CN-122029020-A - Method for producing a fibrous preform for a composite component articulated to other components

CN122029020ACN 122029020 ACN122029020 ACN 122029020ACN-122029020-A

Abstract

The invention relates to a method for producing a fiber core preform (40, 240) for a composite component articulated to other components, comprising forming a single piece of tape (10, 110) by three-dimensional braiding and shaping it so as to have a substantially H-shaped cross section.

Inventors

A. J.P. Fabre
S. D. Leclerc
S. Kolardini

Assignees

赛峰集团
赛峰起落架系统公司

Dates

Publication Date: 20260512
Application Date: 20240826
Priority Date: 20230904

Claims (10)

1. A method of manufacturing a fibrous core preform (40, 240) for a composite component hinged to other components, the method comprising: Forming a single piece of fibrous tape (10, 110) by three-dimensional braiding, the tape having an elongated shape along a longitudinal axis (X) and comprising non-interwoven regions (20) extending along the longitudinal axis and spaced apart from each lateral edge (BL) of the tape, the non-interwoven regions defining a first region (11) overlying and separable from a second region (12) and having a thickness greater than that of the second region and comprising first braided lateral portions (11 a, 111 a) connected by intermediate portions (11 b, 111 b) and comprising second lateral portions (12 a, 112 a) braided with the first lateral portions, Cutting the intermediate portion to separate the first lateral portion, and Shaping the strip after cutting the intermediate portion comprises spreading (D) the first lateral portions transversely to the non-interwoven region and folding (PL) the second lateral portions along the edges (20 a) of the non-interwoven region so as to give the shaped strip an H-shaped cross-section, each first spreading lateral portion defining a section (50) of a respective clevis preform on each longitudinal end of the strip.
2. The method of claim 1, wherein the non-interwoven region (20, 120) has a first width at a first longitudinal End (EB) and a second width different from the first width at a second longitudinal End (EB) opposite the first end, the first unfolded lateral portions (30) being spaced apart by different distances (E1, E2) at the longitudinal ends.
3. The method according to claim 1 or 2, wherein the second region further comprises a second intermediate portion (212 b) connecting the second lateral portions and comprising at least one reinforcing region (2121 b) defined by a local extra thickness.
4. A method according to claim 3, wherein the second intermediate portion (212 b) comprises a reinforcing region (2121 b) defined by a local extra thickness on one side of each longitudinal End (EB).
5. A method of manufacturing a fibrous preform (80, 280) for a composite component hinged to another component, the method comprising: Manufacturing a fiber core preform (40, 240) by implementing the method according to any one of claims 1 to 4, and The woven fibrous tape web (60, 260) is positioned on the first unfolded lateral portion (30) of the core preform so as to define a loop therearound, the tape web so positioned defining, together with the first unfolded lateral portion, a different fork joint preform (70, 270) at each longitudinal End (EB).
6. The method of claim 5, wherein the fiber core preform (40, 240) and the belt fabric (60, 260) are made of carbon yarns.
7. A method of manufacturing a fibrous preform (800) for a composite component hinged to other components, comprising: forming a single piece of fibrous tape (10) by three-dimensional braiding, the tape having an elongated shape along a longitudinal axis (X) and comprising non-interwoven regions (20) extending along the longitudinal axis and spaced apart from each lateral edge (BL) of the tape, the non-interwoven regions defining a first region (11) overlying and separable from a second region (12), the first region having a thickness greater than that of the second region and comprising first braided lateral portions (11 a, 111 a) connected by intermediate portions (11 b, 111 b) and the second region comprising second lateral portions (12 a, 112 a) braided with the first lateral portions, Cutting the intermediate portion to separate the first lateral portion, and The strip is formed after cutting the intermediate portion, comprising spreading (D) the first lateral portions transversely to the non-interwoven region, and folding (PL) the second lateral portions along the edges (20 a) of the non-interwoven region so as to give the formed strip an H-shaped cross-section, each first spreading lateral portion being machined and drilled so as to define a respective clevis preform (700) at each longitudinal end of the strip.
8. A method of manufacturing a composite component for articulation with other components, the method comprising at least: -manufacturing a fibrous preform (80, 280, 800) of the component by implementing the method according to any one of claims 5 to 7, and A matrix is formed in the pores of the fibrous preform thus obtained.
9. The method of claim 8, wherein the matrix is organic.
10. A method according to claim 8 or 9, wherein the component is a landing gear strut, a section of a landing gear strut or a brake lever.

Description

Method for producing a fibrous preform for a composite component articulated to other components Technical Field The present disclosure relates to the manufacture of composite material parts for articulation at their ends with other parts, in particular fiber core preforms for such parts. Background In order to reduce the weight, it may be proposed to use composite materials instead of metallic materials, which is a continuing concern in the specific case of aircraft components. In view of this, document US7704429 proposes the manufacture of a composite landing gear strut comprising a region called a clevis for hinging with other components and transmitting loads, and formed of a laminated structure, with plies interposed between the main plies of the extension reinforcement body. However, this solution may have drawbacks. Indeed, a clevis having a laminated construction may result in an increased size of the load transfer area relative to the metal component to avoid delamination risks. The weight-reducing effect of the overall system becomes less pronounced and the integration of components becomes more challenging due to the increased size. Another problem is that the proposed manufacturing technique involves a lot of manual intervention, which may lead to disqualification and increased costs. Finally, the mechanical properties of the composite material proposed in this document can be improved, in particular in terms of the compressive strength of the central region of the component (referred to as the core region). One option to solve this problem is to add material in the core area, but this increases the mass and thus does not provide a completely satisfactory solution. WO2010146288 discloses a turbine distributor element made of CMC (ceramic matrix composite), FR2983428 discloses a method of manufacturing a turbine blade comprising a monolithic platform, FR3116753 discloses a method of manufacturing a composite blade with a monolithic platform and mounting lugs, and WO2014076408 discloses a preform for a one-piece blade of a turbine. The present invention aims to address all or part of the above-mentioned drawbacks. Disclosure of Invention According to a first aspect, the invention relates to a method of manufacturing a fiber core preform for a composite component hinged to other components, the method comprising: Forming a single piece of fibrous tape by three-dimensional braiding, the tape having an elongate shape along a longitudinal axis and comprising a non-interwoven region extending along the longitudinal axis and spaced apart from each side edge of the tape, the non-interwoven region defining a first region overlying and separable from a second region, the first region having a thickness greater than the second region and the first region comprising a first braided lateral portion connected by an intermediate portion, and the second region comprising a second lateral portion braided with the first lateral portion, -Cutting the intermediate portion to separate the first lateral portion, and -Shaping the strip after cutting the intermediate portion, comprising spreading the first lateral portions transversely to the non-interwoven region, and folding the second lateral portions along the edges of the non-interwoven region, so as to give the shaped strip an H-shaped cross-section, each first spreading lateral portion defining a section of the respective splice preform at each longitudinal end of the strip. The present invention therefore proposes the manufacture of a core preform suitable for obtaining a composite component having two prongs at each longitudinal end. The invention allows, if desired, to form a variable spacing between the side arms of the H-shape (which are formed by the first development) by varying the local width of the non-interlacing areas to obtain different spacing, in particular between the prongs. The non-interwoven regions are designed so that the final shape of the core is created during the forming of the tape. The present invention provides the advantage of manufacturing core preforms from a single piece of fabric (unitary) to avoid handling that may cause defects during manufacturing, and also reduces the interface between multiple preforms that are sources of mechanical weakness. The use of braiding techniques also ensures that there is a yarn extending along the arms of the H-shaped structure from one longitudinal end to the other to withstand the required compressive forces. The second region forms a horizontal joint between the arms, which in turn ensures the overall strength of the component, especially in the event of buckling. In one exemplary embodiment, the non-woven region has a first width at a first longitudinal end and a second width different from the first width at a second longitudinal end opposite the first end, the first flared lateral portions being spaced apart at different distances at the longitudinal ends. This feature allows for different s