Gravity type split oil tank for small unmanned aerial vehicle

A small unmanned aerial vehicle, gravity-based technology, applied in the direction of the fuel tank of the power unit, can solve the problems of limited capacity, inability to install equipment, low utilization rate of fuselage space, etc., to achieve the effect of increasing the volume

Pending Publication Date: 2020-01-31
合肥德智航创科技有限公司
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0003] 1. Limited capacity: Since the fuel tank is installed in the fuselage, limited by the size of the fuselage, the volume of the fuel tank is limited and cannot meet the requirements of long-distance battery life;
[0004] 2. The installation location is inconsistent with the installation location of the airborne equipment: because the fuel tank must be installed on the center of gravity of the fuselage, the traditional fuel tank will occupy the best position in the middle of the fuselage, resulting in a very low utilization rate of the fuselage space, and many equipment cannot be installed and cannot meet the requirements Increased demand for drone capabilities

Method used

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  • Gravity type split oil tank for small unmanned aerial vehicle

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Embodiment Construction

[0016] The principles and features of the present invention are described below in conjunction with the accompanying drawings, and the examples given are only used to explain the present invention, and are not intended to limit the scope of the present invention.

[0017] Such as figure 1 As shown, a kind of gravity type split fuel tank for small unmanned aerial vehicle, comprises the consumption fuel tank 17 that is communicated with drone engine and is positioned at two main fuel tanks 1 ( figure 1 Only the main oil tank on one side is shown in the figure, and the main oil tank on the other side is symmetrical to it, not shown), the main oil tank outlet 8 of the main oil tank and the consumption oil tank inlet 11 of the consumption oil tank are connected through a connecting pipe 15 communication; the side above the main fuel tank close to the consumption fuel tank is provided with a refueling port 6, an air vent 5 and a consumption fuel tank communication port 7, and a main...

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Abstract

The invention relates to a gravity type split oil tank for a small unmanned aerial vehicle. The gravity type split oil tank comprises a consumption oil tank communicating with an unmanned aerial vehicle engine and two main oil tanks on the upper sides of the two sides of the consumption oil tank. Main oil tank oil outlets of the main oil tanks communicate with a consumption oil tank oil inlet of the consumption oil tank through first connecting pipes. The oil tank is placed in an aerofoil, the capacity is not limited any more, and the volume can be increased; the main oil tanks of the oil tankare installed on the two sides of a fuselage, the consumption oil tank is small in volume and does not occupy too much space of the fuselage, and a load device can be freely installed in the middle section of the whole fuselage.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicle fuel tank devices, in particular to a gravity split fuel tank for small unmanned aerial vehicles. Background technique [0002] At present, the UAV industry mostly uses structural fuel tanks or hard-shell fuel tanks, most of which are installed on the center of gravity in the middle of the fuselage. However, due to the small size of most UAVs, their carrying space is limited, and the subsequent mailboxes have the following disadvantages : [0003] 1. Limited capacity: Since the fuel tank is installed in the fuselage, limited by the size of the fuselage, the volume of the fuel tank is limited and cannot meet the requirements of long-distance battery life; [0004] 2. The installation location is inconsistent with the installation location of the airborne equipment: because the fuel tank must be installed on the center of gravity of the fuselage, the traditional fuel tank will occupy the best...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D37/06
CPCB64D37/06
Inventor 肖鑫梁旭黄盼伟
Owner 合肥德智航创科技有限公司
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