CN214256958U - Heat radiation structure of indoor wisdom aircraft carrier - Google Patents

Abstract

The utility model discloses a heat dissipation structure of an indoor smart aircraft carrier, wherein the indoor smart aircraft carrier comprises a main ship body, an upper replaceable module arranged at the top of the main ship body and a heat dissipation module arranged on the main ship body; the main ship body comprises a front-end functional area, an equipment cabin and a rear-end functional area, wherein a wharf connection area is arranged on the side surface of the front-end functional area; the heat dissipation module comprises first heat dissipation holes formed in the left side surface and the right side surface of the main ship body, second heat dissipation holes formed in the front surface and the inclined surface of the main ship body, a heat dissipation fan and a first exhaust heat dissipation groove which are arranged in front of the wharf connection area, a heat dissipation fan and heat dissipation fins of the power supply module and a first heat dissipation well on the back surface of the main ship body, and a second heat dissipation well communicated with the first heat dissipation well is formed in the upper replaceable module. Forced exhaust by a plurality of cooling fans is combined with air intake of the front cooling fins, the first cooling holes and the second cooling holes of the wiring management cabin to form air convection cooling in the main ship body and natural convection cooling of air in a cooling shaft, so that the cooling problem of the indoor intelligent aircraft carrier is solved.

Description

Heat radiation structure of indoor wisdom aircraft carrier

Technical Field

The utility model relates to a wisdom technical field of family especially relates to a heat radiation structure of indoor wisdom aircraft carrier.

Background

The invention discloses an indoor intelligent aircraft carrier device, which is used for solving a plurality of problems existing in the development of intelligent families, is innovatively defined on the basis of the idea that a traditional weak power box is just needed and the idea that an aircraft carrier is a highly integrated combat platform on the sea, has all the characteristics of the traditional weak power box, integrates a plurality of household sensing sensors, modules, AI algorithms, systems and functions in a unique innovative product form, is an indoor highly integrated intelligent platform, and is combined with model building blocks, a mark paste diagram and the aircraft carrier appearance form of a main ship body to build a real indoor intelligent aircraft carrier device. Indoor wisdom aircraft carrier device is a device that is flat appearance, and its characteristics have: the method is thin: the equipment area of the main ship body bulge is about 56MM thick, the bottom wall of the intermediate equipment cabin is about 7MM thick, the built-in equipment area under the detachable module of the rear functional area is about 20MM thick, and the main ship body basically does not occupy indoor space after being mounted on a wall; flattening: the back of the main ship body is of a plane structure, so that the ship is suitable for being quickly installed by any wall surface and wall; the system is complex: the system integrates a plurality of household perception sensors, modules, AI algorithms, systems and functions; installing external equipment: possible external equipment such as optical cats, optical fiber boxes, routers and the like can be arranged in the main ship body, so that the equipment and cables are prevented from being exposed, and the interior decoration is protected to be attractive; the wiring management function: the household weak current signal wires are uniformly wired and managed, so that the integral attractiveness of a household is facilitated; installation, maintenance are convenient: the ultra-thin design almost realizes the installation operation on the surface of equipment, and the installation and maintenance are convenient; the interface is many: the system integrates weak current interfaces required by common families, reduces user integration, does not need professional wire clamping tools and professional installers, and can be installed by users or property service personnel. Just because indoor wisdom aircraft carrier device has above several characteristics, it is limited in this space, integrated hardware module is many, the part that generates heat is many, the cooling surface is few, the back pastes the difficult diffusion of wall heat, still needs to guarantee forceful electric power supply safety, consequently, indoor wisdom aircraft carrier device heat dissipation is not good will seriously influence system normal operating and user safety, still influences user experience, increases problems such as maintenance cost, influences indoor wisdom aircraft carrier device's stability and life.

SUMMERY OF THE UTILITY MODEL

The to-be-solved technical problem of the utility model lies in, to the above-mentioned defect of prior art, provide an indoor wisdom aircraft carrier device of modified, improve the heat dispersion of indoor wisdom aircraft carrier device.

For realizing the above technical effect, the technical scheme of the utility model as follows:

a heat dissipation structure of an indoor smart aircraft carrier comprises a main carrier body, an upper replaceable module and a heat dissipation module, wherein the upper replaceable module is arranged at the top of the main carrier body; the main ship body comprises a front end functional area positioned at the front part, an equipment cabin in the middle part and a rear end functional area positioned at the rear part, wherein the rear end functional area comprises a sound area, a detachable power module, a wiring cabin and a wiring cabin active oxygen anion module cabin cover which are sequentially arranged from front to back, and a wharf connection area is arranged on the side surface of the front end functional area; the heat dissipation module comprises first heat dissipation holes formed in the left side surface and the right side surface of the main ship body, second heat dissipation holes formed in the front surface and the inclined surface of the main ship body, a heat dissipation fan, a first air exhaust heat dissipation groove or a first air exhaust heat dissipation sheet, a heat dissipation fan, a heat dissipation sheet and two first heat dissipation shafts, wherein the heat dissipation fan is arranged on the CPU above the wharf connection area and the heat plug NVR module, the heat dissipation fan is arranged on the power module, the heat dissipation sheet is arranged below the front cabin cover of the wiring cabin, the left side and the right side of the back surface of the main ship body upwards extend to the two first heat dissipation shafts of the upper replaceable module, and the second heat dissipation shafts are communicated with the first heat dissipation shafts.

Furthermore, the two first heat dissipation shafts are arranged at left and right intervals relative to the longitudinal center line of the main ship body, and each first heat dissipation shaft comprises a first shaft which is vertically arranged and a second shaft which forms a certain included angle with the first shaft; the top of the first shaft is directly communicated with the top of the upper replaceable module, the bottom of the first shaft extends to the upper functional area of the rear-end functional area and is communicated with the upper end of the second shaft, the lower end of the second shaft extends to the side face of the main ship body in an inclined mode, and third heat dissipation holes are formed in the side wall of the first heat dissipation shaft and the side wall of the second heat dissipation shaft.

Further, the lower end entrance width of the second shaft is 2 times the top exit width of the first shaft, and the included angle between the first shaft and the second shaft is 135 °.

Further, the main ship body side face, go up the functional area trailing flank and be equipped with a plurality of and dismantle the module, it is a plurality of can dismantle the module and include at least one of NVR module, battery module, route module, environmental sensor module, wherein the NVR module is equipped with the second radiating groove of airing exhaust or the second fin of airing exhaust, and first centrifugal heat dissipation exhaust fan.

Furthermore, a plurality of radar sensors are arranged in the main ship body, the top edge of a chip of each radar sensor and the bottom surface of the main ship body form an angle of 45 degrees, a shielding cover is arranged on the back of the chip of each radar sensor, and the shielding cover is connected with the heat dissipation copper sheet of the radar PCB in a welding mode.

Furthermore, the upper plane and the front side surface and/or the left and right inclined surface shells of the power supply module are made of plastic materials, a heat dissipation through hole is formed in the inclined surface at one side of the power supply module, and a second centrifugal heat dissipation exhaust fan is arranged on the rear side surface of the inclined surface at the other side of the power supply module; the rear trapezoidal side surface of the power module is made of metal; the rear side face of the power supply module and the empty cabin between the wiring cabin active oxygen anion module cabin cover are provided with the cooling fan, the cooling fan comprises a third centrifugal cooling exhaust fan, the cooling fin comprises an L-shaped cooling fin, and the third centrifugal cooling exhaust fan is used for cooling the L-shaped cooling fin in the empty cabin and the rear side face of the power supply module.

Furthermore, the left and right sides of the front face of the wiring cabin are provided with the L-shaped radiating fins, each L-shaped radiating fin is provided with a transverse radiating fin and a vertical metal radiating fin 342, the upper plane of the wiring cabin is provided with a sliding groove used for sliding into the transverse radiating fin, and two sides of each vertical metal radiating fin 342 are provided with a fixing seat and a screw hole.

Furthermore, a seventh heat dissipation hole is formed in the upper portion of the empty cabin, the middle space of the empty cabin is a heat dissipation space of the L-shaped heat dissipation fins, and the left side and the right side of the empty cabin are provided with isolation walls which form a left-right isolation removal window when combined with the heat dissipation fan on the rear side face of the power module.

Furthermore, the left side and the right side of the rear end functional area are provided with fourth heat dissipation holes, and the left side wall and the right side wall of a second wire groove at the bottom of the power supply module are provided with the fourth heat dissipation holes.

Furthermore, fifth heat dissipation holes are formed in the LED lamp belts on the left side surface and the right side surface of the equipment cabin, an equipment cabin cover is arranged on the equipment cabin, and sixth heat dissipation holes are formed in the left inclined surface, the right inclined surface and the upper plane of the equipment cabin cover; the equipment cabin is further provided with an interface protective cover, the rear side face of the interface protective cover and the rear side face of the equipment cabin are provided with cabin cover supporting seats, the middle of the equipment cabin is further provided with a detachable equipment mounting seat, the left bottom face and the right bottom face of the equipment cabin cover are arranged in a concave mode, and the top of the left side wall and the top of the right side wall of the equipment cabin are arranged in a convex mode.

The utility model has the advantages that: because of the front end functional area is the core of indoor wisdom aircraft carrier device, inside is provided with a plurality of circuit boards and intelligent object, the utility model discloses a left and right sides face in front end functional area sets up first louvre, main ship body's front and the second louvre on inclined plane, first exhaust heat dissipation groove, and the first louvre that CPU fan exhaust combines front end functional area admits air and forms the interior air convection of front end functional area and utilize the back air natural convection heat dissipation well of chimney principle design, solves the heat dissipation problem of wall dress indoor wisdom aircraft carrier device. In addition, the vertical design of the first heat dissipation holes can form external air flow from top to bottom, and the cleaning is facilitated, so that dust is not easy to accumulate. This heat dissipation module of indoor wisdom aircraft carrier device can include along vertical direction extension set up a plurality of first louvres on the left surface and the right side in front end functional area, the second louvre on the front of main ship body and inclined plane to and extend along vertical direction and set up a plurality of first exhaust heat dissipation grooves in first louvre below. The vertical design of first louvre, first exhaust heat dissipation groove can form outside air flow from top to bottom, still can be convenient for clean difficult accumulated dust. The top of the first heat dissipation hole can be directly communicated with the top of the left side surface and the top of the right side surface of the main ship body, the bottom of the first heat dissipation hole extends to the lower portion of the system operation area, and the bottom of the first heat dissipation hole can be designed in an inclined plane. The first exhaust heat dissipation groove can be arranged on the right side face of the front end functional area, the heat generated by the core CPU can be guided to the outer side of the equipment through the first exhaust heat dissipation groove by the heat dissipation fan arranged in the front end functional area to be forcibly exhausted and dissipated, meanwhile, the forced exhaust heat dissipation is combined with the heat dissipation holes formed in the front face, the side face and the upper inclined face of the equipment area, air flowing heat dissipation in the equipment area can be formed, and heat dissipation and normal work of other heating components and modules can be guaranteed. The heat dissipation fan on the power module can dissipate heat of internal components, so that reliable operation of the power module is ensured. The radiating fins below the front cabin cover of the wiring cabin can conduct heat from the inside of the main ship body to the other end of the main ship body to dissipate heat, and the other end of the radiating fins is located at the rear end of the power module. The first heat dissipation well and the second heat dissipation well can play a powerful heat dissipation effect on the back of the main ship body and the upper replaceable module, the left and right first heat dissipation wells and the second heat dissipation well can avoid heat of left and right equipment, a wiring groove can be reserved for back lighting of an equipment area, a space is reserved for a back hanging hole of the upper replaceable module, and interference is prevented.

Additional aspects and advantages of the invention will be set forth in part in the description which follows and, in part, will be obvious from the description, or may be learned by practice of the invention.

Drawings

Fig. 1 is an exploded schematic view of an indoor smart aircraft carrier according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of a main vessel body according to an embodiment of the present invention;

fig. 3 is a schematic structural diagram of a power module according to an embodiment of the present invention;

fig. 4 is a schematic partial structure diagram of a back-end functional area according to an embodiment of the present invention;

fig. 5 is a schematic structural diagram of a heat sink according to an embodiment of the present invention.

Reference numerals

110. A front-end functional region; 111. a dock area;

120. an equipment compartment; 121. a cabin cover supporting seat; 122. an equipment mounting base; 123. an interface protection cover;

131. a sound zone; 132. a power supply module; 1321. a heat dissipating through hole; 1322. a third centrifugal heat-dissipating exhaust fan; 1323. a second wire slot; 133. a wiring cabin; 1331. a chute; 134. a wiring cabin active oxygen anion module cabin cover; 135. a radar sensor; 136. a fourth heat dissipation aperture; 137. emptying the cabin;

140. an equipment hatch; 141. a sixth heat dissipation hole;

200. an upper replaceable module; 210. a second heat dissipating well;

30. a first heat dissipation hole; 31. a second heat dissipation hole; 32. a first exhaust heat sink; 33. a heat radiation fan; 34. a heat sink; 341. a transverse heat sink; 342. a vertical metal heat sink 342; 35. a first heat dissipating well; 36. a first hoistway; 37. a second hoistway; 38. a third heat dissipation hole;

400. a detachable module;

500. an LED light strip; 510. and a fifth heat dissipation hole.

Detailed Description

In order to make the technical problem solved by the present invention, the technical solution adopted by the present invention and the technical effect achieved by the present invention clearer, the technical solution of the present invention will be further explained by combining the drawings and by means of the specific implementation manner.

In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, detachably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.

In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.

It will be understood that the terms "central," "longitudinal," "transverse," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in an orientation or positional relationship indicated in the drawings for convenience in describing and simplifying the invention, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be considered as limiting the invention. In the description of the present invention, "a plurality" means two or more unless otherwise specified. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to have a special meaning.

The following describes a specific structure of a heat dissipation structure of an indoor smart aircraft carrier according to an embodiment of the present invention with reference to fig. 1 to 5.

As shown in fig. 1-5, fig. 1 discloses a heat dissipation structure of an indoor smart aircraft carrier, which includes a main vessel body, an upper replaceable module 200 disposed on the top of the main vessel body, and a heat dissipation module disposed on the main vessel body; the main ship body comprises a front end functional area 110 positioned at the front part, an equipment cabin 120 positioned at the middle part and a rear end functional area positioned at the rear part, wherein the rear end functional area comprises a sound area 131, a detachable power supply module 132, a wiring cabin 133 and a wiring cabin active oxygen anion module cabin cover 134 which are sequentially arranged from front to back, and a wharf connection area 111 is arranged on the side surface of the front end functional area 110; the heat dissipation module comprises first heat dissipation holes 30 arranged on the left side surface and the right side surface of the main vessel body, second heat dissipation holes 31 arranged on the front surface and the inclined surface of the main vessel body, a heat dissipation fan and a first air exhaust heat dissipation groove 32 or a first air exhaust heat dissipation sheet of the CPU and hot plug NVR module arranged above the wharf connection area 111, a heat dissipation fan 33 of the power module 132, heat dissipation sheets 34 arranged below a front cabin cover of the wiring cabin 133 and two first heat dissipation shafts 35 extending upwards to the replaceable module 200 on the left side and the right side of the back surface of the main vessel body, and a second heat dissipation shaft 210 communicated with the first heat dissipation shafts 35 is arranged on the upper replaceable module 200.

It can be understood that, because the front end functional area 110 is the core of indoor wisdom aircraft carrier device, inside is provided with a plurality of circuit boards and intelligent object, the utility model discloses a set up first louvre 30, the front of the main ship body and the second louvre 31 on inclined plane, first exhaust heat dissipation groove 32 at the left and right sides face of front end functional area 110, the first louvre 30 of CPU fan exhaust combination front end functional area 110 is intake and is formed the interior air convection of front end functional area 110 and utilize the back air natural convection heat dissipation well of chimney principle design, solves the heat dissipation problem of wall dress indoor wisdom aircraft carrier device. In addition, the vertical design of the first heat dissipation holes 30 can also form external air flow, which is convenient for cleaning and is not easy to accumulate dust. The heat dissipation module of the indoor smart aircraft carrier device may include a plurality of first heat dissipation holes 30 extending in the vertical direction and disposed on the left and right sides of the front functional area 110, a second heat dissipation hole 31 on the front and inclined surfaces of the main body, and a plurality of first exhaust heat dissipation grooves 32 extending in the vertical direction and disposed below the first heat dissipation holes 30. The vertical design of the first heat dissipation holes 30 and the first exhaust heat dissipation grooves 32 can form external air flow, and the cleaning is facilitated, and dust is not easy to accumulate. The top of the first heat dissipation hole 30 may be directly connected to the top of the left and right sides of the main vessel body 1, the bottom of the first heat dissipation hole 30 extends to the lower part of the system operation area, and the bottom of the first heat dissipation hole 30 may be designed as an inclined plane. The first exhaust heat dissipation groove 32 can be arranged on the right side face of the front end functional area 110, a heat dissipation fan arranged in the front end functional area 110 can guide heat generated by the core CPU to the outer side of the equipment through the first exhaust heat dissipation groove 32 to perform forced exhaust heat dissipation, and meanwhile, the forced exhaust heat dissipation is combined with heat dissipation holes which are formed in the front face, the side face and the upper inclined face of the equipment area, so that air flowing heat dissipation in the equipment area can be formed, and heat dissipation and normal work of other heating components and modules can be guaranteed. The heat dissipation fan 33 on the power module 132 can dissipate heat of its internal components, thereby ensuring reliable operation of the power module 132. The heat sink 34 below the front hatch of the wiring compartment 133 is capable of conducting heat from inside the main vessel body to the other end of the heat sink 34 for heat dissipation, the other end of the heat sink 34 being located at the rear end of the power module 132. The first heat dissipation well 35 and the second heat dissipation well 210 can play a powerful heat dissipation effect on the back of the main ship body and the upper replaceable module 200, the left and right first heat dissipation wells 35 and the second heat dissipation well 210 can avoid heat cross of left and right equipment, a wiring groove can be reserved for back lighting of an equipment area, a space is reserved for a back hanging hole of the upper replaceable module 200, and interference is prevented.

In some embodiments, as shown in fig. 1, two first heat dissipating wells 35 are spaced left and right relative to the longitudinal centerline of the main body, each first heat dissipating well 35 includes a first well 36 disposed vertically and a second well 37 disposed at an angle to the first well 36; the top of the first shaft 36 is directly communicated with the top of the upper replaceable module 200, the bottom of the first shaft 36 extends to the upper functional area of the rear functional area and is communicated with the upper end of the second shaft 37, the lower end of the second shaft 37 extends to the side face of the main body in an inclined mode, and third heat dissipation holes 38 are formed in the side wall of the first heat dissipation shaft 35 and the side wall of the second heat dissipation shaft 210.

It can be understood that two first heat dissipating wells 35 and two second heat dissipating wells 210 are recessed in the back of the indoor smart aircraft carrier device and can be symmetrically disposed at left and right intervals with respect to the longitudinal center line of the indoor smart aircraft carrier device, and each first heat dissipating well 35 includes a first well 36 extending in the vertical direction and a second well 37 disposed at an angle to the first well 36. The top of the first shaft 36 communicates with the second heat dissipating shaft 210, the bottom extends to the system operation area and communicates with the upper end of the second shaft 37, and the lower end of the second shaft 37 extends obliquely to the left and right sides of the system operation area. The first heat dissipation well 35 and the second heat dissipation well 210 which are independently arranged on the left and right sides can simplify the internal structures of the first heat dissipation well 35 and the second heat dissipation well 210, air can flow in the first heat dissipation well 35 and the second heat dissipation well 210 conveniently, and meanwhile, heat of left and right equipment is avoided. The width of the lower inlet of the second shaft 37 is greater than that of the top outlet of the first shaft 36, so that cold air on two sides can enter from the lower inlet of the second shaft 37 quickly and form natural ascending air flow with hot air inside, and the purpose of better equipment heat dissipation is achieved. In addition, the third heat dissipation holes 38 are formed in the side walls of the first heat dissipation well 35 and the second heat dissipation well 210, so that heat dissipation inside the main vessel body and the upper replaceable module 200 can be further facilitated.

In some embodiments, the width of the lower end inlet of the second hoistway 37 may be 1.2-3 times, preferably around 2 times, the width of the top outlet of the first hoistway 36. The angle between the first and second hoistways 36, 37 may be 30-60 °, preferably around 45 °. The design not only facilitates the first heat dissipation shaft 35 and the second heat dissipation shaft 210 to realize the back heat dissipation problem of the equipment area by using the chimney principle, but also can reduce the area of the back wall of the equipment area, and is beneficial to the back heat dissipation.

In some embodiments, the main ship body side surface and the upper functional area back side surface are provided with a plurality of detachable modules 400, the plurality of detachable modules 400 comprise at least one of NVR modules, battery modules, routing modules and environment sensor modules, wherein the NVR modules are provided with second air exhaust heat dissipation grooves or second air exhaust heat dissipation fins and first centrifugal heat dissipation exhaust fans.

It can be understood that, first centrifugal heat dissipation exhaust fan and second radiating groove or the cooperation of the second fin of airing exhaust can play effectual radiating effect to NVR module and other modules 400 of dismantling to ensure the reliable work of dismantling module 400, and be favorable to 24 hours long-time operation's NVR treater to force the heat dissipation of airing exhaust, promote system stability, also reduce the internal heat dissipation pressure of main ship simultaneously, the user is according to the functional requirement, can adorn some modules less in order to reach the purpose that reduces inside heating parts and reach the promotion radiating effect.

In some embodiments, as shown in fig. 2, a plurality of radar sensors 135 are disposed in the main vessel, the top edge of the chip of the radar sensor 135 forms an angle of 45 degrees with the bottom surface of the main vessel, and the back of the chip of the radar sensor 135 is provided with a shielding cover, and the shielding cover is connected with the radar PCB heat dissipation copper sheet in a welding manner.

It can be understood that the shield cover is connected with the radar PCB heat dissipation copper sheet in a welding mode to enlarge the heat dissipation area of the PCB copper sheet, achieve the heat dissipation effect of solving the radar sensor 135 and solve the problem of interference prevention of chip signals.

In some embodiments, as shown in fig. 1 and 3, the upper plane and the front side and/or the left and right inclined surface of the power module 132 are made of plastic, the inclined surface of one side of the power module 132 is provided with a heat dissipation through hole 1321, and the rear side of the inclined surface of the other side is provided with a second centrifugal heat dissipation fan (not shown); the rear trapezoidal side of the power module 132 is made of metal; a heat dissipation fan 33 is arranged in the empty chamber 137 between the rear side surface of the power module 132 and the wiring chamber active oxygen anion module chamber cover 134, the heat dissipation fan 33 comprises a third centrifugal heat dissipation exhaust fan 1322, the heat dissipation fins 34 comprise L-shaped heat dissipation fins, and the third centrifugal heat dissipation exhaust fan 1322 is used for dissipating heat between the L-shaped heat dissipation fins in the empty chamber 137 and the rear side surface of the power module 132.

It can be understood that, the second centrifugal heat dissipation exhaust fan and the heat dissipation through hole 1321 are matched to form a heat dissipation structure with heat dissipation holes and fans for forced air exhaust, so that fresh air can pass through the whole power supply area to take away internal heat to achieve the purpose of heat dissipation, the heat dissipation performance of the power supply module 132 is improved, the rear trapezoidal side of the power supply module 132 is made of metal, the thickness of the side can be reduced, the internal space of the power supply is increased, and the heat dissipation of the power supply is facilitated, meanwhile, the third centrifugal heat dissipation exhaust fan 1322 is arranged in the empty chamber 137 between the rear side of the power supply and the wiring chamber active oxygen anion module cabin cover 134, the L-shaped heat dissipation fins in the empty chamber 137 and the rear side of the power supply module 132 can be dissipated, and the heat dissipation effect of the power supply module is improved.

In some embodiments, as shown in fig. 4 and 5, the wiring compartment 133 is provided with L-shaped heat dissipation fins on both sides of the front surface thereof, the L-shaped heat dissipation fins have a transverse heat dissipation fin 341 and a vertical metal heat dissipation fin 342, the upper plane of the wiring compartment 133 is provided with a sliding groove 1331 for sliding into the transverse heat dissipation fin 341, and both sides of the vertical metal heat dissipation fin 342 are provided with fixing seats and screw holes.

It can be understood that the transverse metal radiating fins 34 can conduct heat of heat generating components inside the main ship body to the vertical metal radiating fins 342 for heat dissipation, and the fixing seats and the screw holes arranged on the two sides of the vertical metal radiating fins 342 facilitate the fixing of the L-shaped radiating fins and the main ship body.

In some embodiments, the upper portion of the empty chamber 137 is provided with a seventh heat dissipation hole, the middle space of the empty chamber 137 is a heat dissipation space of an L-shaped heat dissipation fin, and the left and right sides of the empty chamber 137 are provided with isolation walls, so that when the left and right sides of the empty chamber 137 are combined with the heat dissipation fan 33 on the rear side of the power module 132, a left and right isolation exclusion window is formed. It will be appreciated that the above structure is beneficial to protect the integrity of the overall hull of the vessel and also to dissipate heat from the removable power module 132.

In some embodiments, as shown in fig. 1, the rear functional region has fourth heat dissipation holes 136 on left and right sides, and the second wire slot 1323 on the bottom of the power module 132 has fourth heat dissipation holes 136 on left and right side walls. It can be understood that the first heat dissipation hole 30 and the second heat dissipation hole 31 can facilitate forming a heat dissipation channel inside the back-end functional area, thereby improving heat dissipation efficiency and heat dissipation effect.

In some embodiments, as shown in fig. 1 and fig. 2, fifth heat dissipation holes 510 are formed in the LED strip 500 on the left and right sides of the equipment compartment 120, an equipment compartment cover 140 is formed on the equipment compartment 120, and sixth heat dissipation holes 141 are formed in the left and right slopes and the upper plane of the equipment compartment cover 140; the equipment compartment 120 is further provided with an interface protection cover 123, the rear side face of the interface protection cover 123 and the rear side face of the equipment compartment 120 are provided with a compartment cover supporting seat 121, the middle of the equipment compartment 120 is further provided with a detachable equipment mounting seat 122, the left bottom face and the right bottom face of the equipment compartment cover 140 are arranged in a concave mode, and the top of the left side wall and the top of the right side wall of the equipment compartment 120 are arranged in a convex mode.

It can be understood that five heat dissipation holes are formed in the LED strip 500 on the left and right side surfaces of the equipment compartment 120, and sixth heat dissipation holes 141 are formed in the left and right inclined surfaces and the upper plane of the equipment compartment cover 140, so that heat dissipation of equipment inside and outside the equipment compartment 120 is facilitated; the rear side face of the interface protective cover 123 and the rear side face of the equipment compartment 120 are provided with a compartment cover supporting seat 121, the middle of the equipment compartment 120 is also provided with a detachable equipment mounting seat 122, and meanwhile, the equipment compartment cover 140 supporting seat function is also achieved, the concave shape of the left bottom face and the right bottom face of the equipment compartment cover 140 and the convex design of the top of the left side wall and the right side wall of the equipment compartment 120 play a supporting role as well, the thickness of the equipment compartment cover 140 can be reduced through the structure, the strength of the compartment cover is improved, and equipment heat dissipation inside and outside the equipment compartment 120 is facilitated.

In the description herein, references to the description of "some embodiments," "other embodiments," etc., mean that a particular feature, structure, material, or characteristic described in connection with the embodiment or example is included in at least one embodiment or example of the invention. In this specification, the schematic representations of the terms used above do not necessarily refer to the same embodiment or example. Furthermore, the particular features, structures, materials, or characteristics described may be combined in any suitable manner in any one or more embodiments or examples.

The above description is only for the preferred embodiment of the present invention, and for those skilled in the art, there are variations on the detailed description and the application scope according to the idea of the present invention, and the content of the description should not be construed as a limitation to the present invention.

Claims (10)

1. A heat dissipation structure of an indoor smart aircraft carrier is characterized by comprising a main carrier body, an upper replaceable module (200) arranged at the top of the main carrier body and a heat dissipation module arranged on the main carrier body; the main ship body comprises a front end functional area (110) positioned at the front part, an equipment cabin (120) arranged in the middle part and a rear end functional area positioned at the rear part, wherein the rear end functional area comprises a sound area (131), a detachable power module (132), a wiring cabin (133) and a wiring cabin active oxygen anion module cabin cover (134) which are sequentially arranged from front to back, and a wharf connection area (111) is arranged on the side surface of the front end functional area (110); the heat dissipation module comprises first heat dissipation holes (30) arranged on the left side surface and the right side surface of a main ship body, second heat dissipation holes (31) on the front surface and the inclined surface of the main ship body, a heat dissipation fan and a first air exhaust heat dissipation groove (32) or a first air exhaust heat dissipation sheet which are arranged on a CPU and a hot plug NVR module in front of a wharf connection area (111), a heat dissipation fan (33) of a power module (132), heat dissipation sheets (34) arranged below a front cabin cover of a wiring cabin (133) and two first heat dissipation shafts (35) of the main ship body, wherein the left side and the right side of the back surface of the main ship body extend upwards to the upper replaceable module (200), and the upper replaceable module (200) is provided with second heat dissipation shafts (210) communicated with the first heat dissipation shafts (35).

2. The heat dissipation structure of an indoor smart aircraft carrier as claimed in claim 1, wherein two first heat dissipation shafts (35) are arranged at left and right intervals relative to the longitudinal center line of the main vessel body, and each first heat dissipation shaft (35) comprises a first shaft (36) arranged vertically and a second shaft (37) arranged at an angle with respect to the first shaft (36); the top of the first shaft (36) is directly communicated with the top of the upper replaceable module (200), the bottom of the first shaft (36) extends to the upper functional area of the rear-end functional area and is communicated with the upper end of the second shaft (37), the lower end of the second shaft (37) extends to the side face of the main ship body in an inclined mode, and third heat dissipation holes (38) are formed in the side wall of the first heat dissipation shaft (35) and the side wall of the second heat dissipation shaft (210).

3. The heat dissipating structure of an indoor smart aircraft carrier as claimed in claim 2, wherein the lower end entrance width of the second shaft (37) is 2 times the top exit width of the first shaft (36), and the angle between the first shaft (36) and the second shaft (37) is 135 °.

4. The heat dissipation structure of indoor smart aircraft carrier according to claim 2, wherein the main carrier body side surface and the upper functional area rear side surface are provided with a plurality of detachable modules (400), and the plurality of detachable modules (400) comprise at least one of NVR modules, battery modules, routing modules and environmental sensor modules, wherein the NVR modules are provided with second air exhaust heat dissipation grooves or second air exhaust heat dissipation fins and first centrifugal heat dissipation exhaust fans.

5. The heat dissipation structure of an indoor smart aircraft carrier as claimed in claim 1, wherein the main carrier body is internally provided with a plurality of radar sensors (135), the top edges of the chips of the radar sensors (135) are at an angle of 45 degrees with the bottom surface of the main carrier body, and the back of the chip of the radar sensors (135) is provided with a shielding case which is connected with a radar PCB heat dissipation copper sheet in a welding manner.

6. The heat dissipation structure of an indoor smart aircraft carrier as claimed in claim 1, wherein the housing of the power module (132) is made of plastic, and the power module (132) has a heat dissipation through hole (1321) on one side of the power module and a second centrifugal heat dissipation fan on the rear side of the other side; the rear trapezoidal side face of the power module (132) is made of metal; the rear side face of the power supply module (132) and the empty chamber (137) between the wiring chamber active oxygen anion module hatch cover (134) are provided with the heat radiation fan (33), the heat radiation fan (33) comprises at least two third centrifugal heat radiation exhaust fans (1322), the heat radiation fins (34) comprise L-shaped heat radiation fins, and the third centrifugal heat radiation exhaust fans (1322) are used for radiating the L-shaped heat radiation fins in the empty chamber (137) and the rear side face of the power supply module (132).

7. The heat dissipation structure of an indoor smart aircraft carrier as claimed in claim 6, wherein the L-shaped heat dissipation fins are disposed on both sides of the front surface of the wiring compartment (133), each L-shaped heat dissipation fin has a transverse heat dissipation fin (341) and a vertical metal heat dissipation fin (342), a sliding groove (1331) for sliding into the transverse heat dissipation fin (341) is disposed on the upper plane of the wiring compartment (133), and a fixing seat and a screw hole are disposed on both sides of the vertical metal heat dissipation fin (342).

8. The heat dissipation structure of an indoor smart aircraft carrier as claimed in claim 6, wherein a seventh heat dissipation hole is formed at the upper part of the empty chamber (137), the middle space of the empty chamber (137) is the heat dissipation space of the L-shaped heat dissipation fins, and the left and right sides of the empty chamber (137) are provided with isolation walls, so that when the left and right isolation exclusion windows are formed by combining with the heat dissipation fan (33) on the rear side of the power module (132).

9. The heat dissipation structure of an indoor smart aircraft carrier as claimed in any one of claims 1 to 8, wherein the rear functional area is provided with fourth heat dissipation holes (136) on left and right sides, and the fourth heat dissipation holes (136) are provided on left and right side walls of the second slot (1323) at the bottom of the power module (132).

10. The heat dissipation structure of an indoor smart aircraft carrier as claimed in any one of claims 1 to 8, wherein fifth heat dissipation holes (510) are formed in the LED lamp strips (500) on the left and right sides of the equipment compartment (120), an equipment compartment cover (140) is arranged on the equipment compartment (120), and sixth heat dissipation holes (141) are formed in the left and right slopes and the upper plane of the equipment compartment cover (140); the equipment cabin (120) is further provided with an interface protection cover (123), the rear side face of the interface protection cover (123) and the rear side face of the equipment cabin (120) are provided with cabin cover supporting seats (121), the middle of the equipment cabin (120) is further provided with a detachable equipment mounting seat (122), the left bottom face and the right bottom face of the equipment cabin cover (140) are arranged in a concave mode, and the tops of the left side wall and the right side wall of the equipment cabin (120) are arranged in a convex mode.

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