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Thin-wall oil tank of unmanned helicopter

An unmanned helicopter and fuel tank technology, which is applied to the fuel tank and weight reduction of the power unit, can solve the problems of increasing the weight of the fuselage, shortening the working time of the aircraft, and small fuel tank capacity, so as to increase the aircraft load and reduce its own weight. , The effect of increasing the oil load

Active Publication Date: 2015-09-23
TIANXUN INNOVATION BEIJING TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

For a long time, the internal fuel tank of this type of aircraft has a cubic structure, which is limited to the streamlined curved surface design of the aircraft fuselage and the internal complex structure. Directly lead to the shortening of the working hours of the aircraft

Method used

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  • Thin-wall oil tank of unmanned helicopter
  • Thin-wall oil tank of unmanned helicopter
  • Thin-wall oil tank of unmanned helicopter

Examples

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Embodiment Construction

[0024] Embodiment of the present invention is described below by example:

[0025] See figure 1 — Figure 5 , a kind of unmanned helicopter thin-walled fuel tank of the present invention, it is a kind of cubic special-shaped structure, and this structure is formed by connecting and combining upper and lower two parts; Its upper part is the cube structure with groove, and its lower part is made of 4 The triangular plates are spliced ​​into a slope structure and an oil vortex is arranged at the bottom. The interior of the fuel tank is composed of a sponge, a weight and an oil inlet pipe. Because there will be a small amount of residue at the bottom when the fuel tank is filled with oil, after adding the sponge, it can ensure sufficient oil absorption, and at the same time, the oil can directly filter out the residue through the sponge and enter the oil pipe. The design of the heavy hammer is to ensure that the fuel intake is always at the bottom due to gravity, and the slope ...

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Abstract

The invention discloses a thin-wall oil tank of an unmanned helicopter. The oil tank adopts a cubic irregular profile structure, and the oil tank is formed by connecting an upper part and a lower part, wherein the upper part adopts a cubic structure with a groove; the lower part adopts a slope structure formed by splicing four triangle plates, and an oil whirling is arranged at the bottom of the slope structure; a helicopter engine and a belt wheel connected with a helicopter empennage are arranged at the middle upper part of the oil tank; the groove of the oil tank is right matched with the belt wheel, and the heights of both sides of the groove are increased. The lower part of the unmanned helicopter body is curved, and the bottom of the oil tank adopts the slope structure, so that bottom of the oil tank is right fit with the helicopter body. Through the adoption of the design of the oil tank disclosed by the invention, the oil capacity of the oil tank of the helicopter is increased farthest, and the working time of the helicopter is prolonged.

Description

technical field [0001] The invention relates to the component design of a light aircraft and a small unmanned aerial vehicle, in particular to an unmanned helicopter thin-wall fuel tank, which belongs to the technical field of aviation aircraft and mechanical design. Background technique [0002] Unmanned helicopters basically use engines to provide power, and the endurance time is an important indicator to measure the performance of the drone. The design of the fuel tank in the fuselage directly determines the length of the aircraft's endurance time. For a long time, the internal fuel tank of this type of aircraft has a cubic structure, which is limited to the streamlined curved surface design of the aircraft fuselage and the internal complex structure. It directly leads to the shortening of the working hours of the aircraft. Considering the above factors, we designed a special-shaped fuel tank structure to match the overall layout of the fuselage, make full use of the int...

Claims

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Application Information

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IPC IPC(8): B64D37/06B64D37/14
CPCY02T50/40
Inventor 王川于孟利
Owner TIANXUN INNOVATION BEIJING TECH CO LTD
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