A sounding drone and a sounding system

Abstract

The present application provides a sounding drone and a sounding system, wherein the sounding drone includes a rotor body, a parachute structure and a release device. The rotor body includes a fuselage and a rotor assembly, wherein the rotor assembly is movably connected to the fuselage and can move between a climbing position and a gliding position; the parachute structure is arranged on the upper side of the fuselage, and the parachute structure has a folded state and an unfolded state; the release device is arranged on the fuselage and movably connected to the parachute structure, and when the rotor assembly is in the gliding position, the release device can release the parachute structure so that the parachute structure switches from the folded state to the unfolded state. In the present application, when the rotor assembly of the sounding drone is in the gliding position, after the parachute structure switches from the folded state to the unfolded state, the lift generated by the rising airflow can be utilized to significantly reduce the power required for the flight of the sounding drone, thereby effectively improving the detection range of the sounding.

Description

Technical Field

[0001] The present application relates to the field of meteorological monitoring technology, and in particular to a sounding UAV and a sounding system. Background Art

[0002] In meteorology, sounding refers to the collection of key high-altitude meteorological data such as temperature, humidity, pressure, wind direction, and wind speed in the atmosphere of the target airspace through a sounding instrument, and the transmission of this information to a ground receiving station for data statistics and analysis, providing important data support for weather forecasting and climate research.

[0003] In the related technology, a drone equipped with a sonde is used for meteorological detection. However, the drone has a low endurance, which results in a limited detection range of the sonde. Summary of the invention

[0004] The present application provides a sounding UAV and a sounding system, which can effectively improve the detection range of the sounding.

[0005] In a first aspect, the present application provides a sounding drone, comprising:

[0006] A rotor body, comprising a fuselage and a rotor assembly, wherein the rotor assembly is movably connected to the fuselage and can move between a climbing position and a gliding position;

[0007] A parafoil structure, disposed on the upper side of the fuselage, the parafoil structure having a folded state and an unfolded state; and

[0008] A release device, disposed on the fuselage and movably connected to the parachute wing structure;

[0009] Wherein, when the rotor assembly is in the gliding position, the releasing device can release the paraglider structure so that the paraglider structure switches from the folded state to the unfolded state.

[0010] The sounding drone provided by the present application has a rotor assembly movably connected to the fuselage that can switch between a climbing position and a gliding position, and the parachute wing structure on the fuselage can be released under the control of a release device, and switched from a folded state to an extended state. In this way, when the rotor assembly of the sounding drone is in the gliding position, after the parachute wing structure switches from a folded state to an extended state, it can utilize the lift generated by the rising airflow, significantly reduce the power required for the sounding drone to fly, and thus effectively increase the detection range of the sounding drone.

[0011] In conjunction with the first aspect, in some possible implementations, the rotor assembly includes:

[0012] A bracket, rotatably connected to the fuselage;

[0013] a rotor, disposed on the bracket; and

[0014] A tilting device is arranged on the fuselage; the tilting device is used to rotate the bracket to control the tilt angle of the rotor.

[0015] In combination with the first aspect and the above implementations, in some possible implementations, the parachute wing structure includes:

[0016] A support assembly disposed on the upper side of the fuselage; and

[0017] The parachute assembly is rotatably connected to a side of the support assembly away from the fuselage. The parachute assembly has an upward position and a downward position and can move in an upward and downward direction relative to the support assembly between the upward position and the downward position.

[0018] In combination with the first aspect and the above implementations, in some possible implementations, the support assembly includes:

[0019] A column, one end of which is connected to the upper side of the fuselage, and the other end of which is rotatably connected to the parachute assembly; and

[0020] A first elastic member, one end of which is connected to the column, and the other end of which is connected to the umbrella assembly, is used to keep the umbrella assembly in the upward position.

[0021] In combination with the first aspect and the above implementations, in some possible implementations, the umbrella assembly includes:

[0022] Umbrella cloth;

[0023] An umbrella rib is rotatably connected to a side of the support assembly away from the fuselage; the umbrella rib is connected to the umbrella cloth and has a folded state for folding the umbrella cloth and an expanded state for unfolding the umbrella cloth; and

[0024] The driving mechanism is movably connected to the umbrella ribs and is used for driving the umbrella ribs to switch between the unfolded state and the folded state.

[0025] In combination with the first aspect and the above implementations, in some possible implementations, the umbrella rib includes:

[0026] A support rod is rotatably connected to a side of the support assembly away from the fuselage; one end of the support rod is provided with a first connecting portion; and

[0027] Two movable rods are respectively arranged on both sides of the support rod, and one end of the movable rod is movably connected to one end of the support rod.

[0028] In combination with the first aspect and the above implementations, in some possible implementations, the driving mechanism includes:

[0029] A slider is slidably connected to the support rod; the slider is provided with a second connecting portion;

[0030] A connecting rod, disposed between the support rod and the movable rod, one end of the connecting rod being hinged to the slider, and the other end of the connecting rod being connected to the movable rod; and

[0031] A second elastic member, one end of which is connected to the slider, and the other end of which is connected to the support rod, is used to drive the slider and the connecting rod to keep the umbrella ribs in the expanded state.

[0032] In combination with the first aspect and the above implementations, in some possible implementations, the releasing device includes:

[0033] A second motor fixedly connected to the fuselage; and

[0034] A hook is arranged at the output end of the second motor; the hook is connected to the first connecting part and the second connecting part.

[0035] In combination with the first aspect and the above implementations, in some possible implementations, the rotor body further includes:

[0036] A controller, disposed on the fuselage, the controller being electrically connected to the rotor assembly and the release device;

[0037] a pitot tube, arranged on the parafoil structure, the pitot tube being electrically connected to the controller; and / or

[0038] The sonde is fixedly arranged on the fuselage and electrically connected to the controller.

[0039] In a second aspect, the present application also provides a sounding system, comprising:

[0040] Ground stations; and

[0041] As described in any one of the first aspects above, the sounding drone is communicatively connected to the ground station. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] Figure 1 This is a structural schematic diagram of a posture of a sounding drone provided in an embodiment of the present application;

[0043] Figure 2 yes Figure 1 A schematic diagram of the structure of the rotor assembly of the rotor body in the sounding UAV in the climbing position;

[0044] Figure 3 yes Figure 2A schematic diagram of the structure of the rotor assembly of the rotor body;

[0045] Figure 4 yes Figure 1 Schematic diagram of the structure of the sounding drone in another posture;

[0046] Figure 5 yes Figure 4 Schematic diagram of the structure of the parachute wing structure in the sounding UAV omitting the parachute cloth.

[0047] The description of the reference numerals in the figures is as follows:

[0048] 1—sounding drone;

[0049] 100—rotor body;

[0050] 110—fuselage;

[0051] 120—rotor assembly;

[0052] 121—bracket; 1211—crossbeam; 1212—connecting beam;

[0053] 122—rotor;

[0054] 123—tilting device; 1231—first motor; 1232—transmission mechanism;

[0055] 200—parachute wing structure;

[0056] 210—support assembly; 211—column; 212—first elastic member;

[0057] 220 - parachute assembly;

[0058] 221—Umbrella cloth;

[0059] 222—rib; 2221—support rod; 2222—movable rod; 2223—first connecting portion;

[0060] 223—driving mechanism; 2231—sliding block; 2232—connecting rod; 2233—second elastic member; 2234—second connecting portion;

[0061] 300—Release device;

[0062] 310 - second motor;

[0063] 320—hook;

[0064] 400—pitotas;

[0065] 500—sonde;

[0066] 600—Power battery. DETAILED DESCRIPTION

[0067] The following embodiments of the technical solution of the present application are described in detail in conjunction with the accompanying drawings. The following embodiments are only used to more clearly illustrate the technical solution of the present application, and are therefore only used as examples, and cannot be used to limit the scope of protection of the present application.

[0068] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by technicians in the technical field to which this application belongs; the terms used herein are only for the purpose of describing specific embodiments and are not intended to limit this application; the terms "including" and "having" in the specification and claims of this application and the above-mentioned figure descriptions and any variations thereof are intended to cover non-exclusive inclusions.

[0069] Reference to "embodiments" herein means that a particular feature, structure, or characteristic described in conjunction with the embodiments may be included in at least one embodiment of the present application. The appearance of the phrase in various locations in the specification does not necessarily refer to the same embodiment, nor is it an independent or alternative embodiment that is mutually exclusive with other embodiments. It is explicitly and implicitly understood by those skilled in the art that the embodiments described herein may be combined with other embodiments.

[0070] In the description of the embodiments of the present application, the technical terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, which are only for the convenience of describing the embodiments of the present application and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the embodiments of the present application.

[0071] In the description of the embodiments of the present application, unless otherwise clearly specified and limited, technical terms such as "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense. For example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal connection of two elements or the interaction relationship between two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the embodiments of the present application can be understood according to the specific circumstances.

[0072] In the description of the embodiments of the present application, the technical terms "first", "second", etc. are only used to distinguish different objects, and cannot be understood as indicating or implying relative importance or implicitly indicating the number, specific order or primary and secondary relationship of the indicated technical features. In the description of the embodiments of the present application, the term "multiple" refers to more than two (including two), similarly, "multiple groups" refers to more than two groups (including two groups), and "multiple pieces" refers to more than two pieces (including two pieces).

[0073] In the description of the embodiments of the present application, the term "and / or" is only a description of the association relationship of the associated objects, indicating that there may be three relationships. For example, A and / or B can represent: A exists alone, A and B exist at the same time, and B exists alone. In addition, the character " / " in this article generally indicates that the associated objects before and after are in an "or" relationship.

[0074] In meteorology, sounding refers to the collection of key high-altitude meteorological data such as temperature, humidity, pressure, wind direction, and wind speed in the atmosphere of the target airspace through a sounding instrument, and the transmission of this information to a ground receiving station for data statistics and analysis, providing important data support for weather forecasting and climate research.

[0075] In the related technology, a drone equipped with a sonde is used for meteorological detection. However, the drone has a low endurance, which results in a limited detection range of the sonde.

[0076] In order to solve the above technical problems, the present application embodiment provides a sounding drone and a sounding system. The following first introduces a sounding drone and a sounding system provided by the present application embodiment in detail with reference to the accompanying drawings.

[0077] First, please refer to Figures 1 to 3 The present application proposes a sounding system, which includes a sounding drone 1 and a ground station (not shown in the figure), and the sounding drone 1 is communicatively connected with the ground station.

[0078] The sounding drone 1 is an aircraft used for meteorological detection and does not require a pilot to operate on board. The drone can be controlled by remote control or an autonomous flight control system. The ground station is a site for observing high-altitude meteorological parameters, mainly used to receive high-altitude meteorological data and process and store information. Efficient communication and accurate data transmission can be achieved between the sounding drone 1 and the ground station to achieve real-time monitoring and control of the drone and ensure the smooth execution of the sounding mission.

[0079] See also Figure 1 and Figure 4The sounding drone 1 may include a rotor body 100, a parafoil structure 200, and a release device 300. In addition, it may also include a power device, which is connected to the rotor body 100 and is used to provide power for the sounding drone 1. The power device may be an electric motor or an engine. Figure 2 When the sounding drone 1 is driven by an electric motor, it also includes a power battery 600 for power supply. Since the power device is not the invention point of this application, it will not be described in detail.

[0080] The rotor body 100 includes a fuselage 110 and a rotor assembly 120, wherein the rotor assembly 120 is movably connected to the fuselage 110 and can move between a climbing position and a gliding position; the parachute wing structure 200 is arranged on the upper side of the fuselage 110, and the parachute wing structure 200 has a folded state and an unfolded state; the release device 300 is arranged on the fuselage 110 and is movably connected to the parachute wing structure 200; wherein, when the rotor assembly 120 is in the gliding position, the release device 300 can release the parachute wing structure 200 so that the parachute wing structure 200 is switched from the folded state to the unfolded state.

[0081] Among them, the rotor body 100 is a drone with multiple rotors specially designed for sounding, which can serve as a stable flight platform. The fuselage 110 is the main structure of the rotor body 100, carrying components such as the rotor assembly 120, the parafoil structure 200, and the release device 300, and has high structural strength and rigidity. The rotor assembly 120 is used to convert the rotational motion of the motor or engine into thrust, so that the sounding drone 1 can fly in the air. The rotor assembly 120 is movably connected to the fuselage 110, so that the rotor assembly 120 can move between a climbing position and a gliding position relative to the fuselage 110.

[0082] The parachute wing structure 200 is in a folded state when not in use, and in an unfolded state when in use. When not in use, the release device 300 is used to lock the parachute wing structure 200 in the folded state. When in use, the release device 300 can release the lock on the parachute wing structure 200 and release the parachute wing structure 200, so that the parachute wing structure 200 switches from the folded state to the unfolded state. The parachute wing structure 200 in the unfolded state can obtain lift by utilizing rising air currents (such as terrain waves, thermal air currents, etc.) based on aerodynamics.

[0083] See also Figure 1 When the rotor assembly 120 moves to the climbing position relative to the fuselage 110, and the release device 300 locks the parachute wing structure 200 so that the parachute wing structure 200 is in a folded state, the sounding drone 1 can climb upward. Figure 4When the rotor assembly 120 moves to the gliding position relative to the fuselage 110 and the release device 300 releases the parachute structure 200 so that the parachute structure 200 is in an unfolded state, the sounding drone 1 can glide in a predetermined direction.

[0084] The sounding drone 1 provided by the present application has a rotor assembly 120 movably connected to the fuselage 110 that can switch between a climbing position and a gliding position, and the parafoil structure 200 on the fuselage 110 can be released under the control of the release device 300, and switched from a folded state to an extended state. In this way, when the rotor assembly 120 of the sounding drone 1 is in the gliding position, after the parafoil structure 200 switches from a folded state to an extended state, the lift generated by the rising airflow can be utilized to significantly reduce the power required for the flight of the sounding drone 1, thereby effectively improving the detection range of the sounding.

[0085] See also Figure 2 and Figure 3 In some embodiments, the rotor assembly 120 may include a bracket 121, a rotor 122, and a tilt device 123. The bracket 121 is rotatably connected to the fuselage 110; the rotor 122 is disposed on the bracket 121; the tilt device 123 is disposed on the fuselage 110; and the tilt device 123 is used to rotate the bracket 121 to control the inclination angle of the rotor 122.

[0086] It should be noted that the bracket 121 is a frame that supports the rotor 122 and is used to install the rotor 122. The bracket 121 is rotatably connected to the fuselage 110 and can rotate relative to the fuselage 110 under the action of external force. The tilt device 123 is used to apply external force to the bracket 121. Figure 2 The tilting device 123 may include a first motor 1231 and a transmission mechanism 1232. The first motor 1231 is fixedly connected to the fuselage 110; the transmission mechanism 1232 is connected between the first motor 1231 and the bracket 121, and the first motor 1231 drives the bracket 121 to rotate through the transmission mechanism 1232. Among them, the transmission mechanism 1232 can adopt a gear transmission mechanism, a belt transmission mechanism, a chain transmission mechanism, a worm gear transmission mechanism, etc., and the designer can flexibly design it according to the needs. Depending on the number of rotors 122, the bracket 121 can also have multiple structural forms. In one possible implementation, when the number of rotors 122 is four, such as Figure 3 As shown, the bracket 121 may include a crossbeam 1211 and two connecting beams 1212. The crossbeam 1211 is connected to the first motor 1231 through a transmission mechanism 1232; the two connecting beams 1212 are respectively arranged at both ends of the crossbeam 1211, and a rotor 122 is respectively arranged at both ends of the connecting beam 1212.

[0087] See also Figure 4In some embodiments, the parachute wing structure 200 may include a support assembly 210 and a parachute assembly 220. The support assembly 210 is disposed on the upper side of the fuselage 110; the parachute assembly 220 is rotatably connected to a side of the support assembly 210 away from the fuselage 110 and is detachably connected to the release device 300. The parachute assembly 220 has an upward position and a downward position, and can pitch relative to the support assembly 210 between the upward position and the downward position.

[0088] It should be noted that the parachute assembly 220 is rotatably connected to the end of the support assembly 210 away from the fuselage 110, and when the rotor assembly 120 moves between the climbing position and the gliding position relative to the fuselage 110, the parachute assembly 220 and the rotor assembly 120 can be prevented from interfering. In addition, since the parachute assembly 220 can rotate between the upward position and the downward position, when the parachute assembly 220 is in the downward position, it can approach the fuselage 110. When it is necessary to put the parachute wing structure 200 in the unfolded state, the parachute assembly 220 can be released by the release device 300, so that the parachute assembly 220 is in the upward position, away from the fuselage 110.

[0089] See also Figure 4 In some embodiments, the support assembly 210 may include a column 211 and a first elastic member 212. One end of the column 211 is connected to the upper side of the fuselage 110, and the other end of the column 211 is rotatably connected to the umbrella assembly 220; one end of the first elastic member 212 is connected to the column 211, and the other end of the first elastic member 212 is connected to the umbrella assembly 220, so as to keep the umbrella assembly 220 in the upward position.

[0090] It is understandable that the length of the column 211 is the distance between the parachute assembly 220 and the fuselage 110. The length of the column 211 can be flexibly determined according to factors such as the structure of the bracket 121 of the rotor assembly 120 and the size of the parachute assembly 220, and the present application does not make any specific limitation on this.

[0091] It should be noted that before the parachute wing structure 200 is in the unfolded state, the parachute body assembly 220 must first be kept in the upward position. Therefore, the embodiment of the present application sets a first elastic member 212 between the parachute body assembly 220 and the column 211. In this way, after the release device 300 releases the parachute body assembly 220 of the parachute wing structure 200, the elastic force generated by the first elastic member 212 can automatically move the parachute body assembly 220 away from the fuselage 110, and move from the downward position to the upward position and keep it in the upward position. The first elastic member 212 can be a tension spring, a compression spring, etc. Figure 5 As shown, when the first elastic member 212 is a tension spring, the first elastic member 212 can be disposed at the rear side of the column 211. When the first elastic member 212 is a compression spring, the first elastic member 212 can be disposed at the front side of the column 211.

[0092] See also Figure 4 and Figure 5 In some embodiments, the umbrella assembly 220 may include an umbrella cloth 221, an umbrella rib 222, and a driving mechanism 223. The umbrella rib 222 is rotatably connected to the side of the support assembly 210 away from the fuselage 110; the umbrella rib 222 is connected to the umbrella cloth 221, and has a folded state of folding the umbrella cloth 221 and an expanded state of expanding the umbrella cloth 221; the driving mechanism 223 is movably connected to the umbrella rib 222, and is used to drive the umbrella rib 222 to switch between the expanded state and the folded state.

[0093] It is understandable that the umbrella cloth 221 is connected to the ribs 222 to form a flexible wing surface of the umbrella wing structure 200. The driving mechanism 223 can drive the ribs 222 to move. When the ribs 222 are in a folded state, the umbrella cloth 221 can be driven to be folded, and when the ribs 222 are in an unfolded state, the umbrella cloth 221 can be opened. The umbrella cloth 221 is usually made of fiber fabric and is cut and sewn in conjunction with the ribs 222 of a specific structure. In order to enhance the waterproofness and durability of the umbrella cloth 221, a special coating can also be provided on the surface of the umbrella cloth 221. Designers can select suitable materials and coatings for the umbrella cloth 221 based on performance requirements, cost and other factors, and the embodiments of the present application do not specifically limit this.

[0094] The structures of the umbrella ribs 222 are various, see Figure 5 In some embodiments, the rib 222 may include a support rod 2221 and two movable rods 2222. The support rod 2221 is rotatably connected to a side of the support assembly 210 away from the fuselage 110; a first connecting portion 2223 is provided at one end of the support rod 2221, and the first connecting portion 2223 is detachably connected to the release device 300; the two movable rods 2222 are respectively provided on both sides of the support rod 2221, and one end of the movable rod 2222 is movably connected to one end of the support rod 2221.

[0095] The support rod 2221 is the main frame structure of the ribs 222, and the two movable rods 2222 located on both sides of the support rod 2221 can move relative to the support rod 2221. It can be understood that when the two movable rods 2222 move in a direction away from the support rod 2221, the ribs 222 can be switched to an extended state, thereby opening the umbrella cloth 221, and when the two movable rods 2222 move in a direction close to the support rod 2221, the ribs 222 can be switched to a closed state, thereby closing the umbrella cloth 221.

[0096] A first connecting portion 2223 is provided at one end of the support rod 2221, and the first connecting portion 2223 is detachably connected to the release device 300. When the wing structure 200 needs to be released, the release device 300 can release the lock on the umbrella body assembly 220 of the wing structure 200 by separating from the first connecting portion 2223, thereby allowing the umbrella body assembly 220 as a whole to move from a downward-looking position to an upward-looking position under the elastic force of the first elastic member 212.

[0097] Please continue to see Figure 5 In some embodiments, the driving mechanism 223 may include a slider 2231, a connecting rod 2232, and a second elastic member 2233. The slider 2231 is slidably connected to the support rod 2221; the slider 2231 is provided with a second connecting portion 2234, and the second connecting portion 2234 is detachably connected to the release device 300; the connecting rod 2232 is arranged between the support rod 2221 and the movable rod 2222, one end of the connecting rod 2232 is hinged to the slider 2231, and the other end is connected to the movable rod 2222; one end of the second elastic member 2233 is connected to the slider 2231, and the other end of the second elastic member 2233 is connected to the support rod 2221, and is used to drive the slider 2231 and the connecting rod 2232, so that the umbrella rib 222 remains in the unfolded state.

[0098] The slider 2231 is slidably connected to the support rod 2221 and can slide along the extension direction of the support rod 2221. The slider 2231 is connected to the movable rod 2222 via the connecting rod 2232. When the slider 2231 slides along the support rod 2221, the movable rod 2222 can be driven by the connecting rod 2232 to move away from or close to the support rod 2221, thereby switching the ribs 222 to an extended state or a retracted state, thereby realizing the expansion or retraction of the umbrella cloth 221.

[0099] The second connection part 2234 of the slider 2231 is detachably connected to the release device 300, and the slider 2231 is also connected to the support rod 2221 through the second elastic member 2233. When the second connection part 2234 is connected to the release device 300, the ribs 222 are in a folded state, and the second elastic member 2233 connected to the slider 2231 and the support rod 2221 stores elastic potential energy; when the wing structure 200 needs to be released, the release device 300 can be separated from the second connection part 2234, and when the second connection part 2234 is separated from the release device 300, the second elastic member 2233 releases the elastic potential energy, and the slider 2231 connected to the second elastic member 2233 slides along the support rod 2221 under the action of the second elastic member 2233, so that the ribs 222 can be switched from the folded state to the unfolded state.

[0100] See also Figure 2 and Figure 4In some embodiments, the release device 300 may include a second motor 310 and a hook 320. The second motor 310 is fixedly connected to the body 110; the hook 320 is disposed at the output end of the second motor 310; and the hook 320 is connected to the first connection part 2223 and the second connection part 2234.

[0101] It is understandable that the hook 320 is arranged at the output end of the second motor 310 and can rotate with the rotation of the second motor 310. Among them, the first connecting portion 2223 and the second connecting portion 2234 are used to be connected with the hook 320, and their structural forms are various, as long as they meet the requirements of being connected with the hook 320, and the embodiment of the present application does not limit this. Exemplarily, the first connecting portion 2223 and the second connecting portion 2234 can be convex structures, such as extended connecting rods, and can also be other structures such as U-shaped and ring-shaped.

[0102] See also Figure 1 , Figure 4 and Figure 5 When the hook 320 is hooked on the first connection part 2223 of the rib 222 in the umbrella assembly 220, the umbrella assembly 220 is in a downward position. In addition, when the hook 320 is hooked on the second connection part 2234 of the driving mechanism 223 in the umbrella assembly 220, the slider 2231 connected to the second connection part 2234 can make the movable rod 2222 close to the support rod 2221 through the connecting rod 2232, thereby making the rib 222 in a folded state.

[0103] When the second motor 310 drives the hook 320 to rotate, so that the hook 320 is disengaged from the first connection part 2223 of the rib 222 in the umbrella assembly 220, and the second connection part 2234 of the driving mechanism 223 in the umbrella assembly 220, and then the wing structure 200 is released, on the one hand, the elastic force generated by the first elastic member 212 connected to the column 211 and the umbrella assembly 220 can make the umbrella assembly 220 automatically move away from the fuselage 110, move from the downward position to the upward position and maintain it in the upward position; on the other hand, the elastic force generated by the second elastic member 2233 connected to the slider 2231 and the support rod 2221 can drive the slider 2231 to slide along the support rod 2221, so that the rib 222 is switched from the folded state to the unfolded state.

[0104] In summary, if Figure 1 As shown, when the hook 320 is connected to the first connection part 2223 and the second connection part 2234, the umbrella assembly 220 is in a downward position and the ribs 222 are in a folded state. Figure 2 As shown, the second motor 310 drives the hook 320 to separate the hook 320 from the first connection portion 2223 and the second connection portion 2234 , the umbrella assembly 220 is in an upward position, and the ribs 222 are in an unfolded state.

[0105] In some embodiments, rotor body 100 may further include a controller (not shown in the figure), which is disposed on fuselage 110 and is electrically connected to rotor assembly 120 and release device 300 .

[0106] The controller may be a control module in a control circuit of a flight control system in the sounding UAV 1 , or may be a specially designed control unit.

[0107] See also Figure 1 and Figure 4 The controller is electrically connected to the rotor assembly 120, and can control the rotor assembly 120 to move between the climbing position and the gliding position. Exemplarily, when the rotor assembly 120 drives the bracket 121 and the rotor 122 thereon through the first motor 1231 of the tilting device 123, the controller is electrically connected to the first motor 1231. The controller is electrically connected to the release device 300, and can control the release device 300 to release the parachute structure 200, so that the parachute structure 200 is switched from the folded state to the unfolded state. Exemplarily, when the controller drives the hook 320 to rotate through the second motor 310, and then the hook 320 is separated from the first connection part 2223 of the rib 222 in the parachute assembly 220 and the second connection part 2234 of the driving mechanism 223, the parachute assembly 220 moves from the downward position to the upward position and remains in the upward position, and the rib 222 is switched from the folded state to the unfolded state.

[0108] In addition, see Figure 4 and Figure 5 The rotor body 100 may further include a pitot tube 400, which is disposed on the parafoil structure 200 and is electrically connected to the controller. The pitot tube 400 can provide the controller with key flight speed data by measuring the total pressure and static pressure of the airflow. The position and connection method of the pitot tube 400 on the parafoil structure 200 can be flexibly set by the designer according to actual conditions, and the embodiments of the present application do not specifically limit this.

[0109] In addition, the rotor body 100 may also include a sonde 500. The sonde 500 carries a variety of sensors and can measure meteorological and environmental factors such as air temperature, air pressure, humidity, wind direction and wind speed. The sonde 500 is electrically connected to the controller and can transmit the measured data to the ground station through the controller. The sonde 500 is fixedly arranged on the fuselage 110. The sonde 500 can be mounted on the outside of the fuselage 110 or integrated on the inside of the fuselage 110, and this application does not make specific restrictions on this. It can be understood that the sonde 500 mounted on the outside of the fuselage 110 has the advantages of easy installation and maintenance, while the sonde 500 integrated in the fuselage 110 can be protected by the fuselage 110 and has higher reliability.

[0110] The same or similar numbers in the drawings of this embodiment correspond to the same or similar parts; in the description of this application, it should be understood that if the terms "upper", "lower", "left", "right", etc. indicate an orientation or position relationship based on the orientation or position relationship shown in the drawings, it is only for the convenience of describing this application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, the terms describing the position relationship in the drawings are only used for illustrative purposes and cannot be understood as a limitation on this patent. For ordinary technicians in this field, the specific meanings of the above terms can be understood according to specific circumstances.

[0111] The above contents are only specific implementation methods of the present application, but the protection scope of the present application is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed in the present application, which should be included in the protection scope of the present application. Therefore, the protection scope of the present application should be based on the protection scope of the claims.

Claims

1. A sounding drone (1), characterized in that: include: A rotor body (100) comprises a fuselage (110) and a rotor assembly (120), wherein the rotor assembly (120) is movably connected to the fuselage (110) and is capable of moving between a climbing position and a gliding position; A paraglider structure (200) is arranged on the upper side of the fuselage (110), and the paraglider structure (200) has a folded state and an unfolded state; as well as A release device (300) is disposed on the fuselage (110) and is movably connected to the parachute wing structure (200); Wherein, when the rotor assembly (120) is in the gliding position, the release device (300) can release the paraglider structure (200) so that the paraglider structure (200) switches from the folded state to the unfolded state.

2. The sounding drone (1) according to claim 1, characterized in that: The rotor assembly (120) comprises: A bracket (121) rotatably connected to the body (110); A rotor (122) is disposed on the bracket (121); and A tilting device (123) is arranged on the fuselage (110); the tilting device (123) is used to rotate the bracket (121) to control the tilt angle of the rotor (122).

3. The sounding drone (1) according to claim 1, characterized in that: The parachute wing structure (200) comprises: A support assembly (210) is disposed on the upper side of the fuselage (110); and The parachute assembly (220) is rotatably connected to a side of the support assembly (210) away from the fuselage (110); the parachute assembly (220) has an upward position and a downward position, and can move in a pitching motion relative to the support assembly (210) between the upward position and the downward position.

4. The sounding drone (1) according to claim 3, characterized in that: The support assembly (210) comprises: A column (211), one end of the column (211) is connected to the upper side of the fuselage (110), and the other end of the column (211) is rotatably connected to the parachute assembly (220); and A first elastic member (212), one end of the first elastic member (212) is connected to the column (211), and the other end of the first elastic member (212) is connected to the umbrella assembly (220), and is used to keep the umbrella assembly (220) in the upward position.

5. The sounding drone (1) according to claim 4, characterized in that: The parachute assembly (220) comprises: Umbrella cloth (221); An umbrella rib (222) is rotatably connected to a side of the support assembly (210) away from the fuselage (110); the umbrella rib (222) is connected to the umbrella cloth (221) and has a folded state in which the umbrella cloth (221) is folded and an expanded state in which the umbrella cloth (221) is expanded; and The driving mechanism (223) is movably connected to the umbrella ribs (222) and is used to drive the umbrella ribs (222) to switch between the unfolded state and the folded state.

6. The sounding drone (1) according to claim 5, characterized in that: The umbrella rib (222) comprises: a support rod (2221) rotatably connected to a side of the support assembly (210) away from the fuselage (110); a first connecting portion (2223) is provided at one end of the support rod (2221), and the first connecting portion (2223) is detachably connected to the release device (300); and Two movable rods (2222) are respectively arranged on both sides of the support rod (2221), and one end of the movable rod (2222) is movably connected to one end of the support rod (2221).

7. The sounding drone (1) according to claim 6, characterized in that: The driving mechanism (223) comprises: A slider (2231) is slidably connected to the support rod (2221); the slider (2231) is provided with a second connecting portion (2234), and the second connecting portion (2234) is detachably connected to the release device (300); A connecting rod (2232) is arranged between the supporting rod (2221) and the movable rod (2222), one end of the connecting rod (2232) is hinged to the sliding block (2231), and the other end is connected to the movable rod (2222); and A second elastic member (2233), one end of the second elastic member (2233) is connected to the slider (2231), and the other end of the second elastic member (2233) is connected to the support rod (2221), and is used to drive the slider (2231) and the connecting rod (2232) to keep the umbrella rib (222) in the unfolded state.

8. The sounding drone (1) according to claim 7, characterized in that: The release device (300) comprises: A second motor (310) fixedly connected to the body (110); and A hook (320) is arranged at the output end of the second motor (310); the hook (320) is connected to the first connecting portion (2223) and the second connecting portion (2234).

9. The sounding drone (1) according to claim 1, characterized in that: The rotor body (100) further comprises: a controller, disposed on the fuselage (110), the controller being electrically connected to the rotor assembly (120) and the release device (300); a pitot tube (400), arranged on the paraglider structure (200), the pitot tube (400) being electrically connected to the controller; and / or The sonde (500) is fixedly mounted on the fuselage (110) and is electrically connected to the controller.

10. A sounding system, characterized in that: include: Ground station; as well as The sounding drone (1) as claimed in claims 1 to 9, wherein the sounding drone (1) is communicatively connected to the ground station.

Images