An airborne embedded under-drop sounding system and a sounding method

Abstract

The application provides an airborne embedded underthrow sounding system and a sounding method. The system comprises a launching device arranged in a payload cabin of an unmanned aerial vehicle, a plurality of sounding instruments and a control system. The launching device comprises a launching unit provided with a plurality of independent launching tubes and an air path system. The launching tubes are provided with connectors and locking mechanisms. The control system comprises a control device and a wireless communication module. The sounding instruments are activated in a wired manner through the connectors before launching. After launching, the sounding instruments are switched to a wireless mode to receive the detection data returned by the sounding instruments. The application is embedded in the belly of the unmanned aerial vehicle, retains the original aerodynamic shape of the unmanned aerial vehicle, effectively reduces the flight resistance, and independently arranges the sounding instruments in the launching tubes to realize independent on-demand launching. The application adopts an aerodynamic launching scheme to make the sounding instruments leave the unmanned aerial vehicle at a controllable initial speed, improves the launching precision, is suitable for high-precision atmospheric detection in complex environments, and is accurate and efficient in detection.

Description

Technical Field

[0001] This application relates to the field of unmanned aerial vehicle (UAV) technology, and more specifically, to an airborne embedded drop sounding system and sounding method. Background Technology

[0002] With the rapid development of drone technology, drones have been widely used in many fields such as meteorological observation, military reconnaissance, and emergency rescue.

[0003] The UAV-borne dropsonde system is a core component of the UAV. Traditional UAV-borne dropsonde systems typically use a method where the radiosonde is mounted under the wing and deployed via a chain or catapult. This externally mounted approach is primarily suitable for areas with relatively stable climates and gentle airflow changes. However, its operating environment and deployment capabilities are subject to numerous limitations, making it difficult to cope with complex and variable severe weather (such as strong convection, typhoons, cold vortices, and other extreme weather events), thus failing to meet the demands for high-precision meteorological detection. Summary of the Invention

[0004] This application provides an airborne internally embedded drop sounding system and a sounding method, which solves the technical problems of high flight resistance, low deployment reliability, and low detection accuracy of externally mounted sounding systems.

[0005] This application provides an airborne, internally embedded, drop-sonde system, comprising: a launching device disposed within the payload bay of a UAV; the launching device includes a delivery unit and an air path system; the delivery unit includes multiple independently arranged launch tubes; each launch tube stores a radiosonde and allows the radiosonde to be vertically loaded and ejected; the air path system connects to each launch tube and provides pneumatic pressure to each launch tube individually; each launch tube is equipped with a connector and a locking mechanism; the locking mechanism limits the radiosonde and allows it to automatically detach from the radiosonde under the pneumatic pressure; and multiple radiosondes disposed within the launch tubes and connected to the delivery unit. The connector forms a disconnectable electrical connection; and the control system includes a control device and a wireless communication module, configured such that: after receiving an activation command, the control device sends an activation signal to the target radiosonde via the connector in a wired manner; after the target radiosonde is activated, the status information of the target radiosonde is sent to the UAV via the wireless communication module and the control device; after receiving a deployment command, the control device controls the deployment air path corresponding to the target radiosonde to be connected, so that the air path system provides aerodynamic pressure to the target radiosonde; and the wireless communication module receives the detection data returned by the target radiosonde and sends it to the UAV via the control device.

[0006] In some embodiments, the gas path system includes a gas supply component, an air inlet pipe component, and a gas path distribution component. The gas supply component is used to store high-pressure gas and is equipped with a main solenoid valve. The air inlet pipe component connects the gas supply component and the gas path distribution component. The gas path distribution component is equipped with a plurality of station solenoid valves corresponding to each of the launch tubes. Each station solenoid valve is used to control the opening and closing of the delivery gas path corresponding to the launch tube.

[0007] In some embodiments, the locking mechanism includes a lock housing, a lock plug, a lock head, and a spring. The lock plug is disposed at the bottom of the lock housing, and the lock head and the spring are disposed inside the lock housing. The lock head locks the radiosonde inside the launch tube via the spring.

[0008] In some embodiments, the launching device further includes a piston that is slidably disposed within the launching tube to seal the bottom of the launching tube under pneumatic pressure.

[0009] In some embodiments, a guide groove is provided inside the launch tube, and the guide groove is fixed to the inner wall surface of the launch tube in the axial direction so that the piston can slide along the guide groove.

[0010] In some embodiments, the launch tube is an aluminum alloy launch tube or a carbon fiber wound launch tube.

[0011] In some embodiments, the status information includes at least one of the following: the location information, identity information, activation status information, or working status information of the radiosonde.

[0012] In some embodiments, the detection data includes at least one of temperature data, humidity data, air pressure data, location data, wind speed data, or wind direction data collected by the radiosonde.

[0013] In some embodiments, the gas supply assembly further includes a pressure reducing valve for reducing the pressure of the high-pressure gas in the gas cylinder to within a preset pressure range.

[0014] This application also provides a sounding method applied to the airborne embedded drop sounding system described above. The method includes: receiving an activation command for a target sounding device; sending an activation signal to the target sounding device via a connector; the target sounding device activating itself upon receiving the activation signal and transmitting its status information back to the control device via the wireless communication module; the control device forwarding the status information to a drone; receiving a drop command for the target sounding device; controlling the launching device to pneumatically launch the target sounding device from the corresponding launching tube according to the drop command; and switching to wireless communication mode after the target sounding device detaches from the launching tube and disconnects from the connector, and receiving detection data transmitted back by the target sounding device during the detection process.

[0015] In this embodiment, by integrating the launching device and the radiosonde into the payload bay under the fuselage of the UAV, an internal installation is achieved, eliminating the need for external mounting under the wings. This preserves the original aerodynamic shape of the UAV, effectively reducing flight drag, lowering energy consumption, extending flight range, and significantly improving the UAV's detection performance in extreme weather conditions such as typhoons. Secondly, the multiple radiosondes in this application are independently loaded into their respective launch tubes, allowing for individual or batch deployment of the radiosondes, significantly improving detection efficiency. Furthermore, the use of a pneumatic catapult method for launching the radiosondes with a controllable initial velocity effectively avoids the attitude instability problems common in traditional gravity-based deployment methods, improving detection success rate and data validity. Furthermore, this application adopts a hybrid communication mode of wired activation and wireless transmission. Before the radiosonde is deployed, activation is completed in a wired manner through the control device and connector. The signal is stable and reliable, with strong anti-interference ability and precise deployment control. After the radiosonde is removed from the machine, it automatically switches to wireless communication mode and receives the transmitted detection data in real time through the wireless communication module and control device, thus achieving highly reliable deployment and efficient data transmission. Attached Figure Description

[0016] To more clearly illustrate the technical solutions in the embodiments of this application or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only embodiments of this application. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0017] Figure 1 A schematic diagram of the system principle of an airborne embedded drop sounding system provided for some embodiments of this application;

[0018] Figure 2A schematic diagram of the launching device in an airborne embedded drop sounding system provided for some embodiments of this application;

[0019] Figure 3 A schematic diagram of the structure of a launch device with a hidden frame in an airborne embedded drop sounding system provided for some embodiments of this application;

[0020] Figure 4 A schematic diagram of the frame structure of an airborne embedded drop sounding system provided for some embodiments of this application;

[0021] Figure 5 A schematic diagram of the launch tube in an airborne embedded drop sounding system provided for some embodiments of this application;

[0022] Figure 6 A schematic diagram of the structure of a cover plate assembly in an airborne embedded drop sounding system provided in some embodiments of this application;

[0023] Figure 7 A schematic diagram of the locking mechanism in an airborne embedded drop sounding system provided in some embodiments of this application;

[0024] Figure 8 A schematic diagram of the air path system in an airborne embedded drop sounding system provided in some embodiments of this application;

[0025] Figure 9 A schematic diagram of the structure of an air path distribution component in an airborne embedded drop sounding system provided for some embodiments of this application;

[0026] Figure 10 A schematic diagram of the gas pipeline structure in an airborne embedded drop sounding system provided in some embodiments of this application;

[0027] Figure 11 A schematic diagram of the air supply component in an airborne embedded drop sounding system provided in some embodiments of this application;

[0028] Figure 12 A schematic diagram of a control device in an airborne embedded drop sounding system provided for some embodiments of this application;

[0029] Figure 13 A schematic diagram of a wireless communication module in an airborne embedded drop sounding system provided for some embodiments of this application;

[0030] Figure 14 A schematic diagram of the structure of a radiosonde in an airborne embedded drop radiosonde system provided in some embodiments of this application;

[0031] Figure 15An activation flowchart of an airborne embedded drop sounding system provided for some embodiments of this application;

[0032] Figure 16 This application provides a flowchart of the deployment process for an airborne embedded drop sounding system, which is provided for some embodiments of the present application.

[0033] The attached figures are labeled as follows:

[0034] 100. Dropsonde system;

[0035] 1. Launching device; 2. Radiosonde; 3. Control system;

[0036] 11. Deployment unit; 12. Pneumatic system; 21. Parachute compartment; 22. Electronic components compartment; 23. Sensor compartment; 31. Control device; 32. Wireless communication module;

[0037] 111. Launch tube; 112. Connector; 113. Locking mechanism; 114. Frame; 121. Gas supply assembly; 122. Inlet pipe assembly; 123. Gas distribution assembly; 124. Main solenoid valve; 125. Station solenoid valve; 126. Pressure reducing valve; 127. Gas cylinder pressure sensor; 128. Discharge pressure sensor; 129. Gas cylinder; 130. High-pressure safety valve; 131. Filling / discharging manual valve; 132. Low-pressure safety valve;

[0038] 1111, Cover plate assembly; 1112, Launch tube body; 1113, Guide groove; 1114, Middle flange; 1115, Heating film; 1131, Lock housing; 1132, Lock plug; 1133, Lock head; 1134, Spring; 1135, Tail end cap; 1141, Front and rear side plates; 1142, Top cover plate; 1143, Left and right side plates; 1144, Base plate; 1145, Reinforcing strip; 1231, Gas pipeline; 1232, Connector. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments of this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0040] Traditional externally mounted dropsonde systems face numerous challenges when conducting atmospheric sounding missions in extreme environments: First, the external structure is susceptible to severe weather disturbances and mechanical stress, leading to decreased launch reliability; second, external mounts cannot maintain the continuity of the UAV's aerodynamic shape. Furthermore, in some regions, single-point radiosondes cannot provide sufficient continuous or dense vertical profile data to support accurate modeling.

[0041] The embedded system provided in this application sets multiple radiosondes as independent falling unit modules and integrates them into an integrated launch device. It also supports the arrangement of multiple independent launch tubes, enabling batch deployment of tubes one by one or multiple groups in a coordinated manner. This greatly improves the sampling density and response speed within a unit of airspace and demonstrates significant advantages in dealing with sudden severe convective weather or complex meteorological environments.

[0042] Unless otherwise defined, all technical and scientific terms used in this application have the same meaning as commonly understood by one of ordinary skill in the art to which this application pertains; the terminology used in the description of this application is for the purpose of describing particular embodiments only and is not intended to limit the application; the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion. The terms "first," "second," etc., are used to distinguish different objects, not to describe a specific order or hierarchy.

[0043] In this application, the reference to "embodiment" means that a particular feature, structure, or characteristic described in connection with an embodiment may be included in at least one embodiment of this application. The appearance of this phrase in various places in the specification does not necessarily refer to the same embodiment, nor is it a separate or alternative embodiment that is mutually exclusive with other embodiments.

[0044] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," "linking," and "attachment" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal communication between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0045] In this application, the term "and / or" is merely a description of the relationship between related objects, indicating that three relationships can exist. For example, A and / or B can represent: A existing alone, A and B existing simultaneously, or B existing alone. Additionally, in this application, the character " / " generally indicates that the preceding and following related objects have an "or" relationship.

[0046] In the embodiments of this application, the same reference numerals denote the same components, and for the sake of brevity, detailed descriptions of the same components are omitted in different embodiments. It should be understood that the thickness, length, width, and other dimensions of various components in the embodiments of this application shown in the accompanying drawings, as well as the overall thickness, length, width, and other dimensions of the integrated device, are merely illustrative and should not constitute any limitation on this application.

[0047] In this application, "multiple" means two or more (including two).

[0048] Please refer to Figure 1 , Figure 2 and Figure 3 This application provides an airborne embedded dropsonde system 100, which is mainly used on an unmanned aerial vehicle (UAV) platform to perform precise detection tasks of meteorological elements such as atmospheric temperature, humidity, air pressure, wind speed, wind direction, and location under complex weather conditions (such as typhoons, strong convection, etc.).

[0049] Specifically, the system includes a launcher 1 and multiple radiosondes 2. The launcher 1 is installed internally within the payload bay of the UAV. It can be located on the underside of the forward fuselage of the UAV, making the launcher 1 an integral part of the UAV fuselage. This ensures a strong and reliable connection, effectively transferring the weight of the radiosonde system to the main load-bearing structure of the UAV. This minimizes local stress concentration on the UAV's skin, ensures the integrity of the airframe structure, does not damage the original aerodynamic shape of the UAV, and avoids the additional flight drag caused by external mounting.

[0050] The launching device 1 includes a delivery unit 11 and a gas path system 12. The delivery unit 11 includes multiple independent launch tubes 111, which are arranged in a preset manner inside the launching device 1, such as in an array. Each launch tube 111 independently stores a radiosonde 2, and the launch tubes 111 do not interfere with each other. The launch tubes 111 can store the radiosonde 2 and allow the radiosonde 2 to be vertically loaded and fired, for example, it can be fired vertically downwards, realizing sequential delivery of tubes one by one or batch delivery of multiple tubes in a coordinated manner.

[0051] The pneumatic system 12 connects to each launch tube 111 and can provide each launch tube 111 with the compressed gas required for pneumatic launch. The pneumatic paths of each launch tube 111 are independent of each other and do not affect each other, so that individual pneumatic control can be achieved for any launch tube 111.

[0052] The transmitter tube 111 is equipped with a connector 112, which may be, but is not limited to, an RF connector 112. After the radiosonde 2 is loaded into the transmitter tube 111, the connector 112 at the top of the radiosonde 2 mates with the transmitter tube 112, forming a disconnectable wired electrical connection. When the radiosonde 2 is ejected downward from the transmitter tube 111 under pneumatic pressure, the connection is automatically disconnected.

[0053] A locking mechanism 113 is provided on the launch tube 111. The locking mechanism 113 can limit the position of the radiosonde 2 and automatically detach the radiosonde 2 under aerodynamic pressure. Specifically, after the radiosonde 2 is installed in the launch tube 111, the locking mechanism 113 limits and fixes the radiosonde 2 inside the launch tube 111 to prevent the radiosonde 2 from accidentally falling off during flight due to vibration or airflow disturbance. When the air passage is connected, when the aerodynamic pressure acts on the bottom of the radiosonde 2, after the pressure reaches a set threshold, the locking mechanism 113 automatically contracts under force, automatically releasing the radiosonde 2 and driving the radiosonde 2 to be launched downward out of the launch tube 111.

[0054] The system also includes a control system 3, which includes a control device 31 and a wireless communication module 32. After receiving an activation command, the control device 31 sends an activation signal to the target radiosonde 2 via a wired connection through the connector 112. After the target radiosonde 2 is activated, its status information is sent to the UAV via the wireless communication module 32 and the control device 31. After receiving a deployment command, the control device 31 controls the deployment air path corresponding to the target radiosonde 2 to be connected so that the air path system 12 provides aerodynamic pressure to the target radiosonde 2. The wireless communication module 32 receives the detection data returned by the target radiosonde 2 and sends it to the UAV via the control device 31.

[0055] Therefore, during the activation phase, the UAV sends an activation command to the control device 31. The control device 31 sends an activation signal to the target radiosonde 2 via connector 112 in a wired manner. After receiving the activation signal, the target radiosonde 2 completes its own power-on activation and transmits the activation status information back to the control device 31 via the wireless communication module 32. The control device 31 then forwards the status information to the UAV to complete the activation confirmation.

[0056] During the deployment phase, the UAV sends a deployment command to the control device 31. After the control device 31 determines that the deployment conditions are met, it connects the deployment air path corresponding to the target radiosonde 2. The air path system 12 provides aerodynamic pressure to the target launch tube 111, driving the target radiosonde 2 to be launched out of the launch tube 111.

[0057] During the data transmission phase, after the target radiosonde 2 detaches from the launch tube 111, the electrical connection between the connector 112 and the radiosonde 2 is automatically disconnected, and the system automatically switches to wireless communication mode. The wireless communication module 32 receives the meteorological data transmitted back by the target radiosonde 2 during its descent and detection process in real time, forwards it to the UAV via the control device 31, and then transmits it to the ground station for display and processing.

[0058] This application employs an embedded design, fully integrating the sounding system into the UAV's fuselage. This significantly optimizes the UAV's aerodynamic shape, substantially reduces flight drag, and enhances aerodynamic performance. This allows the UAV to fly higher and farther with less energy consumption, enabling it to penetrate the top of typhoon cloud systems and remain in critical areas such as above the typhoon eyewall for long-term, high-precision meteorological data collection. Furthermore, the embedded structure frees up the underwing mounting space, allowing the UAV to use its hardpoints to carry other critical mission payloads, thus improving the UAV's versatility and mission flexibility.

[0059] This application employs a hybrid communication mode of wired activation and wireless data transmission, balancing reliability, low cost, and interference resistance. Before the radiosonde 2 is deployed, a highly reliable activation is performed using the wired network within the transmitter 1, ensuring the accuracy of the deployment command. Once the radiosonde 2 detaches from the UAV and enters its freefall phase, its physical connection with the transmitter 1 is severed, and it switches to wireless communication mode. The onboard wireless receiver then continuously and in real-time receives the meteorological data transmitted back by the radiosonde 2. This setup not only avoids the risk of misoperation due to wireless signal interference before deployment but also reduces the overall cost and complexity of the system, achieving highly reliable deployment and efficient data transmission.

[0060] For example, the launching device 1 includes a frame 114, which can provide mounting positions for the delivery unit 11, the air circuit system 12, and the control system 3. The left and right sides of the frame 114 are respectively provided with protruding mounting ears, and the upper surfaces of the two protruding mounting ears are tightly connected to the lower surfaces of the left and right longitudinal beams of the UAV body structure, thereby effectively transferring the weight of the launching device 1 to the main load-bearing structure of the UAV.

[0061] For example, frame 114 is as follows Figure 4As shown, the device includes a base plate 1144, front and rear side plates 1141, left and right side plates 1143, a top cover plate 1142, and multiple reinforcing strips 1145. The base plate 1144, front and rear side plates 1141, left and right side plates 1143, and top cover plate 1142 are welded or bolted together. Multiple reinforcing strips 1145 are provided on the front and rear side plates 1141 and / or the left and right side plates 1143. The reinforcing strips 1145 can be welded together to increase strength. The frame 114 serves as a load-bearing component of the launching device 1. At the same time, the frame 114 provides an installation position for the delivery unit 11, the air circuit system 12, and the control system 3.

[0062] In one specific embodiment, the launching tube 111 is as follows: Figure 5 As shown, it includes a launch tube body 1112, a cover plate assembly 1111, a guide groove 1113, a piston, and a locking mechanism 113. The radiosonde 2 is installed into the launch tube body 1112 from bottom to top, and after installation, it is fixed in the launch tube body 1112 by the locking mechanism 113.

[0063] The launch tube body 1112 is fixed to the frame 114 via the central flange 1114. The upper part is connected to the end cap assembly by screws. The heating film 1115 is adhered to the inside of the launch tube with adhesive. Three guide slots are fixed to the inside of the launch tube along the axial direction by screws. The tail is connected to the locking mechanism 113 by screws. Heating is achieved through the heating film 1115 inside the launch tube body 1112.

[0064] Cover assembly 1111, such as Figure 6 As shown, it can be made of PEEK special plastic. It is installed on the upper end of the launch tube 111 by screws, and a pipe joint and connector 112 are installed in the middle of the cover plate assembly 1111, so that the actuating energy can be actuated on the radiosonde 2, and the radiosonde 2 can be activated in advance through the connector 112.

[0065] like Figure 8 , Figure 9 and Figure 11As shown. In one specific embodiment, the gas system 12 includes a gas supply assembly 121, an air inlet pipe assembly 122, and a gas distribution assembly 123. The gas supply assembly 121 is used to store high-pressure compressed gas and provide pneumatic energy for the entire gas system 12. A main solenoid valve 124 is provided on the gas supply assembly 121, which acts as the main switch for the entire gas system 12, controlling the overall on / off state of the gas system 12. The gas supply assembly 121 is also equipped with a pressure reducing valve 126 to reduce the pressure of the high-pressure gas in the gas cylinder 129 to a working pressure range suitable for the deployment of the radiosonde 2; a gas cylinder pressure sensor 127 to monitor the remaining gas pressure in the gas cylinder 129 in real time; a deployment pressure sensor 128 to monitor the working pressure after pressure reduction in real time; a low-pressure safety valve 132 and a high-pressure safety valve 130 to prevent the pressure on the working side and the gas cylinder side from exceeding the specified safety limit, respectively, and to automatically release pressure when the pressure exceeds the limit; and a manual valve 131 for ground personnel to perform inflation before the flight mission and deflation after the flight mission.

[0066] like Figure 10 As shown, the gas line 1231 in the gas distribution assembly 123 is connected to the solenoid valve via a connector 1232. The connector 1232 can use a ball-head conical seal to improve the sealing effect.

[0067] like Figure 7 As shown, the locking mechanism 113 is installed at the bottom of the launching tube 111 and is connected to the bottom end of the launching tube 111 by screws. The locking mechanism 113 includes a lock housing 1131, a lock plug 1132, a lock head 1133, a spring 1134, and a tail end cap 1135.

[0068] The lock housing 1131 is the main structure of the locking mechanism 113, providing mechanical support and space for the internal moving parts. The lock plug 1132 is located at the bottom of the lock housing 1131, sealing the bottom opening of the lock housing 1131 to prevent internal parts from coming out. The lock head 1133 and spring 1134 are located inside the lock housing 1131. One end of the spring 1134 abuts against the inner wall of the lock housing 1131, and the other end is connected to the lock head 1133. In its natural state, the spring 1134 pushes the lock head 1133 outward, causing the lock head 1133 to extend into the inner cavity of the launch tube 111 and lock the limiting groove at the bottom of the radiosonde 2, thereby limiting the vertical movement of the radiosonde 2 inside the launch tube 111 and reliably fixing the radiosonde 2 inside the launch tube 111.

[0069] During the loading process of the radiosonde 2, the operator pushes the radiosonde 2 upwards into the launch tube 111 through the bottom opening. As the bottom of the radiosonde 2 passes the locking head 1133, the outer wall of the radiosonde 2 compresses the locking head 1133 inwards, and the spring 1134 is compressed accordingly. The locking head 1133 is temporarily retracted into the lock housing 1131, allowing the radiosonde 2 to pass smoothly. When the radiosonde 2 is pushed to the predetermined position inside the launch tube 111, the limiting groove at the bottom of the radiosonde 2 aligns with the locking head 1133. The elastic force of the spring 1134 ejects the locking head 1133 back into the limiting groove at the bottom of the radiosonde 2, completing the locking of the radiosonde 2. The entire loading and locking process requires no tools or additional operations and is automatically completed by the structure of the spring 1134 and the locking head 1133, making operation simple.

[0070] During the deployment of the radiosonde 2, when the air passage is connected and the pneumatic pressure acts on the bottom of the radiosonde 2 inside the launch tube 111, as the gas pressure gradually increases, the pneumatic thrust acting on the radiosonde 2 exceeds the locking force of the lock head 1133. The radiosonde 2 moves downward, and the inclined surface of the limiting groove of the radiosonde 2 pushes the lock head 1133, compressing the lock head 1133 inward. The spring 1134 is compressed again, and the lock head 1133 is retracted into the lock housing 1131. The lock is released, and the radiosonde 2 is ejected downward from the launch tube 111 under the continuous drive of the pneumatic pressure.

[0071] The locking mechanism 113 adopts a ball-head lock structure, making the contact surface of the lock head 1133 spherical. This helps reduce frictional resistance during loading and unloading, resulting in smoother and more reliable locking and unlocking actions. To ensure reliability under various complex working conditions, the moving parts, including the lock head 1133, are made of self-lubricating materials and undergo wear-resistant surface treatment. The moving parts are also designed with sufficient guide length to prevent jamming during operation. To ensure reliability in low-temperature environments, the moving parts are lubricated with low-temperature general-purpose grease.

[0072] Furthermore, the launching device 1 also includes a piston, which is slidably disposed inside the launching tube 111. The outer diameter of the piston is adapted to the inner diameter of the launching tube 111, so that the piston can slide smoothly along the axial direction of the launching tube 111 under the action of pneumatic pressure.

[0073] After the radiosonde 2 is loaded, the piston is positioned below the radiosonde 2, above the locking mechanism 113 inside the launch tube 111. A sealed air chamber is formed between the piston and the bottom of the radiosonde 2. When the air passage is opened, compressed gas enters the air chamber, and the gas pressure acts simultaneously on the piston and the bottom surface of the radiosonde 2. Because the radiosonde 2 is locked by the locking mechanism 113, both the radiosonde 2 and the piston remain stationary until the gas pressure reaches the unlocking threshold, and the pressure inside the air chamber continues to rise. When the gas pressure reaches the set release pressure, the locking mechanism 113 unlocks, and the radiosonde 2 is ejected downwards from the launch tube 111 under pneumatic pressure.

[0074] After the radiosonde 2 is launched, the piston continues to move downward under the continuous push of pneumatic pressure, sliding axially along the launch tube 111 to the bottom of the launch tube 111. Upon reaching the bottom of the launch tube 111, the piston triggers the locking action of the locking head 1133 in the locking mechanism 113. The locking head 1133 pops out under the elastic force of the spring 1134, locking the bottom of the piston and locking the piston at the bottom of the launch tube 111, thus blocking the bottom opening of the launch tube 111.

[0075] After the piston is deployed, it seals the bottom of the launch tube 111 to prevent external rainwater, foreign objects or airflow from entering the interior of the launch tube 111 through the bottom opening, which could contaminate or damage the internal structure of the remaining radiosonde 2 or the launch device 1, ensure the reliability of the system in continuous deployment missions, and protect the airtightness of the gas circuit system 12.

[0076] After the piston is locked, if the launch tube 111 needs to be reused, ground maintenance personnel can manually unlock the piston, remove the piston, and reload a new radiosonde 2 to complete the reuse of the launch tube 111.

[0077] like Figure 5 As shown, a guide groove 1113 is fixedly provided on the inner wall of the launch tube 111 along the axial direction. Multiple guide grooves 1113 can be provided. Three guide grooves 1113 are fixed to the inner side of the launch tube 111 by screws along the axial direction. The tail end is connected to the locking mechanism 113 by screws.

[0078] The guide groove 1113 is used to guide the piston during its axial movement within the launch tube 111 and to prevent the piston from overturning during its movement.

[0079] During the process of the piston moving downwards under pneumatic pressure, the outer protrusion of the piston slides along the guide groove 1113. The guide groove 1113 provides axial constraint and guidance for the movement of the piston, ensuring that the piston always moves smoothly in the axial direction in the launch tube 111 without deflection, thereby ensuring that the piston can accurately reach the bottom of the launch tube 111 and complete the sealing action.

[0080] Without the constraint of the guide groove 1113, when the piston moves downward at high speed under pneumatic pressure, due to uneven friction between the piston and the inner wall of the launch tube 111, airflow disturbances, and other factors, the piston may flip or tilt during its movement, causing it to jam inside the launch tube 111 and preventing it from reaching the bottom to complete the sealing. The constraint of the guide groove 1113 on the outer protrusion of the piston effectively prevents the piston from flipping during high-speed movement, ensuring the stability and reliability of the piston's movement.

[0081] The guide groove 1113 can be made of lightweight and wear-resistant material with a smooth surface treatment to reduce the frictional resistance when the piston slides in the guide groove 1113, ensuring smooth piston movement. At the same time, the length of the guide groove 1113 covers the entire effective stroke of the inner wall of the launch tube 111, ensuring that the piston is always under the guidance and constraint of the guide groove 1113 throughout the entire movement.

[0082] The launch tube 111 serves as the storage and launch carrier for the radiosonde 2. During system operation, it needs to withstand aerodynamic pressure loads and also requires internal heating and insulation via a built-in heating film 1115 to ensure the radiosonde 2 can operate normally in low-temperature, high-altitude environments. Therefore, the material selection for the launch tube 111 needs to comprehensively consider factors such as structural strength, thermal conductivity, and weight.

[0083] In one specific embodiment, the launch tube 111 can be manufactured using a carbon fiber composite material winding process. Since the launch tube 111 heats up during operation, selecting a carbon fiber composite material with a low thermal conductivity can reduce heat loss. Alternatively, the launch tube 111 can also be made from metal materials such as aluminum alloy or carbon fiber composite materials.

[0084] like Figure 12 As shown. The control box contains four board components: a power board, a main control board, an I / O signal board, and a transmitter board. The main control board's primary functions are to initialize the boards upon power-up, establish RS422 bus communication with the UAV and radiosonde wireless communication modules, acquire pressure signals, and establish a ground inspection communication interface. The I / O signal board's main functions are to acquire external discrete signals and control relay switching on the transmitter board. The transmitter board's main function is to execute the control signals output by the I / O signal board, switching signals from the heating film 1115 and solenoid valves via relay on / off states.

[0085] like Figure 13 As shown, the wireless communication module 32 contains two board components: a power supply board and a signal processing board. The power supply board converts the onboard DC28V power supply to a DC5V power supply usable by the signal processing unit, and performs functions such as EMI filtering and surge suppression. The signal processing unit board completes RS422 communication with the transmitting device and controls the dropsonde to achieve on-site detection and activation. It can also receive detection data such as temperature, humidity, atmospheric pressure, wind speed, and wind direction transmitted by the dropsonde.

[0086] The control device and wireless communication module feature an adaptive design in terms of structure and internal space. They primarily consist of a printed circuit board assembly, a housing, a cover, and electrical connectors. The printed circuit board assembly comprises four parts: a power board, a main control board, a base board, and a transmitter board. The housing and cover are used to secure and encapsulate the printed circuit board assembly. The housing and cover utilize low-density, high-strength aluminum alloy to provide mechanical support for the printed circuit board assembly and other components. Weight is minimized while ensuring reliability, and surface treatment enhances the corrosion resistance of the control device. Electromagnetic shielding sealing strips are installed at the junctions between the housing and cover, and between the housing and the socket, improving the electromagnetic shielding and moisture-proof performance of the control device. Metal shock absorbers are used to reduce the impact of vibration and shock on the control device.

[0087] The status information in this application embodiment may include at least one of the following: the location information, identity information, activation status information, or working status information of the radiosonde 2.

[0088] The detection data in this application embodiment may include at least one of the following: temperature data, humidity data, air pressure data, location data, wind speed data, or wind direction data collected by the radiosonde 2.

[0089] The external structure of the radiosonde 2 is as follows Figure 14 As shown, it includes a parachute compartment 21, an electronic components compartment 22, and a sensing compartment 23. The parachute compartment 21 contains a pilot chute, parachute pack, main parachute, and connecting straps, which generate aerodynamic force during the radiosonde's descent, deploy the parachute system, wrap the main parachute, decelerate and stabilize the radiosonde, and transmit the main parachute's aerodynamic force. The electronic components compartment 22 contains a signal processing module and battery, which collects pressure, latitude, longitude, and altitude information, calculates wind speed and direction based on changes in position, powers the humidity sensor chip, and collects humidity data via two I2C channels. It also calculates the atmospheric temperature by measuring the voltage difference across the temperature sensor. The sensing compartment 23 contains temperature and humidity sensors, which perform raw measurements of meteorological elements during descent.

[0090] like Figure 15 and Figure 16 As shown. Furthermore, this application embodiment also provides a sounding method, applied to the airborne internally embedded drop sounding system in any of the above embodiments, the method comprising:

[0091] Step 1: Receive the activation command for the target radiosonde;

[0092] Step 2: Send an activation signal to the target radiosonde via the connector. After receiving the activation signal, the target radiosonde activates itself and transmits its status information back to the control device via the wireless communication module. The control device then forwards the status information to the UAV.

[0093] Step 3: Receive the deployment command for the target radiosonde;

[0094] Step 4: Control the launching device according to the release command to pneumatically launch the target radiosonde from the corresponding launch tube;

[0095] Step 5: After the target radiosonde detaches from the launch tube and disconnects from the connector, switch to wireless communication mode and receive the detection data transmitted back by the target radiosonde during the detection process.

[0096] In step one, the UAV operator selects the target radiosonde number to be activated via the control handle or on the ground station software and issues an activation command. After receiving the activation command, the UAV forwards it to the control unit. The control unit then sends an activation signal to the target radiosonde via a wired connection through the connector on the target launch tube cover assembly. Upon receiving the activation signal, the target radiosonde completes its power-on initialization and performs a self-test of its internal functional modules. After the self-test, it wirelessly transmits status information, including activation status, battery level, and sensor status, to the wireless communication module. The wireless communication module receives this information and forwards it to the control unit via the RS422 bus. The control unit updates the radiosonde status information and forwards it to the UAV. Upon receiving the status information, the UAV updates the information on the ground station display interface. The operator can then confirm through the ground station interface that the target radiosonde has been successfully activated and is in a ready state.

[0097] In step two, the UAV operator selects the target radiosonde and issues a release command on the ground station software. The UAV forwards the release command to the control unit. Upon receiving the release command, the control unit first determines whether the release conditions are met. These conditions include: a radiosonde is present in the target launch tube; the target radiosonde is activated and functioning normally; the gas cylinder pressure in the gas supply assembly meets the release requirements; and the operating pressure is within the set range. If any condition is not met, the control unit sends a message indicating that the release conditions are not met back to the UAV, suspends the release, and awaits operator intervention. If all conditions are met, the process proceeds to the next step.

[0098] In step three, the control device sends a status feedback command to the target radiosonde via the wireless communication module, requesting the target radiosonde to report its current status information again. Upon receiving the command, the target radiosonde transmits its current status information back to the control device via the wireless communication module. The control device compares the transmitted status information with the status information recorded during the activation phase. If the two sets of status information are inconsistent, the control device sends a notification of inconsistency to the UAV and suspends the deployment; if the two sets of status information are consistent, the control device confirms that the target radiosonde is currently functioning normally and proceeds to the deployment execution step.

[0099] In step four, the control device opens the main solenoid valve on the air supply assembly. After a predetermined delay, it opens the solenoid valve at the corresponding position on the air distribution assembly. Compressed gas flows through the inlet pipe assembly and then through the air distribution assembly into the target launch tube, causing the pneumatic pressure to rise rapidly. When the pneumatic pressure reaches the set release pressure threshold, the locking mechanism automatically unlocks, and the target radiosonde is ejected downwards from the launch tube under the pneumatic pressure. After the radiosonde is ejected, the piston slides down to the bottom of the launch tube under the continued push of the pneumatic pressure and is locked by the tail lock, sealing the opening at the bottom of the launch tube. After the release action is completed, the control device first closes the main solenoid valve, then closes the position solenoid valve, disconnecting the release air path. Simultaneously, the control device sends off-air information to the target radiosonde via the wireless communication module, updates the radiosonde list, and sends the list to the UAV. Upon receiving the information, the UAV updates the radiosonde list.

[0100] In step five, after the target radiosonde detaches from the launch tube, the wired connection between the connector and the radiosonde is automatically disconnected, and the system automatically switches to wireless communication mode. The target radiosonde descends slowly under the deceleration effect of the parachute, continuously collecting meteorological data such as atmospheric temperature, humidity, air pressure, position, wind speed, and wind direction, and wirelessly transmitting the data packets to the wireless communication module on the UAV in real time. The wireless communication module receives the data in real time and forwards it to the control device via the RS422 bus. The control device then forwards the data to the UAV, which ultimately transmits it to the ground station. The ground station software displays and stores the data in real time, providing data support for weather forecasting. During the target radiosonde's descent and detection, the control system can simultaneously activate or deploy radiosondes in other launch tubes, enabling multiple radiosondes to operate in parallel and further improving detection efficiency.

[0101] It should be noted that small drones can be controlled using a remote control handle, while large drones can be controlled using a ground station as a ground command and control container. The ground station sends data to the drones via data links and satellite links.

[0102] In summary, this application provides an airborne, internally mounted dropsonde system and method. By embedding the system within the fuselage of a UAV, it not only solves the aerodynamic and structural problems of traditional external systems but also improves the UAV's flight altitude and endurance, directly serving the observation needs of extreme weather events such as typhoons and enhancing sounding accuracy. The use of a payload bay within the UAV's fuselage and a launch device for deployment of the radiosonde overcomes the safety hazards associated with using externally mounted dropsondes in harsh environments, areas with drastic climate changes, complex climates, and diverse weather conditions.

[0103] The airborne embedded drop sounding system and sounding method provided in 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. It should be noted that those skilled in the art can make several improvements and modifications to this application without departing from the principles of this application, and these improvements and modifications also fall within the protection scope of this application.

Claims

1. An airborne, internally embedded, drop-sonde system, characterized in that, include: The launching device (1) is installed in the payload compartment of the UAV. The launching device (1) includes a delivery unit (11) and an air path system (12). The delivery unit (11) includes multiple independently arranged launch tubes (111). The launch tubes (111) are used to store the radiosonde (2) and to allow the radiosonde (2) to be vertically loaded and launched. The air path system (12) is connected to each of the launch tubes (111) and is used to provide pneumatic pressure to each of the launch tubes (111) individually. The launch tubes (111) are provided with connectors (112) and locking mechanisms (113). The locking mechanisms (113) are used to limit the radiosonde (2) and to automatically detach the radiosonde (2) under the action of the pneumatic pressure. Multiple radiosondes (2), each radiosonde (2) being disposed within the launch tube (111) and forming a detachable electrical connection with the connector (112); and The control system (3) includes a control device (31) and a wireless communication module (32), and is configured such that: after receiving an activation command, the control device (31) sends an activation signal to the target radiosonde (2) via the connector (112) in a wired manner; after the target radiosonde (2) is activated, the status information of the target radiosonde (2) is sent to the UAV via the wireless communication module (32) and the control device (31); after receiving a release command, the control device (31) controls the release air path corresponding to the target radiosonde (2) to be connected so that the air path system (12) provides aerodynamic pressure to the target radiosonde (2); and the wireless communication module (32) receives the detection data returned by the target radiosonde (2) and sends it to the UAV via the control device (31).

2. The airborne embedded drop sounding system according to claim 1, characterized in that, The gas system (12) includes a gas supply component (121), an air inlet pipe component (122), and a gas distribution component (123). The gas supply component (121) is used to store high-pressure gas. The gas supply component (121) is equipped with a main solenoid valve (124). The air inlet pipe component (122) connects the gas supply component (121) and the gas distribution component (123). The gas distribution component (123) is equipped with a plurality of station solenoid valves (125) corresponding one-to-one with each of the launch tubes (111). Each station solenoid valve (125) is used to control the opening and closing of the delivery gas path corresponding to the launch tube (111).

3. The airborne embedded drop sounding system according to claim 1, characterized in that, The locking mechanism (113) includes a lock housing (1131), a lock plug (1132), a lock head (1133), and a spring (1134). The lock plug (1132) is located at the bottom of the lock housing (1131), and the lock head (1133) and the spring (1134) are located inside the lock housing (1131). The lock head (1133) locks the radiosonde (2) inside the launch tube (111) through the spring (1134).

4. The airborne embedded drop sounding system according to claim 1, characterized in that, The launching device (1) further includes a piston, which is slidably disposed inside the launching tube (111) to seal the bottom of the launching tube (111) under pneumatic pressure.

5. The airborne embedded drop sounding system according to claim 4, characterized in that, The launch tube (111) is provided with a guide groove (1113), which is fixed to the inner wall of the launch tube (111) in the axial direction so that the piston can slide along the guide groove (1113).

6. The airborne embedded drop sounding system according to claim 1, characterized in that, The launch tube (111) is an aluminum alloy launch tube or a launch tube (111) formed by winding carbon fiber.

7. The airborne embedded drop sounding system according to claim 1, characterized in that, The status information includes at least one of the following: the location information, identity information, activation status information, or working status information of the radiosonde (2).

8. The airborne internally embedded drop sounding system according to any one of claims 1 to 7, characterized in that, The detection data includes at least one of the following: temperature data, humidity data, air pressure data, location data, wind speed data, or wind direction data collected by the radiosonde (2).

9. The airborne embedded drop sounding system according to claim 2, characterized in that, The gas supply assembly (121) also includes a pressure reducing valve (126), which is used to reduce the pressure of the high-pressure gas in the gas cylinder (129) to within a preset pressure range.

10. A sounding method, characterized in that, The method, applied to any one of the airborne embedded drop sounding systems according to claims 1 to 9, comprises: Receive activation command for the target radiosonde; An activation signal is sent to the target radiosonde via a connector. Upon receiving the activation signal, the target radiosonde activates itself and transmits its status information back to the control device via a wireless communication module. The control device then forwards the status information to the UAV. Receive the deployment command for the target radiosonde; According to the release command, the launching device is controlled to pneumatically launch the target radiosonde from the corresponding launch tube. After the target radiosonde detaches from the launch tube and disconnects from the connector, it switches to wireless communication mode and receives the detection data transmitted back by the target radiosonde during the detection process.

Images