Patent Description:
It is known to use composite materials for curved walls in various applications. However, known walls of composite materials may not be hermetic, especially for liquids or gases.

<CIT> discloses a composite aircraft fuselage section comprising a symmetrical hybrid laminate layup, the layup comprising laminated together:(a) a first layer <NUM> of metal foil comprising an outer surface of the fuselage section; (b) a first hoop ply <NUM> comprising commonly aligned carbon fibers embedded in a polymeric matrix; c) a second layer <NUM> of metal foil; d) a second a hoop ply <NUM> comprising commonly aligned carbon fibers embedded in a polymeric matrix. The metal foil comprise a titanium alloy. The metal foil has thickness of <NUM>-<NUM> (<NUM> to <NUM> inches). The first and second layers of metal foil comprise butt-joined foils.

An object of the invention is to provide a curved wall having an especially high tightness.

According to this first aspect, the invention provides a curved wall comprising, in this order:.

The presence of a metal layer between the composite layers creates a barrier for molecules, which increases the tightness of the wall. The use of strips for the metal layer, narrower than <NUM>, helps for following the curved shape: a foil of higher width may create folds when following the curve. The low thickness of the metal strips provides an especially light wall, which is interesting for aero-spatial applications. Because of its ductility, the titanium-based material makes the rupture of the stress introduction point more progressive in case of an overload on the curved-wall. The combination of the carbon fibers and the titanium-based material is especially interesting because there is no galvanic corrosion between these materials, and their coefficients of thermal expansion are close. This is especially interesting for cryogenic applications where micro cracks may appear, impeding tightness.

In the frame of the present document, a "titanium-based material" is made of titanium and/or an alloy comprising at least <NUM>% of titanium in atomic percent, preferably at least <NUM>%. Examples are Ti-6Al-4V, Ti-15V-3Cr-3Al-3Sn or Ti-6Al-7Nb.

The external surface of the wall may be a metal layer or a composite layer. The internal surface of the wall may be a metal layer or a composite layer.

The thickness of the first and second composite layers is preferably between <NUM> and <NUM>.

Preferably, the metal strips of any of the layer have the same width. The width of the metal strips may change, or not, between metal layers.

The curved wall preferably comprises a third metal layer and a third composite layer located between the second and the third metal layers.

The first metal layer is preferably in contact with the first composite layer and the second composite layer. The second metal layer is preferably in contact with the second composite layer, and possibly also with a third composite layer.

If the radius of curvature of the internal surface of the curved wall is below <NUM> meter, the width of the metal strips is preferably below <NUM>.

In an embodiment of the invention, the curved wall has at least one region where it is non-developable. In a non-developable region, a metal foil cannot follow the shape of the wall. Metal strips are therefore especially interesting. A non-developable region of the wall is a region where the Gauss curvature is different than zero.

In an embodiment of the invention, the curved wall comprises a second metal layer such that the second composite layer is between the first metal layer et and the second metal layer, the second metal layer comprising metal strips of titanium-based material having a thickness between <NUM> and <NUM> and a width between <NUM> and <NUM>, and covering at least <NUM>% of the surface of the second metal layer.

In an embodiment of the invention, at least some of the metal strips of the first metal layer are parallel to a first direction and at least some of the metal strips of the second metal layer are parallel to a second direction different from the first direction. Having metal strips in different directions improves the mechanical properties and the tightness of the wall. At least some of the metal strips of the third metal layer are preferably in a direction than is different from the first direction and from the second direction. The directions of the metal strips is preferably such that there is an angle between <NUM>° and <NUM>° between two successive metal layers.

In an embodiment of the invention, the carbon fibers of the second composite layer are included in carbon-based strips. The width of the carbon-based strips is preferably between <NUM> and <NUM>, more preferably between <NUM> and <NUM>.

In the frame of the present document, a "carbon-based strip" is a strip comprising carbon fibers. It may also comprise a resin, preferably an epoxy.

In an embodiment of the invention, at least some of the carbon-based strips of the second composite layer are parallel to a third direction.

The third direction is different from the first direction and from the second direction. Therefore, the strips are in different directions in three layers, which improves the mechanical properties of the curved wall. The directions of the carbon-based strips is preferably such that there is an angle between <NUM>° and <NUM>° between two successive composite layers.

The directions of the metal strips and the carbon-based strips is preferably such that there is an angle between <NUM>° and <NUM>° between two adjacent layers, one of the adjacent layers being a metal layer and the other being a composite layer.

It is possible that the second composite layer comprise several composite sub-layers with carbon-based strips in different directions.

In an embodiment of the invention, the carbon-based strips have a width that is at most ten times the width of the metal strips of the first metal layer, and/or the width of the metal strips of the first metal layer is at most ten times the width of the carbon-based strips. This makes easier the production of the wall.

In an embodiment of the invention, the distance between two successive metal strips of the first metal layer is lower than <NUM>, preferably lower than <NUM>. Two successive metal strips may partially overlay. They are preferably placed next to each other with a distance as small as possible. However, the invention works even with a distance that is not extremely small, of the order of a few millimeters. It may also happen that the distance between two successive metal strips change because of the curvature of the wall.

In an embodiment of the invention, the curved wall comprises, at an interface between one of the composite layers and the first metal layer, a bonding agent comprising a complex of an organometallic and an organosilane. The bonding agent may be any material improving the adhesion between the composite layer and the metal layer. It may be in a layer between the composite layer and the metal layer, and/or included in the composite layer.

An object of the invention is a fuel tank for liquid and/or gaseous fuel comprising such a curved wall. The fuel tank is preferably a cryogenic fuel tank suitable for containing fuel at temperatures below <NUM>. The fuel may be gaseous and/or liquid hydrogen. The fuel tank has preferably a non-developable curved wall, for example a spherical wall. The curved wall according to the invention may be included at least in the non-developable parts of the fuel tank wall. The metal layer, or the plurality of metal layers, is preferably closer to the internal surface of the wall than the external surface of the wall.

An object of the invention is an aircraft nose comprising such a curved wall. The curved wall according to the invention provides an especially high resistance to erosion. Moreover, the metal layers may be used as heating resistances to heat the aircraft nose. Many other applications of the curved wall are possible.

An object of the invention is a method for producing a curved wall comprising the successive steps of :.

The shift between two successive parallel metal strips is automated.

Filament winding and/or automated fiber placement may be used to produce a curved wall according to the invention.

The tension is preferably applied by a tension application device.

The carbon-based strips may also be applied on the underlying metal layer by the automated tool.

The shape of the curved wall is programmed in the automated tool in such a way that the positioning of the metal strips is automated.

The step of forming the second metal layers preferably comprises applying metal strips of titanium-based material on the second composite layer, in such a way that a mechanical tension is created between the part of the metal strips already placed on the second composite layer and the part of the metal strips to be placed on the second composite layer. The second metal layer is preferably formed with an automated tool, which is preferably the same as the one used for the first metal layer.

In an embodiment of the invention, after being placed on the first composite layer, the metal strips of the first metal layer are pressed against the first composite layer. It improves the positioning and the adhesion. The pressure is preferably applied by a compression device, for example a roller. The compression device moves. Its motion is automated.

In an embodiment of the invention, the automated tool comprises a mobile part, which comprises an application guide positioning the part of the metal strips to be applied with respect to the first composite layer or the second composite layer. The mobile application guide improves the positioning. Its motion is automated.

In an embodiment of the invention, wherein the part of the metal strips to be applied is heated or cooled before being placed on the first composite layer or the second composite layer. The temperature is preferably increased or decreased by a heating and/or cooling device.

For a better understanding of the present invention, reference will now be made, by way of example, to the accompanying drawings in which:.

The present invention will be described with respect to particular embodiments and with reference to certain drawings but the invention is not limited thereto. The described functions are not limited by the described structures.

The term "comprising", used in the claims, should not be interpreted as being restricted to the elements or steps listed thereafter; it does not exclude other elements or steps. It needs to be interpreted as specifying the presence of the stated features, integers, steps or components as referred to, but does not preclude the presence or addition of one or more other features, integers, steps or components, or groups thereof. Thus, the scope of the expression "a device comprising A and B" should not be limited to devices consisting only of components A and B, rather with respect to the present invention, the only enumerated components of the device are A and B, and further the claim should be interpreted as including equivalents of those components.

On the figures, identical or analogous elements may be referred by a same number.

<FIG> illustrates a curved wall <NUM> in an embodiment of the invention. The curved wall <NUM> comprises a first composite layer <NUM>, a first metal layer <NUM>, a second composite layer <NUM>, and, preferably, a second metal layer <NUM>. It may also comprise a third composite layer <NUM>, a third metal layer <NUM>, and a fourth composite layer <NUM>. The curved wall <NUM> preferably comprise an alternation of metal and composite layers on a thickness higher than <NUM> and lower than <NUM>, more preferably lower than <NUM>. It may for example include at least ten composite layers interposed between at least eleven metal layers.

The composite layers <NUM>, <NUM> comprise carbon fibers and, preferably a resin. The composite layers <NUM>, <NUM> may comprise carbon-based strips <NUM>. The composite layers <NUM>, <NUM> preferably have a thickness <NUM> below <NUM>. The composite layers <NUM>, <NUM> are preferably thicker than the metal layers <NUM>, <NUM>.

Since the composite layers <NUM>, <NUM> are made of an elastic material, the metal layers <NUM>, <NUM> may be integrated within one or two of the adjacent composite layers <NUM>, <NUM>.

The metal layers <NUM>, <NUM> comprise metal strips <NUM> of titanium-based material. The metal strips <NUM> have a thickness <NUM> between <NUM> and <NUM>, preferably between <NUM> and <NUM>. Within a metal layer <NUM>, <NUM>, they are preferably parallel to each other. They may be separated by a lateral distance <NUM> below <NUM>, preferably below <NUM>, in such a way that at least <NUM>% of the surface of any the metal layers <NUM>, <NUM> is made of metal strips <NUM>. The metal strips <NUM> may partially overlay. In such a case, there is preferably an adhesive on the interface between the two metal strips <NUM>.

Within a metal layer <NUM>, <NUM>, the metal strips <NUM> preferably have identical width <NUM> (<FIG>) and/or identical thickness <NUM>. Preferably, the width <NUM> (<FIG>) of the metal strips <NUM> of the first <NUM> and second <NUM> metal layers is identical.

The apparent difference in width between the metal strips <NUM> (or the carbon-based strips) in <FIG> comes from the difference in direction of the strips between the layers, as illustrated on <FIG>, which may create cross-sections of different sizes even for strips of the same width.

A bonding agent may be present between, one the one side, the metal of the metal layers <NUM>, <NUM> and, on the other side, the resin and/or the carbon of the composite layers <NUM>, <NUM>. It is applied on the metal and/or the composite before there are joined. In an embodiment of the invention, an organometallic and an organosilane are mixed to create a complex which forms the bonding agent. The bonding agent may be a sol-gel.

<FIG> illustrates the first metal layer <NUM> in an arrangement wherein it comprises two sub-layers <NUM>, <NUM>. The metal strips <NUM> of the sub-layers <NUM>, <NUM> may be aligned in different directions. There is preferably an adhesive where the two metal strips <NUM> are in contact with each other, for example at the interface <NUM> between the sub-layers <NUM>, <NUM>. The space lateral space <NUM> between two metal strips <NUM> of any of the sub-layers <NUM>, <NUM> is preferably filled with resin and/or with the adhesive.

<FIG> shows a superposition of composite <NUM>, <NUM> and metal <NUM>, <NUM> layers. The metal strips <NUM> of the first layer <NUM> are parallel to a first direction <NUM>. The metal strips <NUM> of the second layer <NUM> are parallel to a second direction <NUM>, which is tilted with respect to the first direction <NUM>, preferably by an angle of at least <NUM>°. The first direction <NUM> and the second direction <NUM> make preferably an angle between <NUM>° and <NUM>°. The carbon-based strips <NUM> of the second composite layer <NUM> are parallel to a third direction <NUM>, which is tilted with respect to the first direction <NUM> and to the second direction <NUM>, preferably by angles of at least <NUM>°. The carbon-based strips <NUM> of the first composite layer <NUM> are parallel to a fourth direction <NUM>, which is tilted with respect to the first direction <NUM> and to the third direction <NUM>, preferably by angles of at least <NUM>°.

Preferably, the width <NUM> of the metal strips <NUM> is not more than ten times larger than the width <NUM> of the carbon-based strips <NUM>, and/or the width <NUM> of the carbon-based strips <NUM> is not more than ten times larger than the width <NUM> of the metal strips <NUM>. This preferably applies even if the metal strips <NUM> of different metal layers <NUM>, <NUM> have different widths, and/or the carbon-based strips <NUM> of different composite layers <NUM>, <NUM> have different widths.

<FIG> illustrates two examples of curved walls <NUM> having at least one region where the wall is not developable.

<FIG> shows a fuel tank <NUM>. It comprises an opening <NUM>. The internal surface of the fuel tank <NUM> may be a metal layer of the curved wall <NUM>, as illustrated, or a composite layer of the curved wall <NUM>. It may also be another layer coated on a curved wall <NUM>, even if this embodiment is less preferred.

<FIG> shows a nose <NUM> of an aircraft. The external surface is preferably a metal layer.

<FIG> schematized an automated tool <NUM> placing the first metal layer <NUM> on the first composite layer <NUM> (not shown) already shaped as a curved wall under construction <NUM>.

The automated tool <NUM> preferably comprises a support <NUM> for a spool <NUM> of a carbon-based ribbon <NUM> that will be cut in carbon-based strips <NUM>. The support <NUM> also supports a spool <NUM> of metal ribbon <NUM> that will be cut in metal strips <NUM>. The ribbons <NUM>, <NUM> may be cut before being applied on the curved wall under construction <NUM> or after at least one part of them has been applied on the curved wall under construction <NUM>. The automated tool <NUM> preferably comprises a guiding system <NUM> guiding the ribbon <NUM> being placed between the spool <NUM> and an application guide <NUM>. The ribbon <NUM> may be heated or cooled by a heating and/or cooling device <NUM>.

The resin is preferably present in the carbon-based ribbon <NUM>, and some additional resin may be added later in the production process.

The bonding agent may be present on at least one of the ribbons <NUM>, <NUM> on the spool <NUM>, <NUM> or may be placed on at least one of the ribbons <NUM>, <NUM> by the automated tool <NUM>.

The automated tool <NUM> may comprise a mobile part <NUM>, for example comprising an arm <NUM> and a mobile head <NUM>. The automated tool <NUM> comprises a tension application device <NUM> which applies a tension, preferably by pulling, on the part <NUM> of the metal strips <NUM> to be placed on the first composite layer <NUM>, to keep it taut with respect to the part <NUM> of the metal strips <NUM> already placed on the first composite layer <NUM> and adhering to the curved wall under construction <NUM>. The automated tool <NUM> may comprise a compression device <NUM> pressing on the part <NUM> of the metal strips <NUM> placed on the first composite layer <NUM>.

After application of all the layers <NUM>, <NUM>, <NUM>, <NUM> etc, the curved wall <NUM> is preferably heated to cure the resin.

Claim 1:
Curved wall (<NUM>) comprising, in this order:
• a first composite layer (<NUM>),
• a first metal layer (<NUM>), and
• a second composite layer (<NUM>);
wherein the first (<NUM>) and second (<NUM>) composite layers comprise carbon fibers;
wherein the first (<NUM>) metal layer comprises metal strips (<NUM>) of titanium-based material;
wherein the metal strips (<NUM>) have a thickness (<NUM>) between <NUM> and <NUM> and a width (<NUM>) between <NUM> and <NUM>;
wherein the metal strips (<NUM>) of the first metal layer (<NUM>) cover at least <NUM>% of the surface of the first metal layer (<NUM>).