CN116331537A - Unmanned aerial vehicle fuselage and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle fuselage and unmanned aerial vehicle Download PDFInfo
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- CN116331537A CN116331537A CN202310540653.8A CN202310540653A CN116331537A CN 116331537 A CN116331537 A CN 116331537A CN 202310540653 A CN202310540653 A CN 202310540653A CN 116331537 A CN116331537 A CN 116331537A
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- lower cabin
- waterproof
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/70—Constructional aspects of the UAV body
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
- B64U10/13—Flying platforms
- B64U10/14—Flying platforms with four distinct rotor axes, e.g. quadcopters
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/80—Arrangement of on-board electronics, e.g. avionics systems or wiring
- B64U20/83—Electronic components structurally integrated with aircraft elements, e.g. circuit boards carrying loads
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
- B64U20/92—Cooling of avionics
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/90—Cooling
- B64U20/96—Cooling using air
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Remote Sensing (AREA)
- Aviation & Aerospace Engineering (AREA)
- Microelectronics & Electronic Packaging (AREA)
- Cooling Or The Like Of Electrical Apparatus (AREA)
Abstract
The invention relates to an unmanned aerial vehicle body and an unmanned aerial vehicle, belongs to the technical field of unmanned aerial vehicle equipment, and solves the problems that the unmanned aerial vehicle body is poor in heat dissipation and waterproof performance and is unfavorable for the flight safety of the unmanned aerial vehicle. The unmanned aerial vehicle fuselage of the invention includes the cabin part; the cooling unit of the cabin part comprises a cooling plate and an air deflector, and the cooling plate is provided with an air guide strip subunit and a cooling plate waterproof sealing groove; the air deflector is buckled on the air deflector strip subunit, a heat dissipation cavity is formed by the air deflector and the heat dissipation plate, and the heat dissipation plate waterproof sealing groove is used for installing a heat dissipation plate waterproof sealing ring; the cabin part is also provided with an air inlet and an air outlet respectively; the air guide strip subunit comprises an air guide strip; the projection vertexes of the front ends of the plurality of air guide strips are connected to form an air inlet end curve which is bent towards the air inlet side; the part of the air guide strip, which is close to one end of the air inlet, deflects towards the air inlet direction. And an air guiding strip. The unmanned aerial vehicle body is provided with multiple heat dissipation and waterproof structures, has good directional ventilation and heat dissipation performance and good waterproof performance, and is beneficial to safe flight of the unmanned aerial vehicle.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle body with a heat dissipation waterproof device.
Background
In recent years, with the continuous expansion of the application field of aircrafts, a plurality of kinds of intelligent unmanned aerial vehicles are appeared.
These unmanned aerial vehicles are usually adapted to various flight environments, and are equipped with a large number of electrical equipment, and have comprehensive requirements on heat dissipation and water resistance, and are indispensable. Because the unmanned aerial vehicle executes the flight environment of task complicated, the circuit gathering space of high integrated level is narrow and small, the waterproof requirement of heat dissipation to unmanned aerial vehicle is extra strict.
In the prior art, the heat dissipation of the fuselage of most unmanned aerial vehicles is generally considered in the following ways:
1. the heat dissipation structure of the machine body is not processed, and the following results are: under the condition that the unmanned aerial vehicle continuously irradiates at high temperature, the temperature of the unmanned aerial vehicle cabin body is increased by 20-30 ℃ compared with the outside temperature; in a high-heat environment, the internal integrated electrical components and the circuit board cannot normally operate, so that the safety of the whole machine is threatened.
2. Passive heat dissipation. The passive heat dissipation of the unmanned aerial vehicle body is to utilize the structural members of the unmanned aerial vehicle to dissipate heat. The passive heat dissipation results are: the heat dissipation capacity is limited, and the heat dissipation device is only suitable for microminiature unmanned aerial vehicles, and is not suitable for unmanned aerial vehicles with larger functions; meanwhile, the temperature of the unmanned aerial vehicle body structural member rises, so that a user is easy to scald.
3. Active heat dissipation: the active heat dissipation of the unmanned aerial vehicle body is to add a special heat dissipation device on the structure of the unmanned aerial vehicle body. The active heat dissipation result is that the active heat dissipation power device can generate larger vibration, so that the operation of the gyroscope is seriously influenced, and the safety of the unmanned aerial vehicle is threatened. In addition, due to the fact that the active heat dissipation device is added, waterproof difficulty is increased, and normal operation of electrical equipment in the lower cabin of the unmanned aerial vehicle is affected due to poor waterproof performance. Furthermore, due to the fact that the heat dissipation equipment is added, the weight of the unmanned aerial vehicle is increased, and the flight performance of the unmanned aerial vehicle is affected.
In the prior art, most unmanned aerial vehicle fuselages generally adopt a local fortification mode for waterproof consideration, have poor overall waterproof performance, and have no overall consideration with a heat dissipation structure.
The heat dispersion and the waterproof performance of unmanned aerial vehicle are fully optimized to improve unmanned aerial vehicle's security, must do articles on unmanned aerial vehicle fuselage structure.
Disclosure of Invention
In view of the above analysis, the invention aims to provide an unmanned aerial vehicle body and an unmanned aerial vehicle, which are used for solving the technical problems that the unmanned aerial vehicle is poor in heat dissipation and water resistance and is not beneficial to normal operation of electric elements in the unmanned aerial vehicle to influence flight safety.
The invention is realized by the following technical scheme:
An unmanned aerial vehicle fuselage comprising a cabin portion; the cabin part comprises an air inlet, an air outlet, a heat radiating unit and a waterproof unit; the heat dissipation unit comprises a heat dissipation plate and an air deflector; the heat dissipation plate is provided with an air guide strip subunit and a heat dissipation plate waterproof sealing groove; the air deflector is buckled on the air guide strip subunit and surrounds a heat dissipation cavity with the heat dissipation plate; the waterproof unit comprises a heat-dissipating plate waterproof sealing ring; the heat dissipation plate waterproof sealing groove is used for installing the heat dissipation plate waterproof sealing ring; the waterproof sealing ring of the radiating plate of the radiating cavity can seal and isolate the radiating cavity, so that the radiating cavity becomes an independent radiating air channel in the cabin part; the wind guiding strip subunit comprises a wind guiding strip; the projection vertex connecting lines of the air guide strips close to one end of the air inlet form an air inlet end curve, the curve is bent towards the air inlet side direction, and the radius of curvature of the projection vertex on the curve is larger than the distance from the center of the air inlet to the projection vertex, so that one end of the air guide strips close to the air inlet uniformly bears wind power; the method comprises the steps of carrying out a first treatment on the surface of the The front end of the deflected air guide strip is parallel to the air inlet direction.
Furthermore, the magnitude and deflection angle of the wind force born by one end of the wind guide strip close to the air inlet are calculated through fluid mechanics simulation.
Further, the boundary condition of the hydrodynamic simulation calculation at least comprises the structural parameter of the heat dissipation unit and the air inlet power parameter of the heat dissipation power unit.
Further, the curved line is an arc line, and the center of the arc line is deviated from the center of the air inlet in the front-rear direction toward the front end of the cabin portion, and deviated in the left-right direction toward the position where the wind guiding strip subunit receives the wind force first.
Further, the wind guiding strip sub-units are arranged in a Y-shaped structure; the Y-shaped structure branch ends in the wind guide strip sub-units are wind guide strip air outlet ends which face the air outlets respectively; the converging end of the Y-shaped structure in the wind guiding strip subunit is the wind inlet end of the wind guiding strip and faces the wind inlet.
Furthermore, the positions of the heat dissipation air channels, which are close to the air inlet and bear the wind power, of the deflection angle and the maximum air inlet amount, are obtained through hydrodynamic computational fluid mechanics simulation calculation, so that the lengths and the deflection angles of the air inlet ends of the air guide strips on two sides of the Y-shaped structure of the air guide strip subunit and the distances between the air inlet ends of the air guide strips of the adjacent lower cabin body are different.
Further, the nacelle portion includes a top cover portion, a middle shell portion, and a lower nacelle body portion; the top cover part and the lower cabin body part comprise the heat radiating unit and the waterproof unit.
Further, the top cover part also comprises 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 ribs are buckled in the waterproof sealing groove of the heat dissipation plate of the top cover part.
Further, a top cover waterproof sealing groove is formed in the periphery of the inner surface of the top cover, the outer edge of the upper end of the middle shell part is buckled in the top cover waterproof sealing groove, and an upper waterproof strip unit is arranged in the top cover waterproof sealing groove.
Further, the lower cabin part comprises a bottom shell assembly, an upper shell assembly and a lower cabin waterproof assembly; the bottom shell assembly comprises a heat dissipation unit of the lower cabin body; the lower cabin waterproof assembly comprises a lower cabin equipment cavity waterproof ring, a bottom shell radiating fin waterproof ring and a horn waterproof ring.
Further, the bottom shell assembly comprises a bottom shell, and bottom shell equipment compartment reinforcing ribs are arranged on the inner surface of the bottom shell; the upper housing assembly includes an upper housing; the inner surface of the upper shell is provided with upper shell equipment compartment reinforcing ribs. Further, the bottom shell is buckled with the upper shell, and a lower cabin body combining part and a lower cabin horn outer mounting part are formed at the periphery of the bottom shell and the upper shell; and after the bottom shell equipment cabin reinforcing ribs and the upper shell equipment cabin reinforcing ribs are buckled, an equipment cabin combining part and a lower cabin inner installation part are formed.
Further, the inner space of the equipment cabin joint part is an equipment cabin. Further, the waterproof ring of the lower cabin equipment cavity is arranged at the position of the lower cabin combining part and the mounting part in the lower cabin horn; the method comprises the steps of carrying out a first treatment on the surface of the The horn waterproof ring is arranged at the outer installation part of the lower cabin horn.
Further, the bottom shell equipment compartment reinforcing ribs are buckled in a waterproof sealing groove of a heat dissipation plate on the heat dissipation plate of the lower compartment body; the waterproof sealing groove of the heat dissipation plate is internally provided with the waterproof ring of the bottom shell heat dissipation plate.
Further, 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 body part.
An unmanned aerial vehicle, includes unmanned aerial vehicle fuselage.
Further, unmanned aerial vehicle still includes horn and rotor.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the unmanned aerial vehicle body heat dissipation waterproof structure, the heat dissipation plate and the air deflector are buckled to form the heat dissipation cavity for directional propagation of evacuated heat air, so that heat emitted by an internal heat source of the unmanned aerial vehicle can be efficiently and directionally evacuated, and the heat dissipation efficiency is improved; meanwhile, due to the design that the air inlet ends of the air guide strips are different in length, deflection angle and distance between the air inlet ends of the adjacent top cover air guide strips, the heat dissipation uniformity of the unmanned aerial vehicle body is improved, and the heat dissipation efficiency is further improved.
2. According to the unmanned aerial vehicle body heat dissipation waterproof structure, the waterproof units are arranged between the heat dissipation plate and the shell of the top cover part/lower cabin body part and between the top cover part, the middle shell part and the lower cabin body part, so that the unmanned aerial vehicle body is waterproof comprehensively and has good waterproof performance.
The above technical schemes can be mutually combined to realize more preferable combination schemes. Additional features and advantages of the invention will be set forth in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. The objectives and other advantages of the invention may be realized and attained by the structure particularly pointed out in the written description and drawings.
Drawings
The drawings are only for purposes of illustrating particular embodiment 1 and are not to be construed as limiting the invention, like reference numerals referring to like parts throughout the several views.
FIG. 1 is an exploded view of the overall structure of the unmanned aerial vehicle fuselage of the present invention;
FIG. 2 is a schematic diagram showing the installation state of the whole structure of the unmanned aerial vehicle body;
FIG. 3 is a schematic view of the structure of the cover part of the present invention in a half-cut-away top cover state;
FIG. 4 is a schematic view of a heat dissipating cavity enclosure of the top cover portion of the present invention;
FIG. 5 is a cross-sectional view taken along the direction A-A in FIG. 4;
FIG. 6 is a schematic view of the top cover construction of the top cover section of the present invention;
FIG. 7 is a schematic perspective view of a heat dissipating plate of the top cover of the present invention;
FIG. 8 is a schematic top view of a heat dissipating plate of the top cover of the present invention;
FIG. 9 is a schematic view of the structure of the air deflection plate of the roof dome section of the present invention;
FIG. 10 is a schematic view showing the installation state of the whole structure of the lower cabin part of the invention;
FIG. 11 is a cross-sectional view taken along the direction E-E in FIG. 10;
FIG. 12 is a schematic view of the inner surface structure of the bottom shell of the lower tank body of the present invention;
FIG. 13 is a schematic diagram showing the positional relationship between a heat dissipating unit of a lower cabin and a heat dissipating dust screen of a fan and a heat dissipating dust screen of an air outlet of a top cover;
FIG. 14 is a top view of a lower shell heat sink of the present invention;
FIG. 15 is a schematic view of the structure of the lower cabin air deflector of the present invention;
FIG. 16 is a schematic view of the waterproof ring structure of the lower cabin equipment chamber of the invention;
FIG. 17 is a schematic diagram of a cross-sectional structure of a waterproof ring of a lower tank device cavity of the invention;
fig. 18 is a schematic view of a waterproof ring structure of a horn according to the present invention;
FIG. 19 is a schematic view showing the structural mounting of the inner surface of the upper shell of the lower hull of the present invention;
fig. 20 is a schematic view of the overall structure of the unmanned aerial vehicle of the present invention.
Reference numerals:
1. a top cover part; 11. a top cover; 111. a top cover reinforcing rib; 112. the top cover heat dissipation air inlet; 113. the top cover is waterproof; 114. a top cover explosion flash lamp mounting part; 115. a top cover outlet dust screen mounting port; 116. a top cover waterproof seal groove; 117. a top cover heat radiation plate connecting part; 118. a top cover mounting part; 12. a top cover fan unit; 13. a top cover burst lamp unit; 14. a top cover fan radiating dust screen; 141. a top cover fan radiating dust screen mounting hole; 15. a top cover heat dissipation plate; 151. an air outlet of the top cover heat dissipation plate; 152. waterproof seal groove of top cover heat dissipation plate; 153. a top cover wind guiding strip unit; 154. a top cover heat radiation plate mounting part; 16. a top cover air deflector; 161. the top cover air deflector explodes the flash lamp mounting hole; 162. an outlet mounting hole of the top cover air deflector; 163. an inlet mounting groove of the top cover air deflector; 17. a top cover air outlet heat dissipation dustproof net; 18. waterproof sealing ring of top cover heat dissipation plate; 19. a power button; 191. a waterproof pad for the power key; 192. a power key support;
2. A middle shell portion; 21. an inner clamping part at the upper end of the middle shell;
3. a lower cabin body; 31. a bottom case; 311. a bottom shell explosion flash lamp mounting part; 312. an air inlet part of the bottom shell; 313. an air outlet of the bottom shell; 314. a bottom shell arm outer mounting port; 315. a clamping table part in the bottom shell; 316. a bottom shell equipment compartment reinforcing rib; 317. bottom shell cooling plate reinforcing ribs; 318. a bottom shell heat radiation plate mounting part; 319. a bottom shell mounting part; 3110. a bottom case accessory mounting portion; 3111. a bottom shell fan radiating dust screen mounting part; 3112. drain holes of the bottom shell; 3113. a mounting port in the bottom shell arm; 3114. a bottom shell air outlet heat dissipation dust screen mounting part; 32. a lower cabin heat dissipation assembly; 321. a lower cabin cooling plate; 3211. the lower cabin body heat-dissipation air-guiding strip sub-unit; 3212. a lower cabin heat-dissipating plate waterproof groove; 3213. a bottom shell mounting part of the lower cabin heat dissipation plate; 3214. a lower cabin heat dissipation plate air deflector mounting part; 322. a lower cabin air deflector; 3221. a lower cabin air guide upper plate; 3222. a lower cabin air guide side plate; 3223. a lower cabin explosion flash lamp mounting part; 3224. a lower cabin air deflector positioning part; 323. a lower cabin heat dissipation power unit; 3231. a lower cabin cooling fan; 3232. a lower cabin cooling fan mounting plate; 324. a lower cabin cooling fan cooling dust screen; 325. a heat-dissipation dustproof net at the air outlet of the lower cabin body; 33. an upper housing assembly; 331. an upper housing; 3311. an upper shell outer clamping table part; 3312. an upper case mounting part; 3313. a reinforcing rib of the upper shell equipment compartment; 33131. a reinforcing rib inserting part of the upper shell equipment compartment; 3314. an outer mounting port of the upper shell arm; 3315. an upper case device mounting part; 3316. an installation opening is formed in the upper shell arm; 332. an equipment module; 34. a lower cabin explosion lamp assembly; 35. a bottom shell accessory; 361. a waterproof ring of a lower cabin equipment cavity; 3611. a straight line portion; 3612. a collar portion; 3613. the waterproof strip is convex; 362. waterproof rings of bottom shell radiating fins; 363. a horn waterproof ring; 3631. an inner clamping part of the horn waterproof ring; 3632. the outer clamping part of the waterproof ring of the horn;
41. A waterproof strip unit is arranged; 42. a lower waterproof strip unit;
51. a top cover heat dissipation cavity; 52. a lower cabin heat dissipation cavity; 53. an equipment compartment; 54. the waterproof strip bottom shell is arranged at the installation position; 55. the waterproof strip upper shell is arranged at the installation position;
6. a horn; 7. a rotor wing.
Detailed Description
The following detailed description of preferred embodiments of the invention is made in connection with the accompanying drawings, which form a part hereof, and together with the description of the embodiments of the invention, are used to explain the principles of the invention and are not intended to limit the scope of the invention.
The technical scheme of the present invention is described in more detail with reference to fig. 1 to 20:
the present embodiment defines: the vertical upward direction of the top cover 11 is the upper direction, and the vertical downward direction of the bottom shell 31 is the lower direction in the landing state of the unmanned aerial vehicle; the direction of the air inlet end of the cabin part of the unmanned aerial vehicle is the front end, and the air outlet end is the rear end; the waterproof fastener is composed of the screw rainproof plug, the fastening screw and the rainproof gasket.
The unmanned aerial vehicle body of the embodiment 1 comprises a cabin part; the cabin part comprises an air inlet, an air outlet, a heat dissipation unit and a waterproof unit; the heat radiation unit comprises a heat radiation plate and an air deflector; the heat dissipation plate is provided with an air guide strip subunit and a heat dissipation plate waterproof sealing groove; the air deflector is buckled on the air guiding strip subunit and surrounds a heat dissipation cavity with the heat dissipation plate; the waterproof unit comprises a heat-dissipating plate waterproof sealing ring; the heat dissipation plate waterproof sealing groove is used for installing the heat dissipation plate waterproof sealing ring; the waterproof sealing ring of the radiating cavity radiating plate can seal and isolate the radiating cavity, so that the radiating cavity becomes an independent radiating air channel in the cabin part; the air guide strip subunit comprises an air guide strip; the projection vertexes of the plurality of air guide strips close to one end of the air inlet form an air inlet end curve, the curve is bent towards the side direction of the air inlet, and the radius of curvature of any projection vertex on the curve is larger than the distance from the center of the air inlet to any projection vertex, so that one end of the plurality of air guide strips close to the air inlet uniformly bears wind power; namely, the air guide strip on the air inlet side is firstly subjected to partial deflection at one end, close to the air inlet, of the air guide strip, and the front end of the deflected air guide strip is parallel to the air inlet direction.
The unmanned aerial vehicle body of the present embodiment may include 1 or more cabin parts.
Example 1
Unmanned aerial vehicle fuselage.
As shown in figure 1 of the drawings,
the unmanned aerial vehicle body according to embodiment 1 includes 3 cabin parts, namely a top cover part 1, a middle shell part 2 and a lower cabin part 3 which are hermetically connected in this order. Electronic components which need waterproof and heat dissipation are arranged inside the top cover part 1, the middle shell part 2 and the lower cabin body part 3, and various keys or peripheral interfaces are arranged outside the top cover part 1, the middle shell part 2 and the lower cabin body part 3.
In this embodiment 1, an upper bead unit 41 is provided between the top cover portion 1 and the middle shell portion 2, and a lower bead unit 42 is provided between the middle shell portion 2 and the lower cabin portion 3, for sealing-connecting the top cover portion 1, the middle shell portion 2, and the lower cabin portion 3. The keys or the peripheral interfaces of various external installation are limited by adopting a limiting structure and the double faced adhesive tape is bonded, so that the installation parts are ensured to be stable and stable in position and the installation part is good in waterproof sealing performance.
The top cover portion 1 and the lower cabin body portion 3 include respective heat radiating members including a heat radiating unit and a heat radiating power unit, respectively.
The heat radiation unit of this embodiment 1 includes a heat radiation plate and an air deflector; the heat dissipation plate is provided with an air guide strip subunit and a heat dissipation plate waterproof sealing groove; the air deflector is buckled on the air guiding strip subunit and surrounds the heat dissipation plate to form a heat dissipation cavity; the waterproof sealing groove of the radiating plate is used for installing the waterproof sealing ring of the radiating plate, and the waterproof sealing ring of the radiating plate can seal and isolate the radiating cavity, so that the radiating cavity becomes an independent radiating air channel in the cabin part.
The heat dissipation power unit includes power for supplying air intake required for heat dissipation, and the heat dissipation power unit of embodiment 1 includes a fan.
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.
The air guide strip subunit comprises air guide strips, and a heat dissipation channel is formed between adjacent air guide strips; the front projection vertex connecting line of each air guide strip is an air inlet end curve; the center of the curve at the air inlet end deviates from the center of the air inlet; the distance between the front ends of the adjacent wind guide strips is the largest at the position of maximum wind inlet. The center of the curve at the air inlet end deviates from the center of the air inlet, and the maximum air inlet position is obtained through fluid mechanics simulation calculation, and the boundary conditions of the fluid mechanics simulation calculation at least comprise structural parameters and dynamic parameters.
The heat radiation and waterproofing structure according to embodiment 1 is focused on the top cover portion 1 and the lower cabin body portion 3.
First, the technical solution of the roof portion 1 will be described with reference to fig. 3 to 9:
the top cover part 1 includes a top cover assembly, a top cover heat dissipation assembly, and a top cover waterproof assembly. Wherein, the major structure of top cap portion 1 is top cap 11, and top cap cooling module includes the heat dissipation unit of top cap portion 1, and top cap waterproofing subassembly includes top cap heating panel waterproof seal 18.
As shown in fig. 3, the heat radiating unit of the top cover heat radiating assembly includes a top cover heat radiating plate 15 and a top cover air deflector 16; the middle part of the top cover heat dissipation plate 15 is provided with a top cover air guide strip sub-unit 153, and the periphery of the top cover heat dissipation plate 15 is provided with a top cover heat dissipation plate waterproof seal groove 152; the top cover air deflector 16 is fastened to the top cover air guide strip subunit 153 to form a top cover heat dissipation cavity 51.
The main structure of the top cover part 1 is that the middle part of the inner surface of the top cover 11 is provided with a top cover reinforcing rib 111; the top cover reinforcing ribs 111 are buckled in the top cover heat dissipation plate waterproof sealing groove 152; the heat-dissipating plate waterproof seal ring provided between the top-cover reinforcing ribs 111 and the top-cover heat-dissipating plate waterproof seal groove 152 is a top-cover heat-dissipating plate waterproof seal ring 18.
Referring to fig. 3 and 6, the top cover 11 is a composite shell with an auxiliary structure, and a top cover heat dissipation air inlet 112, a top cover explosion flash lamp mounting portion 114 and a top cover outlet dust screen mounting opening 115 are sequentially formed in the thin shell of the top cover 11. The top cover 11 is provided with a plurality of extended function module interfaces at its periphery.
The middle part of the inner surface of the top cover 11 is provided with a top cover reinforcing rib 111, and the periphery of the inner surface of the top cover 11 is provided with a top cover waterproof sealing unit, a top cover heat dissipation plate connecting part 117 and a top cover mounting part 118. The top cover heat sink connecting portion 117 has a screw structure, and the top cover mounting portion 118 has a via hole structure.
As shown in fig. 6, 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 of a groove-shaped structure and is arranged at the periphery of the rear ends of the two sides of the inner surface of the top cover 11, and the outer clamping structure of the top cover waterproof outer clamping groove 113 is arranged at the periphery of the front end of the inner surface of the top cover 11.
As shown in fig. 1, the upper end surface periphery of the middle case part 2 is provided with a structure matching with the top cover waterproof sealing unit. Specifically, the upper end surface of the middle shell portion 2 is provided with a middle shell upper end inner engaging portion 21.
The top cover 11 is hermetically connected to the middle case part 2 downward by the upper waterproof strip unit 41.
As shown in fig. 6 and fig. 6, the top cover waterproof seal groove 116 provided around the inner surface of the top cover 11 can form a through groove at both sides and the rear end, and the rear end of the inner surface of the top cover 1 is divided into a plurality of sections by the mounting structure of the side mounting accessory 001, and thus, the upper waterproof strip unit 41 includes 1 longer side rear waterproof strip and a plurality of front end side waterproof strips.
When the top cover 11 and the middle shell part 2 are installed, the longer side rear waterproof strip is adhered and arranged on the bottom of the groove in the top cover waterproof sealing groove 116, and the inner clamping part 21 at the upper end of the middle shell part 2 is inserted into the top cover waterproof sealing groove 116 at the position and extrudes the side rear waterproof strip in the up-down direction; the front waterproof strips are adhered to the inner clamping part 21 at the upper end of the middle shell at the front end of the middle shell part 2, the inner clamping part 21 at the upper end of the middle shell at the front end of the middle shell part 2 and the waterproof outer clamping groove 113 of the top cover 11 are mutually extruded left and right, and the front waterproof strips are limited at the combining part.
Preferably, the fastener connecting the middle case portion 2 and the top cover 11 is a waterproof fastener, and a waterproof structure can be formed at the connection.
The top cover 11 and the middle shell 2 are stable in installation and sealing installation structure and good in waterproof performance.
In addition, a plurality of top mounting accessories and side mounting accessories are connected to the upper portion of the top cover 11. The top mounted accessory includes a broadcast module and power key 19, etc., and the side mounted accessory includes a plurality of front decorative pieces and side decorative pieces. The installation of any part in the top installation accessory and the side installation accessory is limited by adopting a limiting structure and a double-sided adhesive tape is adopted for bonding, so that the installation parts are ensured to be stable and stable in position, the upper waterproof sealing is carried out from the inner surface and the outer surface, and the waterproof sealing performance of the installation part is ensured to be good. Examples are as follows:
as shown in fig. 3, the top cover 11 is further provided with a power key installation position, and the power key installation position is sequentially connected with a power key 19, a power key waterproof pad 191 and a power key support 192.
Specifically, in this embodiment 1, the power key 19 is disposed on the power key mounting position of the top cover 1, the power key 19 is provided with the power key waterproof pad 191 of a ring sleeve, the power key support 192 is pressed and fixed on the power key waterproof pad 191, and the key screw sequentially penetrates through the power key support 192, the power key waterproof pad 191 and the power key 19 from outside to inside to fasten the power key 19 on the top cover 1. The waterproof structure of the power key support 192 and the power key waterproof pad 191 can better ensure the waterproof effect of the power key 19.
Further preferably, the power key waterproof pad 191 is made of a silica gel material with random design, specifically a ring-sleeve type silica gel waterproof pad.
All other parts are arranged on the invention structure of the embodiment 1, and the mode of bonding the limiting structure and the double-sided adhesive tape is applicable. The connection mode not only can prevent the falling of the installation part, but also can ensure the integral waterproof function of the unmanned cabin body.
A top cover heat radiation assembly is installed inside the top cover 11. The heat radiation unit top cover heat radiation plate 15 and the top cover air deflector 16 of the top cover part 1 included in the top cover heat radiation assembly further include a top cover fan unit 12, a top cover fan heat radiation dust screen 14 and a top cover air outlet heat radiation dust screen 17.
The top cover fan unit 12 is disposed between the top cover 11 and the top cover heat dissipation plate 15, is connected to the top cover 11, and is specifically connected to the top cover heat dissipation fan center M1.
The top cover fan unit 12 includes a top cover fan and a top cover fan mounting body, and the top cover fan mounting body are fixedly connected into a whole. The top cover fan can implement forced convection to realize continuous heat dissipation of the high-heating-value circuit.
Specifically, the top cover 11 has a top cover fan unit mounting portion with a screw hole structure on the inner surface thereof at the top cover heat dissipation air inlet 112. The fan top cover fan installation body is provided with a fan top cover connection part matched with the position of the top cover fan unit installation part, and the fan top cover connection part is specifically a via hole structure on the top cover fan installation body. The top cover 11 and the top cover fan unit 12 are fixedly connected to the center M1 of the top cover radiator fan by waterproof fasteners, and are also the center positions of the top cover fans. The central M1 point of the top cover cooling fan is a concentrated heating part such as an unmanned aerial vehicle vision main board. The rotation of the top cover fan can take away a large amount of hot fluid.
The top cover fan heat dissipation dust screen 14 is connected to the inner surface of the top cover heat dissipation air inlet 112, and top cover fan dust screen mounting holes are formed in the periphery of the top cover fan heat dissipation dust screen 14. The 2 top cap air outlet heat dissipation dust screen 17 symmetry sets up, connects respectively in 2 top cap export dust screen installing ports 115 departments of top cap 11, and top cap air outlet heat dissipation dust screen 17 periphery is provided with top cap air outlet heat dissipation dust screen mounting hole.
The top cover fan heat dissipation dust screen 14 is connected to the inner surface of the top cover 11 through interference fit.
A top cover air deflector 16 and a top cover heat dissipation plate 15 are provided in this order on the inner surface of the top cover 11. The heat radiation unit formed by the top cover air deflector 16 and the top cover heat radiation plate 15 is a main functional component of the top cover heat radiation assembly.
Wherein, top cap 11 is connected with top cap heating panel 15 periphery, and top cap aviation baffle 16 is connected at top cap heating panel 15 middle part. The connection mode has good effect of isolating external heat from entering for the electronic components with important functions inside.
As shown in fig. 5, a top cover heat dissipation chamber 51 with good fluidity is also formed between the top cover air deflector 16 and the top cover heat dissipation plate 15.
As shown in fig. 7 and 8, a top cover air guiding strip subunit 153 is arranged in the middle of the top cover heat dissipation plate 15, 2 top cover heat dissipation plate air outlets 151 are symmetrically arranged on two sides of the far end of the top cover heat dissipation plate 15, and a top cover heat dissipation plate waterproof seal groove 152 and a top cover heat dissipation plate mounting part 154 are also arranged on the periphery of the top cover heat dissipation plate 15; the top cover air deflector 16 comprises a top cover air deflector upper plate and a top cover air deflector side plate, wherein the inner plate surface of the top cover air deflector upper plate is buckled on the upper end surface of the top cover air deflector strip subunit 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 strip of the top cover air deflector strip subunit 153.
A top cover heat dissipation plate waterproof sealing ring 18 is arranged in the top cover heat dissipation plate waterproof sealing groove 152, and the top cover heat dissipation plate waterproof sealing ring 18 is adhered to the bottom of the top cover heat dissipation plate waterproof sealing groove 152. The top cover reinforcing ribs 111 of the top cover 11 are limited in the top cover heat dissipation plate waterproof sealing groove 152 by extruding the top cover heat dissipation plate waterproof sealing ring 18. The top cover heat radiation plate connection portion 117 of the top cover 11 is matched with the top cover heat radiation plate mounting portion 154 of the top cover heat radiation plate 15, and the top cover heat radiation plate mounting portion 154 has a via hole structure. The top cover heat dissipation plate 15 and the top cover 11 are firmly connected into a whole after being pressed by the fastener arranged at the installation part and the waterproof sealing ring 18 of the top cover heat dissipation plate.
Preferably, the waterproof sealing ring 18 of the top cover heat dissipation plate adopts silica gel foam. The silica gel foam has the advantages of easy manufacture, high compressibility and redundant bonding of the ends.
The top cover air guiding strip sub-unit 153 is a main functional structure on the top cover heat dissipation plate 15, the top cover air guiding strip sub-unit 153 comprises a plurality of air guiding strips, and the top cover air guiding strip sub-unit 153 is arranged in a Y-shaped structure.
Two upward branch ends in the Y shape of the top cover air guide strip subunit 153, namely branch ends of the Y-shaped structure, are air guide strip air outlet ends which respectively face the top cover heat dissipation plate air outlet 151; the converging end in the Y-shape of the top cover air guiding strip subunit 153 is an air guiding strip air inlet end, and the air guiding strip air inlet end of the top cover air guiding strip subunit 153 faces the top cover heat dissipation air inlet 112.
The Y-shaped arrangement structure of the top cover air guiding strip subunit 153 is a mirror symmetry structure at the middle part and the rear end, but the arrangement of the air guiding strips of the top cover air guiding strip subunit 153 at the air inlet end is not completely symmetrical, and the top cover air guiding strips at the air inlet end are arranged according to the direction of incoming air through fluid mechanics simulation calculation, that is, the air inlet end of each top cover air guiding strip is specifically designed, so that the air inlet ends of each top cover air guiding strip are different in length, deflection angle and air inlet end interval of adjacent top cover air guiding strips.
Specifically, the top cover fan rotates anticlockwise by taking the center M1 point of the top cover cooling fan as the center of a circle, and the air inlet ends of the top cover air guide strips are partially inclined.
As shown in fig. 8, the air inlet end of the top cover air guide strip in this embodiment 1 is partially inclined to the side with bilateral symmetry with respect to the center line of the top cover heat dissipation plate 15, so that the top cover air guide heat dissipation channels formed by the adjacent top cover air guide strips are parallel to the trend of the air intake as much as possible at the position with the maximum air intake.
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 connecting line of the top points of projection lines of the air inlet ends of each top cover air guide strip forms a top cover air guide strip sub-unit air inlet end curve BCD taking the center M2 of the top cover air guide strip sub-unit air inlet end curve as the center of a circle, two ends of the top cover air guide strip sub-unit air inlet end curve BCD are a point B and a point D, and a point C is arranged in the middle.
In particular, in this embodiment 1, the air inlet end curve BCD of the top cover air guiding strip subunit is an arc line, and the center of the air inlet end curve BCD of the top cover air guiding strip subunit, that is, the center M2 of the air inlet end curve of the top cover air guiding strip subunit, deviates from the center M1 of the top cover cooling fan in the front-rear direction toward the front end of the top cover 1, deviates from the top cover cooling fan in the left-right direction toward the B point direction of the top cover air guiding strip subunit 153 that receives the wind force first after the top cover fan is started.
As shown in fig. 8, the top cover wind guiding strip subunit 153 of the embodiment 1 is located at the end of the point B on one side where the top cover fan receives the wind force first after being started, and the wind guiding strip capable of receiving the maximum wind volume all the time during ventilation is located around the point C, and the end of the point D on the other side where the top cover fan receives the wind force last.
Specifically, through hydrodynamic simulation calculation, the arrangement of the curve BCD at the air inlet end of the top cover air guide strip subunit enables one end, close to the air inlet, of the plurality of air guide strips to bear wind power in an balanced mode, and meanwhile the ventilation quantity distribution of each top cover heat dissipation air duct is optimized.
Specifically, through fluid mechanics simulation calculation, the point C is the intersection point of the tangent line of the outer edge of the fan and the curve BCD of the air inlet end of the top cover air guiding strip subunit, and the tangent line is parallel to the connecting line of the point M1 of the top cover cooling fan and the point M2 of the curve of the air inlet end of the top cover air guiding strip subunit.
The top cover wind guiding strips of this embodiment 1 have the greatest spacing at point C, and the spacing between the ends of the top cover wind guiding strips on both sides gradually decreases. This arrangement allows the hot air from the top cover fan to flow into the top cover heat dissipation chamber 51 in an optimal manner.
The inclined air inlet ends of the top cover air guide strips of the top cover air guide strip sub-unit 153 are in parallel arrangement in the middle through arc transition, and two symmetrical branches of a Y-shaped structure are formed at the air outlet ends of the top cover air guide strips and respectively face the air outlet 151 of the top cover heat dissipation plate.
The part of the front end of each top cover wind guiding strip deflects towards the wind inlet direction.
Preferably, as shown in fig. 8, the air inlet ends of the top cover heat dissipation and air guide strip subunit 153 of this embodiment 1 will uniformly reach the position of the dashed line L, and are also mirror-symmetrical, without considering that the length of the air inlet ends is limited by the air inlet end arrangement arc BCD of the top cover air guide strip; an example in which a pair of wind-guiding strips arrive at the dashed line L as mirror symmetry is shown in fig. 8; the design ensures that the top cover air guide strip is positioned at the C point and has the maximum air guide quantity, and the manufacturing process is simple.
The top cover air deflector 16 is used for rectifying the air channel and optimizing the hot air evacuation channel.
As shown in fig. 9, the top cover air guide plate 16 is provided with a top cover air guide plate explosion flash mounting hole 161, a top cover air guide plate outlet mounting hole 162 and a top cover air guide plate inlet mounting groove 163.
The top cover fan heat dissipation and dust prevention net 14 is provided with a top cover fan heat dissipation and dust prevention net mounting hole 141 matched with the top cover air deflector inlet mounting groove 163, and the top cover air outlet heat dissipation and dust prevention net 17 is provided with a top cover air outlet heat dissipation and dust prevention net mounting hole matched with the top cover air deflector outlet mounting hole 162. The two ends of the top cover air deflector 16 are respectively connected with the top cover fan heat dissipation dustproof net 14 and the top cover air outlet heat dissipation dustproof net 17.
The top cover air deflector 16 is provided with bent plates at two symmetrical branches forming a Y-shaped structure at the air outlet end of the top cover air deflector for overlapping the top cover fan heat dissipation dust screen 14. The bending plate of the top cover air deflector 16 is designed according to the shape of the edge of the top cover fan heat dissipation dust screen 14.
The top cover explosion flash unit 13 is mounted on the top cover explosion flash mounting part 114 of the top cover 11, and the top cover explosion flash unit 13 comprises a top cover explosion flash base and a top cover explosion flash. The top cover air deflector explosion flash lamp mounting holes 161 are reserved positions on the top cover air deflector 16 for mounting explosion flash lamp bases on the inner surface of the top cover 11. The explosion flash lamp base is provided with an explosion flash lamp power supply device, and is an important heat source.
As shown in fig. 5, the top cover air deflector 16 and the top cover heat dissipation plate 15 are buckled to form a complete and closed top cover heat dissipation cavity 51 at the air outlet end of the air guide strip of the top cover heat dissipation plate air outlet 151 for conveying hot air from the top cover fan, so that the top cover fan is used for directionally transmitting heat dissipation of core heat sources such as a visual support plate and heat dissipation of the top cover explosion flash power supply device, damage of waste heat to electronic components in the unmanned aerial vehicle body is avoided, and heat dissipation efficiency is high.
Meanwhile, the heat-dissipating dust screen 17 of the top cover air outlet also has the function of outwards dispersing heat in the top cover 11. Rainwater entering from the top cover air outlet heat dissipation dust screen 17 can also be discharged through the top cover heat dissipation plate air outlet 151, and the structure integrates the functions of water prevention and heat dissipation.
The top cover air outlet heat dissipation dust screen 17 and the top cover fan heat dissipation dust screen 14 can both prevent large particles from entering the top cover 1.
In addition, the top cover air deflector 16 of embodiment 1 is not only fastened to the top cover heat dissipation plate 15, but also has both ends fixedly connected to the top cover fan heat dissipation dust screen 14 and the top cover air outlet heat dissipation dust screen 17. The arrangement enhances the integration of the heat dissipation and waterproof structure at the top of the unmanned aerial vehicle body, and reduces the vibration caused by fans and the like. The arrangement reduces the influence of temperature and vibration on the working performance of the electronic components.
In a specific application, the top cover air deflector 16 is buckled behind the top cover heat dissipation plate 15, and the top cover fan heat dissipation dust screen 14 and the top cover air outlet heat dissipation dust screen 17 are not fixedly connected at two ends, so that the processing and installation difficulty is reduced.
Next, with reference to fig. 10 to 19, a technical solution of the lower cabin 3 is described:
as shown in fig. 10, the lower tank body 3 of the present embodiment 1 includes a bottom case assembly, an upper case assembly 33, and a lower tank waterproof assembly.
The lower cabin heat dissipation assembly 32 is arranged in the bottom shell assembly, the lower cabin heat dissipation assembly 32 comprises a heat dissipation unit of the lower cabin part 3, and the heat dissipation unit of the lower cabin part 3 comprises 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 cooling cavity 52 faces the air inlet of the lower cabin, and the rear end of the cabin cooling cavity 52 faces the air outlet of the lower cabin.
The bottom case assembly includes a bottom case 31, and the upper case assembly 33 includes an upper case 331. The bottom shell component and the upper shell component 33 are fastened and connected after being buckled, and a lower cabin of the unmanned aerial vehicle is formed inside the bottom shell component; the lower cabin body radiating component 32 is connected to the unmanned aerial vehicle lower cabin inside, and lower cabin horn external connection portion is formed to unmanned aerial vehicle lower cabin periphery for connect the horn.
As shown in connection with fig. 10 and 11, the lower tank waterproof assembly includes a lower tank equipment chamber waterproof ring 361, a bottom case fin waterproof ring 362, and a horn waterproof ring 363.
As shown in fig. 18, the horn waterproof ring 363 has a loop structure. Specifically, the horn waterproof ring 363 has a ring groove structure with two sidewall surfaces, which are respectively an inner horn waterproof ring clamping portion 3631 and an outer horn waterproof ring clamping portion 3632. In the mounted state, the inner clamping part 3631 of the horn waterproof ring is positioned on the inner wall surface of the outer connecting part of the lower cabin horn of the embodiment 1, and the outer clamping part 3632 of the horn waterproof ring is positioned on the outer wall surface of the outer connecting part of the lower cabin horn of the embodiment 1.
The horn waterproof ring 363 can effectively block external rainwater and other liquid motor arm joints from entering the lower cabin of the unmanned aerial vehicle in embodiment 1, prevent rainwater and other rainwater from further entering the equipment cabin 53, and protect electronic components from damage.
Specifically, the waterproof ring 361 of the lower cabin equipment cavity and the waterproof ring 362 of the bottom shell cooling fin are arranged inside the lower cabin of the unmanned aerial vehicle. The lower cabin equipment chamber waterproof ring 361 is provided between the bottom case 31 and the upper case 331, and the bottom case fin waterproof ring 362 is provided between the lower cabin heat dissipation plate 321 and the bottom case 31.
As shown in fig. 11, 12 and 19, the outer periphery of the mounting surface of the bottom shell equipment compartment stiffener 316 of this embodiment 1 is provided with an outer edge of half a wall thickness, the inner periphery of the mounting surface of the upper shell equipment compartment stiffener 3313 is provided with an inner edge of half a wall thickness, and after the outer edge of the bottom shell equipment compartment stiffener 316 is fastened with the inner edge of the upper shell equipment compartment stiffener 3313, the equipment compartment 53 is formed inside the enclosure of the bottom shell equipment compartment stiffener 316 and the upper shell equipment compartment stiffener 3313.
As shown in fig. 16, in particular, a lower cabin equipment chamber waterproof ring 361 is provided at the equipment cabin 53 joint surface and the lower cabin horn inner mounting portion.
Specifically, the junction of the bottom shell equipment compartment stiffener 316 and the upper shell equipment compartment stiffener 3313 forms an equipment compartment 53 junction surface; the junction surface discontinuity of the equipment cabin 53 is formed by the bottom shell 31 and the upper shell 331 to form a lower cabin horn inner mounting part.
The lower cabin equipment cavity waterproof ring 361 is in a loop type. The lower cabin equipment cavity waterproof ring 361 comprises a linear part 3611 and a loop part 3612, the linear part 3611 of the lower cabin equipment cavity waterproof ring 361 is arranged on the joint surface of the equipment cabin 53, and the outer ring of the loop part 3612 of the lower cabin equipment cavity waterproof ring 361 is arranged on the inner mounting part of the lower cabin horn.
The lower cabin equipment chamber waterproof ring 361 is a waterproof layer of the middle portion of the lower cabin 3.
As shown in fig. 17, the cross section of the lower cabin equipment chamber waterproof ring 361 of the annular sleeve type is S-shaped to form a waterproof bottom shell mounting position 54 and a waterproof upper shell mounting position 55, and the upper shell equipment chamber reinforcing rib 3313 of the upper shell 331 and the bottom shell equipment chamber reinforcing rib 316 of the outer connecting bottom shell 31 are connected in a semi-surrounding mode.
Preferably, the top surface of the upper shell equipment compartment stiffener 3313 is provided with an upper shell equipment compartment stiffener plugging portion 33131. The upper shell equipment compartment stiffener plugging portion 33131 is provided with an upwardly narrowing draft angle so as to be able to be quickly inserted into the waterproof strip upper shell mounting location 55 to quickly and completely mount the lower shell equipment compartment waterproof ring 361 on the upper shell equipment compartment stiffener 3313.
Preferably, two sides of the lower cabin equipment cavity waterproof ring 361 at the middle parts of the waterproof bottom shell installation position 54 and the waterproof upper shell installation position 55, that is, two opposite sides of the clamping part at the middle part of the S-shaped structure of the lower cabin equipment cavity waterproof ring 361 are provided with a plurality of waterproof protrusions 3613, so that the waterproof effect is further improved, the elastic deformation is increased, the vibration transmission between the bottom shell 31 and the upper shell 331 is reduced, and the influence of the vibration on the safe operation of electronic components of the flight control equipment is reduced.
The main structure of the unmanned aerial vehicle lower cabin with the heat dissipation waterproof structure of this embodiment 1 is the bottom shell 31 on the bottom shell assembly and the upper shell 331 of the upper shell assembly 33.
Referring to fig. 12 and 19, the bottom case 31 is provided with a bottom case inner clamping portion 315, a bottom case equipment compartment reinforcing rib 316, a bottom case arm outer mounting opening 314, and a bottom case arm inner mounting opening 3113.
The bottom shell 31 and the upper shell 331 are connected by waterproof fasteners to form a lower cabin outer joint portion formed by the bottom shell inner clamping table portion 315 and the upper shell outer clamping table portion 3311, an equipment cabin joint portion of a lower cabin body formed by the bottom shell equipment cabin reinforcing ribs 316 and the upper shell equipment cabin reinforcing ribs 3313, a lower cabin horn outer mounting portion formed by the bottom shell horn outer mounting opening 314 and the upper shell horn outer mounting opening 3314, and a horn inner mounting portion formed by the bottom shell horn inner mounting opening 3113 and the upper shell horn inner mounting opening 3316.
The horn waterproof ring 363 is connected to the outer mounting part of the lower cabin horn. The outer combination part of the lower cabin body and the horn waterproof ring 363 form the outermost waterproof layer of the lower cabin body 3.
The inner space of the equipment cabin joint part is an equipment cabin.
Fig. 10 is a schematic view showing an installation state of the whole structure of the lower cabin body of the unmanned aerial vehicle of this embodiment 1.
As shown in fig. 19, the main structure of the upper case assembly 33 is an upper case 331. Corresponding to the bottom shell 31, 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 which are matched with each other are arranged on the upper shell 331. Wherein the upper shell equipment compartment stiffener 3313 is provided with an upper shell equipment compartment stiffener plugging portion 33131.
The upper case assembly 33 further includes an equipment module 332, the equipment module 332 being a main heat generating body, connected to the upper case 331 at an upper case equipment mounting portion 3315 by fasteners.
As shown in fig. 12, the bottom shell 31 is a composite shell of a thin shell and an auxiliary structure, and a bottom shell air inlet 312, a bottom shell flash lamp mounting 311 and a bottom shell air outlet 313 are sequentially provided on the thin shell of the bottom shell 31 from front to back. The bottom shell air inlet portion 312 and the bottom shell flash lamp mounting portion 311 are arranged on a middle branching line of the whole structure of the bottom shell 31, and the 2 bottom shell air outlets 313 are arranged in a mirror symmetry mode with the middle branching line of the whole structure of the bottom shell 31.
As shown in fig. 10 and 12, a plurality of bottom shell fan heat dissipation and dust prevention net mounting portions 3111 are circumferentially arranged on the inner surface of the bottom shell 31 around the center of the bottom shell air inlet portion 312, for connecting with the lower cabin heat dissipation and dust prevention net 324.
Preferably, the bottom shell fan heat dissipation and dust prevention net mounting part 3111 is a clamping column, the lower cabin heat dissipation and dust prevention net 324 is a steel net, and a through hole structure is arranged at a corresponding position on the lower cabin heat dissipation and dust prevention net 324 and is positioned on the bottom shell 31 by adopting a hot melting or pressing process. The lower cabin body cooling fan cooling dust screen 324 is in interference fit with the plurality of bottom shell fan cooling dust screen mounting portions 3111 and is fixed by hot melting or pressing, so that the lower cabin body cooling fan cooling dust screen 324 is mounted quickly and integrated with the bottom shell 31. Therefore, the lower cabin heat radiation dust screen 324 is less likely to be affected by the rotating parts of the lower cabin heat radiation fan 3231 to generate shake.
As shown in fig. 11 and 13, a bottom case air outlet 313 is provided at its outer periphery with a bottom case air outlet heat dissipation dust screen mounting portion 3114. Is used for connecting the heat dissipation dustproof net 325 of the air outlet of the lower cabin body.
Preferably, the bottom shell air outlet heat dissipation dust screen mounting part 3114 is a clamping column; the lower cabin air outlet heat dissipation dustproof net 325 is a steel net; the lower cabin air outlet heat dissipation dust screen 325 is provided with a via hole structure at a corresponding position. The lower cabin air outlet heat dissipation dust screen 325 is positioned on the bottom shell 31 through a hot melt or press melt process. The lower cabin air outlet heat dissipation dustproof net 325 is in interference fit with the plurality of bottom shell air outlet heat dissipation dustproof net mounting parts 3114 and is fixed on the bottom shell 31 by hot melting or pressing, so that the lower cabin air outlet heat dissipation dustproof net 325 is fast to mount and is integrated with the bottom shell 31. Therefore, the lower cabin air outlet heat radiation dust screen 325 is not easily affected by the rotation of the parts of the lower cabin heat radiation fan 3231 and the operation of the flight control device to generate shake.
A bottom shell heat radiation plate reinforcing rib 317, a bottom shell equipment compartment reinforcing rib 316, and a bottom shell inner clamping table portion 315 are provided in this order from the center to the outside in the thin shell inner portion of the bottom shell 31.
Wherein, the bottom shell cooling plate reinforcing rib 317 and the bottom shell equipment compartment reinforcing rib 316 are in a closed loop structure, and the bottom shell air inlet 312, the bottom shell flash lamp mounting 311 and the bottom shell air outlet 313 are enclosed in the bottom shell cooling plate reinforcing rib 317. A plurality of bottom shell heat dissipation plate mounting portions 318 are provided on the inner surface of the bottom shell 31 around the outer periphery of the bottom shell heat dissipation plate ribs 317. Preferably, the bottom shell heat dissipation plate mounting portion 318 is a pylon structure with a via hole for connecting the lower cabin heat dissipation plate 321 by a waterproof fastener. The bottom shell equipment compartment stiffener 316 is further provided with a plurality of bottom shell inboard mounting openings 3113. In this embodiment 1, 4 symmetrical bottom shell arm inner mounting ports 3113 are provided.
Wherein, the inner clamping table portion 315 of the bottom shell is of a segmented structure, a plurality of outer mounting openings 314 of the bottom shell machine arm are further arranged at intervals of the inner clamping table portion 315 of the bottom shell, and the positions of the outer mounting openings 314 of the bottom shell machine arm correspond to the positions of the inner mounting openings 3113 of the bottom shell machine arm and are jointly used for connecting the machine arm.
Wherein, a bottom shell mounting portion 319 is provided at the inner surface periphery of the bottom shell 31 inside the bottom shell inner clamping portion 315 for connecting the upper housing 331 by a waterproof fastener. Preferably, the bottom housing mounting portion 319 is a post to a via.
The periphery of the bottom shell 31 is further provided with a plurality of circuit board connector expansion interfaces for externally connecting with an expansion function module. The interface waterproof plug cover of interference connection is arranged on the expansion interface of the circuit board connector, so that the circuit board connector can be waterproof and can be prevented from falling off.
As shown in fig. 10, a bottom case attachment fitting portion 3110 and a bottom case drain hole 3112 penetrating the case are further provided on the periphery of the bottom case 31. The bottom chassis accessory mounting portion 3110 is used to mount the bottom chassis accessory 35 including the key (the bottom chassis accessory 35 is not limited to that shown in fig. 10), and the bottom chassis accessory mounting portion 3110 is not limited to that shown in fig. 12.
The installation of any part in the bottom shell accessory 35, including the installation of the lower cabin body explosion lamp assembly 34, adopts a limiting structure to limit and a double-sided adhesive bonding mode to ensure that each installation part is stable and stable in position, and the waterproof sealing of the bottom shell 31 is carried out from the inner side and the outer side, so that the waterproof sealing performance of the installation part is good.
The lower pod explosion flash assembly 34 includes a high heat dissipation lower pod explosion flash.
A plurality of bottom case drain holes 3112 are provided at the periphery of the bottom case 31 for draining fluid such as rainwater entering the lower cabin of the unmanned aerial vehicle through the lower cabin cooling fan cooling dust screen 324 and the lower cabin air outlet cooling dust screen 325.
The lower cabin heat dissipation assembly 32 of the present embodiment 1 is installed inside the bottom chassis 31. The lower cabin heat dissipation assembly 32 includes a lower cabin heat dissipation plate 321, a lower cabin air deflector 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 mounted on the bottom case 31.
As shown in fig. 12, 13 and 14, the lower cabin heat dissipation power unit 323 is disposed between the bottom shell 31 and the lower cabin heat dissipation plate 321, and is connected to the lower cabin heat dissipation plate 321, specifically at the center of the corresponding bottom shell air intake portion 312, that is, at the point of the bottom shell heat dissipation fan center N1.
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 a whole.
Specifically, the lower cabin cooling fan mounting plate 3232 of this embodiment 1 is provided with mounting ears and mounting holes, and the surface of the lower cabin cooling plate 321 is provided with a bottom shell fan unit mounting portion having a screw hole structure at a point N1 corresponding to the bottom shell cooling fan center. The lower cabin heat dissipation power unit 323 is fixedly connected to the lower cabin heat dissipation plate 321 through a fastener. The position of the center N1 point of the bottom shell cooling fan corresponding to the position of the lower cabin cooling fan 3231 is a concentrated heating part of unmanned aerial vehicle flight control equipment. The lower cabin heat radiation fan 3231 rotates, and can take away a large amount of heated air in the equipment cabin 53.
The lower cabin cooling fan 3231 can perform forced convection to realize continuous heat dissipation of high heat generation circuits, components and parts.
The lower cabin heat dissipation cavity 52 and the top cover heat dissipation cavity 51 may have the same structure or different structures. The technical scheme of the lower cabin heat dissipation chamber 52 and the related structure of the embodiment 1 adopts a technical scheme different from the related structure of the top cover part 1, wherein the method for designing the fluid mechanics simulation calculation is consistent:
a lower cabin air deflector 322 and a lower cabin heat dissipation plate 321 are provided in this order on the inner surface of the bottom chassis 31. The lower cabin air deflector 322 and the lower cabin heat dissipation plate 321 constitute a heat dissipation unit of the lower cabin 3, and are main functional components of the lower cabin heat dissipation assembly 32.
As shown in fig. 11, the lower cabin heat dissipation plate 321 and the lower cabin air deflector 322 are fastened to form a lower cabin heat dissipation chamber 52.
As shown in fig. 13 and 14, a lower cabin heat dissipation air guide bar subunit 3211 is disposed in the middle of the lower surface of the lower cabin heat dissipation plate 321, an annular lower cabin heat dissipation plate waterproof groove 3212 is disposed around the lower cabin heat dissipation plate 321, a lower cabin heat dissipation plate bottom guide shell mounting portion 3213 is disposed on the periphery of the lower cabin heat dissipation plate waterproof groove 3212, and the lower cabin heat dissipation plate bottom guide shell mounting portion 3213 is used for fixedly connecting main functional components of the lower cabin heat dissipation assembly 32 to the bottom shell 31.
The lower cabin heat dissipation and air guide strip sub-unit 3211 is a main functional structure on the lower cabin heat dissipation plate 321, the lower cabin heat dissipation and air guide strip sub-unit 3211 comprises a plurality of lower cabin air guide strips, and the lower cabin heat dissipation and air guide strip sub-unit 3211 is integrally arranged in a Y-shaped structure.
Two upward branch ends in the Y shape of the lower cabin body heat radiation air guide strip subunit 3211, namely branch ends of the Y-shaped structure, are lower cabin body air guide air outlet ends which respectively face 2 bottom shell air outlets 313; the converging end in the Y-shape of the lower cabin heat radiation air guide strip subunit 3211 is a lower cabin air guide inlet end, which faces the bottom shell air inlet portion 312.
The Y-shaped arrangement structure of the lower cabin body heat dissipation and wind guide strip subunit 3211 is a mirror symmetry structure at the middle part and the rear end, while the local arrangement of the plurality of lower cabin body wind guide strips of the lower cabin body heat dissipation and wind guide strip subunit 3211 at the air inlet end is not an absolute symmetry structure, and the air inlet end structure of the plurality of lower cabin body wind guide strips is specifically designed through fluid mechanics simulation calculation according to the direction of incoming wind, so that the air inlet end of each lower cabin body wind guide strip is different in length, deflection angle and air inlet end interval of the adjacent lower cabin body wind guide strips.
Specifically, this embodiment 1 sets: the lower cabin cooling fan 3231 rotates clockwise around the center N1 of the bottom shell cooling fan, and the air inlet ends of the plurality of lower cabin air guide strips are partially inclined.
As shown in fig. 14, specifically, the air inlet end of the lower cabin air guiding strip is partially mirrored about the center line of the lower cabin heat dissipating plate 321 and is inclined to the center in bilateral symmetry, so that the lower cabin air guiding heat dissipating channel formed by the adjacent lower cabin air guiding strip is parallel to the trend of the air inlet as much as possible at the position with the maximum air inlet amount.
After each lower cabin air guide strip of the lower cabin air guide strip sub-unit 3211 is projected onto the plane of the lower cabin heat dissipation plate 321 where the lower cabin air guide strip sub-unit 3211 is located, the connecting line of the top points of projection lines of the air inlet ends of each lower cabin air guide strip forms a curve, and the arrangement is obtained through fluid mechanics simulation calculation, so that one end, close to the air inlet of the lower cabin, of each lower cabin air guide strip uniformly bears wind force, and meanwhile, the ventilation quantity distribution of each lower cabin heat dissipation air duct is optimized.
As shown in fig. 14, preferably, a curve formed by connecting the vertexes of projection lines of the air inlet ends of the air guide strips of each lower cabin body is arc-shaped. Specifically, the center of the arc FGH is disposed at the air inlet end 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 subunit, deviates toward the front end of the bottom shell 31 in the front-rear direction relative to the center N1 of the bottom shell cooling fan, and deviates toward the F point of the rear wind force borne by the lower cabin air guiding strip subunit 3211 in the left-right direction after the lower cabin cooling fan 3231 is started. The design ensures that the positions of the air inlet ends of the air guide strips of the lower cabin body are limited by the arrangement arc FGH of the air inlet ends of the air guide strips of the lower cabin body and have different lengths.
Preferably, the lower cabin heat dissipation channel of the lower cabin heat dissipation air conduction strip subunit 3211 which bears the back wind force first after the fan is started is positioned at the point F on one side, the lower cabin heat dissipation cavity always bears the maximum ventilation amount in the ventilation process is positioned at the point G, and the lower cabin heat dissipation channel which bears the back wind force last is positioned at the point H on the other side.
Specifically, the point G is the intersection point of the outer edge tangent line of the lower cabin cooling fan 3231 and the arc FGH arranged at the air inlet end of the lower cabin air guiding strip, and the tangent line is parallel to the line connecting the point N1 of the bottom shell cooling fan center and the point N2 of the curve center of the air inlet end of the lower cabin air guiding strip subunit.
The setting of the G point is the same as the setting of the C point.
Specifically, taking the lower half of the Y-shaped arrangement structure of the lower cabin heat dissipation and air conduction strip subunit 3211 in fig. 14 as an example, on the premise that the Y-shaped arrangement structure of the lower cabin heat dissipation and air conduction strip subunit 3211 is basically a mirror symmetry structure as a whole:
the lower cabin air guide strip is arranged on the central line of the Y-shaped arrangement structure, and is centered, the lower cabin air guide strip on one side of the air inlet is firstly subjected to local deflection relative to the middle of the lower cabin air guide strip on the other side, and the front end of the deflected lower cabin air guide strip is parallel to the air inlet direction.
As shown in fig. 14, through the fluid mechanics simulation calculation, the distances between the front ends of the plurality of lower cabin air guide strips of the lower half part of the Y-shaped arrangement structure of the lower cabin heat dissipation air guide strip subunit 3211 in the embodiment 1 are the largest at the G point, and the distances between the air inlet ends of the lower cabin air guide strips on both sides are gradually reduced. The design of the different air inlet end spacing of the adjacent lower cabin air guide strips optimizes the air flow efficiency in the lower cabin heat dissipation channel formed by the lower cabin air guide strips, so that the hot air sent out by the lower cabin heat dissipation fan 3231 quickly enters the lower cabin heat dissipation cavity 52 in an optimal flow mode.
The inclined air inlet ends of the plurality of lower cabin air guide strips of the lower cabin heat-radiation air guide strip subunit 3211 form parallel middle lower cabin air guide strip sections in the middle after being transited through circular arcs, and two symmetrical branches of a Y-shaped structure are formed at the lower cabin air guide outlet end at the rear end and respectively face 2 bottom shell air outlets 313.
The lower cabin air guide strip section in the middle of the lower cabin heat-dissipation air guide strip subunit 3211 and the air outlet end of the lower cabin air guide strip are in mirror symmetry structures. The part of the front end of each lower cabin air guide strip deflects towards the air inlet direction.
Preferably, as shown in fig. 14, the air inlet end of the lower cabin heat dissipation and air guide strip subunit 3211 of this embodiment 1 is also mirror symmetrical (refer to fig. 8 for illustration) without considering that the air inlet end length is defined by the air inlet end arrangement arc FGH of the lower cabin air guide strip; the design ensures that the air guide strip of the lower cabin body is positioned at the G point and has the maximum air guide quantity, and the manufacturing process is simple.
The lower cabin heat dissipation and wind guiding strip of the lower cabin heat dissipation and wind guiding strip subunit 3211 has an air inlet structure designed such that the hot air sent out by the lower cabin heat dissipation fan 3231 quickly enters the lower cabin heat dissipation cavity 52 in an optimal flow manner and is transported out.
In addition, a plurality of lower cabin heat dissipation plate air deflector mounting portions 3214 are provided at the top of the plurality of lower cabin air guide bars of the lower cabin heat dissipation bar subunit 3211 for connecting the lower cabin air deflector 322.
Specifically, the lower cabin heat dissipation plate air deflector mounting portion 3214 has a convex structure.
As shown in fig. 11 and 13, a bottom shell fin waterproof ring 362 is provided in the lower tank heat radiation plate waterproof groove 3212. Preferably, the bottom shell cooling fin waterproof ring 362 is adhered to the bottom of the bottom shell cooling fin waterproof groove 3212, and the bottom shell cooling fin reinforcing rib 317 of the bottom shell 31 abuts against the bottom shell cooling fin waterproof ring 362 and is limited in the bottom shell cooling fin waterproof groove 3212, and the waterproof fastener seals and connects the bottom shell cooling plate 321 on the bottom shell 31 through the cooling plate bottom shell mounting portion 3213 and the bottom shell cooling plate mounting portion 318, so that the bottom shell 31 and the bottom shell cooling plate 321 are firmly connected into a whole.
Preferably, the bottom shell cooling fin waterproof ring 362 is made of silica gel foam. The silica gel foam has the advantages of easy manufacture, high compressibility and redundant bonding of the ends.
The bottom shell fin waterproof ring 362 is a waterproof layer of the innermost layer of the lower cabin body 3. The bottom shell radiating fin waterproof ring 362 not only can better isolate external fluid from entering the lower cabin radiating cavity 52, but also can play a role in reducing vibration transmission to a certain extent, and is beneficial to normal operation of electronic components and devices.
As shown in fig. 15, the lower cabin air deflector 322 includes a lower cabin air deflector upper plate 3221 and a lower cabin air deflector side plate 3222, the inner surface of the lower cabin air deflector upper plate 3221 is buckled on the upper end surface of the lower cabin heat dissipation and air deflection strip subunit 3211, and the inner side surface of the lower cabin air deflector side plate 3222 is attached to the outer side surface of the lower cabin air deflection strip outermost of the lower cabin heat dissipation and air deflection strip subunit 3211.
As shown in fig. 11, the lower cabin heat dissipation plate 321 and the lower cabin air deflector 322 are fastened to form a lower cabin heat dissipation chamber 52.
The lower cabin air deflector 322 plays a role in rectifying an air channel and optimizing a hot air evacuation channel.
A lower cabin explosion lamp mounting portion 3223 is provided on the lower cabin air guiding upper plate 3221, for the lower cabin explosion lamp assembly to pass through and dissipate heat after being mounted at the bottom shell explosion lamp mounting portion 311 of the bottom shell 31.
The lower cabin air guide upper plate 3221 is further provided with a lower cabin air guide plate positioning portion 3224 for being connected with the lower cabin heat dissipation plate 321. Specifically, the lower cabin air deflector positioning portion 3224 is a hole system structure, the protruding structure of the lower cabin heat dissipation plate air deflector mounting portion 3214 is in interference fit with the lower cabin air deflector positioning portion 3224, and the lower cabin air deflector 322 is positioned on the top of the lower cabin air deflector strip of the lower cabin heat dissipation plate 321 through a hot melting or pressing melting process. The lower cabin air deflector 322 and the lower cabin heat dissipation plate 321 are structurally integrated, so that the structural stability of the lower cabin heat dissipation assembly 32 and the stability of the heat dissipation function of the lower cabin heat dissipation cavity 52 are ensured.
As shown in fig. 13, the air inlet end of the lower cabin air deflector 322 covers the front end of the lower cabin air-guiding sub-unit 3211, and the air outlet end of the lower cabin air deflector 322 forms two symmetrical branches of a Y-shaped structure and covers the Y-shaped lower cabin air-guiding air outlet end of the lower cabin air-guiding sub-unit 3211. The arrangement can enable the hot air output by the lower cabin cooling fan 3231 to enter the lower cabin cooling cavity 52 in a directional manner and be directly transmitted to the bottom shell air outlet 313 to be discharged, and radiate the important heat source lower cabin explosion flash lamp assembly 34 arranged at the bottom shell explosion flash lamp mounting part 311 in the process that the air flow passes through the lower cabin cooling cavity 52.
The lower cabin heat dissipation assembly 32 of this embodiment 1 forms a complete heat dissipation channel from the bottom shell air outlet 313 of the bottom shell 31 through the lower cabin heat dissipation cavity 52 by conveying hot air from the lower cabin heat dissipation fan 3231 to the lower cabin air inlet end, and directionally transfers heat generated by the lower cabin explosion lamp assembly 34 and heat dissipation of the lower cabin heat dissipation fan 3231 to the core heat source such as the equipment cabin 53, thereby avoiding damage of waste heat to electronic components in the unmanned aerial vehicle body and having high heat dissipation efficiency.
In addition, the lower cabin air outlet heat dissipation dust screen 325 and the lower cabin heat dissipation fan heat dissipation dust screen 324 can prevent large particles from entering the lower cabin of the unmanned aerial vehicle in the bottom shell 31 from the air inlet and the air outlet.
As shown in fig. 10, the lower cabin air outlet heat dissipation dust screen 325 and the lower cabin heat dissipation fan heat dissipation dust screen 324 may cause the entry of fluids such as rainwater; accordingly, the bottom case 31 is provided with a bottom case drain hole 3112 for draining fluid such as rainwater.
The unmanned aerial vehicle fuselage of this embodiment 1 has adopted inside and outside dual installation location and waterproof setting to the horn on lower cabin body portion 3, has guaranteed the stability of horn installation on the one hand, on the other hand has also guaranteed the security that communication line is connected between unmanned aerial vehicle horn and unmanned aerial vehicle first cabin body.
Specifically, the bottom shell cooling fin waterproof ring 362 of the embodiment 1 is an integral design of an annular structure and a linear structure, so that the waterproof performance of the equipment cabin 53 of the lower cabin body of the unmanned aerial vehicle is stably ensured; meanwhile, the 3 layers of the lower cabin waterproof assembly ensure that the unmanned aerial vehicle lower cabin with the heat dissipation waterproof structure in the embodiment 1 is safe and reliable in waterproof performance.
Since the middle shell portion 2 and the lower cabin body 3 of this embodiment 1 need to be electrically and physically connected, a plurality of matched positioning or clamping connection structures are provided between the lower end surface of the inner shell portion 2 and the upper end surface of the upper shell 331, and the middle shell portion 2 and the lower cabin body 3 are hermetically connected into a whole at the connection position through the lower waterproof strip unit 42.
Fig. 1 shows that the lower weather strip unit 42 of this embodiment 1 includes a plurality of weather strips.
In this embodiment 1, the direction of deflection of the air inlet end of the air guide strip is related to the direction of rotation of the fan.
The unmanned aerial vehicle body heat dissipation waterproof structure disclosed by the invention integrates heat dissipation and waterproof functions, effectively protects the normal operation of electronic elements and devices of the unmanned aerial vehicle body, and improves the flight safety of the unmanned aerial vehicle. The heat dissipation waterproof structure of the unmanned aerial vehicle is wide in applicability, can be used in aircraft design, and is particularly suitable for small unmanned aerial vehicles.
Example 2
An unmanned aerial vehicle.
The unmanned aerial vehicle of this embodiment 2 includes the unmanned aerial vehicle fuselage of embodiment 1, still includes horn 6 and rotor 7.
The horn 6 corresponds to the rotor 7 one by one. One end of the horn 6 is connected to the side of the unmanned aerial vehicle body in embodiment 1, and the other end of the horn 6 is connected to the rotor 7. A plurality of horn 6 are connected to the unmanned aerial vehicle body.
As shown in fig. 20, the present embodiment 2 preferably includes 4 horn 6. The 4 arms 6 are symmetrically connected to the periphery of the lower cabin body 3 in embodiment 1 in pairs, and the connecting ends of the arms 6 extend into the lower cabin body 3 and are specifically connected to the lower cabin inner mounting part and the lower cabin outer mounting part.
A ring sleeve part 3612 of a lower cabin equipment cavity waterproof ring 361 is arranged at the inner mounting part of the lower cabin horn; the lower cabin horn outer mounting part is provided with a horn waterproof ring 363.
The present invention is not limited to the above-mentioned embodiments, and any changes or substitutions that are easily contemplated by those skilled in the art within the scope of the present invention are intended to be included in the scope of the present invention. Meanwhile, all equipment or facilities provided with the device for expanding the application field and producing compound technical effects belong to the protection scope of the method.
Claims (10)
1. An unmanned aerial vehicle fuselage, characterized by comprising a cabin part; the cabin part comprises an air inlet, an air outlet, a heat radiating unit and a waterproof unit;
the heat dissipation unit comprises a heat dissipation plate and an air deflector; the heat dissipation plate is provided with an air guide strip subunit and a heat dissipation plate waterproof sealing groove; the air deflector is buckled on the air guiding strip subunit and forms a heat dissipation cavity with the heat dissipation plate;
the waterproof unit comprises a heat-dissipating 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 channel in the cabin part;
the wind guiding strip subunit comprises a wind guiding strip; the projection vertex connecting lines of the plurality of air guide strips close to one end of the air inlet form an air inlet end curve, the curve is bent towards the air inlet side direction, and the curvature radius of any projection vertex on the curve is larger than the distance from the center of the air inlet to the projection vertex;
The front end of the deflected air guide strip is parallel to the air inlet direction.
2. The unmanned aerial vehicle fuselage of claim 1, wherein the wind-guiding strip subunits are arranged in a Y-shaped configuration; the Y-shaped structure branch ends in the wind guide strip sub-units are wind guide strip air outlet ends which face the air outlets respectively; and a third branch end of the Y-shaped structure in the air guide strip subunit, which is downward from the converging end, is an air inlet end of the air guide strip and faces the air inlet.
3. The unmanned aerial vehicle fuselage according to claim 2, wherein the cabin part comprises a roof part (1), a middle shell part (2) and a lower cabin body part (3), the roof part (1) and the lower cabin body part (3) each comprising the heat dissipating unit and the waterproof unit.
4. A unmanned aerial vehicle according to claim 3, wherein the roof section (1) further comprises a roof (11), the middle of the inner surface of the roof (11) being provided with a roof stiffener (111); the top cover reinforcing ribs (111) are buckled in the waterproof sealing groove of the heat dissipation plate of the top cover part (1); the periphery of the inner surface of the top cover (11) is provided with a top cover waterproof sealing groove (116), and the outer edge of the upper end of the middle shell part (2) is buckled in the top cover waterproof sealing groove (116).
5. A unmanned aerial vehicle fuselage according to claim 3, wherein the lower cabin part (3) comprises a bottom shell assembly, an upper shell assembly (33) and a lower cabin waterproof assembly; the bottom shell assembly comprises a heat dissipation unit of the lower cabin body (3); the lower cabin waterproof assembly comprises a lower cabin equipment cavity waterproof ring (361), a bottom shell radiating fin waterproof ring (362) and a horn waterproof ring (363).
6. The unmanned aerial vehicle fuselage of claim 5, wherein the pan assembly comprises a pan (31), the inner surface of the pan (31) being provided with pan equipment bay stiffeners (316); the upper housing assembly (33) includes an upper housing (331); the inner surface of the upper shell (331) is provided with an upper shell equipment compartment reinforcing rib (3313).
7. The unmanned aerial vehicle fuselage according to claim 6, wherein the bottom shell (31) and the upper shell (331) are fastened, a lower cabin body joint and a lower cabin horn outer mounting portion are formed at the outer periphery of the bottom shell (31) and the upper shell (331), and an equipment cabin joint and a lower cabin horn inner mounting portion are formed after the bottom shell equipment cabin reinforcing rib (316) and the upper shell equipment cabin reinforcing rib (3313) are fastened.
8. The unmanned aerial vehicle fuselage of claim 7, wherein the lower cabin equipment chamber waterproof ring (361) is disposed at the equipment cabin joint and lower cabin inboard arm mounting portion; the horn waterproof ring (363) is arranged at the outer installation part of the lower cabin horn.
9. A drone fuselage according to claim 3, characterized in that an upper flashing unit (41) is provided between the roof portion (1) and the middle shell portion (2); a lower waterproof strip unit (42) is arranged between the middle shell part (2) and the lower cabin body part (3).
10. A unmanned aerial vehicle comprising a unmanned aerial vehicle fuselage according to any of claims 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310540653.8A CN116331537A (en) | 2023-05-15 | 2023-05-15 | Unmanned aerial vehicle fuselage and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310540653.8A CN116331537A (en) | 2023-05-15 | 2023-05-15 | Unmanned aerial vehicle fuselage and unmanned aerial vehicle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN116331537A true CN116331537A (en) | 2023-06-27 |
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ID=86880646
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310540653.8A Pending CN116331537A (en) | 2023-05-15 | 2023-05-15 | Unmanned aerial vehicle fuselage and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116331537A (en) |
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2023
- 2023-05-15 CN CN202310540653.8A patent/CN116331537A/en active Pending
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