Three dimensional auxetic structure, manufacturing method and tooling

Abstract

A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.

Claims

1. A three-dimensional auxetic structure, comprising: a plurality of adjoining hollow cells, each hollow cell having cell walls formed between adjoining hollow cells, wherein a transversal cross section of the plurality hollow cells form a two-dimensional auxetic pattern, wherein each cell wall comprises a plurality of folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are formed between the folding lines in the cell walls and the cell walls are foldable along said folding lines and the hollow cells are compressible in a direction perpendicular to the plane containing the auxetic pattern.

2. The three-dimensional auxetic structure, according to claim 1, wherein the two-dimensional auxetic pattern comprises hollow cells that are angled in the form of a polygon having a plurality of edges and vertices.

3. The three-dimensional auxetic structure, according to claim 2, wherein the polygon is a re-entrant hexagonal auxetic cell.

4. The three-dimensional auxetic structure, according to claim 1, wherein the cell walls are made from a sheet material.

5. The three-dimensional auxetic structure, according to claim 4, wherein the sheet material is a composite preform, a fabric or a unidirectional preform.

6. The three-dimensional auxetic structure, according to claim 5, wherein the composite preform sheet is a prepreg ply.

7. The three-dimensional auxetic structure, according to claim 4, wherein the sheet material is a thin metal sheet preform.

8. The three-dimensional auxetic structure, according to claim 1, wherein the cell walls are made from a thermoplastic material.

9. A sandwich panel comprising a core structure having a three-dimensional auxetic structure according to claim 1, located between an upper and a lower skin.

10. A fuselage of an aircraft comprising the sandwich panel according to claim 9 for absorbing impacts.

11. A lifting surface of an aircraft comprising the sandwich panel according to claim 9 for absorbing impacts.

12. A blade of an engine of an aircraft comprising the sandwich panel according to claim 9 for absorbing impacts.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

(1) To complete the description and in order to provide for a better understanding of the invention, a set of drawings is provided. The drawings form an integral part of the description and illustrate preferred embodiments of the invention. The drawings comprise the following figures.

(2) FIG. 1 shows an embodiment of a two-dimensional conventional honeycomb configuration and a two-dimensional modified auxetic honeycomb configuration known in the state of the art.

(3) FIG. 2 shows an embodiment of an embodiment of a foldable sheet material.

(4) FIG. 3 shows a perspective view of an embodiment of the three-dimensional hollow cell arrangement corresponding to the object of the invention.

(5) FIG. 4 shows a sectional view of a sandwich panel comprising a first embodiment having a three-dimensional auxetic structure according to the invention in which the structure is located with the hollow direction of the cells parallel to the upper and lower sandwich panels.

(6) FIG. 5 shows a sectional view of a sandwich panel comprising a second embodiment having a three-dimensional auxetic structure according to the invention in which the structure is located with the hollow direction of the cells perpendicular to the upper and lower sandwich panels.

(7) FIG. 6 shows a fuselage cross-section of an aircraft comprising an airframe integrated shield.

(8) FIG. 7 shows a fuselage cross-section of an aircraft comprising an airframe added shield.

(9) FIG. 8 shows a blade cross-section comprising an auxetic structure according to one embodiment of the invention.

(10) FIGS. 9 to 11 shows the process of cut and folding of the sheet of FIG. 2.

(11) FIG. 12 shows an embodiment of a tooling for manufacturing a three-dimensional auxetic structure.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

(12) FIG. 1 shows a known embodiment of a two-dimensional auxetic pattern (1) in which each cell (2) is angled in the form of a polygon having a plurality of edges and vertices, more specifically, a re-entrant hexagonal auxetic cell (2). Each cell (2) defines an internal air-filled cavity.

(13) Considering FIG. 3, the XY plane can be taken as the plane comprising the auxetic pattern (1) formed by cell walls (3) extending in a direction normal to the XY plane, the structure has an auxetic behavior on three dimensions. When the structure is contracted in one of the directions, X, Y or Z it contracts also on the other two directions, and when it is expanded in one direction X, Y or Z it expands also on the other two directions.

(14) The shown structure comprises a plurality of adjoining hollow cells (2), each hollow cell (2) having cell walls (3). The transversal cross section of the plurality hollow cells (2) follows a two-dimensional auxetic pattern (1) as shown in FIG. 1. Each cell wall (3) comprises folding lines (4) parallel to the plane containing the auxetic pattern (1) such that peaks and valleys are defined in the cell walls (3). The cell walls (3) are foldable along the folding lines (4) and therefore can be extended and compressed in the hollow direction of the cells (2).

(15) The claimed structure can be made by 3D printing using a thermoplastic or melting material or, as depicted in FIG. 2, it can be made from a sheet material, comprising zigzagging folding lines defining the cell walls (3) to obtain the desired configuration in order to achieve a three-dimension directions auxetic behavior from a continuous layer of, for instance, prepreg plies.

(16) FIG. 5 discloses a sectional view of a sandwich panel comprising a first embodiment having a three-dimensional auxetic core structure according to an embodiment of the invention in which the structure is located with the hollow direction of the cells (2) perpendicular to the upper and lower sandwich panels (10). When these sandwich panels are subjected to compression forces normal to the panels (10), the sandwich core tends to contract on the other two directions, generating a condensation of material on the impact point. This condensation of material provides additional capability to resist impact and penetration normal to the sandwich panel (10).

(17) Another advantage of this core is that the failure of the cell walls (3) is more progressive and transmits deformation to a larger part of the surrounding structure, so the cell walls are able to absorb more energy than the case when the cell walls (3) are not folded. On the conventional core without folded cell walls (3), they are rigid when they are stable but they become very soft and fail very fast when they start to buckle in compression without being able to deform the surrounding structure.

(18) One additional advantage of this core configuration is that when the distance between the panels (10) is not constant, this configuration is able to adapt to the variations of thickness or shape, as it is the case, for example, on an aerodynamic profile. In a conventional honeycomb core, it is necessary to perform machining in order to adapt to non-uniform sandwich thickness shapes.

(19) FIG. 4 discloses a sectional view of a sandwich panel comprising a second embodiment having a three-dimensional auxetic structure according to an embodiment of the invention in which the structure is located with the hollow direction of the cells (2) parallel to the upper and lower sandwich panels (10). This embodiment provides the additional advantage of not generating closed cells in between the sandwich panels allowing a better drainage of possible water ingested by the sandwich core.

(20) FIGS. 6, 7 and 8 show possible applications to an aircraft:

(21) Fuselage and empennage skins shielding against engine debris and other impact threats.

(22) Lifting surface LE shielding against bird and other impact threats.

(23) Sandwich can be just a panel surrounding the perimeter of aero dynamic profile or can cover the full cavity of the profile section or part of the profile section (LE, box or TE). The proposed core is able to adapt to thickness variations of the sandwich due to the profile non-contact thickness.

(24) Propeller and Turbofan engine blades.

(25) FIGS. 2 and 9 to 11 show an embodiment for the method for manufacturing a three-dimensional auxetic structure from a sheet material.

(26) The sheet material is the one disclosed in FIG. 2 having straight folding lines (20) in one direction for forming the walls of the cells (2) and kinked folding lines (21) in perpendicular direction to the straight folding lines (20), the folding lines (20, 21) defining the edges of the perimeter of the auxetic cell (2) pattern when folded.

(27) More specifically, FIGS. 2 and 9 to 10 show a pattern having a re-entrant hexagonal auxetic cell (2) from which a complete cell (2) and an omega (22), being the omega (22) half of a hexagonal cell (2), are formed by folding and cutting the sheet.

(28) In the specific embodiment of FIGS. 9 and 11, each of the walls (3) comprises three different folding lines and it is able to make up an omega (22) of the pattern. The sheet is cut along a fourth straight line (24) along the sections of the U-shape of the omega in first instance and along the eighth straight line along the sections different from the bottom section of the U-shape.

(29) The number of folded straight lines (4) in between the straight lines (24) containing the cut, can be a different number than three. This number determines the number of folding lines that comprises the cell walls (3) of the resulting three-dimensional auxetic structure.

(30) As showed on FIG. 2, a particularity of this method is that at the intersection of each straight folding line (20) with the kinked line (21), the kinked lines (21) are kinked in an opposite angle with the straight line (20), except at the intersection with the straight lines (24) containing the cut, where the kinked lines (21) are kinked with the same angle with the straight line (20).

(31) This methodology has the advantage that allows the generation of more than one row of omegas at a time with the same sheet to cover a large surface, by increasing the number of folded straight lines (20), instead of just one as described on FIGS. 2, 9 and 11.

(32) As showed in FIG. 11, once formed the omegas and cut, the straight lines (24) containing the cut are turned around so that the upper and lower parts of the U shape of the resulting segments are touching each other and can be joined together by bounding, co-curing or other mechanical joint to form the desired hollow structure ausxetic structure.

(33) An alternative methodology to generate the three-dimensional auxetic structure is to fold several independent sheets to generate each one a row of omegas that are joined by their upper and lower part of the U shapes of the omegas.

(34) FIG. 12 discloses an embodiment of the tooling to generate the row of omegas that comprises a rear panel (30) and a front panel (31) having corresponding counter panels (32, 33) and different blades (34) for forming the two legs of the omega shape which alternatively goes through the rear and front panels (30, 31). These blades (34) go through the tooling of the open side of the half-cell until and rest on a counter-panel part that shapes the closed side of the half cell. This is repeated alternatively for each of the half cells of the flat sheet.

(35) While at least one exemplary embodiment of the present invention(s) is disclosed herein, it should be understood that modifications, substitutions and alternatives may be apparent to one of ordinary skill in the art and can be made without departing from the scope of this disclosure. This disclosure is intended to cover any adaptations or variations of the exemplary embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a” or “one” do not exclude a plural number, and the term “or” means either or both. Furthermore, characteristics or steps which have been described may also be used in combination with other characteristics or steps and in any order unless the disclosure or context suggests otherwise. This disclosure hereby incorporates by reference the complete disclosure of any patent or application from which it claims benefit or priority.