Novel fuel bunker with axial limiting and compressing function

A technology of axial limit and oil material, applied in the direction of the fuel tank of the power unit, etc., to achieve the effect of good reliability, light weight and good safety

Pending Publication Date: 2019-12-03
上海啸风航空科技有限公司
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AI Technical Summary

Problems solved by technology

The effective fuel load of an aircraft directly affects its mileage index. With the continuous expansion of the application of small flight platforms, the demand for flight endurance time, mileage and carrying capacity is also increasing, so a larger fuel load is required. It is expected that Fuel can account for more than 40% of the total take-off weight. When the flight attitude changes, the fuel slosh has a great impact on the overall center of gravity, which brings about problems in stability, controllability, safety, etc. main problem

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  • Novel fuel bunker with axial limiting and compressing function
  • Novel fuel bunker with axial limiting and compressing function
  • Novel fuel bunker with axial limiting and compressing function

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Embodiment Construction

[0054] In order to further explain the technical means and effects of the present invention to achieve the intended purpose of the invention, the specific implementation methods, Structure, characteristic and effect thereof are as follows in detail. see Figure 1-3, which is a schematic diagram of a novel oil tank with axial limit compression of the present invention, which is composed of a soft oil tank compressible in the length direction and a corresponding limit device. It includes an oil tank shell 1 , a front compression limiting device 2 , a rear compression limiting device 3 , a compressible soft oil tank 5 and a drive system 24 . The compressible soft oil tank 5 is placed in the oil tank shell 1, and the front compression limiting device 2 and the rear compression limiting device 3 are driven by the drive system 24 from both ends to the compressible soft oil tank 5. The middle compression makes the length of the space where the compressible soft fuel tank 5 is locat...

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Abstract

The invention relates to a novel fuel bunker with the axial limiting and compressing function. The novel fuel bunker is composed of a soft fuel tank which is compressible in the length direction and corresponding limiting devices which are additionally arranged. The novel fuel bunker comprises an fuel bunker shell (1), the front compacting limiting device (2), the rear compacting limiting device (3), a driving system (24) and the compressible soft fuel tank (5), wherein the compressible soft fuel tank (5) is located in the fuel bunker shell (1); the front compacting limiting device (2) and therear compacting limiting device (3) are compacted at the two ends of the compressible soft fuel tank (5); and when fuel in the compressible soft fuel tank (5) is reduced, the front compacting limiting device (2) and the rear compacting limiting device (3) are driven by the driving system (24) to synchronously move face to face, and the gravity center of the fuel in the compressible soft fuel tank(5) does not change. The new scheme is created for a small aircraft fuel tank.

Description

technical field [0001] The invention relates to an aviation airborne fuel tank, in particular to a new type of volume-adjustable and center-of-gravity controllable fuel tank with axial limit compression created by a new idea. Background technique [0002] Aircraft fuel tanks are important structural components of modern aircraft, and their main function is to store the fuel required for aircraft flight. According to their different structural forms, they can be roughly divided into three categories: soft fuel tanks, hard fuel tanks and integral fuel tanks. The main feature of the soft fuel tank is that it can make full use of the available space of various shapes inside the aircraft to increase the fuel storage capacity. It has a simple structure, is not affected by vibration, and is not easy to crack or damage. The hard fuel tank is mainly used in the high temperature area in the body, and the position where the fuel tank compartment cannot withstand internal pressure. In...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64D37/06
CPCB64D37/06
Inventor 李东妮李承彬上官凯威冯茂龙李永明周仁福
Owner 上海啸风航空科技有限公司
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