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Composite tank, manufacturing method therefor, and wing

A technology of composite material tank and manufacturing method, which is applied in the direction of wings, fuel tank safety measures, power plant fuel tanks, etc., can solve the problems of CFRP strength degradation and achieve the effect of suppressing flow electrification and corrosion

Active Publication Date: 2012-02-29
MITSUBISHI HEAVY IND LTD +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

When burrs are generated, there is a problem that the strength of CFRP tends to deteriorate

Method used

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  • Composite tank, manufacturing method therefor, and wing
  • Composite tank, manufacturing method therefor, and wing
  • Composite tank, manufacturing method therefor, and wing

Examples

Experimental program
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Embodiment Construction

[0048] refer to Figure 1 ~ Figure 4 A main wing according to one embodiment of the present invention will be described.

[0049] figure 1 It is a perspective view explaining the structure of the main wing provided with the fuel tank of this embodiment. figure 2 is description figure 1 X-X sectional view of the composition of the fuel tank.

[0050] In this embodiment, a structure in which a fuel tank (composite material tank) 20 is integrally formed inside is applied to a main wing (wing) 1 of an aircraft made of a composite material such as CFRP and described.

[0051] like figure 1 and figure 2 As shown, the main wing 1 is mainly provided with an upper wing outer panel 11 , a lower wing outer panel 12 , a spar 13 , a rib 14 , and a longitudinal beam 15 . These upper wing outer panels 11 , lower wing outer panels 12 , spars 13 , ribs 14 , and longitudinal beams 15 constitute the main structural parts of the main wing 1 , that is, wing boxes.

[0052] Furthermore, a ...

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Abstract

Disclosed is a composite tank that can curb static buildup, corrosion, and strength degradation. Also disclosed are a wing provided with said composite tank and a method for manufacturing the composite tank. The composite tank is characterized by being provided with: a tank body, inside which combustible material is stored, having a first resin part (11, 12) formed from fiber-reinforced resin as well as a metal part formed from metal; a second resin part (22) comprising fiber-reinforced resin and covering at least the area of the first resin part (11, 12), on the inner surface of the tank body, that adjoins the metal part; and multiple conductive parts (23) that enable transfer of charge to the first resin part (11, 12) from the surface of the second resin part (22) that is in contact with the combustible material. The fibers included in the second resin part (22) have higher electrical resistance than the fibers included in the first resin part (11, 12). The second resin part (22) forms a layer that isolates the first resin part (11, 12) and the metal part from each other.

Description

technical field [0001] The present invention relates to a tank in which fuel is stored, and in particular, to a preferred composite material tank suitable for a tank integrally formed with a wing of an aircraft (hereinafter referred to as "integral tank"), a wing with a composite material tank, and a composite material How the box is made. Background technique [0002] At present, among the fuel tanks that store fuel, the main body is formed of a metal such as an aluminum alloy. In particular, in the overall tank in the aircraft field, some or all of the components constituting the tank are shared with the metal components constituting the main wing, so it is formed of metal. . [0003] In recent years, in the field of transportation equipment such as aircraft, composite materials such as reinforced plastics have begun to be used for structural elements such as airframes and main wings for the purpose of weight reduction and the resulting improvement in performance. [000...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B65D90/46B64D37/06
CPCB64C3/34B64D37/06B64D37/32Y02T50/40
Inventor 山口弘晃神纳祐一郎中村康一桥上彻
Owner MITSUBISHI HEAVY IND LTD
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