Aircraft fuselage section
An aircraft section comprising a first fuel storage tank and a second fuel storage tank arranged in a caudal tandem configuration. The corresponding casings, housing conduits configured for distribution of fuel to and from inside the tanks, are arranged in a common section of the fuselage and spaced between them. Also an aircraft with such a section.
1. An aircraft fuselage section of an aircraft extending along a longitudinal direction, wherein the aircraft fuselage section comprises:
a first fuel storage tank and a second fuel storage tank arranged in a caudal tandem configuration, such that the second fuel storage tank is arranged consecutively with respect to the first fuel storage tank according to the longitudinal direction;
wherein the first fuel storage tank comprises a first end portion oriented towards the second fuel storage tank, and the second fuel storage tank comprises a second end portion oriented towards the first fuel storage tank, such that a fuselage subsection is defined between the first end portion of the first fuel storage tank and the second end portion of the second fuel storage tank;
wherein the aircraft fuselage section further comprises:
a first casing arranged at the first end portion of the first fuel storage tank, the first casing being configured to house at least two conduits in fluid communication with an interior of the first fuel storage tank, such that the at least two conduits pass through the first casing, and
a second casing arranged at the second end portion of the second fuel storage tank, the second casing being configured to house at least two conduits in fluid communication with an interior of the second fuel storage tank, such that the at least two conduits pass through the second casing;
and wherein:
the first casing extends from the first end portion of the first fuel storage tank into the fuselage subsection,
the second casing extends from the second end portion of the second fuel storage tank into the fuselage subsection,
the first casing and the second casing are configured to keep a closed volume confined within the first casing and the second casing under vacuum conditions, and
the first casing spaced apart from the second casing according to a separation direction contained in a plane perpendicular to the longitudinal direction.
2. The aircraft fuselage section according to claim 1 , wherein the first casing and the second casing are arranged such that at least one plane perpendicular to the longitudinal direction intersects both casings.
3. The aircraft fuselage section according to claim 1 , wherein a ratio between a separation distance between the first casing and the second casing in the separation direction and a size of a first and second casing dimension in the separation direction is in a range from 8% to 10%.
4. The aircraft fuselage section according to claim 1 , wherein:
a size of each of the first casing and second casing in the separation direction is a range of 40-45% of a size of the aircraft fuselage section the separation direction; or
a separation distance between the first casing and the second casing in the separation direction is in a range of 2-10% of a size of the aircraft fuselage section in the separation direction of the aircraft fuselage section; or
both.
5. The aircraft fuselage section according to claim 1 , wherein the first casing, the second casing, or both are configured to keep a corresponding closed volume confined within under vacuum conditions.
6. The aircraft fuselage section according to claim 1 , further comprising:
an airframe, and
wherein the first casing, the second casing, or both are spaced apart from the airframe.
7. The aircraft fuselage section according to claim 6 , wherein the first casing, the second casing, or both are spaced apart from a closest part of the airframe a distance greater than or equal to about 4% of a size of the aircraft fuselage section in the separation direction.
8. The aircraft fuselage section according to claim 1 , wherein the first fuel storage tank, the second fuel storage tank, or both comprise a central portion with a substantially cylindrical geometry.
9. The aircraft fuselage section according to claim 1 , wherein the first fuel storage tank, the second fuel storage tank, or both comprise a central portion with a substantially frustoconical geometry.
10. The aircraft fuselage section according to claim 9 , further comprising:
a tail cone,
wherein the second fuel storage tank comprises a central portion with a substantially frustoconical geometry and is arranged at a tapering section of the tail cone, such that a transverse area of both the second fuel storage tank and the tapering section of the tail cone decrease along the longitudinal direction.
11. The aircraft fuselage section according to claim 9 , wherein the first fuel storage tank and the second fuel storage tank are arranged with longitudinal axes, respectively, of a corresponding substantially cylindrical, a substantially frustoconical central portions, or both aligned and parallel to the longitudinal direction of the aircraft fuselage section.
12. The aircraft fuselage section according to claim 1 , wherein the first end portion of the first fuel storage tank, the second end portion of the second fuel storage tank, or both are provided with a dome-shaped geometry.
13. The aircraft fuselage section according to claim 12 , wherein the first casing, the second casing, or both are arranged, respectively, at an apex of a corresponding dome-shaped end portion of the first fuel storage tank or the second fuel storage tank.
14. An aircraft comprising
an aircraft fuselage section according to claim 1 .
15. The aircraft fuselage section according to claim 1 , wherein:
connecting interfaces between the first casing and the at least two conduits which pass through the first casing are provided with a fluid-tight fit;
connecting interfaces between the second casing and the at least conduits which pass through the second casing are provided with a fluid-tight fit;
a connecting interface between the first casing and the first end portion of the first fuel storage tank is provided with a fluid-tight fit; and
a connecting interface between the first casing and the first end portion of the first fuel storage tank is provided with a fluid-tight fit.
16. The aircraft fuselage section according to claim 1 , wherein the first casing and the second casing overlap along at least a portion of the longitudinal direction.
17. The aircraft fuselage section according to claim 1 , wherein the first casing is spaced apart from the second casing along a pitch axis of the aircraft and a yaw axis of the aircraft.