Unmanned aerial vehicle with low wind resistance and high heat dissipation

Abstract

The low-wind-resistance high-heat-dissipation unmanned aerial vehicle comprises a vehicle body and a battery, a mounting groove used for mounting the battery is formed in the upper surface of the vehicle body, the battery is detachably connected with the mounting groove, and the rear end of the mounting groove penetrates through and extends to the outer side of the rear end of the vehicle body; a downward-penetrating air outlet is formed in the position, close to the rear end of the machine body, of the bottom of the mounting groove, an air inlet is formed in the front end of the machine body, and a battery connector is fixedly installed at the position, below the mounting groove, of the rear end of the machine body. And a control module is fixedly mounted at the bottom of the machine body corresponding to the mounting groove. By arranging the mounting groove, the air outlet and the air inlet which are communicated with one another, a large amount of airflow can be guided away, so that the wind resistance during flight of the unmanned aerial vehicle is reduced, meanwhile, heat of the battery and the control module can be taken away together, the heat dissipation effect is achieved, a heat dissipation system does not need to be additionally installed, the weight and cost of the unmanned aerial vehicle are greatly reduced, and the structure is simple.

Description

TECHNICAL FIELD

[0001] The utility model relates to an unmanned plane technical field, concretely is a low wind resistance high heat dissipation unmanned plane. BACKGROUND

[0002] The unmanned plane is not loaded plane for controlling by using radio remote control equipment and self -provided program control device, it has the characteristics such as small size, light weight, low cost, flexible operation, high safety, is widely used in aerial photography, detection, search and rescue, resource exploration etc.

[0003] The unmanned plane will produce wind resistance in the flight process, most unmanned planes on the market adopt streamlined fuselage to reduce the influence of wind resistance, however, still a large part of energy is lost due to overcoming wind resistance when flying, resulting in the endurance of the unmanned plane is reduced, in addition, the unmanned plane needs to rely on the internal fan to dissipate heat when dissipating heat, and the use of the fan makes the battery power consumption of the unmanned plane faster, which is not conducive to the long flight of the unmanned plane, therefore, we provide a low wind resistance high heat dissipation unmanned plane. UTILITY MODEL CONTENT

[0004] The utility model aims at providing a low wind resistance high heat dissipation unmanned plane to solve the problem that the battery power consumption of the unmanned plane is fast due to overcoming wind resistance and using the fan to dissipate heat when flying in the background art, resulting in poor endurance of the unmanned plane.

[0005] To achieve the above object, the utility model provides the following technical scheme: a low wind resistance high heat dissipation unmanned plane, including fuselage and battery, the upper surface of the fuselage is provided with the installation groove for installing the battery, the battery and the installation groove are detachably connected, the rear end of the installation groove penetrates and extends to the outside of the rear end of the fuselage, the bottom of the installation groove is provided with the air outlet that penetrates downward in the position close to the rear end of the fuselage, the front end of the fuselage is provided with the air inlet, the rear end of the fuselage is fixedly installed with the battery connector in the position below the installation groove, the lower surface of the battery is fixedly installed with the socket in the position corresponding to the battery connector, and the bottom of the fuselage is fixedly installed with the control module in the position corresponding to the installation groove.

[0006] When the unmanned plane flies, the airflow enters the installation groove through the air inlet in the front end of the fuselage, and then flows out from the air outlet in the bottom of the installation groove, which reduces the wind resistance and removes the heat generated by the battery and the control module.

[0007] As preferred, the installation groove, the air outlet and the air inlet are communicated and form an air duct. The air duct can guide a large amount of airflow to reduce wind resistance and remove the heat generated by the battery and the control module, without installing an additional heat dissipation fan, reducing the weight of the fuselage and increasing the flight time.

[0008] As preferred, a clamping groove is arranged on each of the two side walls of the mounting groove, and the battery is fixedly installed with a matching clamping block at the position corresponding to the clamping groove, and the battery and the mounting groove are clamped and connected.

[0009] As preferred, the bottom of the battery is fixedly installed with a plurality of protruding ribs.

[0010] As preferred, the plurality of protruding ribs are arranged in parallel along the extension direction of the mounting groove.

[0011] As preferred, the control module comprises a flight control, a speed regulator, a power supply and an image transmission module.

[0012] Compared with the prior art, the above technical scheme has the following technical effects:

[0013] The mounting groove, the air outlet and the air inlet are arranged and communicated to form an air duct, the air duct can guide away a large amount of airflow, thereby reducing the wind resistance when the unmanned aerial vehicle flies, at the same time, when guiding away the airflow, the heat of the battery and the control module is taken away together, thereby playing a heat dissipation role, without additionally installing a heat dissipation system, the weight and cost of the unmanned aerial vehicle are greatly reduced, and the structure is simple. BRIEF DESCRIPTION OF DRAWINGS

[0014] Fig. 1 is an exploded view of the utility model from the lower to the upper oblique angle.

[0015] Fig. 2 is an exploded view of the utility model from the lower to the upper oblique angle.

[0016] Mark 1, fuselage; 2, battery; 3, mounting groove; 4, air outlet; 5, air inlet; 6, battery connector; 7, socket; 8, control module; 9, clamping groove; 10, clamping block; 11, protruding rib. DETAILED DESCRIPTION

[0017] The technical scheme in the embodiments of the utility model will be described clearly and completely below in combination with the drawings in the embodiments of the utility model, and obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments.

[0018] It is to be understood that the structure, proportion, size and the like shown in the drawings of the present application are only used to illustrate the content disclosed in the present application, so as to be understood and read by those skilled in the art, and are not used to limit the implementation conditions of the present application, and therefore do not have technical significance, any modification of the structure, change of the proportion relationship or adjustment of the size, without affecting the effect and purpose of the present application, should still fall within the scope of the technical content disclosed in the present application.

[0019] Please refer to Figs. 1-2 The utility model provides a technical scheme: a low wind resistance high heat dissipation's unmanned plane, including fuselage 1 and battery 2, the upper surface of fuselage 1 is set up with the installation groove 3 for installing battery 2, battery 2 and installation groove 3 are detachably connected, the rear end of installation groove 3 is through and extends to the rear end outside of fuselage 1, the bottom of installation groove 3 is set up with the air outlet 4 that goes down through the position close to the rear end of fuselage 1, the front end of fuselage 1 is set up with the air inlet 5, the rear end of fuselage 1 is fixedly installed with battery connector 6 at the position below installation groove 3, the bottom of battery 2 is fixedly installed with the jack 7 at the position corresponding battery connector 6, the bottom of fuselage 1 is fixedly installed with control module 8 at the position corresponding installation groove 3.

[0020] Installation groove 3, air outlet 4 and air inlet 5 are communicated and form air duct.

[0021] One clamping groove 9 is set up on the both side walls of installation groove 3, and the both sides of battery 2 are fixedly installed with the matching clamping block 10 at the position corresponding clamping groove 9, and battery 2 and installation groove 3 are clampedly connected.

[0022] The bottom of battery 2 is fixedly installed with several convex ribs 11.

[0023] Several convex ribs 11 are parallelly arranged along the extension direction of installation groove 3.

[0024] Control module 8 includes flight control, speed regulator, power supply and image transmission module.

[0025] Working principle or structural principle: first, install battery 2 into installation groove 3, the clamping block 10 on the both sides of battery 2 is clampedly connected with the clamping groove 9 in installation groove 3, the lower surface of the convex rib 11 on the bottom of battery 2 is attached to the bottom of installation groove 3, and the jack 7 of battery 2 is inserted with the battery connector 6 on the fuselage 1, when the unmanned plane flies, the airflow enters into installation groove 3 through the air inlet 5 at the front end of fuselage 1, then flows out from the air outlet 4 at the bottom of installation groove 3 through the gap between battery 2, convex rib 11 and installation groove 3, while taking away the heat generated by battery 2 and control module 8, which not only reduces the wind resistance, but also facilitates the heat dissipation of battery 2 and control module 8, and saves the heat dissipation system, reduces the weight and cost of the product.

[0026] The embodiments of the present application have been described in detail with reference to the drawings. It should be noted that the implementation manners not shown or described in the drawings or the specification are known to those skilled in the art, and are not described in detail. In addition, the definition of each component described above is not limited to the specific structure, shape or manner mentioned in the embodiments, and those skilled in the art can make simple changes or replacements.

[0027] Those skilled in the art can understand that the features described in various embodiments and / or claims of the present application can be combined or / and combined, even if such combination or combination is not explicitly described in the present application. In particular, the features described in various embodiments and / or claims of the present application can be combined and / or combined without departing from the spirit and teachings of the present application. All these combinations and / or combinations fall within the scope of the present application.

[0028] The above specific embodiments further illustrate the purpose, technical solutions and advantages of the present application. It should be understood that the above description is only for specific embodiments of the present application and is not intended to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. A low wind resistance and high heat dissipation unmanned aerial vehicle, comprising a fuselage (1) and a battery (2), characterized in that: The upper surface of the fuselage (1) is provided with a mounting groove (3) for mounting a battery (2), the battery (2) and the mounting groove (3) are detachably connected, the rear end of the mounting groove (3) penetrates and extends to the outside of the rear end of the fuselage (1), the bottom of the mounting groove (3) is provided with a downward air outlet (4) near the position of the rear end of the fuselage (1), the front end of the fuselage (1) is provided with an air inlet (5), the rear end of the fuselage (1) is fixedly installed with a battery connector (6) below the mounting groove (3), the lower surface of the battery (2) is fixedly installed with a socket (7) corresponding to the position of the battery connector (6), and the bottom of the fuselage (1) is fixedly installed with a control module (8) corresponding to the position of the mounting groove (3).

2. The unmanned aerial vehicle of low wind resistance and high heat dissipation according to claim 1, characterized in that: The mounting groove (3), the air outlet (4) and the air inlet (5) are communicated and form an air duct.

3. The unmanned aerial vehicle of claim 1, wherein: A clamping groove (9) is formed in each of the two side walls of the mounting groove (3), and a matching clamping block (10) is fixedly installed on the two sides of the battery (2) corresponding to the position of the clamping groove (9).

4. The unmanned aerial vehicle of claim 1, wherein: The bottom of the battery (2) is fixedly installed with a plurality of protruding ribs (11).

5. The low wind resistance and high heat dissipation unmanned aerial vehicle according to claim 4, characterized in that: The plurality of protruding ribs (11) are arranged in parallel along the extension direction of the mounting groove (3).

6. The low wind resistance and high heat dissipation unmanned aerial vehicle according to claim 1, characterized in that: The control module (8) comprises a flight control, a speed regulator, a power supply and an image transmission module.

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