An unmanned aerial vehicle fuselage and an unmanned aerial vehicle

Abstract

The present invention relates to a drone fuselage and a drone, belonging to the technical field of drone equipment, and solves the problems of poor heat dissipation and waterproof performance of the drone fuselage, which is not conducive to the flight safety of the drone. The drone fuselage of the present invention includes a cabin part; the heat dissipation unit of the cabin part includes a heat dissipation plate and a wind guiding plate. The heat dissipation plate is provided with a wind guiding strip sub-unit and a heat dissipation plate waterproof sealing groove; the wind guiding plate is buckled on the wind guiding strip sub-unit, and the wind guiding plate and the heat dissipation plate enclose a heat dissipation cavity. The heat dissipation plate waterproof sealing groove is used for installing a heat dissipation plate waterproof sealing ring; the cabin part is also respectively provided with an air inlet and an air outlet; the wind guiding strip sub-unit includes a wind guiding strip; the connecting line of the projection vertices at the front ends of multiple wind guiding strips forms an air inlet end curve that bends toward the air inlet side; a part of the wind guiding strip near the air inlet end deflects toward the air inlet direction. The wind guiding strip. The drone fuselage of the present invention is provided with multiple heat dissipation and waterproof structures, has good directional ventilation and heat dissipation performance, good waterproof performance, and is conducive to the safe flight of the drone.

Description

Technical Field

[0001] The invention relates to the technical field of unmanned aerial vehicles, and in particular to a fuselage of an unmanned aerial vehicle with a heat dissipation and waterproof device. Background Art

[0002] In recent years, with the continuous expansion of aircraft application areas, many categories of intelligent drones have emerged.

[0003] These drones are usually adapted to a variety of flight environments and are equipped with a large number of electrical devices, which have comprehensive requirements for heat dissipation and waterproofing. The two are indispensable. Due to the complex flight environment in which drones perform missions and the small space for high-integration circuits, the requirements for heat dissipation and waterproofing of drones are particularly strict.

[0004] In the existing technology, most UAV fuselages usually consider heat dissipation in the following ways:

[0005] 1. Failure to treat the heat dissipation structure of the fuselage will result in the following consequences: when the drone is exposed to high temperature and continuous light, the drone cabin temperature will rise by 20℃-30℃ compared to the outside temperature; in a high-temperature environment, the internal integrated electrical components and circuit boards will not be able to operate normally, thus threatening the safety of the entire machine.

[0006] 2. Passive heat dissipation. The passive heat dissipation of the drone fuselage is to use its own structural parts to dissipate heat. The consequences of passive heat dissipation are: the heat dissipation is limited, which is only suitable for micro-sized drones, not for slightly larger drones with more functions; at the same time, the temperature of the drone fuselage structural parts rises, which can easily burn the user.

[0007] 3. Active heat dissipation: Active heat dissipation of the drone fuselage is to add a special heat dissipation device to its own structure. The consequence of active heat dissipation is that the active heat dissipation power unit will produce large vibrations, seriously affecting the operation of the gyroscope and threatening the safety of the drone. In addition, the addition of active heat dissipation devices increases the difficulty of waterproofing, and the deterioration of waterproofness will affect the normal operation of electrical equipment in the lower cabin of the drone. In addition, the addition of heat dissipation equipment increases the weight of the drone, affecting the flight performance of the drone.

[0008] In the prior art, most UAV fuselages are usually waterproofed by local defense, with poor overall waterproof performance, and without overall consideration of the heat dissipation structure.

[0009] In order to fully optimize the heat dissipation and waterproof performance of the drone and improve its safety, it is necessary to work on the drone's fuselage structure. Summary of the invention

[0010] In view of the above analysis, the present invention aims to provide a drone fuselage and a drone, so as to solve the technical problems that the heat dissipation and waterproof performance of the drone are poor, which is not conducive to the normal operation of the electrical components inside the drone and affects flight safety.

[0011] The present invention is achieved through the following technical solutions:

[0012] A drone fuselage includes a cabin part; the cabin part includes an air inlet, an air outlet, a heat dissipation unit and a waterproof unit; the heat dissipation unit includes a heat dissipation plate and a wind guiding plate; the heat dissipation plate is provided with a wind guiding strip sub-unit and a heat dissipation plate waterproof sealing groove; the wind guiding plate is buckled on the wind guiding strip sub-unit and encloses a heat dissipation cavity with the heat dissipation plate; the waterproof unit includes a heat dissipation plate waterproof sealing ring; the heat dissipation plate waterproof sealing groove is used for installing the heat dissipation plate waterproof sealing ring; the heat dissipation cavity heat dissipation plate waterproof sealing ring can seal and isolate the heat dissipation cavity, so that the heat dissipation cavity becomes an independent heat dissipation air duct inside the cabin part; the wind guiding strip sub-unit includes wind guiding strips; the connecting line of the projection vertices of the ends of multiple wind guiding strips close to the air inlet forms an air inlet end curve, and this curve bends towards the air inlet side, and the curvature radius at the projection vertex on this curve is greater than the distance from the center of the air inlet to this projection vertex, so that the ends of multiple wind guiding strips close to the air inlet evenly bear the wind force; the end of the wind guiding strip on the side that first bears the incoming air near the air inlet partially deflects, and the front end of the deflected wind guiding strip is parallel to the incoming air direction.

[0013] Furthermore, the magnitude of the wind force borne by the end of the wind guiding strip near the air inlet and the deflection angle are obtained through hydrodynamic simulation calculation.

[0014] Furthermore, the boundary conditions of the hydrodynamic simulation calculation at least include the structural parameters of the heat dissipation unit and the incoming air power parameters of the heat dissipation power unit.

[0015] Furthermore, this curve is an arc line, and the center of the arc line deviates from the center of the air inlet towards the front end of the cabin part in the front-back direction and towards the position where the wind guiding strip sub-unit first bears the wind in the left-right direction.

[0016] Furthermore, the wind guiding strip sub-unit is arranged in a Y-shaped structure; the bifurcated ends of the Y-shaped structure in the wind guiding strip sub-unit are the air outlet ends of the wind guiding strips, respectively facing the air outlet; the converging end of the Y-shaped structure in the wind guiding strip sub-unit is the air inlet end of the wind guiding strip and faces the air inlet.

[0017] Furthermore, the magnitude of the wind force borne by the end of the wind guiding strip near the air inlet, the deflection angle, and the position of the heat dissipation air duct with the maximum air intake volume are obtained through hydrodynamic calculation and hydrodynamic simulation calculation, so that the lengths, deflection angles, and the spacing between the air inlet ends of the wind guiding strips on both sides of the Y-shaped structure of the wind guiding strip sub-unit are different from those of the adjacent lower cabin wind guiding strip air inlet ends.

[0018] Furthermore, the cabin part includes a top cover part, a middle shell part, and a lower cabin part; both the top cover part and the lower cabin part include the heat dissipation unit and the waterproof unit.

[0019] Furthermore, the top cover part further includes a top cover, and a top cover reinforcing rib is arranged in the middle of the inner surface of the top cover; the top cover reinforcing rib is buckled in the heat dissipation plate waterproof sealing groove of the top cover part.

[0020] Furthermore, a top cover waterproof sealing groove is arranged around the inner surface of the top cover, and the upper outer edge of the middle shell part is buckled in the top cover waterproof sealing groove; an upper waterproof strip unit is arranged in the top cover waterproof sealing groove.

[0021] Furthermore, the lower cabin part includes a bottom shell assembly, an upper shell assembly, and a lower cabin waterproof assembly; the bottom shell assembly includes the heat dissipation unit of the lower cabin part; the lower cabin waterproof assembly includes a lower cabin equipment cavity waterproof ring, a bottom shell heat sink waterproof ring, and an arm waterproof ring.

[0022] Furthermore, the bottom shell assembly includes a bottom shell, and a bottom shell equipment cavity reinforcing rib is arranged on the inner surface of the bottom shell; the upper shell assembly includes an upper shell; an upper shell equipment cavity reinforcing rib is arranged on the inner surface of the upper shell. Furthermore, the bottom shell and the upper shell are buckled, and a lower cabin joint part and a lower cabin arm outer installation part are formed at the outer periphery of the bottom shell and the upper shell; after the bottom shell equipment cavity reinforcing rib and the upper shell equipment cavity reinforcing rib are buckled, an equipment cavity joint part and a lower cabin arm inner installation part are formed.

[0023] Furthermore, the internal space of the equipment cavity joint part is the equipment cavity. Furthermore, the lower cabin equipment cavity waterproof ring is arranged at the lower cabin joint part and the lower cabin arm inner installation part; the arm waterproof ring is arranged at the lower cabin arm outer installation part.

[0024] Furthermore, the bottom shell equipment cavity reinforcing rib is buckled in the heat dissipation plate waterproof sealing groove on the heat dissipation plate of the lower cabin part; the bottom shell heat sink waterproof ring is arranged in the heat dissipation plate waterproof sealing groove.

[0025] Furthermore, an upper waterproof strip unit is arranged between the top cover part and the middle shell part; a lower waterproof strip unit is arranged between the middle shell part and the lower cabin part.

[0026] An unmanned aerial vehicle includes the unmanned aerial vehicle fuselage described above.

[0027] Furthermore, the unmanned aerial vehicle further includes arms and rotors.

[0028] Compared with the prior art, the present invention can achieve the following beneficial effects:

[0029] 1. In the heat dissipation and waterproof structure of the UAV fuselage of the present invention, the heat dissipation plate and the air guiding plate are buckled to form a heat dissipation cavity for the directional propagation of the dissipated hot air, which can efficiently direct the dissipation of the heat generated by the internal heat source of the UAV, improving the heat dissipation efficiency. At the same time, the design of different lengths, deflection angles and the spacing between the air inlet ends of adjacent top cover air guiding strips at the air inlet end of the air guiding strip improves the uniformity of the UAV fuselage heat dissipation and further improves the heat dissipation efficiency.

[0030] 2. In the heat dissipation and waterproof structure of the UAV fuselage of the present invention, waterproof units are provided between the heat dissipation plate and the shells of the top cover part / lower cabin part, between the top cover part, the middle shell part and the lower cabin part, making the UAV fuselage fully waterproof and having good waterproof performance.

[0031] The above technical solutions can also be combined with each other to achieve more preferred combination schemes. Other features and advantages of the present invention will be described in the subsequent description, and some advantages can be made obvious from the description or understood by implementing the present invention. The objectives and other advantages of the present invention can be realized and obtained from the content specifically pointed out in the description and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] The drawings are only for the purpose of showing specific Embodiment 1 and are not considered as a limitation to the present invention. Throughout the drawings, the same reference signs denote the same components.

[0033] Figure 1 It is an exploded view of the overall structure of the UAV fuselage of the present invention;

[0034] Figure 2 It is a schematic diagram of the installation state of the overall structure of the UAV fuselage of the present invention;

[0035] Figure 3 It is a schematic diagram of the structure of the top cover part of the invention in the state of half-section of the top cover;

[0036] Figure 4 It is a schematic diagram of the heat dissipation cavity enclosure structure of the top cover part of the invention;

[0037] Figure 5 It is Figure 4 a cross-sectional view taken along the line A-A in

[0038] Figure 6 It is a schematic diagram of the top cover structure of the top cover part of the present invention;

[0039] Figure 7 It is a three-dimensional structure schematic diagram of the heat dissipation plate of the top cover part of the present invention;

[0040] Figure 8 It is a top view structure schematic diagram of the heat dissipation plate of the top cover part of the present invention;

[0041] Figure 9Schematic diagram of the air deflector structure of the top cover part of the present invention;

[0042] Figure 10 Schematic diagram of the overall structure installation state of the lower cabin part of the present invention;

[0043] Figure 11 is Figure 10 Cross-sectional view in the E-E direction in;

[0044] Figure 12 Schematic diagram of the inner surface structure of the bottom shell of the lower cabin part of the present invention;

[0045] Figure 13 Schematic diagram of the positional relationship between the heat dissipation unit of the lower cabin part of the present invention, the fan heat dissipation and dust prevention net, and the top cover air outlet heat dissipation and dust prevention net;

[0046] Figure 14 Top view of the lower cabin heat dissipation plate of the present invention;

[0047] Figure 15 Schematic diagram of the air deflector structure of the lower cabin of the present invention;

[0048] Figure 16 Schematic diagram of the waterproof ring structure of the equipment cavity of the lower cabin of the invention;

[0049] Figure 17 Cross-sectional structure schematic diagram of the waterproof ring of the equipment cavity of the lower cabin of the invention;

[0050] Figure 18 Schematic diagram of the waterproof ring structure of the machine arm of the present invention;

[0051] Figure 19 Schematic diagram of the installation of the inner surface structure of the upper shell of the lower cabin of the present invention;

[0052] Figure 20 Schematic diagram of the overall structure of the unmanned aerial vehicle of the present invention.

[0053] Reference numerals:

[0054] 1. Top cover part; 11. Top cover; 111. Top cover reinforcing rib; 112. Top cover heat dissipation air inlet; 113. Top cover waterproof outer card slot; 114. Top cover strobe light installation part; 115. Top cover outlet dust-proof net installation port; 116. Top cover waterproof sealing groove; 117. Top cover heat dissipation plate connection part; 118. Top cover installation part; 12. Top cover fan unit; 13. Top cover strobe light unit; 14. Top cover fan heat dissipation dust-proof net; 141. Top cover fan heat dissipation dust-proof net installation hole; 15. Top cover heat dissipation plate; 151. Top cover heat dissipation plate air outlet; 152. Top cover heat dissipation plate waterproof sealing groove; 153. Top cover air guide strip sub-unit; 154. Top cover heat dissipation plate installation part; 16. Top cover air guide plate; 161. Top cover air guide plate strobe light installation hole; 162. Top cover air guide plate outlet installation hole; 163. Top cover air guide plate inlet installation groove; 17. Top cover air outlet heat dissipation dust-proof net; 18. Top cover heat dissipation plate waterproof sealing ring; 19. Power button; 191. Power button waterproof pad; 192. Power button bracket;

[0055] 2. Middle shell part; 21. Inner clamping part at the upper end of the middle shell;

[0056] 3. Lower cabin part; 31. Bottom shell; 311. Bottom shell flash lamp installation part; 312. Bottom shell air intake part; 313. Bottom shell air outlet; 314. Bottom shell outer arm installation opening; 315. Bottom shell inner clamping part; 316. Bottom shell equipment cabin reinforcing rib; 317. Bottom shell heat dissipation plate reinforcing rib; 318. Bottom shell heat dissipation plate installation part; 319. Bottom shell installation part; 3110. Bottom shell accessory installation part; 3111. Bottom shell fan heat dissipation dust-proof net installation part; 3112. Bottom shell drain hole; 3113. Bottom shell inner arm installation opening; 3114. Bottom shell air outlet heat dissipation dust-proof net installation part; 32. Lower cabin heat dissipation component; 321. Lower cabin heat dissipation plate; 3211. Lower cabin heat dissipation air guiding strip sub-unit; 3212. Lower cabin heat dissipation plate waterproof groove; 3213. Lower cabin heat dissipation plate bottom shell installation part; 3214. Lower cabin heat dissipation plate air guiding plate installation part; 322. Lower cabin air guiding plate; 3221. Lower cabin air guiding upper plate; 3222. Lower cabin air guiding side plate; 3223. Lower cabin flash lamp installation part; 3224. Lower cabin air guiding plate positioning part; 323. Lower cabin heat dissipation power unit; 3231. Lower cabin heat dissipation fan; 3232. Lower cabin heat dissipation fan installation plate; 324. Lower cabin heat dissipation fan heat dissipation dust-proof net; 325. Lower cabin air outlet heat dissipation dust-proof net; 33. Upper shell assembly; 331. Upper shell body; 3311. Upper shell outer clamping part; 3312. Upper shell installation part; 3313. Upper shell equipment cabin reinforcing rib; 33131. Upper shell equipment cabin reinforcing rib insertion part; 3314. Upper shell outer arm installation opening; 3315. Upper shell equipment installation part; 3316. Upper shell inner arm installation opening; 332. Equipment module; 34. Lower cabin flash lamp assembly; 35. Bottom shell accessory; 361. Lower cabin equipment cavity waterproof ring; 3611. Straight part; 3612. Ring part; 3613. Waterproof strip protrusion; 362. Bottom shell heat sink waterproof ring; 363. Arm waterproof ring; 3631. Inner clamping part of arm waterproof ring; 3632. Outer clamping part of arm waterproof ring;

[0057] 41. Upper waterproof strip unit; 42. Lower waterproof strip unit;

[0058] 51. Top cover heat dissipation cavity; 52. Lower cabin heat dissipation cavity; 53. Equipment cabin; 54. Waterproof strip bottom shell installation position; 55. Waterproof strip upper shell body installation position;

[0059] 6. Arm; 7. Rotor blade. Detailed implementation manners

[0060] The following will specifically describe the preferred embodiments of the present invention in conjunction with the accompanying drawings. Among them, the accompanying drawings form a part of the present invention and are used together with the embodiments of the present invention to explain the principle of the present invention, rather than to limit the scope of the present invention.

[0061] In conjunction with Figures 1 - 20 , the technical solutions of the present invention will be described more specifically:

[0062] In this embodiment, it is defined that the direction vertically upward of the top cover 11 when the UAV is in the landing state is the up direction, and the direction vertically downward of the bottom shell 31 is the down direction; the direction where the air inlet end of the UAV cabin is located is the front end, and the direction where the air outlet end is located is the rear end; the screw rainproof plug, fastening screw and rainproof gasket form a waterproof fastener.

[0063] The UAV fuselage in this embodiment 1 includes a cabin part; the cabin part includes an air inlet, an air outlet, a heat dissipation unit and a waterproof unit; the heat dissipation unit includes a heat dissipation plate and a wind guiding plate; the heat dissipation plate is provided with a wind guiding strip sub-unit and a heat dissipation plate waterproof sealing groove; the wind guiding plate is buckled on the wind guiding strip sub-unit and encloses a heat dissipation cavity with the heat dissipation plate; the waterproof unit includes a heat dissipation plate waterproof sealing ring; the heat dissipation plate waterproof sealing groove is used for installing the heat dissipation plate waterproof sealing ring; the heat dissipation cavity heat dissipation plate waterproof sealing ring can seal and isolate the heat dissipation cavity, making the heat dissipation cavity an independent heat dissipation air duct inside the cabin part; the wind guiding strip sub-unit includes wind guiding strips; the connecting line of the projection vertices at one end of multiple wind guiding strips close to the air inlet forms an air inlet end curve, which bends towards the air inlet side, and the curvature radius at any projection vertex on this curve is greater than the distance from the air inlet center to any projection vertex, so that multiple wind guiding strips at one end close to the air inlet evenly bear the wind force; that is, first, one end of the wind guiding strip on the air inlet side close to the air inlet is locally deflected, and the front end of the deflected wind guiding strip is parallel to the air inlet direction.

[0064] The UAV fuselage in this embodiment may include one or more cabin parts.

[0065] Embodiment 1

[0066] A UAV fuselage.

[0067] As Figure 1 shown,

[0068] Specifically, the UAV fuselage in this embodiment 1 includes 3 cabin parts, which are the top cover part 1, the middle shell part 2 and the lower cabin part 3 that are sequentially sealed and connected. Electronic components that need to be waterproof and heat-dissipated are arranged inside the top cover part 1, the middle shell part 2 and the lower cabin part 3, and a variety of buttons or peripheral interfaces are installed outside the top cover part 1, the middle shell part 2 and the lower cabin part 3.

[0069] In this embodiment 1, an upper waterproof strip unit 41 is provided between the top cover part 1 and the middle shell part 2, and a lower waterproof strip unit 42 is provided between the middle shell part 2 and the lower cabin part 3, which are used to seal and connect the top cover part 1, the middle shell part 2 and the lower cabin part 3. All externally installed buttons or peripheral interfaces adopt the method of being limited by a limiting structure and bonded with double-sided tape, ensuring that each installed part is not only firmly positioned but also has good waterproof sealing at the installation place.

[0070] The top cover part 1 and the lower cabin part 3 respectively include their own heat dissipation components, and the heat dissipation components include a heat dissipation unit and a heat dissipation power unit.

[0071] The heat dissipation unit of this Embodiment 1 includes a heat dissipation plate and a wind guiding plate; a wind guiding strip sub-unit and a heat dissipation plate waterproof sealing groove are arranged on the heat dissipation plate; the wind guiding plate is buckled on the wind guiding strip sub-unit and encloses a heat dissipation cavity with the heat dissipation plate; the heat dissipation plate waterproof sealing groove is used for installing a heat dissipation plate waterproof sealing ring, and the heat dissipation plate waterproof sealing ring can seal and isolate the heat dissipation cavity, so that the heat dissipation cavity becomes an independent heat dissipation air duct inside the engine room part.

[0072] The heat dissipation power unit includes the power to provide the intake air required for heat dissipation. The heat dissipation power unit of this Embodiment 1 includes a fan.

[0073] The top cover part 1 and the lower cabin part 3 are also respectively provided with an air inlet and an air outlet. The front end of the heat dissipation cavity faces the air inlet, and the rear end of the heat dissipation cavity faces the air outlet.

[0074] The wind guiding strip sub-unit includes wind guiding strips, and heat dissipation channels are formed between adjacent wind guiding strips; the connecting line of the front projection vertices of each wind guiding strip is an air inlet end curve; the center of the air inlet end curve deviates from the center position of the air inlet; the front-end spacing between adjacent wind guiding strips is the largest at the maximum air intake position. The fact that the center of the air inlet end curve deviates from the center position of the air inlet and the maximum air intake position are obtained through hydrodynamic simulation calculations. The boundary conditions of the hydrodynamic simulation calculations at least include structural parameters and power parameters.

[0075] The heat dissipation and waterproof structures involved in this Embodiment 1 are concentrated in the top cover part 1 and the lower cabin part 3.

[0076] First, in combination with Figures 3 - 9 , the technical solution of the top cover part 1 will be introduced:

[0077] The top cover part 1 includes a top cover assembly, a top cover heat dissipation assembly, and a top cover waterproof assembly. Among them, the main structure of the top cover part 1 is the top cover 11. The top cover heat dissipation assembly includes the heat dissipation unit of the top cover part 1, and the top cover waterproof assembly includes the top cover heat dissipation plate waterproof sealing ring 18.

[0078] As Figure 3 shown, the heat dissipation unit of the top cover heat dissipation assembly includes a top cover heat dissipation plate 15 and a top cover wind guiding plate 16; a top cover wind guiding strip sub-unit 153 is arranged in the middle of the top cover heat dissipation plate 15, and a top cover heat dissipation plate waterproof sealing groove 152 is arranged around the top cover heat dissipation plate 15; the top cover wind guiding plate 16 is buckled on the top cover wind guiding strip sub-unit 153 to form a top cover heat dissipation cavity 51.

[0079] The main structure of the top cover part 1 is that a top cover reinforcing rib 111 is arranged in the middle of the inner surface of the top cover 11; the top cover reinforcing rib 111 is buckled in the top cover heat dissipation plate waterproof sealing groove 152; the heat dissipation plate waterproof sealing ring arranged between the top cover reinforcing rib 111 and the top cover heat dissipation plate waterproof sealing groove 152 is the top cover heat dissipation plate waterproof sealing ring 18.

[0080] Combined Figure 3 and Figure 6 As shown, the top cover 11 is a composite shell of a thin shell plus an auxiliary structure. The thin shell of the top cover 11 is successively provided with a top cover heat dissipation air inlet 112, a top cover stroboscopic lamp mounting part 114, and a top cover outlet dust-proof net mounting opening 115. Multiple expansion function module interfaces are arranged around the top cover 11.

[0081] In the middle of the inner surface of the top cover 11, a top cover reinforcing rib 111 is provided. Around the inner surface of the top cover 11, a top cover waterproof sealing unit, a top cover heat dissipation plate connecting part 117, and a top cover mounting part 118 are provided. The top cover heat dissipation plate connecting part 117 is a threaded structure, and the top cover mounting part 118 is a through-hole structure.

[0082] As Figure 6 shown, the top cover waterproof sealing unit includes a top cover waterproof sealing groove 116 and a top cover waterproof outer clamping groove 113. The top cover waterproof sealing groove 116 is a groove-shaped structure, which is arranged around the rear ends on both sides of the inner surface of the top cover 11. The outer clamping structure of the top cover waterproof outer clamping groove 113 is arranged around the front end of the inner surface of the top cover 11.

[0083] As Figure 1 shown, around the upper end surface of the middle shell part 2, a structure matching the top cover waterproof sealing unit is provided. Specifically, around the upper end surface of the middle shell part 2, a middle shell upper inner clamping part 21 is provided.

[0084] The top cover 11 is hermetically connected to the middle shell part 2 downward through the upper waterproof strip unit 41.

[0085] As Figure 6 and shown, the top cover waterproof sealing groove 116 arranged around the inner surface of the top cover 11 can form a through groove on both sides and at the rear end, and is divided into multiple segments by the mounting structure of the side-mounted accessory 001 at the rear end side of the inner surface of the top cover 1. Therefore, the upper waterproof strip unit 41 includes 1 long side rear waterproof strip and multiple front side waterproof strips.

[0086] When the top cover 11 and the middle shell part 2 are installed, the long side rear waterproof strip is adhesively arranged on the bottom of the groove in the top cover waterproof sealing groove 116. The middle shell upper inner clamping part 21 of the middle shell part 2 is inserted into the top cover waterproof sealing groove 116 at this place and squeezes the side rear waterproof strip in the up and down directions; multiple front side waterproof strips are adhesively bonded to the middle shell upper inner clamping part 21 at the front end of the middle shell part 2. The middle shell upper inner clamping part 21 at the front end of the middle shell part 2 and the top cover waterproof outer clamping groove 113 on the top cover 11 squeeze each other left and right, and limit the multiple front side waterproof strips at the joint.

[0087] Preferably, the fastener connecting the middle shell part 2 and the top cover 11 is a waterproof fastener, which can form a waterproof structure at the connecting part.

[0088] The installation and sealing structure of the top cover 11 and the middle shell part 2 is stable and has good waterproof performance.

[0089] In addition, a plurality of top mounting accessories and side mounting accessories are also connected to the upper part of the top cover 11. The top mounting accessories include a broadcast module, a power button 19, etc., and the side mounting accessories include a plurality of front decorative pieces and side decorative pieces. For the installation of any part of the top mounting accessories and side mounting accessories, a limiting structure is used for limitation and double-sided tape is used for bonding, so as to ensure that each installed part is not only firmly positioned, but also waterproof sealed from both the inner and outer sides, ensuring good waterproof sealing at the installation location. For example:

[0090] As Figure 3 shown, a power button installation position is also provided on the top cover 11, and a power button 19, a power button waterproof pad 191, and a power button bracket 192 are sequentially connected to the power button installation position.

[0091] Specifically, in this Embodiment 1, the power button 19 is arranged at the power button installation position on the top cover 1. A ring-shaped power button waterproof pad 191 is arranged on the power button 19. The power button bracket 192 is pressed and fixed on the power button waterproof pad 191. The button screw sequentially passes through the power button bracket 192, the power button waterproof pad 191, and the power button 19 from outside to inside, fastening the power button 19 on the top cover 1. This waterproof structure of the power button bracket 192 plus the power button waterproof pad 191 can better ensure the waterproof effect at the power button 19.

[0092] Further preferably, the power button waterproof pad 191 is made of a silicone material with a conformal design, specifically a ring-shaped silicone waterproof pad.

[0093] This limiting structure plus double-sided tape bonding method is applicable to the installation of all other parts on the inventive structure of this Embodiment 1. This connection method can not only prevent the installed parts from falling off, but also ensure the overall waterproof function of the unmanned aircraft cabin.

[0094] A top cover heat dissipation component is installed inside the top cover 11. The top cover heat dissipation component includes a heat dissipation unit top cover heat dissipation plate 15 and a top cover air guide plate 16 of the top cover part 1, and also includes a top cover fan unit 12, a top cover fan heat dissipation dustproof net 14, and a top cover air outlet heat dissipation dustproof net 17.

[0095] The top cover fan unit 12 is arranged between the top cover 11 and the top cover heat dissipation plate 15 and is connected to the top cover 11, specifically connected to the center M1 of the top cover heat dissipation fan.

[0096] The top cover fan unit 12 includes a top cover fan and a top cover fan installation body, and the top cover fan and the top cover fan installation body are fixedly connected into one body. The top cover fan can implement forced convection to achieve continuous heat dissipation of high-heat generating circuits.

[0097] Specifically, on the inner surface of the top cover 11 at the position of the top cover heat dissipation air inlet 112, there is also a mounting part for the top cover fan unit with a screw hole structure. On the top cover fan mounting body, there is a fan top cover connection part that matches the position of the top cover fan unit mounting part. The fan top cover connection part is specifically a through-hole structure on the top cover fan mounting body. The top cover 11 and the top cover fan unit 12 are fixedly connected by waterproof fasteners at the position of the center M1 of the top cover heat dissipation fan, which is also the center position of the top cover fan. The center M1 of the top cover heat dissipation fan is a concentrated heat generation part such as the UAV vision main board. The rotation of the top cover fan can carry away a large amount of hot fluid.

[0098] The top cover fan heat dissipation dust-proof net 14 is connected to the inner surface of the top cover heat dissipation air inlet 112. The periphery of the top cover fan heat dissipation dust-proof net 14 is provided with top cover fan dust-proof net mounting holes. Two top cover outlet heat dissipation dust-proof nets 17 are symmetrically arranged and are respectively connected to the two top cover outlet dust-proof net mounting openings 115 of the top cover 11. The periphery of the top cover outlet heat dissipation dust-proof net 17 is provided with top cover outlet heat dissipation dust-proof net mounting holes.

[0099] The top cover fan heat dissipation dust-proof net 14 is connected to the inner surface of the top cover 11 by interference fit.

[0100] On the inner side of the top cover 11 and facing downwards, a top cover air deflector 16 and a top cover heat dissipation plate 15 are sequentially arranged. The heat dissipation unit formed by the top cover air deflector 16 and the top cover heat dissipation plate 15 is the main functional part of the top cover heat dissipation assembly.

[0101] Among them, the top cover 11 is connected to the periphery of the top cover heat dissipation plate 15, and the top cover air deflector 16 is connected to the middle of the top cover heat dissipation plate 15. This connection method has a good effect of isolating external heat from entering for the important internal functional electronic components.

[0102] Such as Figure 5 shown, a top cover heat dissipation cavity 51 with good fluidity is also formed between the top cover air deflector 16 and the top cover heat dissipation plate 15.

[0103] Such as Figure 7 and Figure 8 shown, a top cover air deflector sub-unit 153 is arranged in the middle of the top cover heat dissipation plate 15. Two top cover heat dissipation plate air outlets 151 are symmetrically arranged at both ends of the distal end of the top cover heat dissipation plate 15. The periphery of the top cover heat dissipation plate 15 is also provided with a top cover heat dissipation plate waterproof seal groove 152 and a top cover heat dissipation plate mounting part 154; the top cover air deflector 16 includes a top cover air deflector upper plate and a top cover air deflector side plate. The inner surface of the top cover air deflector upper plate is buckled on the upper end surface of the top cover air deflector sub-unit 153, and the inner surface of the top cover air deflector side plate is attached to the outer side surface of the outermost air deflector bar of the top cover air deflector sub-unit 153.

[0104] A top cover heat dissipation plate waterproof seal groove 152 is provided with a top cover heat dissipation plate waterproof seal ring 18, and the top cover heat dissipation plate waterproof seal ring 18 is bonded to the bottom of the top cover heat dissipation plate waterproof seal groove 152. The top cover reinforcement rib 111 of the top cover 11 is limited in the top cover heat dissipation plate waterproof seal groove 152 by extruding the top cover heat dissipation plate waterproof seal ring 18. The top cover heat dissipation plate connection part 117 of the top cover 11 matches the top cover heat dissipation plate installation part 154 of the top cover heat dissipation plate 15, and the top cover heat dissipation plate installation part 154 is a through-hole structure. The top cover heat dissipation plate 15 and the top cover 11 are firmly connected into a whole by setting fasteners at the installation part and pressing the top cover heat dissipation plate waterproof seal ring 18.

[0105] Preferably, the top cover heat dissipation plate waterproof seal ring 18 is made of silicone foam. Silicone foam has the advantages of being easy to manufacture, having large compressibility, and redundant bonding at the ends.

[0106] The top cover air guide bar sub-unit 153 is the main functional structure on the top cover heat dissipation plate 15. The top cover air guide bar sub-unit 153 includes multiple air guide bars, and the top cover air guide bar sub-unit 153 is arranged in a Y-shaped structure.

[0107] The two upward branch ends in the Y shape of the top cover air guide bar sub-unit 153, that is, the bifurcated ends of the Y-shaped structure, are the air guide bar air outlet ends, and respectively face the top cover heat dissipation plate air outlet 151; the converging end in the Y shape of the top cover air guide bar sub-unit 153 is the air guide bar air inlet end, and the air guide bar air inlet end of the top cover air guide bar sub-unit 153 faces the top cover heat dissipation air inlet 112.

[0108] The Y-shaped layout structure of the top cover air guide bar sub-unit 153 is a mirror-symmetrical structure in the middle and at the rear, while the arrangement of the multiple air guide bars of the top cover air guide bar sub-unit 153 at the air inlet end is not completely symmetrically arranged. The air guide bars at the air inlet end of the top cover are arranged according to the incoming air direction through hydrodynamic simulation calculation, that is, specific designs are made for one end of the air inlet of each top cover air guide bar, so that there are differences in the length, deflection angle, and the distance between adjacent top cover air guide bar air inlet ends at the air inlet end of each top cover air guide bar.

[0109] Specifically, the top cover fan rotates counterclockwise with the center M1 point of the top cover heat dissipation fan as the center, and the air inlet ends of multiple top cover air guide bars are locally inclined.

[0110] As Figure 8 shown, the air inlet ends of the top cover air guide bars in Embodiment 1 are locally inclined symmetrically to the sides with the center line of the top cover heat dissipation plate 15 as the reference. The purpose is to make the top cover air guide heat dissipation channels formed by adjacent top cover air guide bars as parallel as possible to the incoming air direction at the part with the largest air intake.

[0111] After each top cover air guide strip of the top cover air guide strip sub-unit 153 is projected onto the plane of the top cover heat dissipation plate 15 of the top cover air guide strip sub-unit, the connection line of the vertices of the projection lines of the air inlet ends of each top cover air guide strip forms a curve BCD at the air inlet end of the top cover air guide strip sub-unit with the center M2 of the curve at the air inlet end of the top cover air guide strip sub-unit as the center of the circle. The two ends of the curve BCD at the air inlet end of the top cover air guide strip sub-unit are point B and point D, and point C is arranged in the middle.

[0112] Specifically in this Embodiment 1, the curve BCD at the air inlet end of the top cover air guide strip sub-unit is an arc line. The center of the curve BCD at the air inlet end of the top cover air guide strip sub-unit, that is, the center M2 of the curve at the air inlet end of the top cover air guide strip sub-unit, deviates from the center M1 of the top cover heat dissipation fan towards the front end of the top cover 1 in the front-back direction and deviates towards the direction of point B where the top cover air guide strip sub-unit 153 first receives wind after the top cover fan starts in the left-right direction.

[0113] As Figure 8 shown, the position of the top cover air guide strip sub-unit 153 in this Embodiment 1 that first bears wind after the top cover fan starts is the guide strip at the end where point B is located on one side. The guide strip that can always receive the maximum air volume during the ventilation process is around point C. The position that finally bears wind is the guide strip at the end where point D is located on the other side.

[0114] Specifically, through hydrodynamic simulation calculation, the setting of the curve BCD at the air inlet end of the top cover air guide strip sub-unit enables multiple air guide strips to evenly bear wind at the end close to the air inlet, and at the same time optimizes the air volume distribution of each top cover heat dissipation air duct.

[0115] Specifically, through hydrodynamic simulation calculation, point C is the intersection point of the tangent line of the outer edge of the fan and the curve BCD at the air inlet end of the top cover air guide strip sub-unit, and this tangent line is parallel to the connection line between the center M1 of the top cover heat dissipation fan and the center M2 of the curve at the air inlet end of the top cover air guide strip sub-unit.

[0116] The front ends of multiple top cover air guide strips in this Embodiment 1 have the largest spacing at point C, and the spacing gradually decreases towards the ends of the air guide strips on both sides. This setting enables the hot air sent out by the top cover fan to quickly enter the top cover heat dissipation cavity 51 in the best flow mode.

[0117] The inclined air inlet ends of multiple top cover air guide strips of the top cover air guide strip sub-unit 153 are arranged in parallel in the middle through arc transition, and form two symmetric branches with a Y-shaped structure at the air outlet ends of the top cover air guide strips, respectively facing the air outlet 151 of the top cover heat dissipation plate.

[0118] The local parts at the front ends of each top cover air guide strip are all deflected towards the air inlet direction.

[0119] Preferably, as Figure 8As shown, without considering the length of the air inlet end being limited by the arc BCD of the air inlet end of the top cover air guide strip, the air inlet end of the top cover heat dissipation air guide strip sub-unit 153 in Embodiment 1 will reach the dotted line L uniformly and is also mirror-symmetrical. Figure 8 An example is shown in which a pair of air guide strips reach the dotted line L and are mirror-symmetrical; this design makes the manufacturing process simple on the premise of ensuring the maximum air volume at point C of the top cover air guide strip.

[0120] The top cover air guide plate 16 is used to rectify the air duct and optimize the hot air evacuation channel.

[0121] As Figure 9 shown, the top cover air guide plate 16 is provided with a top cover air guide plate stroboscopic lamp mounting hole 161, a top cover air guide plate outlet mounting hole 162, and a top cover air guide plate inlet mounting groove 163.

[0122] There are top cover fan heat dissipation dust-proof net mounting holes 141 on the top cover fan heat dissipation dust-proof net 14 that match the top cover air guide plate inlet mounting groove 163, and top cover air outlet heat dissipation dust-proof net mounting holes on the top cover air outlet heat dissipation dust-proof net 17 that match the top cover air guide plate outlet mounting hole 162. The two ends of the top cover air guide plate 16 are respectively connected to the top cover fan heat dissipation dust-proof net 14 and the top cover air outlet heat dissipation dust-proof net 17.

[0123] The top cover air guide plate 16 is provided with bending plates at two symmetrical branches of the Y-shaped structure formed at the air outlet end of the top cover air guide strip for lapping the top cover fan heat dissipation dust-proof net 14. The bending plates of the top cover air guide plate 16 are designed according to the shape of the edge of the top cover fan heat dissipation dust-proof net 14.

[0124] The top cover stroboscopic lamp unit 13 is installed at the top cover stroboscopic lamp mounting part 114 of the top cover 11. The top cover stroboscopic lamp unit 13 includes a top cover stroboscopic lamp base and a top cover stroboscopic lamp. The top cover air guide plate stroboscopic lamp mounting hole 161 is a reserved position on the top cover air guide plate 16 for installing the stroboscopic lamp base on the inner surface of the top cover 11. The stroboscopic lamp base is provided with stroboscopic lamp power equipment, which is an important heat source.

[0125] As Figure 5 shown, the top cover air guide plate 16 and the top cover heat dissipation plate 15 are buckled to form a complete and closed top cover heat dissipation cavity 51 from the air guide inlet end for the hot air conveyed by the top cover fan to the air guide strip outlet end of the top cover heat dissipation plate outlet 151, and the heat dissipation of the top cover fan for core heat sources such as the visual support plate and the heat dissipation of the top cover stroboscopic lamp power equipment are directionally transmitted, which not only avoids the harm of waste heat to the electronic components in the UAV body, but also has high heat dissipation efficiency.

[0126] Meanwhile, the top cover air outlet heat dissipation and dust-proof net 17 also has the function of dissipating the heat inside the top cover 11 to the outside. The rainwater entering from the top cover air outlet heat dissipation and dust-proof net 17 can also be discharged through the top cover heat dissipation plate air outlet 151, where the structure combines the functions of waterproofing and heat dissipation.

[0127] Both the top cover air outlet heat dissipation and dust-proof net 17 and the top cover fan heat dissipation and dust-proof net 14 can prevent large particles from entering the top cover 1.

[0128] In addition, the top cover air deflector 16 of Embodiment 1 not only buckles on the top cover heat dissipation plate 15, but also is fixedly connected to the top cover fan heat dissipation and dust-proof net 14 and the top cover air outlet heat dissipation and dust-proof net 17 at both ends. This setting enhances the integration of the heat dissipation and waterproof structure at the top of the drone fuselage of the present invention and reduces the vibration caused by the fan and the like. This setting reduces the influence of temperature and vibration on the working performance of electronic components.

[0129] In specific applications, after the top cover air deflector 16 buckles on the top cover heat dissipation plate 15, it may not be fixedly connected to the top cover fan heat dissipation and dust-proof net 14 and the top cover air outlet heat dissipation and dust-proof net 17 at both ends, so as to reduce the processing and installation difficulty.

[0130] Secondly, in combination with Figures 10 - 19 , the technical solution of the cabin part 3 will be introduced:

[0131] As Figure 10 shown, the lower cabin part 3 of Embodiment 1 includes a bottom shell assembly, an upper shell assembly 33 and a lower cabin waterproof assembly.

[0132] The lower cabin heat dissipation assembly 32 is arranged inside the bottom shell assembly. The lower cabin heat dissipation assembly 32 includes the heat dissipation unit of the lower cabin part 3. The heat dissipation unit of the lower cabin part 3 includes a lower cabin heat dissipation plate 321 and a lower cabin air deflector 322; the lower cabin heat dissipation plate 321 and the lower cabin air deflector 322 are buckled to form a lower cabin heat dissipation cavity 52. The front end of the cabin heat dissipation cavity 52 faces the air inlet of the lower cabin, and the rear end of the cabin heat dissipation cavity 52 faces the air outlet of the lower cabin.

[0133] The bottom shell assembly includes a bottom shell 31, and the upper shell assembly 33 includes an upper shell 331. After the bottom shell assembly and the upper shell assembly 33 are buckled, they are fixedly connected, and a drone lower cabin is formed inside; the lower cabin heat dissipation assembly 32 is connected inside the drone lower cabin, and a lower cabin arm external connection part is formed around the drone lower cabin for connecting the arm.

[0134] In combination with Figure 10 and Figure 11 shown, the lower cabin waterproof assembly includes a lower cabin equipment cavity waterproof ring 361, a bottom shell heat sink waterproof ring 362 and an arm waterproof ring 363.

[0135] As Figure 18As shown, the arm waterproof ring 363 is a ring structure. Specifically, the arm waterproof ring 363 is a ring groove structure with two side wall surfaces, which are the inner clamping part 3631 and the outer clamping part 3632 of the arm waterproof ring respectively. In the installed state, the inner clamping part 3631 of the arm waterproof ring is located on the inner wall surface of the outer connecting part of the lower cabin arm in Embodiment 1, and the outer clamping part 3632 of the arm waterproof ring is located on the outer wall surface of the outer connecting part of the lower cabin arm in Embodiment 1.

[0136] The arm waterproof ring 363 can effectively block external rainwater and other liquids from entering the lower cabin of the UAV in Embodiment 1 at the arm connection, preventing rainwater and the like from further entering the equipment compartment 53 and protecting the electronic components from damage.

[0137] Specifically, the waterproof ring 361 for the equipment cavity of the lower cabin and the waterproof ring 362 for the bottom shell heat sink are arranged inside the lower cabin of the UAV. The waterproof ring 361 for the equipment cavity of the lower cabin is arranged between the bottom shell 31 and the upper shell 331, and the waterproof ring 362 for the bottom shell heat sink is arranged between the heat dissipation plate 321 of the lower cabin and the bottom shell 31.

[0138] Combined Figure 11 、 Figure 12 and Figure 19 As shown, on the installation surface of the bottom shell equipment compartment reinforcing rib 316 in Embodiment 1, an outer edge with a half wall thickness is provided along the outer circumference, and on the installation surface of the upper shell equipment compartment reinforcing rib 3313, an inner edge with a half thickness is provided along the inner circumference. After the outer edge of the bottom shell equipment compartment reinforcing rib 316 is buckled with the inner edge of the upper shell equipment compartment reinforcing rib 3313, an equipment compartment 53 is formed inside the enclosure of the bottom shell equipment compartment reinforcing rib 316 and the upper shell equipment compartment reinforcing rib 3313.

[0139] As Figure 16 shown, specifically, the waterproof ring 361 for the equipment cavity of the lower cabin is arranged at the joint surface of the equipment compartment 53 and the inner installation part of the lower cabin arm.

[0140] Specifically, the joint of the bottom shell equipment compartment reinforcing rib 316 and the upper shell equipment compartment reinforcing rib 3313 forms the joint surface of the equipment compartment 53; the discontinuous part of the joint surface of the equipment compartment 53 is composed of the bottom shell 31 and the upper shell 331 to form the inner installation part of the lower cabin arm.

[0141] The waterproof ring 361 for the equipment cavity of the lower cabin is in a ring shape. The waterproof ring 361 for the equipment cavity of the lower cabin includes a straight part 3611 and a ring part 3612. The straight part 3611 of the waterproof ring 361 for the equipment cavity of the lower cabin is arranged at the joint surface of the equipment compartment 53, and the outer ring of the ring part 3612 of the waterproof ring 361 for the equipment cavity of the lower cabin is arranged at the inner installation part of the lower cabin arm.

[0142] The waterproof ring 361 for the equipment cavity of the lower cabin is the waterproof layer in the middle part of the lower cabin part 3.

[0143] As Figure 17As shown, the cross-section of the waterproof ring 361 of the lower cabin equipment cavity in the shape of a ring sleeve adopts an S shape, forming a waterproof strip bottom shell installation position 54 and a waterproof strip upper shell installation position 55, which are connected to the upper shell equipment cabin reinforcing rib 3313 of the upper shell 331 in a semi-surrounding form inside and to the bottom shell equipment cabin reinforcing rib 316 of the bottom shell 31 outside.

[0144] Preferably, the upper shell equipment cabin reinforcing rib insertion parts 33131 are intermittently arranged between the top surfaces of the upper shell equipment cabin reinforcing ribs 3313. The upper shell equipment cabin reinforcing rib insertion parts 33131 are provided with a draft angle that narrows upward, so as to be able to quickly insert into the waterproof strip upper shell installation position 55 and quickly and completely install the lower cabin equipment cavity waterproof ring 361 on the upper shell equipment cabin reinforcing ribs 3313.

[0145] Preferably, on both sides of the lower cabin equipment cavity waterproof ring 361 in the middle part between the waterproof strip bottom shell installation position 54 and the waterproof strip upper shell installation position 55, that is, on the two opposite surfaces of the clamping part in the middle of the S-shaped structure of the lower cabin equipment cavity waterproof ring 361, a plurality of waterproof strip protrusions 3613 are provided. While further increasing the waterproof effect, the elastic deformation amount is increased, thereby reducing the vibration transmission between the bottom shell 31 and the upper shell 331, which is beneficial to reducing the impact of vibration on the safe operation of the electronic components of the flight control equipment.

[0146] The main structure of the lower cabin of the unmanned aerial vehicle with a heat dissipation and waterproof structure in this Embodiment 1 is the bottom shell 31 on the bottom shell assembly and the upper shell 331 of the upper shell assembly 33.

[0147] Combined Figure 12 and Figure 19 , the bottom shell 31 is provided with a bottom shell inner clamping part 315, a bottom shell equipment cabin reinforcing rib 316, a bottom shell arm outer installation port 314 and a bottom shell arm inner installation port 3113.

[0148] The bottom shell 31 and the upper shell 331 are connected by waterproof fasteners, forming an outer joint part of the lower cabin composed of the bottom shell inner clamping part 315 and the upper shell outer clamping part 3311, an equipment cabin joint part of the lower cabin composed of the bottom shell equipment cabin reinforcing rib 316 and the upper shell equipment cabin reinforcing rib 3313, an outer installation part of the lower cabin arm composed of the bottom shell arm outer installation port 314 and the upper shell arm outer installation port 3314, and an inner installation part of the arm composed of the bottom shell arm inner installation port 3113 and the upper shell arm inner installation port 3316.

[0149] The arm waterproof ring 363 is connected to the outer installation part of the lower cabin arm. The outer joint part of the lower cabin and the arm waterproof ring 363 form the outermost waterproof layer of the lower cabin part 3.

[0150] The internal space of the equipment cabin joint part is the equipment cabin.

[0151] Figure 10Shows the schematic diagram of the overall structure installation state of the lower cabin part of the drone in Embodiment 1.

[0152] As Figure 19 shown, the main structure of the upper shell assembly 33 is the upper shell 331. Corresponding to the bottom shell 31, on the upper shell 331, there are provided an upper shell outer clamping platform part 3311, an upper shell equipment cabin reinforcing rib 3313, an upper shell arm outer mounting port 3314 and an upper shell arm inner mounting port 3316 with matching structures. Among them, on the upper shell equipment cabin reinforcing rib 3313, there is provided an upper shell equipment cabin reinforcing rib insertion part 33131.

[0153] The upper shell assembly 33 further includes an equipment module 332. The equipment module 332 is the main heat generating body and is connected to the upper shell 331 at the upper shell equipment mounting part 3315 through fasteners.

[0154] As Figure 12 shown, the bottom shell 31 is a composite shell of a thin shell plus an auxiliary structure. On the thin shell of the bottom shell 31, there are successively provided a bottom shell air inlet part 312, a bottom shell strobe light mounting part 311 and a bottom shell air outlet 313 from front to back. The bottom shell air inlet part 312 and the bottom shell strobe light mounting part 311 are arranged on the center line of the overall structure of the bottom shell 31, and the two bottom shell air outlets 313 are symmetrically arranged with respect to the center line of the overall structure of the bottom shell 31 in a mirror image.

[0155] Combined with Figure 10 and Figure 12 shown, on the inner surface of the bottom shell 31, with the center position of the bottom shell air inlet part 312 as the center of the circle, a plurality of bottom shell fan heat dissipation and dust prevention net mounting parts 3111 are arranged in a circumferential manner for connecting the lower cabin heat dissipation fan heat dissipation and dust prevention net 324.

[0156] Preferably, the bottom shell fan heat dissipation and dust prevention net mounting part 3111 is a clamping column. The lower cabin heat dissipation fan heat dissipation and dust prevention net 324 is made of a steel mesh. At the corresponding position on the lower cabin heat dissipation fan heat dissipation and dust prevention net 324, there is a through-hole structure and it is positioned on the bottom shell 31 by using a hot melting or pressure melting process. The lower cabin heat dissipation fan heat dissipation and dust prevention net 324 is in interference fit with the plurality of bottom shell fan heat dissipation and dust prevention net mounting parts 3111 and is fixed by hot melting or pressure melting, so that the installation of the lower cabin heat dissipation fan heat dissipation and dust prevention net 324 is fast and integrated with the bottom shell 31. Therefore, the lower cabin heat dissipation fan heat dissipation and dust prevention net 324 is not easily affected by the rotating parts of the lower cabin heat dissipation fan 3231 and does not generate jitter.

[0157] Combined with Figure 11 and Figure 13 shown, around the bottom shell air outlet 313, there is provided a bottom shell air outlet heat dissipation and dust prevention net mounting part 3114 for connecting the lower cabin air outlet heat dissipation and dust prevention net 325.

[0158] Preferably, the installation part 3114 of the heat dissipation and dust-proof net at the air outlet of the bottom shell is a clamping column; the heat dissipation and dust-proof net 325 at the air outlet of the lower cabin is made of steel mesh; there are through-hole structures at corresponding positions on the heat dissipation and dust-proof net 325 at the air outlet of the lower cabin. Through a hot melting or pressure melting process, the heat dissipation and dust-proof net 325 at the air outlet of the lower cabin is positioned on the bottom shell 31. The heat dissipation and dust-proof net 325 at the air outlet of the lower cabin is in interference fit with multiple installation parts 3114 of the heat dissipation and dust-proof net at the air outlet of the bottom shell and is fixed on the bottom shell 31 by hot melting or pressure melting, making the installation of the heat dissipation and dust-proof net 325 at the air outlet of the lower cabin fast and integrated with the bottom shell 31. Due to this design, the heat dissipation and dust-proof net 325 at the air outlet of the lower cabin is not easily affected by the rotating parts of the heat dissipation fan 3231 in the lower cabin and the operation of the flight control equipment and does not generate jitter.

[0159] Inside the thin shell of the bottom shell 31, from the center outwards, there are successively arranged a bottom shell heat dissipation plate reinforcing rib 317, a bottom shell equipment cabin reinforcing rib 316, and a bottom shell inner clamping part 315.

[0160] Among them, the bottom shell heat dissipation plate reinforcing rib 317 and the bottom shell equipment cabin reinforcing rib 316 are in a closed-loop structure, and the bottom shell air inlet part 312, the bottom shell strobe light installation part 311, and the bottom shell air outlet 313 are enclosed within the bottom shell heat dissipation plate reinforcing rib 317. On the inner surface of the bottom shell 31 outside the periphery of the bottom shell heat dissipation plate reinforcing rib 317, there are multiple bottom shell heat dissipation plate installation parts 318. Preferably, the bottom shell heat dissipation plate installation part 318 is a column platform structure with a through-hole, which is used to connect the lower cabin heat dissipation plate 321 through a waterproof fastener. There are also multiple bottom shell inner arm installation openings 3113 on the bottom shell equipment cabin reinforcing rib 316. In this embodiment 1, there are 4 pairwise symmetric bottom shell inner arm installation openings 3113.

[0161] Among them, the bottom shell inner clamping part 315 is a segmented structure, and there are multiple bottom shell outer arm installation openings 314 in the interval segments of the bottom shell inner clamping part 315. The positions of the bottom shell outer arm installation openings 314 correspond to the orientations of the bottom shell inner arm installation openings 3113, and they are jointly used to connect the arm.

[0162] Among them, around the inner surface of the bottom shell 31, inside the bottom shell inner clamping part 315, there is a bottom shell installation part 319, which is used to connect the upper shell 331 through a waterproof fastener. Preferably, the bottom shell installation part 319 is a column platform with a through-hole.

[0163] Among them, there are also multiple circuit board connector expansion interfaces on the periphery of the bottom shell 31, which are used to externally connect expansion function modules. The circuit board connector expansion interfaces are covered with an interference-connected interface waterproof plug, which can not only prevent water but also prevent the interface waterproof plug from falling off.

[0164] Such as Figure 10As shown, on the periphery of the bottom shell 31, there are also provided a bottom shell accessory installation part 3110 penetrating the shell and a bottom shell drain hole 3112. The bottom shell accessory installation part 3110 is used to install the bottom shell accessories 35 including buttons (the bottom shell accessories 35 are not limited to Figure 10 as shown), and the bottom shell accessory installation part 3110 is not limited to Figure 12 as shown.

[0165] For the installation of any part of the bottom shell accessories 35, including the installation of the lower cabin flashing light assembly 34, a limiting structure is used for limitation and double-sided tape is used for bonding, ensuring that each installed part is not only firmly positioned, but also waterproof-sealed to the bottom shell 31 from both the inner and outer sides, ensuring good waterproof sealing at the installation location.

[0166] The lower cabin flashing light assembly 34 includes a lower cabin flashing light with high heat dissipation.

[0167] A plurality of bottom shell drain holes 3112 are provided on the periphery of the bottom shell 31, used for discharging fluids such as rainwater that enter the lower cabin of the drone through the lower cabin heat dissipation fan heat dissipation dust screen 324 and the lower cabin air outlet heat dissipation dust screen 325.

[0168] The lower cabin heat dissipation assembly 32 of this Embodiment 1 is installed inside the bottom shell 31. The lower cabin heat dissipation assembly 32 includes a lower cabin heat dissipation plate 321, a lower cabin air guide plate 322, and a lower cabin heat dissipation power unit 323. In addition, the lower cabin heat dissipation assembly 32 further includes a lower cabin heat dissipation fan heat dissipation dust screen 324 and a lower cabin air outlet heat dissipation dust screen 325 installed on the bottom shell 31.

[0169] Combined with Figure 12 , Figure 13 and Figure 14 as shown, the lower cabin heat dissipation power unit 323 is arranged between the bottom shell 31 and the lower cabin heat dissipation plate 321, connected to the lower cabin heat dissipation plate 321, and specifically located at the center of the corresponding bottom shell air inlet part 312, that is, at the center N1 point of the bottom shell heat dissipation fan.

[0170] The lower cabin heat dissipation power unit 323 includes a lower cabin heat dissipation fan 3231 and a lower cabin heat dissipation fan mounting plate 3232, and the lower cabin heat dissipation fan 3231 and the lower cabin heat dissipation fan mounting plate 3232 are fixedly connected into one body.

[0171] Specifically, the lower cabin heat dissipation fan mounting plate 3232 of this Embodiment 1 is provided with mounting ears and mounting holes. On the surface of the lower cabin heat dissipation plate 321, a bottom shell fan unit mounting portion with a screw hole structure is provided at the center N1 point corresponding to the bottom shell heat dissipation fan. The lower cabin heat dissipation power unit 323 is fixedly connected to the lower cabin heat dissipation plate 321 through fasteners. The position of the center N1 point of the bottom shell heat dissipation fan corresponding to the lower cabin heat dissipation fan 3231 is the concentrated heat generation part of the UAV flight control equipment. When the lower cabin heat dissipation fan 3231 rotates, a large amount of heated gas in the equipment cabin 53 can be taken away.

[0172] Similar to the function of the top cover fan, the lower cabin heat dissipation fan 3231 can implement forced convection to achieve continuous heat dissipation of high-heat-generating circuits, components, and devices.

[0173] The structure of the lower cabin heat dissipation cavity 52 and the top cover heat dissipation cavity 51 can be the same or different. In this Embodiment 1, the technical solutions of the lower cabin heat dissipation cavity 52 and its related structures adopt different technical solutions from those of the related structures of the top cover part 1. Among them, the method of designing fluid dynamics simulation calculation is the same:

[0174] On the inner surface of the bottom shell 31 facing upward, a lower cabin air guide plate 322 and a lower cabin heat dissipation plate 321 are sequentially arranged. The lower cabin air guide plate 322 and the lower cabin heat dissipation plate 321 constitute the heat dissipation unit of the lower cabin part 3 and are the main functional components of the lower cabin heat dissipation assembly 32.

[0175] As Figure 11 shown, the lower cabin heat dissipation plate 321 and the lower cabin air guide plate 322 are buckled to form the lower cabin heat dissipation cavity 52.

[0176] Combined with Figure 13 and Figure 14 shown, in the middle of the lower surface of the lower cabin heat dissipation plate 321, a lower cabin heat dissipation air guide strip sub-unit 3211 is provided. Around the lower cabin heat dissipation plate 321, an annular lower cabin heat dissipation plate waterproof groove 3212 is provided. Outside the lower cabin heat dissipation plate waterproof groove 3212, a lower cabin heat dissipation plate guide bottom shell mounting portion 3213 is provided. The lower cabin heat dissipation plate guide bottom shell mounting portion 3213 is used to fixedly connect the main functional components of the lower cabin heat dissipation assembly 32 to the bottom shell 31.

[0177] The lower cabin heat dissipation air guide strip sub-unit 3211 is the main functional structure on the lower cabin heat dissipation plate 321. The lower cabin heat dissipation air guide strip sub-unit 3211 includes multiple lower cabin air guide strips, and the lower cabin heat dissipation air guide strip sub-unit 3211 is arranged in a Y-shaped structure as a whole.

[0178] The two upward branch ends of the Y shape of the lower cabin heat dissipation air guiding strip sub-unit 3211, that is, the forked ends of the Y-shaped structure, are the air outlet ends of the lower cabin air guiding, and are respectively oriented towards the two bottom shell air outlets 313; the converging end of the Y shape of the lower cabin heat dissipation air guiding strip sub-unit 3211 is the air inlet end of the lower cabin air guiding. The air inlet end of the lower cabin air guiding is oriented towards the bottom shell air inlet part 312.

[0179] The Y-shaped layout structure of the lower cabin heat dissipation air guiding strip sub-unit 3211 is a mirror-symmetrical structure in the middle and rear ends. However, the local layout of the multiple lower cabin air guiding strips of the lower cabin heat dissipation air guiding strip sub-unit 3211 at the air inlet end is not an absolutely symmetrical structure. According to the direction of the incoming air, through fluid mechanics simulation calculation, the structure of the air inlet ends of the multiple lower cabin air guiding strips is specifically designed, so that the air inlet ends of each lower cabin air guiding strip are different in length, deflection angle, and the distance between the air inlet ends of adjacent lower cabin air guiding strips.

[0180] Specifically, in this Embodiment 1, it is set that the lower cabin heat dissipation fan 3231 rotates clockwise with the center N1 of the bottom shell heat dissipation fan as the center of the circle, and the air inlet ends of the multiple lower cabin air guiding strips are locally inclined.

[0181] As Figure 14 shown, specifically, the air inlet ends of the lower cabin air guiding strips are locally mirrored with the center line of the lower cabin heat dissipation plate 321 as the reference, and are symmetrically inclined towards the center from left to right. The purpose is to make the lower cabin air guiding and heat dissipation channels formed by adjacent lower cabin air guiding strips as parallel as possible to the incoming air direction at the part with the largest air intake volume.

[0182] After the projection of each lower cabin air guiding strip of the lower cabin heat dissipation air guiding strip sub-unit 3211 onto the plane of the lower cabin heat dissipation plate 321 where the lower cabin heat dissipation air guiding strip sub-unit 3211 is located, the connection line of the vertices of the projection lines of the air inlet ends of each lower cabin air guiding strip forms a curve. This setting is obtained through fluid mechanics simulation calculation, which can enable the air inlet ends of the multiple lower cabin air guiding strips near the air inlet of the lower cabin to evenly bear the wind force, and at the same time optimize the ventilation volume distribution of each lower cabin heat dissipation air duct.

[0183] As Figure 14 shown, preferably, the curve formed by the connection line of the vertices of the projection lines of the air inlet ends of each lower cabin air guiding strip is an arc. Specifically, the center of the arc FGH of the air inlet end layout of the lower cabin air guiding strip, that is, the center N2 of the curve at the air inlet end of the lower cabin air guiding strip sub-unit, deviates from the center N1 of the bottom shell heat dissipation fan towards the front end of the bottom shell 31 in the front-rear direction and towards the direction of the F point that first bears the rear wind force after the lower cabin heat dissipation fan 3231 is started in the left-right direction of the lower cabin heat dissipation air guiding strip sub-unit 3211. This design makes the lengths of the air inlet ends of each lower cabin air guiding strip different due to the limitation of the arc FGH of the air inlet end layout of the lower cabin air guiding strip.

[0184] Preferably, the position of the lower cabin heat dissipation air guide strip sub-unit 3211 in the lower cabin heat dissipation channel that first bears the rear wind force after the fan starts is at point F on one side, the lower cabin air guide channel that always receives the maximum ventilation volume during ventilation is at point G, and the position of the lower cabin heat dissipation channel that finally bears the rear wind force is at point H on the other side.

[0185] Specifically, point G is the intersection of the tangent of the outer edge of the lower cabin heat dissipation fan 3231 and the arc FGH of the inlet end of the lower cabin air guide strip. This tangent is parallel to the line connecting the center N1 of the bottom shell heat dissipation fan and the center N2 of the curve at the inlet end of the lower cabin air guide strip sub-unit.

[0186] The setting of point G is the same as that of point C.

[0187] Specifically, on the premise that the Y-shaped layout structure of the lower cabin heat dissipation air guide strip sub-unit 3211 is generally a mirror-symmetrical structure as a whole, taking Figure 14 the lower half of the Y-shaped layout structure of the lower cabin heat dissipation air guide strip sub-unit 3211 as an example:

[0188] Except for the lower cabin air guide strip in the middle of the Y-shaped layout structure, the lower cabin air guide strip in the middle that first bears the incoming air has a local deflection at the end near the inlet relative to its own middle part. The front end of the deflected lower cabin air guide strip is parallel to the incoming air direction.

[0189] As Figure 14 shown, through hydrodynamic simulation calculations, the front ends of multiple lower cabin air guide strips in the lower half of the Y-shaped layout structure of the lower cabin heat dissipation air guide strip sub-unit 3211 in Embodiment 1 have the largest spacing at point G, and the spacing gradually decreases towards the inlet ends of the lower cabin air guide strips on both sides. This design with different spacings at the inlet ends of adjacent lower cabin air guide strips optimizes the gas flow efficiency in the lower cabin heat dissipation channel formed by each lower cabin air guide strip, enabling the hot air sent out by the lower cabin heat dissipation fan 3231 to quickly enter the lower cabin heat dissipation cavity 52 in the best flow manner.

[0190] The inclined inlet ends of multiple lower cabin air guide strips of the lower cabin heat dissipation air guide strip sub-unit 3211 form parallel middle lower cabin air guide strip segments in the middle through arc transitions, and form two symmetric branches of a Y-shaped structure at the outlet ends of the lower cabin air guide at the rear, respectively facing the 2 bottom shell air outlets 313.

[0191] The middle lower cabin air guide strip segment and the outlet end of the lower cabin air guide strip of the lower cabin heat dissipation air guide strip sub-unit 3211 are mirror-symmetrical structures. The local parts at the front ends of each lower cabin air guide strip are all deflected towards the incoming air direction.

[0192] Preferably, as Figure 14As shown, without considering the length of the air inlet end being limited by the arc FGH of the air inlet end of the lower cabin air guide strip, the air inlet end of the lower cabin heat dissipation air guide strip sub-unit 3211 in this Embodiment 1 is also mirror-symmetrical (for illustration reference Figure 8 ); This design simplifies the manufacturing process on the premise of ensuring the maximum air volume at point G of the lower cabin air guide strip.

[0193] The air inlet structure design of the lower cabin heat dissipation air guide strip sub-unit 3211 enables the hot air sent out by the lower cabin heat dissipation fan 3231 to quickly enter the lower cabin heat dissipation cavity 52 in the best flow manner and be conveyed out.

[0194] In addition, a plurality of lower cabin heat dissipation plate air guide plate mounting parts 3214 are provided at the tops of the plurality of lower cabin air guide strips of the lower cabin heat dissipation air guide strip sub-unit 3211 for connecting the lower cabin air guide plate 322.

[0195] Specifically, the lower cabin heat dissipation plate air guide plate mounting part 3214 is a convex structure.

[0196] Combined with Figure 11 and Figure 13 As shown, a bottom shell heat sink waterproof ring 362 is arranged in the lower cabin heat dissipation plate waterproof groove 3212. Preferably, the bottom shell heat sink waterproof ring 362 is bonded to the bottom of the lower cabin heat dissipation plate waterproof groove 3212. After the bottom shell heat sink reinforcing rib 317 of the bottom shell 31 presses against the bottom shell heat sink waterproof ring 362 and is limited in the lower cabin heat dissipation plate waterproof groove 3212, the waterproof fastener seals and connects the lower cabin heat dissipation plate 321 to the bottom shell 31 through the heat dissipation plate bottom shell mounting part 3213 and the bottom shell heat dissipation plate mounting part 318, so that the bottom shell 31 and the lower cabin heat dissipation plate 321 are firmly connected into a whole.

[0197] Preferably, the bottom shell heat sink waterproof ring 362 is made of silicone foam. Silicone foam has the advantages of being easy to manufacture, having large compressibility, and redundant bonding at the ends.

[0198] The bottom shell heat sink waterproof ring 362 is the innermost waterproof layer of the lower cabin part 3. The bottom shell heat sink waterproof ring 362 can not only better isolate the external fluid from entering the lower cabin heat dissipation cavity 52, but also play a certain role in reducing vibration transmission, which is beneficial to the normal operation of electronic components and devices.

[0199] As Figure 15 shown, the lower cabin air guide plate 322 includes a lower cabin air guide upper plate 3221 and a lower cabin air guide side plate 3222. The inner surface of the lower cabin air guide upper plate 3221 is buckled on the upper end surface of the lower cabin heat dissipation air guide strip sub-unit 3211, and the inner side surface of the lower cabin air guide side plate 3222 is attached to the outer side surface of the outermost lower cabin air guide strip of the lower cabin heat dissipation air guide strip sub-unit 3211.

[0200] AsFigure 11 As shown, the lower cabin heat dissipation plate 321 and the lower cabin air guiding plate 322 are buckled to form the lower cabin heat dissipation cavity 52.

[0201] The lower cabin air guiding plate 322 functions as a rectifying air duct to optimize the hot air evacuation channel.

[0202] On the upper plate 3221 of the lower cabin air guiding plate, there is an installation part 3223 for the lower cabin flash lamp, which is used for the lower cabin flash lamp assembly to pass through and dissipate heat here after being installed at the flash lamp installation part 311 of the bottom shell 31.

[0203] On the upper plate 3221 of the lower cabin air guiding plate, there is also a positioning part 3224 for the lower cabin air guiding plate, which is used to connect with the lower cabin heat dissipation plate 321. Specifically, the positioning part 3224 of the lower cabin air guiding plate is a hole system structure, and the protruding structure of the air guiding plate installation part 3214 of the lower cabin heat dissipation plate passes through the positioning part 3224 of the lower cabin air guiding plate with interference fit. Through hot melting or pressure melting process, the lower cabin air guiding plate 322 is positioned on the top of the lower cabin air guiding strip of the lower cabin heat dissipation plate 321. This makes the structures of the lower cabin air guiding plate 322 and the lower cabin heat dissipation plate 321 integrated, ensuring the structural stability of the lower cabin heat dissipation component 32 and the stable heat dissipation function of the lower cabin heat dissipation cavity 52.

[0204] As Figure 13 shown, the air inlet end of the lower cabin air guiding plate 322 covers the front end of the lower cabin heat dissipation air guiding strip sub-unit 3211, and the air outlet end of the lower cabin air guiding plate 322 forms two symmetric branches of a Y-shaped structure, covering the Y-shaped lower cabin air guiding air outlet end of the lower cabin heat dissipation air guiding strip sub-unit 3211. This setting enables the hot air output by the lower cabin heat dissipation fan 3231 to enter the lower cabin heat dissipation cavity 52 directionally and be directly transmitted to the bottom shell air outlet 313 to be discharged. During the process of the air flow passing through the lower cabin heat dissipation cavity 52, it dissipates heat from the important heat source, the lower cabin flash lamp assembly 34, installed at the flash lamp installation part 311 of the bottom shell.

[0205] The lower cabin heat dissipation component 32 of this Embodiment 1 forms a complete heat dissipation channel from the lower cabin heat dissipation fan 3231 delivering hot air into the air inlet end of the lower cabin air guiding plate, passing through the lower cabin heat dissipation cavity 52, and being sent out from the bottom shell air outlet 313 of the bottom shell 31. It directionally transmits the heat dissipation of the lower cabin heat dissipation fan 3231 to core heat sources such as the equipment cabin 53 and the heat generated by the lower cabin flash lamp assembly 34. This not only avoids the harm of waste heat to the electronic components inside the UAV fuselage but also has high heat dissipation efficiency.

[0206] In addition, the lower cabin air outlet heat dissipation and dust-proof net 325 and the lower cabin heat dissipation fan heat dissipation and dust-proof net 324 can prevent large particles from entering the lower cabin of the UAV inside the bottom shell 31 from the air inlet and air outlet.

[0207] As Figure 10The heat dissipation and dust-proof net 325 of the lower cabin air outlet and the heat dissipation and dust-proof net 324 of the lower cabin heat dissipation fan may cause fluids such as rainwater to enter; therefore, a bottom shell drain hole 3112 is provided on the bottom shell 31 to drain fluids such as rainwater.

[0208] In the drone fuselage of this Embodiment 1, the arm is installed, positioned, and waterproofed both internally and externally in the lower cabin part 3. On the one hand, it ensures the stability of the arm installation, and on the other hand, it also ensures the security of the connection of the communication line between the drone arm and the front cabin of the drone.

[0209] Specifically, the bottom shell heat sink waterproof ring 362 of this Embodiment 1 is an integrated design of a ring structure and a linear structure, which stably ensures the waterproofness of the equipment cabin 53 of the lower cabin of the drone; at the same time, the three-layer setting of the lower cabin waterproof component ensures the safety and reliability of the waterproof performance of the lower cabin of the drone with a heat dissipation and waterproof structure in this Embodiment 1.

[0210] In this Embodiment 1, the middle shell part 2 and the lower cabin part 3 need to be electrically and physically connected. Therefore, multiple matching positioning or clamping connection structures are provided between the lower end face of the inner middle shell part 2 and the upper end face of the upper shell 331. The middle shell part 2 and the lower cabin part 3 are hermetically connected into a whole through the lower waterproof strip unit 42 at the connection.

[0211] Figure 1 It shows that the lower waterproof strip unit 42 of this Embodiment 1 includes multiple sealing strips.

[0212] In this Embodiment 1, the deflection direction of the air guide strip air inlet end is related to the rotation direction of the fan.

[0213] The heat dissipation and waterproof structure of the drone fuselage of the present invention integrates the functions of heat dissipation and waterproofing, effectively protects the normal operation of the electronic components of the drone body, and improves the flight safety of the drone. The heat dissipation and waterproof structure of the drone of the present invention has a wide range of applicability and can be used in aircraft design, especially suitable for small drones.

[0214] Embodiment 2

[0215] A drone.

[0216] The drone of this Embodiment 2 includes the drone fuselage of Embodiment 1, and also includes an arm 6 and a rotor 7.

[0217] The arms 6 and the rotors 7 are in one-to-one correspondence. One end of the arm 6 is connected to the side of the drone body of Embodiment 1, and the other end of the arm 6 is connected to the rotor 7. Multiple arms 6 are connected to the drone body.

[0218] Such as Figure 20As shown, preferably, Embodiment 2 of the present invention includes 4 robotic arms 6. The 4 robotic arms 6 are symmetrically connected to the periphery of the lower cabin part 3 of Embodiment 1 in pairs, and the connection ends of the robotic arms 6 extend deep into the interior of the lower cabin part 3 and are specifically connected to the inner mounting part of the lower cabin robotic arm and the outer mounting part of the lower cabin robotic arm.

[0219] A sleeve part 3612 of the waterproof ring 361 of the lower cabin equipment cavity is provided in the inner mounting part of the lower cabin robotic arm; a robotic arm waterproof ring 363 is provided in the outer mounting part of the lower cabin robotic arm.

[0220] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention. At the same time, any equipment or facility equipped with this device to expand the application field and produce composite technical effects belongs to the protection scope of the method invention.

Claims

1. An unmanned aerial vehicle fuselage, characterized in that, It includes an engine room part; the engine room part includes an air inlet, an air outlet, a heat dissipation unit and a waterproof unit; The heat dissipation unit includes a heat dissipation plate and a wind guiding plate; a wind guiding strip sub-unit and a heat dissipation plate waterproof sealing groove are arranged on the heat dissipation plate; the wind guiding plate is buckled on the wind guiding strip sub-unit and encloses a heat dissipation cavity with the heat dissipation plate; The waterproof unit includes a heat dissipation plate waterproof sealing ring; the heat dissipation plate waterproof sealing groove is used for installing the heat dissipation plate waterproof sealing ring; the heat dissipation plate waterproof sealing ring can seal and isolate the heat dissipation cavity, so that the heat dissipation cavity becomes an independent heat dissipation air duct inside the engine room part; The wind guiding strip sub-unit includes wind guiding strips; the connecting line of the projection vertices of the ends of multiple wind guiding strips close to the air inlet on the heat dissipation plate forms an air inlet end curve, the curve bends towards the air inlet side direction, and the curvature radius at any projection vertex on the curve is greater than the distance from the air inlet center to the projection vertex; Firstly, one end of the wind guiding strip on the air inlet side bears local deflection, and the front end of the deflected wind guiding strip is parallel to the air inlet direction.

2. The drone fuselage according to claim 1, wherein The wind guiding strip sub-unit is arranged in a Y-shaped structure; the bifurcated ends of the Y-shaped structure in the wind guiding strip sub-unit are the air outlet ends of the wind guiding strips, respectively facing the air outlet; the third branch end downward at the converging end of the Y-shaped structure in the wind guiding strip sub-unit is the air inlet end of the wind guiding strip and faces the air inlet.

3. The drone fuselage according to claim 2, characterized in that, The engine room part includes a top cover part (1), a middle shell part (2) and a lower cabin part (3), and both the top cover part (1) and the lower cabin part (3) include the heat dissipation unit and the waterproof unit.

4. The drone fuselage according to claim 3, characterized in that, The top cover part (1) further includes a top cover (11), and a top cover reinforcing rib (111) is arranged in the middle of the inner surface of the top cover (11); the top cover reinforcing rib (111) is buckled in the heat dissipation plate waterproof sealing groove of the top cover part (1); a top cover waterproof sealing groove (116) is arranged around the inner surface of the top cover (11), and the upper outer edge of the middle shell part (2) is buckled in the top cover waterproof sealing groove (116).

5. The drone fuselage according to claim 3, characterized in that, The lower cabin part (3) includes a bottom shell assembly, an upper shell assembly (33) and a lower cabin waterproof assembly; the bottom shell assembly includes the heat dissipation unit of the lower cabin part (3); the lower cabin waterproof assembly includes a lower cabin equipment cavity waterproof ring (361), a bottom shell heat sink waterproof ring (362) and an arm waterproof ring (363).

6. The drone fuselage according to claim 5, characterized in that The bottom shell assembly includes a bottom shell (31), and a bottom shell equipment cabin reinforcing rib (316) is arranged on the inner surface of the bottom shell (31); the upper shell assembly (33) includes an upper shell body (331); an upper shell equipment cabin reinforcing rib (3313) is arranged on the inner surface of the upper shell body (331).

7. The drone fuselage according to claim 6, wherein , the bottom shell (31) and the upper shell body (331) are buckled, a lower cabin joint part and a lower cabin arm outer installation part are formed at the outer periphery of the bottom shell (31) and the upper shell body (331), and an equipment cabin joint part and a lower cabin arm inner installation part are formed after the bottom shell equipment cabin reinforcing rib (316) and the upper shell equipment cabin reinforcing rib (3313) are buckled.

8. The drone fuselage according to claim 7, characterized in that, The waterproof ring (361) of the lower cabin equipment cavity is arranged at the joint of the equipment cabin and the installation part inside the lower cabin arm; the arm waterproof ring (363) is arranged at the installation part outside the lower cabin arm.

9. The drone fuselage according to claim 3, wherein An upper waterproof strip unit (41) is arranged between the top cover part (1) and the middle shell part (2); a lower waterproof strip unit (42) is arranged between the middle shell part (2) and the lower cabin part (3).

10. A drone, characterized in that, It includes the unmanned aircraft fuselage according to any one of claims 1-9.

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