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Energy-absorbing structural element made of a composite material and aircraft fuselage having said absorber

A technology for structural parts and energy absorption, applied in the direction of fuselage, fuselage frame, aircraft parts, etc., can solve problems such as failure to guarantee the function of energy absorbers, beam fracture, beam material damage, etc.

Active Publication Date: 2013-07-31
AIRBUS OPERATIONS (SAS)
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0012] However, this gradual beam material failure phenomenon, which theoretically allows the energy absorber to gradually collapse itself, is difficult to control and predict - even in a laboratory setting
[0013] On the other hand, if the material failure is not properly induced when the fixings are sheared or pulled out under loads applied to the beam after an impact situation, the beam will not only fail to guarantee its function as an energy absorber, but the beam Fracture free and may behave like a ram and prematurely damage other structures such as floors
This solution is therefore unsatisfactory as it is not suitable for the requirement of resistance to impacts with vertical principal components

Method used

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  • Energy-absorbing structural element made of a composite material and aircraft fuselage having said absorber
  • Energy-absorbing structural element made of a composite material and aircraft fuselage having said absorber
  • Energy-absorbing structural element made of a composite material and aircraft fuselage having said absorber

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Embodiment Construction

[0043] Such as figure 1 As shown, the main structure of the aircraft fuselage comprises a substantially cylindrical frame 1 on which a skin 11 reinforced by beams 12 extends substantially along the longitudinal axis of the main structure of the aircraft fuselage.

[0044] The skeleton 1 of the main structure of the aircraft fuselage is mainly formed by stiffening frames 13 . These stiffening frames are positioned in a fuselage section substantially perpendicular to the longitudinal axis of the fuselage and are regularly distributed over the entire length of the aircraft fuselage. The shape of each reinforcing frame is basically consistent with the partial section of the fuselage, usually circular, at least partially circular, such as figure 1 as shown in the example.

[0045] Each reinforcing frame 13 is fixed with a beam 14 . Advantageously, the beam 14 is straight and horizontal in the frame of reference of the aircraft, so that said beam can support a floor (not shown), ...

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Abstract

An aircraft fuselage has at least one reinforcement frame (13), at least one crossbar (14) and at least one energy-absorbing structural element (2) that includes a compression beam (21) having a longitudinal axis Z and oriented substantially in the direction of compression forces to be absorbed upon an impact, the compression beam being attached at a first end (213) thereof to the crossbar (14) and at a second end (214) thereof to the reinforcement frame (13). The compression beam (21) is attached at least one of its ends (213, 214) via a shoulder bracket (22), wherein the shoulder bracket further has the function of cutting the compression beam (21) in case of an impact.

Description

technical field [0001] The present invention relates to the main structure of aircraft. More particularly, the present invention relates to aircraft primary structures designed to absorb energy during sudden compressive loads, especially during landings or sudden water drops that induce fuselage stresses along the vertical axis of the fuselage Emissions during crashes (impacts with a vertical component) induced after an accident. Background technique [0002] The aircraft fuselage mainly consists of a structure consisting of a skin reinforced internally by reinforcing frames and stringers. The reinforcing frame is positioned along a fuselage section substantially perpendicular to the longitudinal axis of the fuselage, and the ribs extend substantially along the longitudinal axis. In the aircraft reference frame (repère aéronef), the reinforcement frame supports generally horizontal straight beams to which the floor is fastened. [0003] In the event of a collision with a ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/00F16F7/12B64C1/06
CPCB64C1/062F16F7/127B64C1/064
Inventor J·米利埃D·安迪塞克C·罗洛O·樊尚
Owner AIRBUS OPERATIONS (SAS)