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Composite connecting rod, method for producing same and aircraft ceiling or floor structure including same

A composite structure and connecting rod technology, which is applied in connecting rods, aircraft floors, transportation and packaging, etc., can solve the problems of weak elongation at break and fragility of thermosetting resins, and achieve the effect of improving mechanical properties and avoiding oversize

Active Publication Date: 2016-03-23
HUTCHINSON SA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In fact, thermosetting resins such as epoxy types are extremely fragile due to their weak elongation at break (usually a few percent)

Method used

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  • Composite connecting rod, method for producing same and aircraft ceiling or floor structure including same
  • Composite connecting rod, method for producing same and aircraft ceiling or floor structure including same
  • Composite connecting rod, method for producing same and aircraft ceiling or floor structure including same

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Embodiment Construction

[0059] as in Figure 1 to Figure 3 Specifically shown in , the connecting rod 1 according to the invention comprises a male body 2 with two shells 3 and 4 and two connecting ends 5 and 6, said two shells resting against each other Assembled, said two connecting ends are designed to connect the connecting rod 1 to the adjoining structure by means of two connecting pins (not shown) to be mounted respectively on said ends 5 and 6 . Each connecting end 5, 6 constitutes a yoke having two parallel flat walls 5a and 5b, 6a and 6b spaced on either side of the axis of symmetry X'X of the connecting rod 1 and punched with Two opposing holes 5c, 6c designed to receive one of the connecting shafts.

[0060] Figure 4 Shown are two profiled blanks (profiled blanks) 3' and 4' used to manufacture the housings 3 and 4 of the connecting rod 1 of the present invention, shown in two pairs of each housing 3, 4 The ends 3a and 3b, 4a and 4b are shaped to obtain Figure 1 to Figure 3 In front o...

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PUM

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Abstract

The invention relates to a composite structural connecting rod, an aircraft ceiling or floor structure including same and a method for producing said connecting rod. The invention is intended to take-up mainly axial loads, in particular in the field of aeronautics. The connecting rod includes an elongate body that is convex about a longitudinal axis of symmetry (X'X) and two ends (5a, 5b and 6a, 6b) for connecting to adjacent structures, and comprises two shells (3 and 4) having two longitudinal edges which are assembled at said edges and which are each made up of at least one shell layer having continuous shell fibres which are mostly parallel to said axis of symmetry and impregnated with a thermoplastic shell matrix (7b). According to the invention, the connecting rod includes means for assembling the shells including at least one assembly layer (14, 15) wound around and along the shells on said body and having assembly fibres that are mostly at an angle relative to said axis and impregnated with a molten thermoplastic assembly matrix (14b, 15b) in contact with the shell matrix.

Description

technical field [0001] The invention relates to a composite connecting rod, an aeronautical ceiling or floor structure comprising the composite rod and a method for manufacturing the connecting rod. In particular, but not exclusively, the invention applies generally to connecting rods of the kind adapted to resist main axial forces, in the field of aeronautics. Background technique [0002] Composite connecting rods of prior construction for resisting axial forces generally have an elongated shape and a central body terminating in two flattened ends for connection to, inter alia, generating axial forces. The structure of the tension-compression force, the connection is usually realized by connecting shafts respectively installed through the above-mentioned ends. [0003] Document WO-A1-2009 / 000925 describes such a connecting rod obtained by a method comprising the step of discontinuously thermoforming a composite preform based on fibers impregnated with a thermosetting or t...

Claims

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Application Information

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IPC IPC(8): F16C7/02B29C65/00
CPCB29C53/60B29C57/00B29C67/0044B29C70/32B29C70/462B29C70/521B29K2101/12B29L2031/06F16C7/026F16C2326/43Y02T50/40B29C70/06B29C70/50B29D23/00B29K2023/00B29K2071/00B29K2077/00B29K2081/04B29K2081/06B29K2105/0881B29K2105/089B29K2105/10B29K2307/04B29L2031/3076B64C1/18
Inventor 迈克尔·戈东克里斯提那·冈萨雷斯-巴永伯特兰·弗洛伦兹J-P·西奥齐克
Owner HUTCHINSON SA
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