ES2961556A1 - Métodos de manufactura de bordes de rigidizadores a neto - Google Patents

Métodos de manufactura de bordes de rigidizadores a neto Download PDF

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Publication number
ES2961556A1
ES2961556A1 ES202230738A ES202230738A ES2961556A1 ES 2961556 A1 ES2961556 A1 ES 2961556A1 ES 202230738 A ES202230738 A ES 202230738A ES 202230738 A ES202230738 A ES 202230738A ES 2961556 A1 ES2961556 A1 ES 2961556A1
Authority
ES
Spain
Prior art keywords
edge
web
section
stiffener
cross
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Pending
Application number
ES202230738A
Other languages
English (en)
Inventor
Charines Yolanda Miguez
García Noelia Colas
Pastor Augusto Pérez
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SL
Original Assignee
Airbus Operations SL
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Airbus Operations SL filed Critical Airbus Operations SL
Priority to ES202230738A priority Critical patent/ES2961556A1/es
Priority to EP23382783.1A priority patent/EP4321329A2/en
Priority to CN202310969429.0A priority patent/CN117584496A/zh
Priority to US18/365,803 priority patent/US20240051244A1/en
Publication of ES2961556A1 publication Critical patent/ES2961556A1/es
Pending legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/681—Component parts, details or accessories; Auxiliary operations
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/34—Rim rolling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
    • B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
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    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0003—Producing profiled members, e.g. beams
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    • B29C53/02—Bending or folding
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    • B29C53/80—Component parts, details or accessories; Auxiliary operations
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    • B29C53/845—Heating or cooling especially adapted for winding and joining
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    • B29C63/0026—Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor an edge face with strip material, e.g. a panel edge
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    • B29C63/02—Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor using sheet or web-like material
    • B29C63/04—Lining or sheathing, i.e. applying preformed layers or sheathings of plastics; Apparatus therefor using sheet or web-like material by folding, winding, bending or the like
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/302—Details of the edges of fibre composites, e.g. edge finishing or means to avoid delamination
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/74—Moulding material on a relatively small portion of the preformed part, e.g. outsert moulding
    • B29C70/76—Moulding on edges or extremities of the preformed part
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
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    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
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    • B29C70/76—Moulding on edges or extremities of the preformed part
    • B29C70/763—Moulding on edges or extremities of the preformed part the edges being disposed in a substantial flat plane
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Abstract

Métodos de manufactura de bordes de rigidizadores a neto. Método de manufactura de un rigidizador de material compuesto polimérico reforzado con fibra de carbono, CFRP, con una sección trasversal en "T", donde el rigidizador se obtiene de una preforma (100) que comprende un alma (120) y un pie (130), donde el pie (130) corresponde a un borde del rigidizador configurado para estar en contacto con un panel de una aeronave, y donde el alma (120) corresponde a la parte restante del rigidizador y la cual comprende un borde del alma (120a), el método de manufactura comprende las siguientes etapas obtener dos laminados (110a, 110b) que comprenden un conjunto de capas de material compuesto, conformar los dos laminados (110a, 110b) mediante el doblado de los dos laminados (110a, 110b) en sección trasversal en "L", unirlos dos laminados (110a, 110b) para obtener la preforma (100) con una sección trasversal en "T", moldear el borde del alma (120a) para obtener una sección trasversal semicircular, aplicar al borde del alma (120a) una tira de tejido de carbono semicurado (L1), una tira húmeda de fibra de vidrio preimpregnado (L2)en fresco y curar la preforma (100) para obtener el rigidizador con una sección trasversal en "T" con el borde del alma (120a) a neto.

Description

DESCRIPCIÓN
Métodos de manufactura de bordes de rigidizadores a neto
Objeto de la invención
El objeto de la presente invención se refiere a métodos de manufactura de rigidizadores de material compuesto polimérico reforzado con fibra de carbono, en particular, a métodos para la obtención de la forma "a neto” de un borde de los rigidizadores que permite eliminar las operaciones de recanteado y de sellado.
Antecedentes de la invención
El proceso estándar para conseguir la fabricación ‘a neto’ de un borde de los rigidizadores o larguerillos con una sección trasversal en “T” con un "alma” y un "pie” (donde el pie corresponde a un borde del rigidizador configurado para estar en contacto con un panel de una aeronave, y donde el alma corresponde a la parte restante del rigidizador) es la de recortar el exceso de material sobrante mediante un proceso llamado recanteado (i.e. se corta el material sobrante del borde con fresa o disco aplicando chorro de agua). El proceso de recanteado se lleva a cabo después del curado de la preforma sobre el que se obtiene el rigidizador con una sección trasversal en “T”. El recanteado se realiza con equipos especializados, los cuales consumen tiempo, así como materiales duros y abrasivos.
La necesidad de recantear el borde del rigidizador después del curado se debe a la mala calidad obtenida en los bordes de la preforma de laminado de material compuesto. Si el borde se moldea usando útiles de conformado (por ejemplo, conformado mediante rodillos), es altamente complicado hacer coincidir el borde del laminado ya conformado con la cavidad del útil de curado. Por lo tanto, se genera un espacio entre el borde del laminado ya conformado y la cavidad del útil de curado. Este espacio se llena con resina y fibras, lo que reduce las propiedades del laminado.
Desventajosamente:
La operación de recanteado puede generar delaminaciones en el borde de la preforma sometida a recanteado y la operación de conformado de los laminados de material compuesto puede crear el denominado efecto libro. En particular:
La figura 1 muestra una preforma (100) de un rigidizador con sección transversal en "T”. La preforma (100) comprende un alma (120) y un pie (130) (donde el pie (130) corresponde al borde del rigidizador configurado para estar en contacto con un panel de una aeronave). Cuando la preforma (100) se ha conformado mediante el doblado de dos laminados de material compuesto (110a, 110b) con una sección transversal en "L” por el "alma” (120) del rigidizador, las diferentes longitudes de cada capa de los laminados de material compuesto (110a, 110b) que siguen al radio (R) crean lo que se denomina efecto libro en el borde del alma (120a), donde las capas internas (C) de los laminados de material compuesto (110a, 110b) son más cortas que las externas.
Por último, cuando las piezas (por ejemplo, las costillas del ala de la aeronave) de metal (por ejemplo, de aluminio o titanio) están cerca del borde del rigidizador recanteado, se requiere de una operación adicional de sellado para cubrir los filamentos de carbono y evitar la corrosión en el metal.
La presente invención solventa las desventajas remanentes en el estado de la técnica a la hora de la fabricación "a neto” del borde del alma de un rigidizador con una sección transversal en "T”.
Descripción de la invención
La presente invención se refiere a un método de manufactura que permite la fabricación ‘a neto’ de un borde del alma de los rigidizadores o larguerillos con sección trasversal en "T” y que evita los procedimientos de recanteado y de sellado existentes en el estado de la técnica, aislando los filamentos de carbono del borde del alma del rigidizador.
Así pues, en un primer aspecto, la presente invención se refiere a un método de manufactura de un rigidizador de material compuesto polimérico reforzado con fibra de carbono, CFRP, con una sección trasversal en "T”, donde el rigidizador se obtiene de una preforma que comprende un alma y un pie, donde el pie corresponde a un borde del rigidizador configurado para estar en contacto con un panel de una aeronave, y donde el alma corresponde a la parte restante del rigidizador y la cual comprende un borde del alma.
El método de manufactura comprende la etapa de obtener dos laminados que comprenden un conjunto de capas de material compuesto, y la etapa de conformar cada uno de los dos laminados de material compuesto mediante el doblado de los laminados de material compuesto, cada laminado con una sección trasversal en "L” ;
El método de manufactura comprende la etapa de unir los dos laminados para obtener la preforma con una sección trasversal en "T”. En particular, con dos laminados cada uno con sección trasversal en "L” , se pueden unir con un alma de la "L” de un primer laminado, a espalda de un alma de la "L” del segundo laminado, con los bordes del alma a misma altura, de tal forma a obtener la preforma con una sección trasversal en "T”.
El método de manufactura comprende la etapa de moldear el borde del alma para obtener una sección trasversal del borde del alma semicircular. El borde libre del alma de la preforma es así redondeado, de tal forma que es menos propenso a delaminación o al almacenar líquidos como agua, grasas, etc. que con tiempo, podrían deteriorar el laminado.
El método de manufactura comprende la etapa de aplicar al borde del alma una tira de fibra de vidrio semicurado y una tira de fibra de vidrio preimpregnado en fresco Las tiras de fibra aplicadas al borde moldeado del alma, permiten mantener juntos los bordes de los laminados, y así asegurar que el borde del alma mantendrá su forma redondeada en el tiempo, así como evitar aún más la delaminación del borde del alma. Con tiras, el borde del alma queda con un acabado continuo liso, o "a neto”.
Finalmente, el método de manufactura comprende la etapa de curar la preforma para obtener el rigidizador con una sección trasversal en "T” con el borde del alma a neto. Una vez curada, la forma del borde del alma, y las tiras que lo cubren se mantienen en su posición y su forma se mantiene sin modificación.
En un primer ejemplo, el método de manufactura comprende la etapa de aplicar a la preforma una bolsa de vacío flexible previamente al curado, la cual se retira del rigidizador después de la etapa de curado.
En un primer ejemplo, el método de manufactura comprende la etapa de aplicar calor al borde del alma para ablandar el conjunto de capas de material compuesto. El calor aplicado es suficientemente bajo para que no se cure la resina del CFRP.
En un primer ejemplo, el método de manufactura además comprende moldear el borde del alma para obtener una sección trasversal con forma de cuña previa a la sección trasversal semicircular. Moldear el borde del alma para obtener una sección trasversal con forma de cuña permite pasar más fácilmente de una forma abierta de borde del alma en "V” cuando los dos laminados están unidos el uno con el otro "a espaldas”, a una forma semicircular.
Otro aspecto de la invención se refiere a un rigidizador que comprende una geometría específica con una sección transversal en "T” obtenido mediante el método de manufactura de acuerdo con el primer aspecto de la invención.
Un tercer aspecto de la invención se refiere a un dispositivo para el moldeado de un borde de un alma de una preforma de un rigidizador de material compuesto polimérico reforzado con fibra de carbono, CFRP, con una sección trasversal en "T”, donde el rigidizador comprende un alma y un pie, donde el pie corresponde a un borde del rigidizador configurado para estar en contacto con un panel de una aeronave, y donde el alma corresponde a la parte restante del rigidizador.
El dispositivo comprende un dispositivo de aplicación de calor configurado para ablandar el conjunto de capas de material compuesto del borde del alma de la preforma y un conjunto de rodillos configurados para obtener el borde del alma con una sección trasversal semicircular.
El conjunto de rodillos comprende un primer grupo de rodillos en cuña para moldear el borde del alma con una sección trasversal en cuña.
El conjunto de rodillos comprende un segundo grupo de rodillos de redondeado con forma de medialuna para moldear el borde del alma con una sección trasversal semicircular.
Descripción de los dibujos
Para complementar la descripción que se está realizando y con objeto de ayudar a una mejor comprensión de las características de los métodos de manufactura de acuerdo con la presente invención, se acompaña como parte integrante de dicha descripción, un juego de dibujos en donde con carácter ilustrativo y no limitativo, se ha representado lo siguiente:
La figura 1 muestra una preforma de un rigidizador con una sección transversal en "T” y el efecto libro generado en el borde del alma del rigidizador.
La figura 2 muestra el conformado mediante moldeo del borde del alma de la preforma.
Las figuras 3A y 3B muestran las etapas de moldeado del proceso de manufactura de acuerdo con la presente invención.
La figura 3C muestra la etapa de aplicación al borde del alma de una tira de fibra de vidrio semicurado, una tira de fibra de vidrio preimpregnado, así como la aplicación a la preforma de una bolsa de vacío flexible.
Realización detallada de la invención
La figura 1 muestra la preforma (100) ( "en fresco” o "pre-curada”) obtenida tras las etapas del método de manufactura de acuerdo con la presente invención correspondientes a obtener dos laminados de material compuesto (110a, 110b) que comprenden un conjunto de capas de material compuesto, conformar cada uno de los dos laminados de material compuesto (110a, 110b) mediante el doblado de los laminados de material compuesto (110a, 110b) cada uno con una sección trasversal en "L” y unir los dos laminados de material compuesto (110a, 110b) para obtener la preforma (100) con una sección trasversal en "T”.
Como se aprecia en la figura 1, las diferentes longitudes de cada capa de los laminados de material compuesto (110a, 110b) crean un borde del alma (120a) en forma abierta en "V”.
La figura 2 muestra la etapa de moldear (o etapa de moldeado) el borde del alma (120a) de la preforma (100) que elimina el efecto libro:
El moldeado se lleva a cabo posteriormente a la etapa de obtener dos laminados de material compuesto (110a, 110b) que comprenden un conjunto de capas de material compuesto, como se muestra en la preformar (100) de la figura 1.
El moldeado también se lleva a cabo posteriormente a la etapa de conformar los dos laminados de material compuesto (110a, 110b) mediante el doblado de los dos laminados de material compuesto (110a, 110b) en sección trasversal en "L” , y a la etapa de unir los dos laminados de material compuesto (110a, 110b) con una sección trasversal en "T” para obtener la preforma (100) del rigidizador.
Al doblar los dos laminados de material compuesto (110a, 110b) se genera un efecto libro en el borde del alma (120a), el cual se aprecia en la figura 1 del estado de la técnica resultando en un borde del alma en "V”, y se describe en el apartado antecedentes de la invención de la presente descripción. Para eliminar el efecto libro del borde del alma (120a), el proceso de manufactura de acuerdo con la presente invención comprende la etapa de moldeado del borde del alma (120a) de la preforma (100), el cual se muestra en la figura 2, una vez obtenida la sección trasversal en "T”.
Como se muestra en la figura 2, la etapa u operación de moldeado se lleva a cabo con el dispositivo (1000) configurado para, mediante un dispositivo de aplicación de calor (300), en una primera fase, aplicar calor al borde del alma (120a) para ablandar el conjunto de capas de material compuesto de dicho borde, y en una segunda fase, mediante un conjunto de rodillos en cuña (310) y un conjunto de rodillos de redondeado (311), moldear la superficie del borde del alma (120a) para obtener el borde del alma (120a) con una sección trasversal semicircular. Al final de esta etapa se crea una forma redondeada en borde del alma (120a), cerrando el espacio interno asociado a las capas interiores más cortas y eliminando así el efecto libro.
La figura 3A muestra la etapa de moldeo de la superficie del borde del alma (120a) mediante un grupo de rodillos en cuña (310) los cuales comprenden una forma de cuña para moldear el borde del alma (120a) con una sección en cuña.
La figura 3B muestra la etapa de moldeo de la superficie del borde del alma (120a) mediante un grupo de rodillos de redondeado (311) con forma de medialuna para moldear el borde del alma (120a) con una forma final que comprende una sección trasversal semicircular.
La figura 3C muestra la etapa de aplicar al borde del alma (120a) una tira de fibra de vidrio semicurado (L1), una tira de fibra de vidrio preimpregnado (L2) en fresco, así como la aplicación a la preforma de una bolsa de vacío flexible (L3), previamente a la etapa de curado, consiguiendo así un borde del alma (120a) "a neto”.
El borde del alma (120a) se cubre con un perfil de fibra de vidrio semicurado (L1), y por encima una tira de fibra de vidrio preimpregnado (L2) en fresco. El estado del perfil de fibra de vidrio (L1) proporciona la suficiente rigidez para moldear el borde del alma (120a) de forma controlada y permite conseguir una buena adhesión con la resina de la preforma (100). El estado fresco de la tira preimpregnada de fibra de vidrio (L2) permite fijar el perfil de fibra de vidrio semicurado (L1) en el borde del alma (120a) una vez curada la preforma (100).
La preforma (100) junto con el perfil de fibra de vidrio que comprende la tira de fibra de vidrio semicurado (L1) y la tira de fibra de vidrio preimpregnado (L2) en fresco se curan envueltos en la bolsa de vacío flexible (L3) que se adapta a la forma real del borde del alma (120a) como se aprecia en la figura 3C, consiguiendo una buena consolidación sin movimientos de resina ni de fibra, obteniendo así un borde del alma (120a) "a neto”. Dicha bolsa de vacío flexible (L3) se puede retirar del rigidizador después de la etapa de curado.

Claims (8)

REIVINDICACIONES
1. Método de manufactura de un rigidizador de material compuesto polimérico reforzado con fibra de carbono, CFRP, con una sección trasversal en "T”, donde el rigidizador se obtiene de una preforma (100) que comprende un alma (120) y un pie (130), donde el pie (130) corresponde a un borde del rigidizador configurado para estar en contacto con un panel de una aeronave, y donde el alma (120) corresponde a la parte restante del rigidizador y la cual comprende un borde del alma (120a), el método de manufactura comprende las siguientes etapas:
- obtener dos laminados de material compuesto (110a, 110b) que comprenden un conjunto de capas de material compuesto;
- conformar cada uno de los dos laminados de material compuesto (110a, 110b) mediante el doblado de los laminados de material compuesto (110a, 110b) cada uno con una sección trasversal en "L”;
- unir los dos laminados de material compuesto (110a, 110b) para obtener la preforma (100) con una sección trasversal en "T”;
- moldear el borde del alma (120a) para obtener una sección trasversal del borde del alma (120a) semicircular;
- aplicar al borde del alma (120a) una tira de fibra de vidrio semicurado (L1) y una tira de fibra de vidrio preimpregnado (L2) en fresco y
- curar la preforma (100) para obtener el rigidizador con una sección trasversal en "T” con el borde del alma (120a) a neto.
2. Método de manufactura de acuerdo con la reivindicación 1, que además comprende aplicar calor al borde del alma (120a) para ablandar el conjunto de capas de material compuesto.
3. Método de manufactura de acuerdo con las reivindicaciones 1 o 2, que además comprende:
- aplicar a la preforma una bolsa de vacío flexible (L3) previamente a la etapa de curar la preforma (100); y
retirar la bolsa de vacío flexible (L3) después de dicha etapa.
4. Método de manufactura de acuerdo con las reivindicaciones anteriores, , que además comprende moldear el borde del alma (120a) para obtener una sección trasversal en cuña previa a la sección trasversal semicircular.
5. Rigidizador que comprende una geometría específica con una sección transversal en "T” obtenido mediante el método de manufactura de acuerdo con las reivindicaciones 1 a 4.
6. Dispositivo (1000) para el moldeado de un borde de un alma (120a) de una preforma (100) de un rigidizador de material compuesto polimérico reforzado con fibra de carbono, CFRP, con una sección trasversal en "T”, donde el rigidizador comprende un alma (120) y un pie (130), donde el pie (130) corresponde a un borde del rigidizador configurado para estar en contacto con un panel de una aeronave, y donde el alma (120) corresponde a la parte restante del rigidizador, el dispositivo (1000) comprende: - un dispositivo de aplicación de calor (300) configurado para ablandar el borde del alma (120a) de la preforma (100); y
- un conjunto de rodillos configurados para moldear el borde del alma (120a) para obtener una sección trasversal semicircular.
7. El dispositivo (1000) de acuerdo con la reivindicación 6, donde el conjunto de rodillos comprende un grupo de rodillos en cuña (310) configurados para moldear el borde del alma (120a) para obtener una sección trasversal en cuña.
8. El dispositivo (1000) de acuerdo con la reivindicación 7, donde el conjunto de rodillos comprende un grupo de rodillos de redondeado (311) configurados para moldear el borde del alma (120a) con forma de medialuna para obtener la sección trasversal semicircular.
ES202230738A 2022-08-09 2022-08-09 Métodos de manufactura de bordes de rigidizadores a neto Pending ES2961556A1 (es)

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ES202230738A ES2961556A1 (es) 2022-08-09 2022-08-09 Métodos de manufactura de bordes de rigidizadores a neto
EP23382783.1A EP4321329A2 (en) 2022-08-09 2023-07-27 Manufacturing methods of net stiffeners
CN202310969429.0A CN117584496A (zh) 2022-08-09 2023-08-03 网状加强筋的制造方法
US18/365,803 US20240051244A1 (en) 2022-08-09 2023-08-04 Manufacturing methods of net stiffeners

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Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080087768A1 (en) * 2006-06-14 2008-04-17 Airbus Uk Limited Aircraft component
US20110220006A1 (en) * 2007-08-08 2011-09-15 Airbus Uk Limited Composite laminate structure
US9676147B2 (en) * 2012-06-29 2017-06-13 Airbus Operations S.L. Method of manufacturing T-shaped stringer with a rounded web end

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080087768A1 (en) * 2006-06-14 2008-04-17 Airbus Uk Limited Aircraft component
US20110220006A1 (en) * 2007-08-08 2011-09-15 Airbus Uk Limited Composite laminate structure
US9676147B2 (en) * 2012-06-29 2017-06-13 Airbus Operations S.L. Method of manufacturing T-shaped stringer with a rounded web end

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US20240051244A1 (en) 2024-02-15
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