Box-shaped monolithic structure in composite material for fuselages and wings of aircraft and method for manufacturing said structure

Patent metadata

Field	Value
Publication number	US-12006041-B2
Application number	US-202117183877-A
Country	US
Kind code	B2
Filing date	Feb 24, 2021
Priority date	Feb 26, 2020
Publication date	Jun 11, 2024
Grant date	Jun 11, 2024

Abstract

The invention relates to a method for manufacturing a box-shaped monolithic structure with a cavity by curing a fiber-reinforced prepreg material. The method comprises using two or more elongated and internally hollow support tools which have a complementary form to that of the cavities to be manufactured, and a composition based on reinforcement material and polymer suitable to allow the passage from a rigid state to a flexible elastomeric state and vice versa in response to heating/cooling down. In the rigid state, the support tools allow the direct lamination of the prepreg material on their external walls and are configured to set the flexible elastomeric state at a temperature lower than the curing temperature and higher than 50° C. During the curing operation, the curing pressure is applied both outside the structure being formed and inside the support tools, whose walls have become flexible, to push on the prepreg material to be cured.

First claim

The invention claimed is:

1. A method for manufacturing a box-shaped monolithic structure for fuselages and wings of an aircraft using a prepreg material comprising a fiber-reinforced polymer matrix, said box-shaped monolithic structure comprising:
an upper wall;
a lower wall facing said upper wall and spaced a non-zero amount apart from the upper wall; and
at least one interconnection element extending transversely between said upper and lower walls, connected to them and delimiting with the upper and lower walls themselves respective elongated cavities;
said method comprising the steps of:
a) providing at least two elongated support tools, each having a cross section with an external polygonal profile complementary to the profile of the cavities to be formed in said box-shaped monolithic structure;
b) externally disposing, on three adjoining walls of each support tool, an elongated profiled bar made of said prepreg material, having a C-shaped cross section and comprising a back and two end appendices protruding transversely from said back and arranged on the same side of the back itself;
c) joining said elongated profiled bars along the respective backs placing side by side said elongated support tools so that the elongated profiled bars themselves have opposing concavities to form an assembly;
d) laminating one or more layers of said prepreg material on a lower plate of a forming mold to form a lower skin destined to constitute said lower wall of said box-shaped monolithic structure;
e) inserting the assembly of step c) on said lower skin carried by said lower plate of said forming mold and between respective side plates delimiting the forming mold itself; said elongated profiled bars being arranged with respective end appendages coplanar in contact with said lower skin;
f) laminating one or more layers of said prepreg material on an upper plate of said forming mold to form an upper skin destined to constitute said upper wall of said box-shaped monolithic structure;
g) mounting said upper plate on said side plates of said forming mold in a position facing said lower plate so that said upper skin is placed in contact with the end appendages of said profiled bars opposite the end appendages in contact with the lower skin;
h) bringing to autoclave the forming mold thus prepared and filled with the upper and lower skins and with the profiled bars to carry out a curing operation at predefined curing temperature and pressure;

wherein:
said elongated support tools are internally hollow and have a composition based on reinforcement material and polymer suitable to allow a transition from a rigid state to a flexible elastomeric state upon a heating and to allow a transition from the flexible elastomeric state to the rigid state upon a cooling;
said elongated support tools are configured to set the flexible elastomeric state at a temperature lower than the curing temperature and higher than 50° C.;
step b) is carried out by laminating the said prepreg material directly onto the external surface of the walls of said elongated support tools in a rigid state; and
during phase h), the curing pressure is applied both inside the forming mold and inside said elongated support tools, whose walls are made flexible by the passage from the rigid state to the flexible elastomeric state and are therefore pushed by the curing pressure itself to adhere to said profiled bars and to said lower and upper skins.

2. The method according to claim 1 , further comprising, preliminary to step h), the steps of:
i) inserting inside each elongated support tool at least one tubular bag protruding from respective opposite front and rear end portions of the elongated support tool itself;
l) Sealing, at each of the opposite front and rear ends of the forming mold, a first axial end of a respective external tubular bag suitable for positioning in use around the respective front or rear end portions of the elongated support tools protruding from the forming mold itself; and
m) sealing the adjoining ends of the tubular bags protruding from the respective elongated support tools to each other and to the respective second axial ends of the relative tubular external bags opposite the first axial ends; said curing pressure being applied inside said tubular bags.

3. The method according to claim 1 , wherein step b) is preceded only by a step n) of applying a first resin-based adhesive agent at least on the parts of the walls of the elongated support tools in the rigid state destined to receive said prepreg material.

4. The method according to claim 1 , wherein steps d) and f) are preceded by a step o) of applying a second resin-based adhesive agent at least on the part of said lower and upper plates of said forming mold destined to receive said prepreg material.

5. The method according to claim 1 , wherein the polymer of said elongated support tools is a thermosetting or thermoplastic polymer with shape memory.

6. The method according to claim 1 , wherein the reinforcing material of said elongated support tools includes one or more elastic fibers.

7. The method according to claim 1 , wherein at least two interconnection elements are formed; wherein in said step a) at least three said elongated support tools are provided; and wherein, in said step b), on the walls of at least one of said elongated support tools two said profiled bars are laminated directly on opposite sides.

8. The method according to claim 1 , further comprising, after step h), a step p) of heating the elongated support tools to bring them to the flexible elastomeric state and extract them from the respective cavities of the box-shaped monolithic structure just formed.

9. A method for manufacturing a box-shaped monolithic structure for fuselages and wings of an aircraft comprising:
a) providing at least two elongated support tools that are formed of a reinforcement material and a polymer, whereby the polymer transitions from a rigid state to a flexible elastomeric state upon a heating and transitions from the flexible elastomeric state to the rigid state upon a cooling, each of the elongated support tools are internally hollow and extend along a longitudinal axis, the elongated support tool comprising a plurality of walls extending along the longitudinal axis and include at least a first external surface, a second external surface, and a third external surface, whereby the first external surface is orthogonal to the second external surface, and whereby the second external surface is orthogonal to the third external surface,
b) externally disposing an initial layer of a prepreg material comprising a fiber-reinforced polymer matrix material onto the second external surface of each elongated support tool and subsequently shaping the initial layer of the prepreg material in-situ on the elongated support tool to form a shaped prepreg material that conforms to the plurality of walls of the elongated support tool, the shaped prepreg material having a C-shaped cross-section and the combination of the shaped prepreg material and elongated support tool resulting in an elongated profiled bar that comprises:
a back of the shaped prepreg material adjacent to the second external surface of the elongated support tool,
a first end appendices of the shaped prepreg material adjacent to first external surface of the elongated support tool, and
a second end appendices of the shaped prepreg material adjacent to the third external surface of the elongated support tool;

c) joining said elongated profiled bars along the respective backs placing side by side said elongated support tools so that the elongated profiled bars themselves have opposing concavities to form an assembly;
d) laminating one or more lower l

Assignees

• Leonardo Spa

Inventors

• Corvaglia Stefano Giuseppe
• Gallo Nicola
• Fuggiano Danila

Classifications

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B64C3/26

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title

• B64C3/24

  Moulded or cast structures · CPC title

• B64C3/185

  Spars · CPC title