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Structure, especially a fuselage structure of an aircraft or a spacecraft

A spacecraft and aircraft technology, which is applied in the field of aircraft or spacecraft fuselage structure, can solve the problems of unsatisfactory weight in fuselage structure assembly and stringent requirements in the aircraft field, and achieve low weight, simple structure, and easy production Effect

Inactive Publication Date: 2010-09-22
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] However, it has been found that these airframe structures do not meet the more stringent requirements of the aircraft sector, either in terms of fit or weight

Method used

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  • Structure, especially a fuselage structure of an aircraft or a spacecraft
  • Structure, especially a fuselage structure of an aircraft or a spacecraft
  • Structure, especially a fuselage structure of an aircraft or a spacecraft

Examples

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Embodiment Construction

[0041] In the following, reference will be made to figure 1 An embodiment of the present invention is described in detail through FIG. 3 .

[0042] The structure 1 is configured as a fuselage structure of an aircraft.

[0043] In this case, a coordinate system with x, y and z axes is used, the (positive) x direction represents the longitudinal direction of the aircraft (from the nose to the tail of the aircraft), and the (positive) y direction represents the lateral direction of the aircraft (in the front view of the aircraft From right to left in the figure), the (positive) z direction indicates the vertical direction of the aircraft.

[0044] The fuselage structure 1 comprises a skin section 2 configured as an annular skin section. This annular skin section 2 forms the outer shell of the so-called fuselage barrel of the aircraft and is preferably made of CFRP and / or and / or aluminum alloys.

[0045] The annular skin section 2 has an opening 3 configured as a cross-sectio...

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Abstract

The invention relates to a fuselage structure (1, 1') of a vehicle, comprising an annular panelling segment (2; 2') having a cross-sectional opening (3; 3'), a pressure cap (4; 4') for sealing the cross-sectional opening (3; 3') in a pressure-tight manner, and a plurality of diagonal ties (7, 8, 9; 7', 8', 9') which each connect the pressure cap (4; 4') to the annular panelling segment (2; 2') and receive loads acting on the pressure cap (4; 4') as tensile loads. In this way, advantageously, the diagonal ties (7, 8, 9; 7', 8', 9') essentially do not receive any bending moments. They can therefore have a smaller cross-section, reducing the weight thereof. Such diagonal ties (7, 8, 9; 7, 8, 9) can also be easily produced and assembled.

Description

technical field [0001] The invention relates to a structure, in particular to an aircraft or spacecraft fuselage structure. Background technique [0002] Although the invention and the problem on which it is based can be applied to any structure, it will be described in detail with reference to the fuselage structure of an aircraft. [0003] During flight, the cabin of an aircraft is subjected to an internal pressure above atmospheric pressure. For this reason, the nacelle must be constructed pressure-tight. The fuselage structure of the aircraft is therefore provided with a pressure bulkhead in the aft region. Such fuselage structures with pressure bulkheads are known, for example, from EP 0 847 916 B1, DE 3923871 C2 or EP 0 217 117 B1. [0004] However, it has been found that these fuselage structures do not meet the more stringent requirements in the aircraft sector, neither in terms of fit nor in terms of weight. Contents of the invention [0005] It is therefore a...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C1/10
CPCB64C1/10
Inventor 安德烈亚斯·斯蒂芬
Owner AIRBUS OPERATIONS GMBH
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