by the response module; The reconnaissance data, the meteorological detection results, and the intervention information are sent to the ground station.

9. An electronic device, characterized in that, include: processor; A memory storing a computer program that, when executed by the processor, causes the processor to perform the method as described in claim 8.

10. A non-transitory computer-readable storage medium, characterized in that, It stores computer-readable instructions that, when executed by a processor, cause the processor to perform the method as described in claim 8.

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