FLOW BODY FOR AN AIRCRAFT WITH INTEGRATED GAS TANK

Abstract

A flow body for an aircraft includes a torsion box with spars and/or ribs and at least two skin portions for enveloping the spars and/or ribs, wherein at least one inner cell is formed in the torsion box. It is provided that a gas tank with a gas tank shell is arranged in the at least one inner cell, and that the gas tank includes fastening elements coupled to retaining elements in the relevant inner cell in order to hold the gas tank such that the gas tank shell is supported at a distance from the spars and/or ribs and the skin portions and is supported in three spatial directions.

Claims

1. A flow body for an aircraft, comprising: a torsion box comprising: a plurality of spars; and/or ribs; and at least two skin portions for enveloping the spars and/or ribs, wherein at least one inner cell is formed in the torsion box, wherein a gas tank with a gas tank shell is in the at least one inner cell, and wherein the gas tank comprises fastening elements coupled to retaining elements in a relevant inner cell to hold the gas tank such that the gas tank shell is supported at a distance from the spars and/or ribs and the skin portions and is supported in three spatial directions.

2. The flow body of claim 1, wherein the gas tank is a pressurized gas tank.

3. The flow body of claim 1, wherein the gas tank is configured to store liquid hydrogen.

4. The flow body of claim 1, wherein the flow body has a plurality of inner cells in which a plurality of independent gas tanks are arranged.

5. The flow body of claim 1, wherein the fastening elements are arranged on or coupled to the gas tank shell, and wherein the fastening elements comprise tension elements which are connected to the retaining elements.

6. The flow body of claim 5, wherein the tension elements are arranged symmetrically about at least one extension axis of the gas tank.

7. The flow body of claim 1, wherein the gas tank has an elongate shape, wherein a main extension axis runs parallel or angularly symmetrically to longitudinal stiffening elements arranged at the skin portions.

8. The flow body of claim 1, wherein the at least one inner cell is bounded at least by two spaced-apart spars and the skin portions.

9. The flow body of claim 1, wherein the gas tank comprises first fastening elements and second fastening elements coupled to retaining elements in the relevant inner cell, wherein the first fastening elements and the second fastening elements are attached to two spaced-apart longitudinal portions of the gas tank and are configured to be supported in different spatial directions.

10. The flow body of claim 1, wherein the torsion box comprises two, three or more planar box portions forming the torsion box when arranged adjacently in a row, wherein a plurality of inner cells are formed in each of the box portions, wherein at least one group of gas tanks are arranged in relevant inner cells in each box portion.

11. The flow body of claim 1, wherein the flow body is a vertical stabilizer or a horizontal stabilizer of an aircraft.

12. An aircraft comprising at least one flow body of claim 1.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Further features, advantages and possible applications of the disclosure herein will become apparent from the following description of the example embodiments and the figures. Here, all the features described and/or illustrated constitute the subject of the disclosure herein in themselves and in any combination, also irrespective of their composition in the individual claims or the back-references of the latter. Furthermore, in the figures, like reference signs are used for like or similar objects.

[0023] FIG. 1 shows a flow body as a vertical stabilizer in a partially cut side view.

[0024] FIG. 2 shows an enlargement of the view in FIG. 1.

[0025] FIG. 3 shows a plan view of a gas tank in an inner cell.

[0026] FIG. 4 shows two gas tanks in two adjacent inner cells.

[0027] FIG. 5 shows a front view of a gas tank in an inner cell.

[0028] FIG. 6 shows an aircraft with a vertical stabilizer designed in accordance with the disclosure herein.

DETAILED DESCRIPTION

[0029] FIG. 1 shows a flow body in the form of a vertical stabilizer 2. For orientation purposes, a coordinate system showing a longitudinal axis X, a lateral axis Y and a vertical axis Z of an aircraft on which the vertical stabilizer 2 is arranged is shown.

[0030] A torsion box 4 is a central, load-bearing component of the flow body 2. A hinge 8 is arranged on the trailing edge 6 of the flow body 2, by which hinge a rudder 10 is movably mounted. A leading edge 12 is provided on an opposite side. The torsion box 4 has a plurality of spars 14 extending between the leading edge 12 and the trailing edge 6 with an upwardly decreasing spacing. A first skin portion 16 (partially obscured in the drawing plane by the spars 14) and a second skin portion (omitted in this view) are disposed on the spars 14 and close the torsion box 4. This results in a plurality of inner cells 18. It is conceivable that the inner cells 18 may be divided in places by ribs (not shown here). Longitudinal stiffening elements in the form of stringers 20 are also arranged on the skin portions 16.

[0031] At a lower end of the flow body 2, four gas tanks 22 are visible, which are arranged in separate inner cells 18 and are designed to store a gas. In particular, this may be hydrogen. The gas tanks 22, by way of example, can be designed to store liquid hydrogen cryogenically.

[0032] FIG. 2 shows an enlarged view of the arrangement of the gas tanks 22. It can be seen that the gas tanks 22 are elongate or tubular and have rounded end caps. They each have a main extension axis 24, which may represent a longitudinal axis, which runs substantially parallel to the stringers 20.

[0033] FIG. 3 shows a plan view of a plane perpendicular to the extension axis 24 of a gas tank 22. The gas tank 22 has fastening elements 26 that are coupled to retaining elements 30 via tension elements 28. As will be explained further below, these fastening elements 26 are also referred to as second fastening elements. The retaining elements 30 may be positioned at intersections between spars 14 and the first skin portion 16 or an oppositely disposed second skin portion 32, where they are connected to the spars 14 and the skin portions 16 and 32. The tension elements 28 are configured to brace the gas tank 22 against the retaining elements 30. For this purpose, four second fastening elements 26 by way of example are distributed regularly and symmetrically around the longitudinal extension axis 24 along the circumference of the gas tank 22. The tension elements 28 can further be designed to achieve a damping effect by selection of a suitable material and a corresponding stretching behavior.

[0034] A plurality of gas tanks 22 in adjacent inner cells 18 are shown in FIG. 4. Here, it can be seen that the gas tanks 22 are spaced a certain distance from inner surfaces 34 of the inner cell 18. This can prevent damage caused by the gas tanks 22 striking against the inner surfaces 34. At the same time, heat input into the gas tanks 22 could be reduced, particularly when cryogenic gas tanks 22 are used.

[0035] FIG. 5 shows the gas tank 22 in a front view approximately perpendicular to a spar 14. Here, first fastening elements 36 are visible, which are coupled to the retaining elements 30 by the tension elements 28 and fix the gas tank 22 substantially in the X and Y direction. The first fastening elements 36 are found both at an upper first end portion 38 of the gas tank 22, and at a lower second end portion 40 of the gas tank 22. By way of example, they are annular in shape and may include eyelets, flanges, or other means to permit fastening of the tension elements 28. Similarly, the retaining elements 30 are arranged laterally adjacent to the first fastening elements 36. The second fastening elements 26 are arranged centrally between the first end portion 38 and the second end portion 40 and are likewise braced with the retaining elements 30 via tension elements 28. They can also have an annular structure 42, via which they are connected to the gas tank 22. This can be used in particular for fixing in the Z direction.

[0036] Lastly, FIG. 6 shows an aircraft 44, which has a vertical stabilizer 2 designed according to the principles presented above.

[0037] It should additionally be noted that “comprising” does not exclude other elements or steps, and “a” or “one” does not exclude a plurality. Further, it should be noted that features that have been described with reference to any of the above example embodiments may also be used in combination with other features of other example embodiments described above. Reference signs in the claims are not to be considered as a limitation.

[0038] While at least one example 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 example embodiment(s). In addition, in this disclosure, the terms “comprise” or “comprising” do not exclude other elements or steps, the terms “a”, “an” 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.

REFERENCE SIGNS

[0039] 2 flow body/vertical stabilizer [0040] 4 torsion box [0041] 6 trailing edge [0042] 8 hinge [0043] 10 rudder [0044] 12 leading edge [0045] 14 spar [0046] 16 first skin portion [0047] 18 inner cell [0048] 20 stringer [0049] 22 gas tank [0050] 24 main extension axis [0051] 26 second fastening element [0052] 28 tension element [0053] 30 retaining element [0054] 32 second skin portion [0055] 34 inner surface [0056] 36 first fastening element [0057] 38 first end portion [0058] 40 second end portion [0059] 42 annular structure