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Fuselage structure for the combined fastening of an insulation mattress and devices, and aircraft including such a structure

A technology of fixing structure and isolation pad, applied in the direction of fuselage, fuselage bulkhead, fuselage insulation, etc., can solve problems such as difficulty in setting fastening points, damage to the outer skin of the fuselage, and difficulty in perforating Ω-shaped stringers, etc. Achieving the effect of fixing and stabilization improvements, reducing weakening, and eliminating weakening

Active Publication Date: 2014-12-10
AIRBUS OPERATIONS GMBH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0009] On the other hand, due to the obviously impossible inspection and detection risk of delamination on the inner surface, and because of the risk of damage to the outer skin of the fuselage, the traditionally used Ω-shaped stringers are particularly difficult to perforate at the core or inner bottom plate
Therefore, it is difficult to provide fastening points on such a part of the fuselage structure

Method used

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  • Fuselage structure for the combined fastening of an insulation mattress and devices, and aircraft including such a structure
  • Fuselage structure for the combined fastening of an insulation mattress and devices, and aircraft including such a structure
  • Fuselage structure for the combined fastening of an insulation mattress and devices, and aircraft including such a structure

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Embodiment Construction

[0043] Figures 1 to 3 The prior art fuselage structure 1 shown above has omega-shaped longitudinal stringers 10 and frames 12 which bear vertically on the stringers 10 at constant distances. An "L" shaped retaining clip 14 of the frame is located at the frame 12 between two adjacent stringers 10 and is secured to the frame and the bottom plate 10a of the stringers, respectively. The skin 16 of the fuselage is attached to the bottom plate 10a of the stringer 10 and to the clips 14 by riveting.

[0044] Such as figure 1 Stabilizers 18 are arranged at each intersection between the frame 12 and the stringers 10 as shown in the detail drawing of . Said stabilizer 18 has a core plate terminating at both ends in vertical flanges 18a and 18b in order to fix them by riveting to the frame 12 and the corresponding stringer 10 respectively. In particular, the stabilizer is fixed at the bottom plate 10a of the stringer.

[0045] The function of the stabilizer 18 is to hold the frame 1...

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Abstract

An installation of systems in aircraft fuselages such as thermophonic insulation mattresses and devices such as onboard systems, and bundles of electric wires or fluid ducts (air, water, oxygen, hydraulic fluid). A structure for fastening onto an aircraft fuselage includes at least frames and stringers, the structure further including: fuselage stabilizers connecting the frames and stringers, wherein two stabilizers of two consecutive frames face each other between the two consecutive frames; and a strip board connecting the two stabilizers and including a fastening mechanism arranged so as to receive corresponding fastening mechanisms of the insulation mattresses and the devices.

Description

technical field [0001] The present invention relates to the installation of systems in the fuselage of aircraft, especially civil transport aircraft, and in particular to the combination of fixed thermal and acoustic insulation spacers and equipment such as on-board systems, cable harnesses or fluid conduits (air, water, oxygen, hydraulic oil) fixed structure. Background technique [0002] Known to use fastening points even on the fuselage structure, such as figure 1 shown. These fastening points usually comprise openings implemented in the primary structural members such as frames or stringers. Therefore, improved fastening means or plastic pins as described in application FR 2904804 are used to fix the equipment and pads by means of the frames and stringers. [0003] However, these fastening points have a number of disadvantages for aircraft structures. [0004] On the one hand, openings in frames and stringers weaken the structure and are a source of fatigue hazards f...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/12B64C1/40
CPCB64C1/406B64C1/403B64C1/12
Inventor F·德尔沃N·当图G·梅卡迪耶
Owner AIRBUS OPERATIONS GMBH
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