Line system arrangement in an aircraft or spacecraft having a fuselage
View Patent ↗A line system arrangement in an aircraft or spacecraft having a fuselage includes at least one receiving region for receiving at least one component of a line system, wherein the at least one receiving region is accessible, at least in some sections, from outside the fuselage of the aircraft and spacecraft for installation and/or maintenance of the line system; and an aircraft or spacecraft with a corresponding arrangement.
1. A line system arrangement in an aircraft or spacecraft having a fuselage, comprising at least a first receiving region and a second receiving region, wherein the first and second receiving regions each receive at least one component of a line system, wherein the component of the line system in at least one of the first and second receiving regions is a line for gaseous substances, wherein the receiving regions are accessible, at least in some sections, from outside the fuselage of the aircraft or spacecraft for at least one of installation and maintenance of the line system, and wherein the first and second receiving regions are adapted to an internal pressure which corresponds to a particular external pressure of the fuselage, wherein the arrangement comprises a pressure-tight separating device for pressure-tight separation of the first and second receiving regions from an interior space of the fuselage, and wherein the pressure-tight separating device comprises a connecting device for connecting the line for gaseous substances to a consumption unit and wherein the first receiving region is arranged along the length of the fuselage and wherein the second receiving region is arranged at an angle to the first receiving region along the circumference of the fuselage.
2. The arrangement according to claim 1 , wherein at least the first receiving region extends along an inner wall of the fuselage in a longitudinal direction of the fuselage.
3. The arrangement according to claim 1 , wherein at least the second receiving region extends along an inner wall of the fuselage at an angle to the longitudinal direction of the fuselage.
4. The arrangement according to claim 3 , wherein at least the second receiving region extends along an inner wall of the fuselage in a direction perpendicular to the longitudinal direction of the fuselage.
5. The arrangement according to claim 1 , wherein at least one of the first and second receiving regions is arranged outside an impact region of the fuselage.
6. The arrangement according to claim 1 , wherein the line system further comprises at least one of an electric line, a line for liquid and a supporting element for the line system.
7. The arrangement according to claim 6 , wherein the pressure-tight separating device comprises a connecting device for connecting the electric line to a power supply unit.
8. The arrangement according to claim 6 , wherein the pressure-tight separating device comprises a connecting device for connecting the line for liquid to a consumption unit.
9. The arrangement according to claim 1 , wherein at least one of the first and second receiving regions comprises a closable opening serving as an access region.
10. The arrangement according to claim 9 , wherein the closable opening of the at least one of the first and second receiving regions can be closed by at least one removable outer wall section.
11. The arrangement according to claim 10 , wherein the at least one removable outer wall section is designed to at least one of absorb and pass on forces occurring in the fuselage.
12. The arrangement according to claim 10 , wherein the at least one removable outer wall section is attached releasably to the at least one of the first and second receiving regions by means of fastening elements.
13. The arrangement according to claim 9 , wherein the removable outer wall section is designed as a section of an outer wall of the fuselage with a contour matched to said outer wall.
14. The arrangement according to claim 9 , wherein the line system is designed as a premanufactured subassembly in such a manner that the line system can be placed into the at least one of the first and second receiving regions via the closable opening.
15. An aircraft or spacecraft with a line system arrangement according to claim 1 .
16. The arrangement according to claim 1 , wherein the line for gaseous substances is an oxygen line and the pressure-tight separating device comprises the connecting device for connecting the oxygen line to an oxygen supply.