HYDROGEN-POWERED AIRCRAFT WITH ANTENNA FOR SATELLITE INTERNET ACCESS

Abstract

A hydrogen-powered aircraft with a fuselage with an unpressurised aft portion containing or configured to contain at least one hydrogen tank. A roof portion of the fuselage at least partially covers the unpressurised aft portion and integrates an antenna for satellite internet access from within the aircraft. The antenna may be counter sunk and/or covered by a skin.

Claims

1. A hydrogen-powered aircraft comprising: a fuselage with an unpressurised aft portion containing or configured to contain at least one hydrogen tank, wherein an antenna for satellite internet access from within the hydrogen-powered aircraft is integrated in a roof portion of the fuselage, at least partially covering the unpressurised aft portion.

2. The hydrogen-powered aircraft according to claim 1, wherein said antenna is at least partially or entirely countersunk in the roof portion.

3. The hydrogen-powered aircraft according to claim 1, wherein said antenna is covered by a skin at least partially made of glass fiber reinforced plastic.

4. The hydrogen-powered aircraft according to claim 1, wherein said antenna is integrated in a panel releasably closing an opening of the fuselage.

5. The hydrogen-powered aircraft according to claim 4, wherein the opening provides access to the at least one hydrogen tank, or to a fuel distribution system configured to supply hydrogen from the at least one hydrogen tank to a combustion chamber of an engine or to a fuel cell of the aircraft, or to both.

6. The hydrogen-powered aircraft according to claim 4, wherein the opening is configured as a tank port for selectively extracting or installing the at least one hydrogen tank.

7. The hydrogen-powered aircraft according to claim 4, wherein the unpressurised aft portion includes two hydrogen tanks with an interspace in-between, the interspace at least partially covered by said panel.

8. The hydrogen-powered aircraft according to claim 4, wherein the antenna is at least partially attached to, or at least partially embedded in, or both at least partially attached to and at least partially embedded in a sub-panel made of glass fiber reinforced plastic and included in said panel.

9. The hydrogen-powered aircraft according to claim 4, wherein an outer surface of the roof portion is at least partially formed by a portion of a shell fastened to a reinforcement structure of the fuselage.

10. The hydrogen-powered aircraft according to claim 1, wherein the roof portion comprises a fairing at least partially made of glass fiber reinforced plastic and at least partially covering the antenna and a portion of a shell of the fuselage.

11. The hydrogen-powered aircraft according to claim 10, wherein the roof portion further comprises at least a portion of a hydrogen distribution system, or a ventilation system arranged between the fairing and the shell, or both.

12. The hydrogen-powered aircraft according claim 11, wherein at least a portion of the antenna is arranged between two channels at least partially formed in the roof portion and containing at least a part of a respective hydrogen transport pipe of the hydrogen distribution system, or the ventilation system, or both.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In what follows, preferred embodiments of the present invention are explained with respect to the accompanying drawings. As is to be understood, the various elements and components are depicted as examples only, may be facultative and/or combined in a manner different than that depicted. Reference signs for related elements are used comprehensively and not defined again for each figure, and the same holds for analogies which are visually evident.

[0034] Shown is schematically in

[0035] FIG. 1 is a part of a first exemplary embodiment of a hydrogen-powered aircraft according to the present invention;

[0036] FIG. 2 is a part of a second exemplary embodiment of a hydrogen-powered aircraft according to the present invention;

[0037] FIG. 3 is a part of a third exemplary embodiment of a hydrogen-powered aircraft according to the present invention;

[0038] FIG. 4 is a part of a fourth exemplary embodiment of a hydrogen-powered aircraft according to the present invention;

[0039] FIG. 5 is a part of a fifth exemplary embodiment of a hydrogen-powered aircraft according to the present invention; and

[0040] FIG. 6 is a part of a sixth exemplary embodiment of a hydrogen-powered aircraft according to the present invention in a cross section.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS

[0041] In FIG. 1, a part of a hydrogen-powered aircraft 100.sub.1 according to an exemplary embodiment of the present invention is schematically shown in schematic side view providing insight into a section of a fuselage 10.sub.1 of the aircraft 100.sub.1. As indicated by a coordinate system, an image plane thus corresponds to an x-z-plane, where x runs opposite to a designated direction D of flight, and z runs upwards. The aircraft 100.sub.1 is depicted in an orientation designated for normal horizontal flight.

[0042] As apparent from FIG. 1, the fuselage 10.sub.1 comprises an unpressurised aft portion A and, separated therefrom by a pressure bulkhead 20, a pressurized passenger cabin P and a cargo area L.

[0043] The unpressurised aft portion A includes two hydrogen tanks 11, 12 which are arranged in a caudal tandem configuration. A roof portion R covers the unpressurised aft portion A upwards. In the present case, its outer surface (exposed to an environment of the hydrogen-powered aircraft) forms part of a surface of a shell 14.sub.1 of the fuselage; the shell 14.sub.1 is fastened to a fuselage reinforcement structure (not shown) as known in the art.

[0044] Integrated in the roof portion R, the aircraft 100.sub.1 further comprises an antenna 13 for satellite internet access from within the aircraft. In the embodiment depicted in FIG. 1, the antenna 13 is countersunk in a panel 15.sub.1 releasably closing an opening O.sub.1 of the fuselage 10.sub.1 (and formed in the shell 14.sub.1); in the situation shown in FIG. 1, the panel 15.sub.1 closes the opening O.sub.1. It may be configured as a swivelling door or as a detachable separate component (not visible).

[0045] The antenna 13 is arranged in a top region of the roof portion R, which ensures a clear line of sight with different satellite constellations. It is protected against exterior impacts by a skin 16 whose surface facing away from the antenna 13 forms a portion of an exterior surface of the fuselage 10.sub.1, in particular, of the roof portion R thereof. An outer surface of the skin 16 is arranged flush with its surrounding; accordingly, neither the antenna nor the skin protrudes from the outer surface of the fuselage. Thereby, an aerodynamic drag of the antenna and a risk of a bird strike (and a resulting loss of the antenna) is avoided. To allow signals to pass through, the skin 16 is made of glass fiber reinforced plastic (not visible).

[0046] In the present case, the opening O.sub.1 provides access from an environment of the fuselage 10.sub.1 to the unpressurised aft portion A thereof. In particular, the opening O.sub.1 is arranged above an interspace I arranged between the tanks 11, 12. It thereby in particular facilitates easy access to both hydrogen tanks 11, 12 and to a related distribution system (not shown), such as for maintenance operations. Accordingly, the panel 15.sub.1 not only serves to hold the antenna 13, but has a multiple function.

[0047] FIGS. 2 and 3 show respective parts of a hydrogen-powered aircrafts 100.sub.2, 100.sub.3 according to a second and a third embodiment of the present invention, respectively. In case of FIG. 2, an antenna 13 is embedded in a panel 15.sub.2 releasably closing an opening O.sub.2 formed in a shell 14.sub.2 of a fuselage 10.sub.2. Analogously, in case of FIG. 3, an antenna 13 is embedded in a panel 15.sub.3 releasably closing an opening O.sub.3 formed in a shell 14.sub.3 of a fuselage 10.sub.3.

[0048] Contrary to the embodiment shown in FIG. 1, the openings O.sub.2 and O.sub.3 of the embodiments shown in FIGS. 2 and 3 each are configured as a tank port for selectively extracting or installing the at least one hydrogen tank 11, 12. Therein, the opening O.sub.2 extends to a bottom portion B of the fuselage 10.sub.2 (thus facilitating a lateral tank installation and tank extraction), and the antenna 13 is located in an edge region of the panel 15.sub.2.

[0049] By contrast, the opening O.sub.3 shown in FIG. 3 entirely faces upwards (thus being designed for tank installing and extracting from/to above). Therein, although not visible in FIG. 3, the opening O.sub.3 may preferably be symmetric to a plane extending along a longitudinal center axis of the fuselage 10.sub.3 in the x-z-directions, such that a view from the other side (in the other direction) is laterally reversed to that provided by FIG. 3. In this embodiment, the antenna 13 may thus be positioned in a center region of the panel 15.sub.3.

[0050] In FIG. 4, a part of a hydrogen-powered aircraft 100.sub.4 according to a fourth embodiment of the present invention is shown. Analogous to the embodiment depicted in FIG. 3, an antenna 13 is embedded in a panel 15.sub.4 releasably closing an opening O.sub.4 formed in a shell 14.sub.4 of a fuselage 10.sub.4 and serving as a tank port for tank installation and extraction from above.

[0051] Therein, contrary to the embodiment shown in FIG. 3, the antenna 13 of the embodiment depicted in FIG. 4 is embedded in a sub-panel 18 included in the panel 15.sub.4, the sub-panel 18 made of glass fiber reinforced plastic, which enables signals respectively coming from or transmitted to the antenna 13 to pass through. A further component 19 of the panel 15.sub.4 preferably is at least partially made of a different material such as aluminum and/or carbon fiber reinforced plastic. Thereby, a high strength of the panel 15.sub.4 particularly in regard of its size can be achieved. In particular, such embodiment thus implements a panel-in-panel concept.

[0052] The sub-panel 18 may be entirely surrounded by the further component 19 of the panel 15.sub.4 (not visible due to the perspective).

[0053] FIG. 5 illustrates a part of a hydrogen-powered aircraft 100.sub.5 according to a fifth embodiment of the present invention. In this case, the roof portion R of the fuselage 10.sub.5 comprises a fairing 30 covering the antenna 13 and a portion of a shell 14.sub.5 of the fuselage 10.sub.5. The fairing 30 preferably is at least partially made of glass fiber reinforced plastic, in particular in a region above the antenna 13. Accordingly, the fairing 30 may form a skin covering the antenna 13 and being made of glass fiber reinforced plastic enabling signals to pass through.

[0054] As further apparent from FIG. 5, the roof portion R includes pipes 17b of a hydrogen distribution system 17 further comprising tank operation systems 17a respectively connected to the tanks 11, 12.

[0055] The pipes 17b may advantageously run through respective channels C, as illustrated in FIG. 6 showing a hydrogen-powered aircraft 100.sub.6 according to a further embodiment of the present invention in a cross section orthogonally to a longitudinal direction of the fuselage 10.sub.6 of the aircraft 100.sub.6 (thus, in a y-z-plane).

[0056] In this case, an antenna 13 is arranged between the channels C each comprising at least a portion of a respective pipe 17b positioned between a fairing 30 and a shell 14.sub.6 of the fuselage 10.sub.6. In regions covering the channels C, the fairing 30 may advantageously have ventilation holes (not shown), such that the channels C provide for a leakage safety system; as mentioned above, the provision of such pipes within such channels covered by a fairing having ventilation holes is known from documents US 2023/0086167 A1 and US 2023/0382551 A1. The inventive positioning of the antenna 13 between the channels C in such embodiments facilitates a particularly compact arrangement of the aircraft.

[0057] Disclosed is a hydrogen-powered aircraft 100.sub.1, 100.sub.2, 100.sub.3, 100.sub.4, 100.sub.5, 100.sub.6 comprising a fuselage 10.sub.1, 10.sub.2, 10.sub.3, 10.sub.4, 10.sub.5, 10.sub.6 with an unpressurised aft portion A containing or configured to contain at least one hydrogen tank 11, 12. A roof portion R of the fuselage 10.sub.1, 10.sub.2, 10.sub.3, 10.sub.4, 10.sub.5, 10.sub.6 at least partially covers the unpressurised aft portion A and integrates an antenna 13 for satellite internet access from within the aircraft.

[0058] 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.

Reference Signs

[0059] 10.sub.1, 10.sub.2, 10.sub.3, 10.sub.4, 10.sub.5, 10.sub.6 fuselage [0060] 11 hydrogen tank [0061] 12 hydrogen tank [0062] 13 antenna for satellite internet access [0063] 14.sub.1, 14.sub.2, 14.sub.3, 14.sub.4, 14.sub.5, 14.sub.6 shell [0064] 15.sub.1, 15.sub.2, 15.sub.3, 15.sub.4 panel [0065] 16 skin of glass fiber reinforced plastic [0066] 17 hydrogen distribution system [0067] 17a tank operation system [0068] 17b hydrogen transport pipe [0069] 18 sub-panel made of glass fiber reinforced plastic [0070] 20 pressure bulkhead [0071] 30 fairing [0072] 100.sub.1, 100.sub.2, 100.sub.3, 100.sub.4, 100.sub.5, 100.sub.6 aircraft [0073] A unpressurised aft section [0074] C channel [0075] D designated direction of flight [0076] I interspace between tanks [0077] L cargo area [0078] O.sub.1, O.sub.2, O.sub.3, O.sub.4 opening [0079] P passenger cabin