A leading edge structure of an aircraft external auxiliary fuel tank that resists bird strikes

A technology for auxiliary fuel tanks and aircraft, applied to the fuel tanks of power plants, etc., can solve the problems of high manufacturing process requirements, increased difficulty, and increased test items, and achieve the effect of simple structural design and convenient manufacturing and assembly

Active Publication Date: 2018-01-16
XI'AN AIRCRAFT INTERNATIONAL
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The first design scheme has higher requirements on the manufacturing process; the second design scheme needs to change the shape of the entire aircraft, which increases the difficulty of design, manufacture and assembly, and more test items need to be verified, which not only wastes time but also wastes manpower

Method used

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  • A leading edge structure of an aircraft external auxiliary fuel tank that resists bird strikes
  • A leading edge structure of an aircraft external auxiliary fuel tank that resists bird strikes
  • A leading edge structure of an aircraft external auxiliary fuel tank that resists bird strikes

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Embodiment Construction

[0022] Such as figure 1 As shown, a front-edge structure of an aircraft external auxiliary fuel tank for anti-bird strike includes a fairing 1, a buffer baffle 3, a plug body 4, a front skin I2, and a front skin II6. The minimum thickness section 11 is located at the edge of the fairing, which is 5 mm to 10 mm, and the maximum thickness section 10 is located at the center of the fairing, which is 10 mm to 30 mm. 1. Connected by connectors to ensure that the assembly step difference between the front skin I2 and the outer surface of the fairing 1 is less than 1 mm; the buffer baffle 3 is located behind the fairing 1 and connected to the front skin I2 by welding; the plug body 4 is welded to the buffer baffle The hole in the middle of the plate 3 is used to isolate the front skin I2 from the fairing 1, so that the fuel in the front skin I2 and its rear structure cannot enter the fairing 1.

[0023] Specific design examples such as Figure 1 ~ Figure 3 As shown, the front edge ...

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Abstract

This application provides a bird-strike-resistant aircraft external auxiliary fuel tank leading edge structure, including a fairing, a buffer baffle, a plug body, a front skin I and a front skin II, the fairing is a variable-section thick-walled structure, and the front skin Ⅰ and the fairing are connected by connecting pieces to ensure that the assembly step difference between the front skin Ⅰ and the outer surface of the fairing is less than 1mm; the buffer baffle is located behind the fairing and is used to separate the front skin Ⅰ from the fairing so that the front skin Ⅰ and the fairing Fuel in its rear structure cannot enter the fairing. The structure design of the application is simple, the manufacture and assembly are very convenient, it can effectively resist the impact of flying birds, and ensure that the auxiliary fuel tank will not cause oil leakage or parts fall off, which will affect the flight safety of the aircraft.

Description

technical field [0001] The application relates to an anti-bird impact design of an aircraft external auxiliary fuel tank, in particular to a bird impact-resistant front edge structure of an aircraft external auxiliary fuel tank. Background technique [0002] When the aircraft is flying, if the external auxiliary fuel tank is hit by flying birds, the auxiliary fuel tank may be damaged, fuel leakage, etc. may affect the safety of the aircraft. [0003] The design of external auxiliary fuel tanks for civil aircraft must meet the provisions of Article 25.571(e)(1) of the "Airworthiness Standards for Transport Aircraft" formulated by the Civil Aviation Administration of China, that is, it must be guaranteed After the impact of the bird, the aircraft can still successfully complete the flight. The relative speed of the aircraft and the bird along the flight path of the aircraft at the time of the collision is Vc at sea level or 0.85Vc at 2,450 meters (8,000 feet), whichever is mor...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64D37/06
Inventor 赵佳欣姚建成魏敏楠钱利民
Owner XI'AN AIRCRAFT INTERNATIONAL
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