CN216509109U

CN216509109U - Novel cooling system of multi-rotor electric aircraft

Info

Publication number: CN216509109U
Application number: CN202122902289.4U
Authority: CN
Inventors: 阳李; 杨其巧; 杨贤明; 燕发学
Original assignee: Guangxi Xiangyun Yihang Intelligent Technology Co ltd
Current assignee: Guangxi Xiangyun Yihang Intelligent Technology Co ltd
Priority date: 2021-11-24
Filing date: 2021-11-24
Publication date: 2022-05-13
Anticipated expiration: 2031-11-24

Abstract

The utility model discloses a heat dissipation system of a novel multi-rotor electric aircraft, which comprises an aircraft body, wherein the aircraft body comprises arms, blades and a control cabin, a plurality of arms are arranged on the outer side of the control cabin in a star-shaped radial manner, the tail ends of the arms are connected with the blades, a battery assembly is arranged in the control cabin, one end of each arm, close to the blades, is provided with a plurality of air inlets, and the air inlets are formed in the upper surfaces of the arms; the horn is hollow tube structure, and the inlet port communicates with the inside of horn, and the other end and the control cabin intercommunication of horn. The utility model has the advantages of novel structure, high heat dissipation efficiency, improvement of the endurance time and endurance mileage of the aircraft and the like.

Description

Novel cooling system of multi-rotor electric aircraft

Technical Field

The utility model relates to the technical field of aircrafts, in particular to a novel heat dissipation system of a multi-rotor electric aircraft.

Background

Current electronic many rotor unmanned aerial vehicle can divide into according to the size: micro (less than or equal to 0.25kg), light (less than or equal to 7kg) small (less than or equal to 25kg) medium (less than or equal to 150kg) and large (more than 150 kg). With the increase of models, the problem of increased difficulty in heat dissipation can be faced. Because: the ratio is increased by N times, the surface area volume ratio is reduced to 1/N, and the temperature reduction rate is 1/N if the original heat dissipation mode is adopted). Common heat dissipation methods can be divided into two types: 1. adding a radiating fin; 2. a small fan is added; for the electric multi-rotor unmanned aerial vehicle with more than medium-sized heat dissipation modes, the heat dissipation speed cannot keep up with the heating speed particularly in the process of flying for a long time in summer, so that the phenomena of high temperature of a battery and high temperature of electric regulation are caused, when the temperature of the battery reaches 60 ℃ and the temperature of the electric regulation reaches 80 ℃, the aircraft is required to be forced to land, and the endurance time and the endurance mileage are seriously influenced.

The above background disclosure is only for the purpose of assisting understanding of the concept and technical solution of the present invention and does not necessarily belong to the prior art of the present patent application, and should not be used for evaluating the novelty and inventive step of the present application in the case that there is no clear evidence that the above content is disclosed at the filing date of the present patent application.

SUMMERY OF THE UTILITY MODEL

The utility model aims to provide a heat dissipation system which is novel in structure, high in heat dissipation efficiency and capable of improving the endurance time and the endurance mileage of an aircraft.

Therefore, the utility model provides a novel heat dissipation system of a multi-rotor electric aircraft.

Preferably, the utility model can also have the following technical features:

a heat dissipation system of a novel multi-rotor electric aircraft comprises an aircraft body, wherein the aircraft body comprises arms, blades and a control cabin, the arms are radially arranged on the outer side of the control cabin in a star shape, the tail ends of the arms are connected with the blades, a battery assembly is arranged inside the control cabin, one end, close to the blades, of each arm is provided with a plurality of air inlets, and the air inlets are formed in the upper surfaces of the arms; the horn is hollow tube structure, and the inlet port communicates with the inside of horn, and the other end and the control cabin of horn communicate.

Furthermore, the air inlet holes are all arranged in the coverage range of the radius of the blade.

Further, the axial direction of each air inlet hole is respectively parallel to the airflow direction of the position where the downwash airflow collides with the air inlet hole.

Furthermore, a plurality of drain holes are formed in the bottom of the control cabin.

Furthermore, each horn is provided with a drain hole corresponding to the horn, and the drain holes corresponding to the horns are respectively arranged near the tail ends of the corresponding horns.

Further, the battery pack is fixed to the bracket.

Further, the height of the bracket is 17-23 mm.

Furthermore, a spacer block is further arranged at the end part of the horn connected with the control cabin, and the spacer block is fixed at the end part of the horn to separate the longitudinal section of the horn into a structure shaped like a Chinese character 'ri'; an upper air inlet hole is formed above the spacer block, and a lower air inlet drain hole is formed below the spacer block.

Compared with the prior art, the utility model has the advantages that: through set up the inlet port on the horn, can pass through the horn behind the inlet port and get into the control cabin when lower washing air current strikes the horn, increase the air flow speed and improve battery pack's radiating rate. The position and the orientation of seting up of accurate control inlet port are favorable to collecting more downwash air currents and provide the battery pack heat dissipation, improve the time of endurance and the mileage of airborne vehicle.

Drawings

Fig. 1 is a schematic structural view of the present invention.

Fig. 2 is a partially enlarged view of fig. 1.

Fig. 3 is a schematic top view of the present invention.

Fig. 4 is a schematic bottom view of the present invention.

Fig. 5 is an end view of the horn of the present invention.

Fig. 6 is a partial cross-sectional view of the horn of the present invention.

Detailed Description

The present invention will be described in further detail with reference to the following detailed description and accompanying drawings. It should be emphasized that the following description is merely exemplary in nature and is not intended to limit the scope of the utility model or its application.

Non-limiting and non-exclusive embodiments will be described with reference to the following figures, wherein like reference numerals refer to like parts, unless otherwise specified.

The novel heat dissipation system of the multi-rotor electric aircraft comprises an aircraft body, wherein the aircraft body comprises a plurality of arms 3, blades 5 and a control cabin 1, the plurality of arms 3 are radially arranged on the outer side of the control cabin 1 in a star shape, the tail ends of the arms 3 are connected with the blades 5, and a battery assembly 2 is arranged inside the control cabin 1. A plurality of air inlets 4 are formed in one end, close to the blade 5, of the machine arm 3, and the air inlets 4 are formed in the upper surface of the machine arm 3. The horn 3 is the hollow tube structure, and inlet port 4 and the inside intercommunication of horn 3, the other end and the control cabin 1 intercommunication of horn 3. In a preferred embodiment, for the unmanned aerial vehicle blade, the bottom surface of the blade is an inclined surface, the inclination angle of the bottom surface of the blade gradually changes and decreases from the root to the tip (the root is the connecting end close to the horn, and the tip is the tail end far away from the horn; in some blade structures, the inclination angle of the bottom surface of the blade is controlled through the local thickness change of the blade), and the inclination angle is set to be close to horizontal. In order to obtain a better air inlet effect, the air inlet holes 4 are all formed in the orthographic projection of the paddle 5 on the horn 3 (namely, in the coverage range of the radius of the paddle), and the axial direction of each air inlet hole 4 is parallel to the airflow direction of the lower washing airflow impacting on the horn 3.

Specifically, paddle 5 rotates and changes unmanned aerial vehicle's motion state under the drive of motor, and the paddle is at rotatory in-process, and its bottom surface forms down the washing air current downwards, and down the washing air current strikes on horn 3 in the motion. For the horn 3, the outer surface is generally a circular arc surface, either circular or elliptical in shape. Due to the existence of the inclined surface of the bottom surface of the paddle 5, the angles of the lower washing air flow impacting on the machine arm 3 are different, and therefore the axial directions of the air inlet holes 4 arranged corresponding to the lower washing air flow respectively have requirements. The axial direction of the air inlet hole 4 is parallel to the corresponding direction of the lower washing air flow, so that the lower washing air flow can conveniently send air into the machine arm 3 through the air inlet hole 4. Referring to fig. 1 and combining the structural characteristics of the existing paddle, the angle of the lower washing air flow impacting on the horn 3 changes due to the change of the inclination angle of the bottom surface of the paddle 5, and further the axial direction of the air inlet holes 4 is changed, so that the axial direction of each air inlet hole is parallel to the air flow direction of the lower washing air flow impacting on the position of the air inlet hole. Therefore, when the exhaust holes 4 are arranged, the air inlet holes 4 formed close to the blades 5 are fewer, and the air inlet holes 4 formed far away from the blades 5 are more. Through set up inlet port 4 on horn 3, can pass through behind inlet port 4 behind the horn 3 entering control cabin 1 when lower washing air current strikes horn 3, increase the radiating rate that air flow speed improves battery pack 2. The position and the orientation of seting up of accurate control inlet port 4 are favorable to collecting more downwash air current and provide the heat dissipation for battery pack 2, improve the time of endurance and the mileage of airborne vehicle.

According to the further improvement of the technical scheme, the bottom of the control cabin 1 is provided with the plurality of drain holes 8, so that the control cabin 1 is communicated with the external environment, and the drain holes 8 can not only improve the gas circulation inside the control cabin 1, but also drain rainwater out of the control cabin 1. Especially use unmanned aerial vehicle to make in rainy day, the rainwater is inside from inlet port 4 entering control cabin 1, can be through wash port 8 with rainwater drainage control cabin 1 outside, and guarantee control cabin 1 is in better operational environment, avoids the rainwater to stop for a long time in control cabin 1 as far as possible. In a preferred embodiment, each of the booms has a drain hole corresponding thereto, and the drain holes corresponding to the booms are respectively disposed near the ends of the booms. Like this, after the rainwater passes through horn 3 entering control cabin, can arrange the rainwater outside the control cabin through the wash port that corresponds the setting fast.

In a preferred embodiment, the bottom of the battery component 2 is provided with a bracket 7, and the height of the bracket 7 is 17-23 mm. Guarantee that battery pack 2 and control cabin 1 bottom have certain suspension height, avoid the rainwater bubble to battery pack 2.

More specifically, referring to fig. 5 and 6, a spacer 9 is further disposed at an end of the horn 3 connected to the control cabin 1, the spacer 9 is welded and fixed to the end of the horn 3 to divide a longitudinal section of the horn 3 into a structure shaped like a Chinese character ri, an upper air inlet hole 10 is formed above the spacer 9, and a lower air inlet drain hole 11 is formed below the spacer 9. The gas from the gas inlet 4 can be introduced into the control cabin 1 above and below the spacer block 9, and the circuit passes through the upper gas inlet hole 10, so that the power supply circuit is prevented from being soaked by rainwater. After entering the horn 3, the rainwater enters the control cabin 1 through the lower air inlet and drain hole 11 and then is drained to the outside of the control cabin 1 through the drain hole 8.

Those skilled in the art will recognize that numerous variations are possible in light of the above description, and therefore the examples and drawings are merely intended to describe one or more specific embodiments.

While there has been described and illustrated what are considered to be example embodiments of the present invention, it will be understood by those skilled in the art that various changes and substitutions may be made therein without departing from the spirit of the utility model. In addition, many modifications may be made to adapt a particular situation to the teachings of the present invention without departing from the central concept described herein. Therefore, it is intended that the utility model not be limited to the particular embodiments disclosed, but that the utility model will include all embodiments and equivalents falling within the scope of the utility model.

Claims

1. The utility model provides a novel many rotors electric aircraft's cooling system, includes the aircraft organism, the aircraft organism includes horn, paddle, control cabin, and several horn is the star type radiation and arranges in the outside of control cabin, the end-to-end connection of horn the paddle, the inside of control cabin is equipped with battery pack, its characterized in that: one end of the horn, which is close to the blade, is provided with a plurality of air inlets, and the air inlets are formed in the upper surface of the horn; the horn is hollow tube structure, and the inlet port communicates with the inside of horn, and the other end and the control cabin of horn communicate.

2. The novel heat dissipation system of a multi-rotor electric aircraft as recited in claim 1, wherein: the air inlet holes are all arranged in the coverage range of the radius of the paddle.

3. The novel heat dissipation system of a multi-rotor electric aircraft as recited in claim 1, wherein: the axial direction of each air inlet is respectively parallel to the direction of the air flow of the position where the lower washing air flow collides with the air inlet.

4. The novel heat dissipation system of a multi-rotor electric aircraft as recited in claim 1, wherein: the bottom of the control cabin is provided with a plurality of drain holes.

5. The novel heat dissipation system of a multi-rotor electric aircraft as recited in claim 4, wherein: each horn is provided with a drain hole corresponding to the horn, and the drain holes corresponding to the horns are respectively arranged near the tail ends of the corresponding horns.

6. The novel heat dissipation system of a multi-rotor electric aircraft as recited in claim 1, wherein: the battery pack is fixed to the bracket.

7. The novel heat dissipation system of a multi-rotor electric aircraft as recited in claim 6, wherein: the height of the bracket is 17-23 mm.

8. The novel heat dissipation system of a multi-rotor electric aircraft as recited in claim 1, wherein: the end part of the machine arm connected with the control cabin is also provided with a spacer block, and the spacer block is fixed at the end part of the machine arm to separate the longitudinal section of the machine arm into a structure shaped like a Chinese character 'ri'; an upper air inlet hole is formed above the spacer block, and a lower air inlet drain hole is formed below the spacer block.