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Small airplane fuel supply system

A technology of fuel supply system and small aircraft, applied in aircraft parts, aircraft power units, fuel supply of power units, etc., can solve problems such as affecting system operation stability, fuel suction port hanging in the air, affecting flight safety, etc., to enhance flexibility Compensation capability and fire protection design requirements, the effect of reducing fuel vapor and improving flight safety

Inactive Publication Date: 2016-06-01
XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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AI Technical Summary

Problems solved by technology

[0002] For small aircraft in the low-altitude field, it is easy to be bumpy and the flight attitude is unstable. The traditional two-point fuel system inlet design of the left and right wing fuel tanks is easy to cause the fuel inlet to be suspended, and the engine fuel supply is not continuous; the traditional fuel supply system design , the gas in the fuel supply pipeline cannot be discharged in time, which will easily lead to poor fuel supply and cavitation to the engine, which will affect the stability of the system and flight safety.

Method used

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Embodiment Construction

[0006] The specific implementation manner of the present invention will be described in combination with the drawings of the invention. Such as figure 1 , the lower positions of the left and right wing fuel tanks 1 are respectively designed with two fuel inlets 3, and each fuel inlet 3 is designed with an oil sump 13, which can ensure that at least one fuel inlet 3 can suck fuel under various flight attitudes of the aircraft. , to ensure continuous and reliable supply of fuel to the engine; the oil supply pipelines of the left and right wing fuel tanks are aggregated after the fuel selector 12, which can maintain the fuel balance of the left and right wings; the lower position of the fuel supply pipeline is designed with a fuel collection tank 5, which is usually full of fuel state, the upper part is designed with a ventilation pipeline 4, which is connected with the wing fuel tank ventilation pipeline 2, and the gas in the fuel supply pipeline and the oil collection tank 5 ca...

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Abstract

The invention belongs to the technical field of airplane fuel supply system design and relates to a small airplane fuel supply system. Two fuel suction ports are designed in the lower positions of the front portion and the rear portion of a left wing fuel tank and two fuel suction ports are designed in the lower positions of the front portion and the rear portion of a right wing fuel tank. Fuel collection grooves are designed at the positions of the suction ports. After fuel of fuel supply pipelines at the front portion and the rear portion of the left wing fuel tank and fuel supply pipelines at the front portion and the rear portion of the right wing fuel tank is collected, the fuel then passes through a fuel selector, is input into a small fuel collection tank through gravity and then passes through an auxiliary fuel pump, a fuel cut-off valve, a fuel filter and a fuel supply fireproof hose assembly into an engine fuel inlet. A fuel return pipeline is arranged between the fuel collection tank and an engine fuel adjusting component and provided with a one-way valve. The fuel return pipeline is connected through a fuel return fireproof hose in a fire region. Fuel steam generated in a fuel pipe in hot weather can be effectively reduced, maintainability is improved, and the requirement for fireproof design is met. A ventilation pipeline is arranged at the upper portion of the fuel collection tank and the fuel collection tank is connected with a whole wing fuel tank 1 through the ventilation pipeline. By the adoption of the small airplane fuel supply system, it can be guaranteed that the fuel can be supplied to an engine continuously and reliably in various flight attitudes and the airplane flight safety is improved.

Description

technical field [0001] The invention belongs to the technical field of aircraft fuel supply systems, and relates to a fuel supply system for small aircraft. Background technique [0002] For small aircraft in the low-altitude field, it is easy to be bumpy and the flight attitude is unstable. The traditional two-point fuel system inlet design of the left and right wing fuel tanks is easy to cause the fuel inlet to be suspended, and the engine fuel supply is not continuous; the traditional fuel supply system design , The gas in the fuel supply pipeline cannot be discharged in time, which will easily lead to poor fuel supply, easy to cause cavitation to the engine, affect the stability of the system operation, and affect flight safety. Contents of the invention [0003] A design method for a small aircraft fuel supply system, characterized in that two fuel inlets 3 are respectively designed at the lower positions of the left and right wing fuel tanks 1, and the suction inlets...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D37/00
Inventor 李小刚熊桂碧罗海涛孙百峰
Owner XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
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