Drone and Its Power Plant

Abstract

The present invention discloses a drone and its power device. The power device includes a driving component and a power component. The driving component includes: a mounting base, a servo motor, a transmission component, a lead screw, and a rotating member. The servo motor is mounted on the mounting base; the transmission component is in transmission connection with the servo motor; a first thread segment and a second thread segment are provided on the outer peripheral surface of the lead screw, and the first thread segment is in threaded transmission connection with the transmission component; the rotating member is in transmission connection with the second thread segment to convert the translational movement of the lead screw into the rotational movement of the rotating member. Among them, the power component includes a power motor and a propeller assembly. The power motor is connected to the propeller assembly, and the power motor drives the propeller assembly to rotate. The power motor is connected to the rotating member to rotate along with the rotation of the rotating member. According to the power device of the drone of the present invention, it can directly change the rotation direction of the propeller assembly, thereby changing the flight direction of the drone in the air, and has a simple structure.

Description

Technical Field

[0001] The present invention belongs to the technical field of aircraft, and particularly relates to a power device for an unmanned aerial vehicle and an unmanned aerial vehicle having the power device. Background Art

[0002] The unmanned aerial vehicles in the related art adopt an even number of rotors such as four, six or eight. This is because the flight control algorithm of the flight control system of the unmanned aerial vehicle with an even number of rotors usually changes the pulling force generated by each rotor by adjusting the rotation speed of each rotor, and realizes the change of the flight direction of the unmanned aerial vehicle through the different pulling forces generated on both sides of the unmanned aerial vehicle. For example, it turns during a straight flight.

[0003] In the related art, only by adjusting the rotation speed of the rotors to adjust the flight direction and flight state of the unmanned aerial vehicle in the air, when using this adjustment method, generally, the unmanned aerial vehicle is required to have at least four rotors to realize the effective turning of the unmanned aerial vehicle. This makes the size of the unmanned aerial vehicle relatively large, and at the same time, due to the increase in the number of rotors, the overall manufacturing cost of the unmanned aerial vehicle increases. Summary of the Invention

[0004] The present invention provides a power device for an unmanned aerial vehicle. The power device can be applied to an unmanned aerial vehicle and can change the rotation direction of a propeller assembly relative to a fuselage assembly.

[0005] The present invention also provides an unmanned aerial vehicle having the aforementioned power device.

[0006] According to the power device of the unmanned aerial vehicle of the embodiment of the present invention, the power device includes a driving component and a power component. The driving component includes: a mounting seat, a steering gear, a transmission component, a lead screw and a rotating member. The steering gear is mounted on the mounting seat; the transmission component is in transmission connection with the steering gear; the outer peripheral surface of the lead screw is provided with a first thread section and a second thread section, and the first thread section is in threaded transmission connection with the transmission component; the rotating member is in transmission connection with the second thread section to convert the translational motion of the lead screw into the rotational motion of the rotating member. Wherein, the power component includes a power motor and a propeller assembly connected to the propeller assembly. The power motor drives the propeller assembly to rotate, and the power motor is connected to the rotating member to rotate along with the rotation of the rotating member.

[0007] According to the power device of the unmanned aerial vehicle of the embodiment of the present invention, it can directly change the rotation direction of the propeller assembly, thereby changing the flight direction of the unmanned aerial vehicle in the air. The structure is simple, and there is no need to cooperate with different rotation speeds of multiple propeller assemblies to change the flight direction of the unmanned aerial vehicle. Therefore, the number of propeller assemblies of the unmanned aerial vehicle can be reduced, and thus the size and manufacturing cost of the unmanned aerial vehicle can be reduced.

[0008] Optionally, the mounting seat includes a socket portion and a fixing seat. The socket portion is provided with a socket hole for socketing the machine arm. The fixing seat is connected to the socket portion, and a receiving cavity is provided in the fixing seat for receiving the steering gear.

[0009] Optionally, the mounting seat further includes a mounting end cap, which is connected to one end of the fixing seat away from the socket portion. Wherein, one end of the receiving cavity away from the socket portion is open and sealed by the mounting end cap.

[0010] Optionally, the transmission assembly includes a first gear and a second gear. The first gear is sleeved on the output shaft of the steering gear. The second gear meshes with the first gear. Wherein, the second gear has a mating hole extending along the axis, and a mating thread is provided in the mating hole. The first thread section is in driving cooperation with the mating thread.

[0011] Optionally, the drive assembly further includes a limiting assembly. The limiting assembly includes a connecting rod. One end of the connecting rod is swingably connected to the mounting seat, and the other end of the connecting rod is pivotally connected to the lead screw.

[0012] Optionally, the mounting seat further includes at least two mounting portions arranged at intervals along the axis direction of the lead screw. Mounting holes are provided on the mounting portions, and the lead screw is movably inserted through the mounting holes along the axis direction of the lead screw.

[0013] Optionally, the rotating member is rotatably sleeved outside the lead screw, and the end of the rotating member is rotatably embedded inside the mounting portion. The power device further includes a bearing, and the bearing is provided between the mounting portion and the rotating member.

[0014] Optionally, the power assembly further includes a mounting table and a fixing portion. The fixing portion is connected to the mounting table and extends in a direction perpendicular to the mounting table. A mating groove is formed at one end of the fixing portion away from the mounting table. The inner surface of the mating groove is provided with a plurality of internal gear teeth. A plurality of external gear teeth are provided on the outer wall of the rotating member in a circumferential direction. The plurality of external gear teeth cooperate with the plurality of internal gear teeth. Wherein, the power motor is mounted on the mounting table.

[0015] Optionally, the first thread section and the second thread section are arranged at intervals along the axis of the lead screw.

[0016] The unmanned aerial vehicle according to an embodiment of the present invention includes a fuselage, a machine arm, and a power device. One end of the machine arm is connected to the fuselage. The power device is the power device of the unmanned aerial vehicle as described above, and the power device is connected to the other end of the machine arm.

[0017] Additional aspects and advantages of the present invention will be given in part in the following description, become apparent in part from the following description, or be learned by practice of the present invention. Brief Description of the Drawings

[0018] The above and / or additional aspects and advantages of the present invention will become apparent and be readily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0019] Figure 1 is a perspective view of a drone according to an embodiment of the present invention;

[0020] Figure 2 is a top view of a drone according to an embodiment of the present invention;

[0021] Figure 3 is a perspective view of an arm of a drone according to an embodiment of the present invention;

[0022] Figure 4 is a perspective view of a first connecting member of a drone according to an embodiment of the present invention;

[0023] Figure 5 is a perspective view of a second connecting member of a drone according to an embodiment of the present invention;

[0024] Figure 6 is a top view of a partial structure of a fuselage of a drone according to an embodiment of the present invention;

[0025] Figure 7 is a perspective view of a liquid storage container of a drone according to an embodiment of the present invention;

[0026] Figure 8 is a perspective view of a lead screw of a drone according to an embodiment of the present invention;

[0027] Figure 9 is a partial cross-sectional view of a power device of a drone according to an embodiment of the present invention;

[0028] Figure 10 is Figure 9 a partially enlarged schematic view at A in

[0029] Figure 10-1 is Figure 10 a partially enlarged schematic view at B in

[0030] Figure 11 is a perspective view of a mounting seat according to an embodiment of the present invention;

[0031] Figure 12 is a perspective view of a second gear of a drone according to an embodiment of the present invention;

[0032] Figure 13Is a perspective view of the mounting platform of the unmanned aerial vehicle according to an embodiment of the present invention;

[0033] Figure 14 Is a perspective view of the rotating member of the unmanned aerial vehicle according to an embodiment of the present invention.

[0034] Reference numerals:

[0035] Unmanned aerial vehicle 1000,

[0036] Airframe assembly 1, airframe 11, first mounting frame 110, first mounting space 111, second mounting frame 112, second mounting space 113, arm 12, first arm segment 122, second arm segment 124, landing gear 13, liquid storage container 14, connection assembly 15, first connecting member 152, first through hole 1522, first groove 1524, first flange 1526, first connecting lug 1527, first connecting portion 1528, second connecting member 154, second through hole 1542, second protrusion 1544, second flange 1546, pivot joint portion 1547, second connecting portion 1548,

[0037] Power device 2, drive assembly 21, mounting seat 211, socket portion 2112, socket hole 2113, fixed seat 2114, receiving cavity 2115, mounting end cover 2116, mounting portion 2117, enclosing plate 201, bottom plate 202, mounting hole 2118, servo 212, transmission assembly 213, first gear 2131, second gear 2132, mating hole 21322, lead screw 214, first threaded section 2141, second threaded section 2142, rotating member 215, limiting assembly 216, connecting rod 2161, hinge portion 2162, power assembly 22, power motor 221, propeller assembly 222, mounting platform 223, mating groove 2232, fixing portion 224, battery 23, electronic speed control module 24, bearing 25, first axis L1, second axis L2. Detailed implementation manners

[0038] The embodiments of the present invention will be described in detail below. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described by referring to the drawings below are exemplary and are only used to explain the present invention and should not be construed as a limitation to the present invention. It should be understood that the various concepts and embodiments introduced above, as well as those described in more detail below, can be implemented in any of many ways, because the concepts and embodiments disclosed in the present invention are not limited to any implementation manner. In addition, some of the solutions disclosed in the present invention can be used alone, or in any appropriate combination with other solutions disclosed in the present invention.

[0039] The power plant 2 of the unmanned aerial vehicle 1000 according to an embodiment of the present invention will be described below with reference to the accompanying drawings.

[0040] The power plant 2 of the unmanned aerial vehicle 1000 according to an embodiment of the present invention includes: a drive assembly 21 and a power assembly 22. Among them, the power assembly 22 is used to provide the driving power for the unmanned aerial vehicle 1000, and the drive assembly 21 is used to drive the power assembly 22, and the state of the power assembly 22 can be adjusted through the drive assembly 21.

[0041] Among them, the drive assembly 21 includes a mounting base 211, a servo 212, a transmission assembly 213, a lead screw 214, and a rotating member 215. As Figure 1 , Figure 2 , Figure 9 , Figure 10 and Figure 14 shown, specifically, the servo 212 is mounted on the mounting base 211, and the transmission assembly 213 is in transmission connection with the servo 212. The outer peripheral surface of the lead screw 214 is provided with a first thread section 2141 and a second thread section 2142. The first thread section 2141 is in threaded transmission connection with the transmission assembly 213 to convert the rotational motion of the servo 212 into the translational motion of the lead screw 214 along the axis direction of the lead screw 214. The rotating member 215 is in transmission connection with the second thread section 2142 to convert the translational motion of the lead screw into the rotational motion of the rotating member 215. That is to say, the rotational motion of the servo 212 is transmitted to the transmission assembly 213 through the transmission assembly 213, and then through threaded transmission, the rotational motion is transmitted to the lead screw 214, and the lead screw 214 is driven to perform telescopic motion relative to the mounting base; under the helical transmission cooperation between the second thread section 2142 and the rotating member 215, the telescopic motion of the lead screw 214 relative to the mounting base 211 is converted into the rotational motion of the rotating member 215.

[0042] The power assembly 22 includes a power motor 221 and a propeller assembly 222. The power motor 221 is connected to the rotating member 215 so that the power motor 221 rotates as the rotating member 215 rotates, so as to change the position or tilt direction of the power assembly 22 through the drive assembly. The propeller assembly 222 is connected to the power motor 221, and the power motor 221 drives the propeller assembly 222 to rotate to provide power during the flight of the unmanned aerial vehicle.

[0043] In a specific embodiment of the present invention, the servo 212 drives the transmission assembly 213 to move. Since the transmission assembly 213 is in threaded driving connection with the lead screw 214, the lead screw 214 is driven by the transmission assembly 213 to expand and contract relative to the mounting seat 211 along the first axis L1. Since the rotating member 215 is in threaded driving connection with the lead screw 214, while the lead screw 214 expands and contracts relative to the mounting seat 211 along the first axis L1, the lead screw 214 drives the rotating member 215 to rotate around the first axis L1, thereby realizing driving the rotating member 215 to rotate around the first axis L1 by the servo 212.

[0044] The power motor 221 drives the propeller assembly 222 to rotate around the second axis L2, and the driving assembly 21 drives the rotating shaft of the propeller assembly 222 to rotate around the first axis L1 to adjust the force application direction of the propeller assembly 222 on the fuselage assembly 1 during operation. Among them, since the power assembly 22 is connected to the rotating member 215, while the servo 212 drives the rotating member 215 to rotate around the first axis L1, the rotating member 215 will drive the power motor 221 and the propeller assembly 222 to rotate around the first axis L1. And the drone 1000 can fly precisely by relying on the pulling force generated by the rotation of the propeller assembly 222 around the second axis L2. When the propeller assembly 222 rotates around the first axis L1 by a certain angle along with the power motor 221 and the rotating member 215, the angle of the second axis L2 around which the propeller assembly 222 rotates also changes accordingly, so that the direction of the pulling force generated by the rotation of the propeller assembly 222 can be changed, thereby changing the flight direction of the drone 1000 in the air.

[0045] Optionally, there is an angle greater than 0° between the first axis L1 and the second axis L2 (for example, the first axis L1 is perpendicular to the second axis L2), which can better change the rotation direction of the propeller assembly 222, so that it is easier to control the flight direction of the drone 1000 in the air, as well as the flight attitude and position of the drone 1000.

[0046] According to the drone 1000 of the embodiment of the present invention, the flight direction of the drone 1000 in the air can be changed by directly changing the rotation direction of the propeller assembly 222. The structure is simple, and there is no need to cooperate with different rotation speeds of multiple propeller assemblies 222 to change the flight direction of the drone 1000. Therefore, the number of propeller assemblies 222 of the drone 1000 can be reduced, thereby reducing the size and manufacturing cost of the drone 1000.

[0047] Such as Figure 1 and Figure 2 、 Figure 9 and Figure 10As shown, in some embodiments, the drone 1000 may at least have a propeller assembly 222 with the structure of this embodiment. By setting the drive assembly 21, the flight direction and attitude of the drone 1000 in the air can be changed (for example, turning left when going straight, or turning right when going straight, etc.). As Figure 2 shown, the drone 1000 has two propeller assemblies 222. Each propeller assembly 222 can change the direction of the force exerted on the drone through the correspondingly arranged drive assembly 21. Of course, only one propeller assembly 222 can also be driven by the corresponding drive assembly 21 to change the direction of the force it exerts on the drone.

[0048] Optionally, the included angle between the first axis L1 and the second axis L2 in the present invention can be set to about 90°. For example, the included angle between the first axis L1 and the second axis L2 is set within the range of 60° to 90°. Of course, the above limitation on the included angle between the first axis L1 and the second axis L2 is only a specific embodiment of the present invention and is not a limitation on the protection scope of the present invention. The included angle between the first axis L1 and the second axis L2 in the present invention can also be set to be less than 60°.

[0049] In some embodiments of the present invention, the mounting seat 211 includes a socket part 2112 and a fixed seat 2114. Specifically, a socket hole 2113 is provided on the socket part 2112, and the socket part 2112 is used to be socketed on the arm of the drone. For example, in a drone applying this power device 2, the socket part 2112 is socketed on the free end of the arm 12, so as to connect the mounting seat 211 and the arm 12 together, and this connection method is more stable and reliable. The fixed seat 2114 is connected to the socket part 2112, and a receiving cavity 2115 is provided in the fixed seat 2114. The servo 212 is received in the receiving cavity 2115, thereby realizing the installation of the servo 212. On the one hand, it can prevent the servo 212 from being affected by rain and snow washing during the flight of the drone 1000 and affecting its working performance. On the other hand, setting the servo 212 in the receiving cavity 2115 can better avoid the interference of other components on the working state of the servo 212.

[0050] In addition, the socket hole and the receiving cavity of the present invention can be set in a form that communicates with each other, and the arm can be set to be hollow or in other forms. At this time, the wiring harness of the servo (such as the power line, control line, etc.) can extend to the fuselage through the socket hole and the arm, so as to facilitate the wiring and control of the servo.

[0051] As Figure 9 and Figure 10As shown, optionally, the mounting base 211 further includes a mounting end cap 2116. The mounting end cap 2116 is connected to one end of the fixed base 2114 away from the socket part 2112. One end of the receiving cavity 2115 away from the socket part is open, and the mounting end cap 2116 covers the receiving cavity 2115. Thereby, the possibility that the servo 212 is interfered by other components during operation can be reduced, and at the same time, the possibility that the servo 212 is damaged by rain, snow, etc. can be prevented during rainy and snowy weather.

[0052] As Figure 8 , Figure 9 , Figure 10 and Figure 12 As shown, according to some embodiments of the present invention, the transmission assembly 213 includes a first gear 2131 and a second gear 2132. The first gear 2131 is sleeved on the output shaft of the servo 212, and the servo 212 drives the first gear 2131 to rotate. The second gear 2132 meshes with the first gear 2131. When the first gear 2131 rotates, it drives the second gear 2132 to rotate. Among them, a mating hole 21322 extending axially is provided in the second gear 2132, and mating threads are provided in the mating hole 21322. One end of the lead screw 214 is inserted into the mating hole 21322, and the first thread section 2141 on the lead screw 214 is in driving cooperation with the mating threads. The rotation of the second gear 2132 drives the lead screw 214 to telescopically move along the first axis L1 direction, so as to realize driving the lead screw 214 to telescopically move along the first axis L1 direction through the servo 212.

[0053] Optionally, the first gear 2131 and the second gear 2132 are arranged in the receiving cavity 2115, and the lead screw 214 passes through the side wall of the receiving cavity 2115 to cooperate with the second gear 2132. Thereby, the interference of other components to the operation of the first gear 2131 and the second gear 2132 can be prevented, and at the same time, the possibility that the first gear 2131 and the second gear 2132 are damaged by rain, snow, etc. can be prevented. Of course, a multi-stage gear transmission can also be provided between the first gear 2131 and the second gear 2132, which is not limited in this application.

[0054] Specifically, the aforementioned first gear 2131 and second gear 2132 can be arranged on the inner side of the aforementioned mounting end cap.

[0055] As Figure 9 and Figure 10 As shown, according to some embodiments of the present invention, the drive assembly 21 further includes a limit assembly 216. The limit assembly 216 includes a connecting rod 2161. One end of the connecting rod 2161 is swingably connected to the mounting base 211, and the other end of the connecting rod 2161 is pivotally connected to the lead screw 214.

[0056] Specifically, the limiting component 216 may include a hinge portion 2162 and a connecting rod 2161. Among them, the hinge portion 2162 is rotatably arranged on the mounting base 211, the connecting rod 2161 is inserted on the hinge portion 2162, and the connecting rod 2161 can rotate following the hinge portion 2162. In addition, the connecting rod 2161 is movably connected to the hinge portion 2162 along the axis of the connecting rod 2161. That is to say, the connecting rod 2161 is rotatably and telescopically connected to the mounting base. The connecting rod 2161 is pivotally connected to the lead screw 214, and the rotation of the lead screw 214 is restricted by the connecting rod 2161, reducing the possibility of the lead screw 214 rotating. Among them, the limiting component 216 can be a ball hinge or a universal joint, etc., which is not limited in this application. In this way, during the translation of the lead screw along the axis of the lead screw, the connecting rod 2161 will be driven to swing. During the swinging process of the connecting rod 2161, relative sliding can occur between the connecting rod 2161 and the hinge portion 2162, thereby ensuring the stable translation of the lead screw.

[0057] As Figure 9 - Figure 11 shown, according to some embodiments of the present invention, the mounting base 211 further includes at least two mounting portions 2117 arranged at intervals along the axis direction of the lead screw 215. Mounting holes 2118 are provided on the mounting portions 2117, and the lead screw 214 is movably inserted through the mounting holes 2118 along the axis direction of the lead screw. Thus, the supporting effect on the lead screw 214 is realized through the mounting portions 2117, thereby realizing the connection between the lead screw 214 and the mounting base 211. At the same time, by using at least two mounting portions 2117, the translation direction of the lead screw 214 can be restricted, improving the stability of the lead screw movement.

[0058] As Figure 9 、 Figure 10 and Figure 14 shown, according to some embodiments of the present invention, the rotating member 215 is rotatably connected to the mounting portion 2117, and a bearing 25 is provided between the rotating member 215 and the mounting portion 2117. Thus, the rotating member 215 is rotatably fixed on the mounting base 211.

[0059] Specifically, the rotating member 215 is rotatably sleeved outside the lead screw 214, and the end of the rotating member 215 is rotatably embedded inside the mounting portion 2117. The power device 2 further includes a bearing 25, and the bearing 25 is provided between the mounting portion 2117 and the rotating member 215.

[0060] More specifically, the installation part 2117 includes a surrounding plate 201 whose axis is parallel to the axis of the lead screw. One end of the surrounding plate 201 is closed by a bottom plate 202, and the aforementioned installation hole 2118 can be provided on the bottom plate 202. The rotating member 215 extends along the axis of the lead screw, and both ends of the rotating member 215 are respectively inserted into the inner side of the surrounding plate 201 of the installation part 2117, and a bearing 25 is provided between the surrounding plate 201 and the rotating member. Among them, the bearing 25 can have an inner ring, an outer ring and balls. The balls are arranged between the inner ring and the outer ring. The inner ring is sleeved on the rotating member 215, and the outer ring is embedded in the surrounding plate 201.

[0061] In addition, the lead screw 214 is nested inside the rotating member 215. The lead screw 214 and the rotating member 215 can be arranged in a form of screw drive, so as to effectively improve the stability of the cooperation between the lead screw 215 and the rotating member 215, and thus improve the stability of the lead screw 214 driving the rotating member 215 to rotate.

[0062] As Figure 9 、 Figure 10 and Figure 13 shown, according to some embodiments of the present invention, the power assembly 22 further includes an installation table 223 and a fixing part 224. The fixing part 224 is connected to the installation table 223, and the fixing part 224 extends in a direction perpendicular to the installation table 223. A mating groove 2232 is formed at one end of the fixing part 224 away from the installation table 223. The inner surface of the mating groove 2232 is provided with a plurality of internal gear teeth, and the outer wall of the rotating member 215 is circumferentially provided with a plurality of external gear teeth. The plurality of external gear teeth cooperate with the plurality of internal gear teeth, thereby realizing the fixed connection between the installation table 223 and the rotating member 215. While the rotating member 215 rotates around the first axis L1, the installation table 223 rotates around the first axis L1 simultaneously with the rotating member 215. Among them, the power motor 221 is installed on the installation table 223, and the power motor 221 rotates synchronously with the installation table 223.

[0063] In some embodiments of the present invention, the first thread section 2141 and the second thread section 2142 are spaced apart in the axial direction of the lead screw. In this way, the end portions of the first thread section 2141 and the second thread section 2142 will form a limiting structure to realize the stroke limit of the lead screw and the rotating member, effectively improving the stability and safety of the power device.

[0064] Of course, other structures can also be used for limiting, and the first thread section 2141 and the second thread section 2142 are arranged as continuous threads on the outer peripheral surface of the lead screw 214.

[0065] In addition, as described above, the first threaded section 2141 cooperates with the transmission assembly 213 (specifically, the second gear in the transmission assembly 213) to achieve screw drive, so as to convert the rotational motion of the servo 212 into the telescopic motion of the lead screw 214; the second threaded section 2142 cooperates with the rotating member 215 to achieve screw drive, so as to convert the telescopic motion of the lead screw 214 into the rotational motion of the rotating member 215. Therefore, the helix angle of the first threaded section 2141 in the present invention is smaller than that of the second threaded section 2142, thereby improving the stability of the screw drive.

[0066] In addition, the present invention also provides a drone, including a fuselage 11, a boom 12 and a power device 2. One end of the boom 12 is connected to the fuselage 11; the power device 2 is the power device of the drone according to the foregoing, and the power device 2 is connected to the other end of the boom 12.

[0067] The drone 1000 according to the embodiment of the present invention is driven by the foregoing power device 2, and can change the flight direction of the drone 1000 in the air by directly changing the rotation direction of the propeller assembly 222. The structure is simple, and there is no need to cooperate with different rotational speeds of multiple propeller assemblies 222 to change the flight direction of the drone 1000. Therefore, the number of propeller assemblies 222 of the drone 1000 can be reduced, thereby reducing the size and manufacturing cost of the drone 1000.

[0068] Optionally, according to some embodiments of the present invention, there are at least two power devices 2 along the circumferential direction of the fuselage assembly 1, and the first axis L1 extends radially along the circumferential direction of the fuselage assembly 1, thereby enabling the drone 1000 to fly more smoothly and reliably. Preferably, the power device 2 may be two along the circumferential direction of the fuselage assembly 1, but the present application is not limited thereto, and it may also be three, four, five or more along the circumferential direction of the fuselage assembly 1.

[0069] In addition, in some embodiments of the present invention, the fuselage may also be provided with a power device that only includes a power component and does not include a drive component.

[0070] The drone 1000 of the present invention can be used for operations such as pesticide spraying or water irrigation of crops in the farming industry, spraying of fire extinguishing liquid in forest fires, etc. The drone 1000 for this purpose can carry a liquid storage container 14. The drone 1000 can also be used in other fields such as aerial photography, power line inspection, environmental monitoring, forest fire prevention and disaster inspection. The drone 1000 for this purpose can carry a camera. Of course, the present invention does not limit the use of the drone 1000 and other structures carried thereon.

[0071] Such as Figure 1 、 Figure 9 、 Figure 10 andFigure 11 As shown in Figure 11 , in the unmanned aerial vehicle with the above-mentioned power device according to an embodiment of the present invention, the unmanned aerial vehicle further includes a fuselage assembly 1, and the fuselage assembly 1 may include a fuselage 11 and arms 12. The arms 12 are connected to the fuselage 11. One end of the arm 12 is connected to the fuselage 11, and the other end of the arm 12 is connected to the mounting seat 211.

[0072] In the embodiment as Figure 2 shown, the unmanned aerial vehicle 1000 includes two arms 12. The two arms 12 are distributed around the fuselage 11 and fixedly connected to the fuselage 11. For example, the two arms 12 of the unmanned aerial vehicle 1000 are symmetrically arranged on the opposite sides of the unmanned aerial vehicle 1000.

[0073] As Figure 2 shown, optionally, the fuselage assembly 1 further includes a landing gear 13. The landing gear 13 is fixedly arranged below the fuselage 11 to support the landing of the fuselage 11, and at the same time can improve the stability of the take-off and landing of the unmanned aerial vehicle 1000.

[0074] As Figure 1 and Figure 7 shown, optionally, the fuselage assembly 1 further includes a liquid storage container 14. The liquid storage container 14 is arranged on the fuselage 11 and is used to contain the items to be sprayed or transported.

[0075] Optionally, the intersection of the connection between the axes of the power motors 221 on the two arms 12 and the axis of the fuselage 11 falls within the liquid storage container 14, so that the weight of the unmanned aerial vehicle 1000 can be better balanced, enabling the unmanned aerial vehicle 1000 to be better balanced and more stable during flight.

[0076] As Figure 1 shown, optionally, the unmanned aerial vehicle further includes a battery 23. The battery 23 is fixedly arranged on the fuselage 11 and is used to provide energy for the power assembly 22. Of course, the battery 23 can also provide energy for other components. For example, the working components on the unmanned aerial vehicle (for example, in the unmanned aerial vehicle for spraying pesticides, the working component can be a spraying structure).

[0077] Optionally, the power device 2 further includes an electronic speed control module 24 and a control module. The electronic speed control module 24 and the control module are both fixedly arranged on the fuselage 11 and are used to control the flight attitude of the unmanned aerial vehicle 1000. Of course, the electronic speed control module 24 can also be arranged at other positions according to actual needs. As Figure 9 and Figure 10 shown, the electronic speed control module 24 is arranged on the arm 12, and the present application does not make any restrictions.

[0078] As Figure 6As shown, optionally, the fuselage 11 includes a fuselage body, a first mounting frame 110 and a second mounting frame 112 connected to the fuselage body. The liquid storage container 14 and the battery 23 are disposed within the first mounting frame 110 and the second mounting frame 112. The fuselage body includes a fixed frame, and a top plate and a bottom plate 202 oppositely disposed on both sides of the fixed frame. The top plate and the bottom plate 202 can be used to carry the electronic speed control module 24 and the control module. The first mounting frame 110 is provided with a circumferentially extending side wall, and the second mounting frame 112 is provided with a circumferentially extending side wall. The first mounting frame 110 and the second mounting frame 112 respectively define a first mounting space 111 and a second mounting space 113. The liquid storage container 14 is installed in the first mounting space 111, and the battery 23 is installed in the second mounting space 113.

[0079] As Figure 3 shown, optionally, the arm 12 includes a first arm segment 122 and a second arm segment 124. The first arm segment 122 and the second arm segment 124 are connected by a connecting component 15. The first arm segment 122 and the second arm segment 124 are configured as cylindrical hollow rods. The first arm segment 122 and the second arm segment 124 can be plastic parts or carbon fiber parts, which are not limited in this application. Among them, the first arm segment 122 is fixedly connected to the fuselage 11 through an arm 12 clamping component. The other end of the first arm segment 122 is connected to one end of the second arm segment 124 through the connecting component 15, and the other end of the second arm segment 124 is connected to the power device 2.

[0080] As Figure 3 - Figure 5As shown, optionally, the connecting component 15 includes a first connecting member 152 and a second connecting member 154, and the first connecting member 152 and the second connecting member 154 are pivotally connected. Among them, the first connecting member 152 is provided with a first through hole 1522 that penetrates the first connecting member 152 axially. One end of the first arm segment 122 away from the fuselage 11 is inserted into the first through hole 1522. Preferably, an adhesive layer is provided between the outer wall of the first arm segment 122 away from the fuselage 11 and the inner wall of the first through hole 1522, so that the connection between the first arm segment 122 and the first connecting member 152 is more stable and reliable. A first groove 1524 is provided on the inner wall of one end of the first through hole 1522 close to the second connecting member 154. The second connecting member 154 is provided with a second through hole 1542 that penetrates the second connecting member 154 axially. One end of the second arm segment 124 away from the power device 2 is inserted into the second through hole 1542. Preferably, an adhesive layer is provided between the outer wall of the second arm segment 124 and the inner wall of the second through hole 1542, so that the connection between the second arm segment 124 and the second connecting member 154 is more stable and reliable. A second protrusion 1544 is provided at one end of the second through hole 1542 close to the first connecting member 152. Since the first connecting member 152 and the second connecting member 154 are pivotally connected, the second arm segment 124 can move between a first position and a second position relative to the first arm segment 122. When the second arm segment 124 rotates from the second position to the first position, the power device 2 gradually moves away from the fuselage 11. When the second arm segment 124 is in the first position, the axis of the second arm segment 124 and the axis of the first arm segment 122 are on the same straight line. When the second arm segment 124 is in the second position, the axis of the second arm segment 124 and the axis of the first arm segment 122 form an angle. When the second arm segment 124 is in the first position, the first groove 1524 cooperates with the second protrusion 1544.

[0081] As Figure 4 and Figure 5 shown, optionally, a first convex edge 1526 is provided on the outer circumference of one end of the first connecting member 152 close to the second connecting member 154, and a second convex edge 1546 is provided on the outer circumference of one end of the second connecting member 154 close to the first connecting member 152. When the second arm segment 124 is in the first position, the first convex edge 1526 and the second convex edge 1546 are in contact with each other, thereby increasing the contact area between the first connecting member 152 and the second connecting member 154, increasing the friction force, and preventing the first connecting member 152 and the second connecting member 154 from sliding relative to each other when the second arm segment 124 is in the first position.

[0082] As Figure 4 and Figure 5As shown, optionally, a first connecting lug 1527 and a first connecting portion 1528 are oppositely provided on an outer wall of one end of the first connecting member 152 close to the second connecting member 154, and a pivoting portion 1547 and a second connecting portion 1548 are oppositely provided on an outer wall of one end of the second connecting member 154 close to the first connecting member 152. The first connecting lug 1527 and the pivoting portion 1547 are rotatably connected. When the second arm segment 124 is in the first position, the first connecting portion 1528 and the second connecting portion 1548 are aligned and connected by a fastener to fasten the first arm segment 122 and the second arm segment 124, reducing the possibility of relative movement between the first arm segment 122 and the second arm segment 124 when the drone 1000 is flying.

[0083] Optionally, at least one first limiting notch is provided on one of the inner wall of the first through hole 1522 and the first arm segment 122, and at least one first limiting protrusion is provided on the other one. The first limiting notches and the first limiting protrusions are in one-to-one cooperation, thereby being able to further reduce the relative rotation between the inner wall of the first arm segment 122 and the first through hole 1522.

[0084] Optionally, at least one second limiting notch is provided on one of the inner wall of the second through hole 1542 and the second arm segment 124, and at least one second limiting protrusion is provided on the other one. The second limiting notches and the second limiting protrusions are in one-to-one cooperation, thereby being able to further reduce the relative rotation between the inner wall of the second arm segment 124 and the second through hole 1542.

[0085] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "left", "right", "top", "bottom", "inner", "outer", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention 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, and thus should not be construed as a limitation of the present invention. In addition, the features defined as "first" and "second" may explicitly or implicitly include one or more of such features. In the description of the present invention, unless otherwise stated, the meaning of "a plurality" is two or more.

[0086] In the description of the present invention, it should be noted that unless otherwise clearly defined and limited, the terms "mounted", "connected", and "connected" should be understood in a broad sense. For example, it may be a fixed connection, a detachable connection, or an integral connection; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific situations.

[0087] In the description of this specification, the descriptions referring to terms such as "one embodiment", "some embodiments", "schematic embodiments", "examples", "specific examples", or "some examples", etc., mean that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples.

[0088] Although the embodiments of the present invention have been shown and described, those of ordinary skill in the art can understand that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principles and spirit of the present invention, and the scope of the present invention is defined by the claims and their equivalents.

Claims

1. A power device (2) of an unmanned aerial vehicle (1000), characterized in that, the power device (2) comprises a driving assembly (21) and a power assembly (22), and the driving assembly (21) comprises: a mounting base (211); a steering gear (212) mounted on the mounting base (211); a transmission assembly (213) in transmission connection with the steering gear (212); a lead screw (214) having a first thread section (2141) and a second thread section (2142) on its outer peripheral surface, and the first thread section (2141) is in threaded transmission connection with the transmission assembly (213); a rotating member (215) in transmission connection with the second thread section (2142) to convert the translational movement of the lead screw (214) into the rotational movement of the rotating member (215), wherein, the power assembly (22) comprises a power motor (221) and a propeller assembly (222) connected to the power motor (211), and the power motor (221) drives the propeller assembly (222) to rotate; the power motor (221) is connected to the rotating member (215) and rotates along with the rotation of the rotating member (215).

2. The power device (2) of the unmanned aerial vehicle (1000) according to claim 1, characterized in that, the mounting base (211) comprises: a socket part (2112) provided with a socket hole (2113) for socketing the machine arm; a fixing base (2114) connected to the socket part (2112), and a receiving cavity (2115) is provided in the fixing base (2114) for receiving the steering gear (212).

3. The power device (2) of the unmanned aerial vehicle (1000) according to claim 2, characterized in that, the mounting base (211) further comprises: a mounting end cover (2116) connected to one end of the fixing base (2114) away from the socket part (2112), wherein, one end of the receiving cavity (2115) away from the socket part (2112) is open and sealed by the mounting end cover (2116).

4. The power device (2) of the unmanned aerial vehicle (1000) according to claim 1, characterized in that, the transmission assembly (213) comprises: a first gear (2131) sleeved on the output shaft of the steering gear (212); a second gear (2132) meshing with the first gear (2131), wherein, the second gear (2132) has a mating hole (21322) extending along the axis, and mating threads are provided in the mating hole (21322), and the first thread section (2141) is in transmission fit with the mating threads.

5. The power device (2) of the unmanned aerial vehicle (1000) according to any one of claims 1-4, characterized in that, The driving assembly (21) further includes a limiting assembly (216), and the limiting assembly (216) includes: a connecting rod (2161), one end of the connecting rod (2161) is swingably connected to the mounting base (211), and the other end of the connecting rod (2161) is pivotally connected to the lead screw (214).

6. The power device (2) of the unmanned aerial vehicle (1000) according to any one of claims 1-4, characterized in that the mounting base (211) further includes at least two mounting portions (2117) arranged at intervals along the axis direction of the lead screw (214), mounting holes (2118) are provided on the mounting portions (2117), and the lead screw (214) is movably disposed in the mounting holes (2118) along the axis direction of the lead screw (214).

7. The power device (2) of the unmanned aerial vehicle (1000) according to claim 6, characterized in that the rotating member (215) is rotatably sleeved outside the lead screw (214), and the end portion of the rotating member (215) is rotatably embedded inside the mounting portion (2117), and the power device (2) further includes: a bearing (25), and the bearing (25) is disposed between the mounting portion (2117) and the rotating member (215).

8. The power device (2) of the unmanned aerial vehicle (1000) according to any one of claims 1-4, characterized in that the power assembly (22) further includes: a mounting table (223); a fixing portion (224), the fixing portion (224) is connected to the mounting table (223) and extends in a direction perpendicular to the mounting table (223), a mating groove (2232) is formed at the end of the fixing portion (224) away from the mounting table (223), a plurality of internal gear teeth are provided on the inner surface of the mating groove (2232), a plurality of external gear teeth are provided on the outer wall circumference of the rotating member (215), and the plurality of external gear teeth cooperate with the plurality of internal gear teeth, wherein, the power motor (221) is mounted on the mounting table (223).

9. The power device (2) of the unmanned aerial vehicle (1000) according to any one of claims 1-4, characterized in that the first thread section (2141) and the second thread section (2142) are arranged at intervals along the axis of the lead screw (214).

10. An unmanned aerial vehicle (1000), characterized in that it includes: a fuselage (11); an arm (12), one end of the arm (12) is connected to the fuselage (11); a power device (2), the power device (2) is the power device (2) of the unmanned aerial vehicle (1000) according to any one of claims 1-8, and the power device (2) is connected to the other end of the arm (12).

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