Internal cladding part for cladding a fuselage structure of an aircraft
An internal cladding part for cladding a fuselage structure of an aircraft is disclosed having a first cover layer that extends in a planar manner, a second cover layer that extends in a planar manner, a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity, and an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner. The insulation structure is disposed in the receptacle cavity between the first and the second cover layer.
1. A fuselage structure for an aircraft, comprising:
a multiplicity of formers which are disposed so as to be mutually spaced apart along a fuselage longitudinal direction (L 100 ) and define a fuselage interior space (IR);
an internal cladding part, comprising
a first cover layer that extends in a planar manner;
a second cover layer that extends in a planar manner;
a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity; and
an insulation structure having a porous insulation core and an evacuated film sheath completely enclosing and encasing the insulation core in a gas-tight manner;
wherein the insulation structure is disposed in the receptacle cavity between the first and the second cover layer, which in terms of the fuselage longitudinal direction (L 100 ) the internal cladding part is disposed in the fuselage interior space (IR) so as to overlap with at least one former;
wherein the insulation structure of the internal cladding part in terms of the fuselage longitudinal direction (L 100 ) is disposed so as to overlap with the former.
2. A fuselage structure for an aircraft, comprising:
a multiplicity of formers which are disposed so as to be mutually spaced apart along a fuselage longitudinal direction (L 100 ) and define a fuselage interior space (IR);
an internal cladding part, having
a first cover layer that extends in a planar manner;
a second cover layer that extends in a planar manner;
a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cavity; and
an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner;
wherein the insulation structure is disposed in the receptacle cavity between the first and the second cover layer, which in terms of the fuselage longitudinal direction (L 100 ) the internal cladding part is disposed in the fuselage interior space (IR) so as to overlap with at least one former;
wherein the insulation structure of the internal cladding part in terms of the fuselage longitudinal direction (L 100 ) is disposed so as to overlap with the former, the fuselage structure further comprising
a planar external skin which is fastened to former bases of the formers;
a primary insulation having first insulation mats which are disposed on an internal face of the external skin that faces the fuselage interior space (IR), between two formers which are successive in the fuselage longitudinal direction (L 100 ), and having second insulation mats which cover in each case one former head of a respective former that faces the interior space (IR).
3. A fuselage structure for an aircraft, comprising:
a multiplicity of formers which are disposed so as to be mutually spaced apart along a fuselage longitudinal direction (L 100 ) and define a fuselage interior space (IR);
an internal cladding part, having
a first cover layer that extends in a planar manner;
a second cover layer that extend in a planar manner;
a core layer which is disposed between the first and the second cover layer and is connected to the first and the second cover layer and defines a receptacle cover; and
an insulation structure having a porous insulation core and an evacuated film sheath that encases the insulation core in a gas-tight manner;
wherein the insulation structure is disposed in the receptacle cavity between the first and the second cover layer, which in terms of the fuselage longitudinal direction (L 100 ) the internal cladding part is disposed in the fuselage interior space (IR) so as to overlap with at least one former;
wherein the insulation structure of the internal cladding part in terms of the fuselage longitudinal direction (L 100 ) is disposed so as to overlap with the former, wherein an end region of the internal cladding part is in each case disposed between two formers which are successive in the fuselage longitudinal direction (L 100 ).
4. The fuselage structure according to claim 1 , wherein a plurality of internal cladding parts are disposed in succession in the fuselage longitudinal direction (L 100 ), and wherein a connecting strip is disposed on a joint between a first internal cladding part ( 1 A) and a second internal cladding part ( 1 B) which is successive in the fuselage longitudinal direction (L 100 ).
5. The fuselage structure according to claim 4 , wherein the first and the second internal cladding part are configured such that a first end region of the internal cladding part forms a first connection structure, and wherein a second end region of the internal cladding part that lies opposite the first end region forms a second connection structure, and wherein the connecting strip is connected to the first connection structure of the first internal cladding part and to the second connection structure of the second internal cladding part.
6. The fuselage structure according to claim 4 , wherein the connecting strip on a rear side that is oriented so as to face away from the fuselage interior space (IR) has an insulation layer.
7. The fuselage structure according to claim 1 , wherein the porous insulation core is formed by a pulverulent material.
8. The fuselage structure according to claim 1 , wherein the insulation structure has a thickness in a range between 3 mm and 11 mm and extends between the first and the second cover layer.
9. The fuselage structure according to claim 1 , wherein the first cover layer and the second cover layer are in each case formed from a fiber-reinforced plastics material.
10. The fuselage structure according to claim 1 , wherein the first connection structure has a groove, and the second connection structure has a tongue.
11. The fuselage structure according to claim 2 , wherein the porous insulation core is formed by a pulverulent material.
12. The fuselage structure according to claim 2 , wherein the insulation structure has a thickness in a range between 3 mm and 11 mm and extends between the first and the second cover layer.
13. The fuselage structure according to claim 2 , wherein the first cover layer and the second cover layer are in each case formed from a fiber-reinforced plastics material.
14. The fuselage structure according to claim 2 , wherein the first connection structure has a groove, and the second connection structure has a tongue.
15. The fuselage structure according to claim 3 , wherein the porous insulation core is formed by a pulverulent material.
16. The fuselage structure according to claim 3 , wherein the insulation structure has a thickness in a range between 3 mm and 11 mm and extends between the first and the second cover layer.
17. The fuselage structure according to claim 3 , wherein the first cover layer and the second cover layer are in each case formed from a fiber-reinforced plastics material.
18. The fuselage structure according to claim 3 , wherein the first connection structure has a groove, and the second connection structure has a tongue.