CABIN LINING ELEMENT FOR AN AIRCRAFT CABIN AND RIB FOR AN AIRCRAFT FUSELAGE STRUCTURE

Abstract

A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side and a cabin side. The cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side. A rib is provided for an aircraft fuselage structure, having at least one foot portion on the outer skin facing side and a cabin facing side head portion. The rib comprises an electrically contactable heating lacquer layer at least in regions on a side of the head portion facing the cabin. As a result of the heating lacquer layer, it is possible to omit insulation which otherwise surrounds the rib heads and, as a consequence, to enlarge the width of the cabin.

Claims

1-11. (canceled)

12. A cabin lining element for an aircraft cabin which is arranged in the interior of an aircraft fuselage structure, having a fuselage structure side, and a cabin side, wherein the cabin lining element comprises an electrically contactable heating lacquer layer at least in regions on its fuselage structure side.

13. A rib for an aircraft fuselage structure, comprising at least one foot portion on an outer skin facing side, and one cabin facing side head portion, wherein the rib comprises an electrically contactable heating lacquer layer at least in regions on a cabin-facing side of the head portion.

14. A system including a cabin lining element as claimed in claim 12.

15. The system as claimed in claim 14, wherein no cabin-lining-element-side or rib-head-side insulation is arranged in the regions of the heating lacquer layer.

16. The system as claimed in claim 14, wherein the heating lacquer layer comprises a strip-shaped extent, a strip width of which corresponds substantially to a rib head width.

17. The system as claimed in claim 14, wherein a thickness of the heating lacquer layer is between 0.1 mm and 0.5 mm.

18. The system as claimed in claim 14, wherein an electrically insulating protective layer is provided between the heating lacquer layer and the cabin lining element.

19. The system as claimed in claim 14, additionally including two conductors to which the respective electrical poles of the heating lacquer layers are electrically connectable, and a power source, to which the conductors are electrically connectable.

20. The system as claimed in claim 19, wherein the system includes a plurality of cabin lining elements, wherein at least one of the two conductors is formed by busbars which are integrated in portions into adjacent cabin lining elements.

21. The system as claimed in claim 20, wherein the cabin lining elements comprise electrical connecting means for electrical contacting of adjacent busbars.

22. An aircraft including a cabin lining element as claimed in claim 12.

23. A system including a rib as claimed in claim 13.

24. The system as claimed in claim 23, wherein no cabin-lining-element-side or rib-head-side insulation is arranged in the regions of the heating lacquer layer.

25. The system as claimed in claim 23, wherein a thickness of the heating lacquer layer is between 0.1 mm and 0.5 mm.

26. The system as claimed in claim 23, wherein an electrically insulating protective layer is provided between the heating lacquer layer and the rib.

27. The system as claimed in claim 23, additionally including two conductors to which the respective electrical poles of the heating lacquer layers are electrically connectable, and a power source, to which the conductors are electrically connectable.

28. The system as claimed in claim 27, wherein the system includes a plurality of cabin lining elements, wherein at least one of the two conductors is formed by busbars which are integrated in portions into adjacent cabin lining elements.

29. The system as claimed in claim 28, wherein the cabin lining elements comprise electrical connecting means for electrical contacting of adjacent busbars.

30. An aircraft including a rib as claimed in claim 13.

31. An aircraft including a system as claimed in claim 14.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Identical reference symbols are used for identical or at least similar elements, components or aspects in the figures. It is noted that an embodiment is described in detail below which is simply illustrative and not limiting. In the claims, the word “comprising” does not exclude other elements and the indefinite article “a” does not exclude a plurality. Solely the circumstance of certain features being named in different dependent claims does not limit the object of the invention. Combinations of said features are able to be used in an advantageous manner. The reference symbols in the claims are not to limit the extent of the claims. The figures are not be understood to scale but are only schematic and illustrative in character, in which:

[0027] FIG. 1 shows a cross section through an aircraft fuselage external wall according to the prior art, including an aircraft fuselage structure and a cabin lining element,

[0028] FIG. 2 shows a longitudinal section through an aircraft fuselage external wall according to the prior art, including a fully insulated rib for an aircraft fuselage structure,

[0029] FIG. 3 shows a side view of a cabin lining element according to the invention,

[0030] FIG. 4 shows a longitudinal section through an aircraft fuselage external wall with a rib according to the invention,

[0031] FIG. 5 shows a side view of connecting means according to the invention for adjacent cabin lining elements,

[0032] FIG. 6 shows views, in the longitudinal direction of the aircraft, of the connecting means of the cabin lining elements from FIG. 5, and

[0033] FIG. 7 shows a side view of an aircraft according to the invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0034] FIG. 1 shows a conventional aircraft fuselage wall 10 in cross section. The aircraft fuselage wall 10 includes, on the one hand, an aircraft fuselage structure 12 with an outer skin 14 and a primary insulation 16 which is fastened to the aircraft fuselage structure 12. On the other hand, the aircraft fuselage wall 10 includes a cabin lining element 18 which is arranged on the cabin side and has secondary insulation 20. The primary insulation 16 typically covers the aircraft fuselage structure 12 on the side of the outer skin. The primary insulation 16 and the secondary insulation 20 are typically formed from insulating mats which are filled in their interior with glass wool. The thermal management and the temperature setting in the aircraft cabin is influenced as a result of arranging the primary and secondary insulation 16, 20 in the aircraft fuselage wall 10. The aircraft cabin is limited, among other things, by a plurality of cabin lining elements 18 which are adjacent and are arranged side by side in the longitudinal direction of the aircraft, each cabin lining element 18 being fastened indirectly to the aircraft fuselage structure 12.

[0035] FIG. 2 shows a longitudinal section through a conventional aircraft fuselage structure 12. The outer skin 14 is fastened to a rib 22 which comprises a foot portion 24 on the outer skin facing side and a cabin facing side head portion 26. The aircraft fuselage structure 12, that is to say, the outer skin 14 and the rib 22, are covered entirely by the insulation 16. In the region of the foot portion 26 of the rib 22, the insulation 16, which includes insulating mats of glass wool, is fastened to the rib 22 by clips 28 on both sides. In the case of the known aircraft fuselage structure 12, the insulation 16 is also arranged in the region of the head portion 26, in particular around the same, such that it is laid on, for instance, by the insulation thickness D in the direction toward the cabin.

[0036] FIG. 3 shows a cabin lining element 18′ according to the invention. The cabin lining element 18′ is suitable to be mounted on an aircraft fuselage structure (for example, the aircraft fuselage structure 12 described in FIG. 1) on the cabin side. It comprises a fuselage structure side 30 and a cabin side 32, an electrically contactable heating lacquer layer 34 being provided at least in regions on its fuselage structure side 30. The heating lacquer layer 34 is a thin coating of a heating lacquer which generates heat when current and/or voltage is applied. Electrically conductive carbon-based polymers are preferred, in particular, as heating lacquer.

[0037] According to the invention, the heating lacquer layer 34 is arranged on the cabin lining element 18′ in the regions of the fuselage structure side 32 which, with the cabin lining element 18′ in the installed state, are located directly opposite the respective ribs 22, in particular, the respective head portions 26. In FIG. 3, this is one heating lacquer layer 34′ which is arranged in a central region on the cabin lining element 18′ and two heating lacquer layers 34″ which are arranged in the regions of the front and rear edges 36 of the cabin lining element 18′. The heating lacquer layers 34′, 34″ comprise a strip-shaped extent, the strip width B of which corresponds substantially to a rib head width S (cf. FIG. 4). In FIG. 3, the strip width of the heating lacquer layer applied to the front and rear edges 36 amounts to approximately half the rib head width S/2 so that together with the respective adjacent cabin lining element 18′ approximately the full rib head width S is reached again.

[0038] Consequently, with the cabin lining element 18′ according to the invention in the installed state, the heating lacquer layers 34′, 34″ come to rest against the respectively corresponding head portions 26 of the oppositely situated rib 22 of the aircraft fuselage structure 12, without any insulation 16 being provided on the head portion 26 of the oppositely situated rib 22 (cf. FIG. 4). In other words: There is no rib-head-side or cabin-lining-element-side insulation 16 arranged in the region of the heating lacquer layer 34. It is consequently possible, as a result of the cabin lining element 18′ according to the invention, to dispense in an advantageous manner with any rib head insulation because by utilizing electric energy in order to heat the heating lacquer layers 34′, 34″, it is possible to compensate for the thermal loss due to the lack of insulation on the head portion 26.

[0039] Using the cabin lining element 18′, a system 38 is provided as a result of which it is no longer necessary to provide insulation on the ribs 22, which is typically laid on by the insulation thickness D (cf. FIG. 2) in the direction of the center of the cabin. The thickness of the heating lacquer layers 34′, 34″ can be between 0.1 mm and 0.5 mm in a preferred manner Consequently, it is possible to install the cabin lining elements 18′ closer to the aircraft fuselage structure 12 and, as a consequence, to enlarge the useful internal diameter of the cabin. In other words: As a result of the cabin lining element 18′, it is possible to reduce the distance between the fuselage structure 12 and the cabin lining element 18′.

[0040] The system 38, irrespective of whether it includes the cabin lining element 18′ and/or the rib 22 according to FIG. 4, can additionally comprise two conductors 40 by way of which the respective electrical poles 42′, 42″ of the heating lacquer layer 34′, 34″ can be electrically connected together. In addition, the system 38 also includes a power source 44 by way of which the conductors 40 are electrically connectable. The system 38 typically comprises a plurality of cabin lining elements 18′. These are then arranged on the aircraft fuselage structure 12 along the longitudinal direction of the cabin. The two conductors 40 are formed by busbars which are integrated in portions into adjacent cabin lining elements 18′.

[0041] FIG. 4 shows an alternative embodiment of the invention in the form a rib 22′. The rib 22′ comprises at least one foot portion 24 on the side of the outer skin and one cabin facing side head portion 26, the rib 22′ comprising an electrically contactable heating lacquer layer 46 at least in regions on a side of the head portion 26 facing the cabin. The heating lacquer layer 46 is, as in the case of the alternative cabin lining element 18′, a coating of a heating lacquer which generates heat when electrical current and/or voltage is applied. The thickness of the heating lacquer layer 46 is also, in a preferred manner, between 0.1 mm and 0.5 mm. The heating lacquer layer 46 is arranged on the side of the rib 22′ which faces the cabin, as a result of which the heating lacquer layer 46, with the cabin lining element 16 in the mounted state, comes to rest close to the fuselage structure side 30 thereof. The heating lacquer layer 46 comprises a strip-shaped extent, the strip width C thereof corresponding substantially to the rib head width S (cf. FIG. 4). In order to uncouple the heating lacquer layer 46 electrically from the fuselage structure 12, it is possible to provide an electrically insulating protective layer between the heating lacquer layer 46 and the rib 22′ (not shown).

[0042] In this way, with the cabin lining element 18, 18′ in the mounted state, the heating lacquer layer 46 of the rib 22′ comes to abut against the fuselage structure side 30 of the cabin lining element 18, 18′ without any insulation being arranged on the head portions 26. (The cabin lining element 18 can then also be realized in a conventional manner, i.e., without the heating lacquer layer 34 according to the invention). Accordingly, no rib-head-side or cabin-lining-element-side insulation 16 is provided in the region of the heating lacquer layer 46. Using the rib 22′ according to the invention, a system 48 is provided by means of which insulation, which would typically be laid by the insulation thickness D (cf. FIG. 2) in the direction of the center of the cabin, is no longer necessary on the head portions 26. Consequently, it is possible to install the cabin lining elements 18, 18′ closer to the aircraft fuselage structure 12 and, as a consequence, to enlarge the useful inside diameter of the cabin.

[0043] FIG. 5 and FIG. 6 show details of a side view and of a view directed in the longitudinal direction of the aircraft of two adjacent cabin lining elements 18′ according to FIG. 3 in the region of the conductors 40, which are realized by busbars. The cabin lining elements 18′ comprise electrical connecting means 50, 52 for the electrical contacting of the respectively adjacent busbars. The corresponding male and female connecting means 50, 52 can be realized, for example, as quick-closing electric plug-socket elements. Spring elements, which ensure secure and permanent contacting, can be provided for this purpose in each case on the male and female connecting means 50, 52.

[0044] Finally, FIG. 7 shows an aircraft 54, in the interior of which cabin lining elements 18′ and/or ribs 22′ and/or a corresponding system 38, 48 are provided.

[0045] 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.

LIST OF REFERENCES

[0046] 10 Aircraft fuselage wall [0047] 12 Aircraft fuselage structure [0048] 14 Outer skin [0049] 16 Primary insulation [0050] 18 Cabin lining element (prior art) [0051] 18′ Cabin lining element (according to the invention) [0052] 20 Secondary insulation [0053] 22 Rib (prior art) [0054] 22′ Rib (according to the invention) [0055] 24 Foot portion [0056] 26 Head portion [0057] 28 Clips [0058] 30 Fuselage structure side [0059] 32 Cabin side [0060] 34 Heating lacquer layer for cabin lining element (according to the invention) [0061] 34′ Heating lacquer layer for cabin lining element (according to the invention) [0062] 34″ Heating lacquer layer for cabin lining element (according to the invention) [0063] 36 Edges of the cabin lining element [0064] 38 System [0065] 40 Conductor [0066] 42′ Electrical pole [0067] 42″ Electrical pole [0068] 44 Power source [0069] 46 Heating lacquer layer for rib (according to the invention) [0070] 48 System [0071] 50 Electrical connecting means, female [0072] 52 Electrical connecting means, male [0073] 54 Aircraft (according to the invention) [0074] B Strip width [0075] C Strip width [0076] S Rib head width