Side-by-side distribution-typed oil tank system

Abstract

The invention discloses a side-by-side distribution-typed oil tank system, which is characterized in that: five oil tanks are sequentially distributed along the longitudinal direction of an airplane and are symmetrically distributed along a longitudinal axis and a transverse axis in an axon system adopting the gravity center of the airplane as an origin, two bubble-preventing oil tanks or counterweights are symmetrically distributed on the left side and the right side of the airplane, all oil tanks are sequentially connected with each other through connecting pieces and flexible rubber oil pipes according to a stipulated oil supply path, so the obvious variation of the position of the gravity center of the airplane with a flying swing layout caused by the consumption of the fuel oil can be overcome; and under the situation that the oil is non-uniformly absorbed because of stalling of one engine at one side of the airplane or asymmetric power of the engines at two sides of the airplane during flying, the position of the gravity center of the airplane can be maintained constant. In addition, the side-by-side distribution-typed oil tank system is simple to produce, has low cost and short period, is practical and reliable and is convenient to use, different fuel systems with different sizes can be produced according to a specific size of the airplane, and the side-by-side distribution-typed oil tank system is particularly suitable for the small-sized turbo-jet flying-swing layout unmanned proof airplane.

Description

technical field [0001] The invention relates to a fuel tank system, in particular to a fuel tank system designed for a small flying-wing layout unmanned aerial vehicle. Background technique [0002] Compared with the conventional layout aircraft, the flying wing aerodynamic layout mainly has the advantages of weight reduction and drag reduction. However, the adoption of the flying wing layout also brings a series of problems, such as weak longitudinal stability, the sensitivity of the aircraft to the position of the longitudinal center of gravity, the problem of longitudinal trimming and so on. In recent years, various researches on flying-wing layout aircraft have been carried out gradually in China. With the rapid development of remote control aircraft technology and automatic control technology, scaled-down aircraft flight test technology has attracted more and more attention because of its low cost, low risk and short cycle characteristics. [0003] For small flying wi...

AI Technical Summary

Problems solved by technology

[0005] In order to overcome the obvious change of the center of gravity position of the flying wing layout aircraft in the prior art due to fuel consumption, resulting in the deficiencies of the aircraft control and trim problems, the present invention aims at the small flying wing layout on the bas...

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