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Passive load alleviation for a fiber reinforced wing box of an aircraft with a stiffened shell structure

一种纤维增强材料、增强壳的技术，应用在机翼、飞机零件、弦杆/纵梁等方向，能够解决损失弯曲刚度等问题，达到强度和稳定性提高的效果

Active Publication Date: 2014-03-12
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This approach increases nose down torsion, but also results in a loss of bending stiffness, which needs to be enhanced

Method used

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  • Passive load alleviation for a fiber reinforced wing box of an aircraft with a stiffened shell structure
  • Passive load alleviation for a fiber reinforced wing box of an aircraft with a stiffened shell structure
  • Passive load alleviation for a fiber reinforced wing box of an aircraft with a stiffened shell structure

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Embodiment Construction

[0035] according to figure 1, the aircraft 2 basically includes a vertical tail plane 9 , two wings 10 a and 10 b and a fuselage 11 . These parts are generally made of composite material constituting a reinforced shell structure 3 comprising a skin 4 and stringers 5 arranged inside the skin 4 . The wings 10a and 10b of the aircraft 2 are swept backwards. By having the wings 10a and 10b swept back at flight load levels above 1 g, the cabin load will be increased, which may save weight. An additional portion of the cabin load can be obtained if anisotropic composite materials are used. The elastic properties of the wing box 1 can then be designed in such a way that the angle of attack decreases with increasing range at higher flight loads. The downward torsion of the front end is generated by the bending-torsion coupling of the wing box 1 , which is specially designed with anisotropic characteristics.

[0036] figure 2 A schematic diagram of a wing box 1 cut across an airc...

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PUM

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Abstract

The invention relates to a wing box (1) of an aircraft (2) with a stiffened shell structure (3), consisting of fiber reinforced material comprising a skin (4) for absorbing shear loads, and several stringers (5) arranged on the inner side of the wing box (1) for absorbing axial loads, in which at least 60% of the mass of the stiffened shell structure (3) is concentrated in the stringers (5), wherein the stringers (5) provide at least 80% of the axial stiffness of the stiffened shell structure (3). In the specific case of wing structure, this embodiment allows the use of unbalanced laminates for the skin (4) to induce higher nose-down twist of the wing box (1) without any loss in bending stiffness and so envisaging higher weight saving capability.

Description

technical field [0001] The invention relates to a wing box for an aircraft with a reinforced shell structure, the wing box is made of fiber reinforced material, the wing box comprises a skin for absorbing shear loads and a number of blades arranged inside the wing box for absorbing axial loads stringer. [0002] By taking advantage of the anisotropy of composite materials, the field of the invention extends to controlling the deformation of the airfoil in order to passively reduce the aerodynamic loads and thus reduce the weight of the airfoil structure. [0003] Fiber-reinforced composite materials such as carbon fiber-reinforced plastics are used in the manufacture of aircraft structures to [0004] Offering better weight and maintenance performance is becoming increasingly common. In addition, the anisotropy of composite materials provides design space for tuning the stiffness of the wing, i.e., for controlling the distribution of loads not only on the structural componen...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/06
CPCB64C3/185B64C3/18
Inventor 帕斯夸莱·巴索贝恩德·汤姆施克
Owner AIRBUS OPERATIONS GMBH
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