Hydrogen powered aircraft with antenna for satellite internet access

Abstract

A hydrogen powered aircraft 1001, 1002, 1003, 1004, 1005, 1006 is disclosed that includes a fuselage 101, 102, 103, 104, 105, 106 having an unpressurized rear portion A containing or configured to contain at least one hydrogen tank 11, 12. The top portion R of the fuselage 101, 102, 103, 104, 105, 106 at least partially covers the unpressurized rear portion A and integrates an antenna 13 for satellite internet access from within the aircraft.

Description

Technical Field

[0001] The present invention relates to a hydrogen-powered aircraft comprising a fuselage having an unpressurized rear portion including at least one hydrogen tank. Background Technology

[0002] Modern aircraft that conventionally run on aviation gasoline or jet fuel often provide in-flight internet access to their crews and / or passengers. To achieve this access even when far from ground-based stations, such as when flying over oceans, satellites are typically involved.

[0003] While other antennas are known to be mounted flush with the fuselage surface in such conventional aircraft, as taught, for example, in US2022216601 A1 and EP 3560817 A1, antennas providing satellite internet access at acceptable data rates are typically positioned on top of the aircraft fuselage, beneath a hump-shaped radome, due to their significantly larger size. To prepare for potential rapid decompression, such radomes often feature ventilation openings.

[0004] However, the hump causes aerodynamic drag and thus reduces the aircraft's performance. It also increases operational risks, such as those caused by potential bird strikes or air turbulence. Furthermore, the antenna location on the top of the fuselage increases the risk of corrosion due to moisture and necessary de-icing fluid entering the ventilation openings.

[0005] For example, hydrogen / electric aircraft engines have emerged as a promising possibility for achieving substantial emissions reductions. In particular, turbofan engines powered by hydrogen and fuel cell / electric engines are being developed as aircraft engines. Summary of the Invention

[0006] The purpose of this invention is to provide such hydrogen-powered aircraft with an antenna for satellite internet access.

[0007] This objective is achieved using the hydrogen-powered aircraft according to claim 1. Advantageous embodiments are disclosed in the dependent claims, the specification, and the drawings.

[0008] The hydrogen-powered aircraft according to the invention includes a fuselage having an unpressurized rear portion that includes or is configured to include at least one hydrogen tank. The hydrogen-powered aircraft further includes an antenna enabling satellite internet access from within the hydrogen-powered aircraft.

[0009] The antenna is integrated into the roof section of the fuselage, which at least partially covers the unpressurized rear portion; in the orientation of a hydrogen-powered aircraft designated for horizontal flight, the outer surface of the roof section (exposed to the environment of the hydrogen-powered aircraft) therefore faces upward (vertically or obliquely).

[0010] As will be further understood, the term “rear” refers to a specified flight direction of an aircraft; in particular, one or more hydrogen tanks are mounted in a tail configuration or are configured to be mounted in a tail configuration.

[0011] Furthermore, in this document, when the corresponding relationships are clear, the attribute "hydrogen-powered" relating to the aircraft and the restrictive clause "achieving satellite internet access from within the hydrogen-powered aircraft" relating to the antenna are sometimes omitted, at least partially, to improve readability. Descriptions relating to the location of the aircraft or its surroundings (such as "top," "side," or "upward") relate to the aircraft's orientation designated for normal level flight.

[0012] The inventive integration of the antenna in the top section (which covers the unpressurized rear section designated to contain one or more hydrogen tanks) facilitates advantageous space management of the hydrogen-powered aircraft architecture. In fact, this hydrogen-powered aircraft allows for a wider reinforcement structure than conventional aircraft. Specifically, the antenna can be advantageously arranged at a sufficient distance from obstacles that impair signal transmission (such as frames) while simultaneously being close to other internet equipment (such as onboard servers and / or routers), thereby avoiding bandwidth loss. Furthermore, in the top section covering the unpressurized rear section, the antenna has a clear line of sight with different satellite constellations (such as those referred to as LEO, MEO, or GEO satellites) and still does not interfere with systems associated with the pressurized passenger cabin (such as ductwork for cabin air distribution).

[0013] The antenna is preferably at least partially recessed within the top section of the fuselage, for example, so that it protrudes at most 2 cm or at most 1 cm from the outer surface of the fuselage (in the top section), or so that it does not protrude from said outer surface. This avoids or at least reduces the aerodynamic drag and the risk of bird strikes (and consequently, antenna loss). The reduced load (e.g., aerodynamic load) acting on the antenna arrangement structure facilitates particularly lightweight structural integration.

[0014] Furthermore, this embodiment reduces the antenna's sensitivity to corrosion because the embedding of the antenna into the top section provides protection against substances such as water and / or de-icing fluid, and because ventilation holes for rapid depressurization can be omitted in the top section covering the unpressurized rear section.

[0015] Preferably, the antenna is covered at least partially by a skin made of fiberglass-reinforced plastic. This skin (the surface facing away from the antenna is preferably a section of the fuselage's outer surface (and thus directly exposed to the aircraft's surrounding environment)) protects the antenna from impacts from the aircraft's environment while still allowing signal transmission (between the antenna and the satellite). Preferably, the outer surface of the skin is arranged flush with its surrounding area (and therefore, on a common horizontal plane / without steps) or at least substantially flush with its surrounding area.

[0016] Alternatively or additionally, the antenna may be integrated into a panel that releasably closes an opening in the fuselage (and thus, in particular, the opening is formed in the outer surface of the fuselage). The opening may be defined to the top portion of the fuselage (and thus entirely upward-facing); in this case, the antenna may be located in the central region of the panel. Alternatively, the opening may extend to the side portions of the fuselage and / or even the bottom portions (and thus include areas facing to the sides and / or even downwards); in this case, the antenna may be positioned in the edge region of the panel.

[0017] According to an advantageous embodiment, the opening may be formed in the outer shell of the fuselage; such outer shell is typically reinforced by a fuselage reinforcement system comprising a plurality of longitudinal beams extending in the longitudinal direction of the fuselage and a plurality of frames intersecting the longitudinal beams, as known in the art.

[0018] For example, the panel can be configured as a door that rotates relative to the edge of the opening, or the panel as a separate component can be detachable from the edge of the opening.

[0019] This embodiment facilitates easy installation and maintenance of the antenna. The opening may be dedicated to antenna-related purposes (such as mounting the antenna and accessing its contacts), or the opening may have at least one additional function.

[0020] For example, the opening can provide access from the fuselage environment to the interior of the fuselage, particularly to the unpressurized rear portion of the fuselage, more specifically to the at least one hydrogen tank and / or to a fuel distribution system configured to supply hydrogen from the at least one hydrogen tank to the combustion chamber of the engine or the fuel cell of the aircraft; such fuel distribution system may advantageously be located below the opening.

[0021] Therefore, these embodiments facilitate the performance of corresponding maintenance operations through openings.

[0022] In particular, in embodiments where the unpressurized rear portion includes two hydrogen tanks (particularly in a tail-to-tail configuration) arranged with a gap between them, the opening may be arranged at least partially above the gap; thus, when the opening is closed, the panel may at least partially cover the gap. This facilitates easy access to the two fuel tanks, where no passageway along their space is required.

[0023] According to a particularly advantageous embodiment, the opening can be configured for selective extraction or installation into the tank port of the least one hydrogen tank.

[0024] The panel may be made wholly or at least partially of glass fiber reinforced plastic. The antenna may be at least partially embedded in (particularly encapsulated by) the glass fiber reinforced plastic and / or at least partially attached to the surface of the glass fiber reinforced plastic. This embodiment facilitates easy panel manufacturing, thereby enabling signal transmission to and from the antenna.

[0025] According to a specific embodiment, the panel may include a sub-panel made of fiberglass reinforced plastic, wherein at least a portion of the antenna is attached to the sub-panel, and / or wherein at least a portion of the antenna is embedded (e.g., encapsulated in fiberglass reinforced plastic) within the sub-panel. Such a sub-panel, as a first panel component, can be combined with one or more other panel components that the panel may also include. For example, the sub-panel may be wholly or at least partially surrounded by at least one of the one or more other panel components. In particular, a panel having a sub-panel thus implements the concept of a (sub)panel within a panel. The sub-panel may be detachable from one or more other components, thus facilitating easy maintenance operations on the antenna.

[0026] For example, in this embodiment, the one or more additional panel components may be made at least partially of a material different from glass fiber reinforced plastic, such as metal (particularly aluminum) and / or carbon fiber reinforced plastic. This embodiment allows for particularly high panel strength, which is particularly advantageous when there is an opening and therefore a large panel, for example to facilitate corresponding additional functions, such as extraction or installation of the at least one fuel canister through the opening.

[0027] As mentioned above, regarding the orientation of an aircraft designated for normal level flight, by definition, the top portion has an upward-facing outer surface (exposed to the environment of the hydrogen-powered aircraft), either vertically or at an angle.

[0028] Wherein, at least a portion of the outer surface of the top section may form part of the surface of one of the fuselage / the outer shell, the outer shell being fastened to the reinforcing structure of the fuselage (including the frame and longitudinal beams as mentioned above).

[0029] Additionally or alternatively, the top section may include a fairing made at least partially of fiberglass reinforced plastic and at least partially covering a portion of the outer shell (a reinforcing structure fastened to the fuselage). At least a portion of the hydrogen distribution system and / or ventilation system may be included in the top section and disposed between said portion of the outer shell and the fairing.

[0030] In this embodiment, the surface of the fairing may form at least a portion of the outer surface of the top portion. The antenna may be integrated into the fairing. Specifically, the antenna may be at least partially embedded in (e.g., enclosed therein) the fairing, particularly embedded in a portion of the fairing made of glass fiber reinforced plastic, and / or at least partially arranged between the housing portion and the fairing, particularly below the portion of the fairing made of glass fiber reinforced plastic.

[0031] At least a portion of the antenna may be arranged between two channels, which may be at least partially formed within the top section and may each contain at least a portion of a corresponding hydrogen transport pipe of the distribution system and / or a ventilation system. This embodiment allows for a particularly space-efficient antenna arrangement. In the respective areas covering these channels, the fairing may have vents that allow for the purging of hydrogen in the event of a potential leak, as taught in US2023 / 0086167 A1 and US2023 / 0382551A1.

[0032] In the following, preferred embodiments of the invention are explained with reference to the accompanying drawings. As will be understood, various elements and components are depicted only as examples and may be combined in any and / or different ways than those depicted. Reference numerals for related elements are used collectively and are not redefined for each drawing, and this also applies to visually obvious analogies. Attached Figure Description

[0033] The following are illustrated schematically:

[0034] Figure 1 This is a part of a first exemplary embodiment of a hydrogen-powered aircraft according to the present invention;

[0035] Figure 2 This is part of a second exemplary embodiment of a hydrogen-powered aircraft according to the present invention;

[0036] Figure 3 This is part of a third exemplary embodiment of a hydrogen-powered aircraft according to the present invention;

[0037] Figure 4 This is part of a fourth exemplary embodiment of a hydrogen-powered aircraft according to the present invention;

[0038] Figure 5A portion of a fifth exemplary embodiment of a hydrogen-powered aircraft according to the present invention; and

[0039] Figure 6 A portion of a sixth exemplary embodiment of a hydrogen-powered aircraft according to the present invention in cross-section. Detailed Implementation

[0040] exist Figure 1 The image schematically illustrates a portion of a hydrogen-powered aircraft 1001 according to an exemplary embodiment of the invention in a side view, providing insight into a cross-section of the fuselage 101 of the aircraft 1001. As indicated by the coordinate system, the image plane thus corresponds to the xz plane, where x extends opposite to the designated flight direction D, and z extends upward. The aircraft 1001 is depicted in an orientation designated for normal level flight.

[0041] As from Figure 1 Obviously, the fuselage 101 includes an unpressurized rear portion A, and a pressurized passenger compartment P and a cargo area L separated from the unpressurized rear portion by a pressure bulkhead 20.

[0042] The unpressurized rear section A includes two hydrogen tanks 11 and 12 arranged in a tail-tandem configuration. The top section R covers the unpressurized rear section A upwards. In its current form, its outer surface (exposed to the environment of the hydrogen-powered aircraft) forms part of the surface of the fuselage shell 141; the shell 141 is fastened to a fuselage reinforcement structure (not shown) as known in the art.

[0043] The aircraft 1001 further includes an antenna 13 for satellite internet access from within the aircraft, which is integrated in the top section R. Figure 1 In the embodiment depicted, the antenna 13 is recessed in a panel 151 that releasably closes an opening O1 in the housing 101 (and this opening is formed in the outer casing 141); Figure 1 In the case shown, panel 151 closes opening O1. This panel can be configured as a revolving door or a detachable separate component (not visible).

[0044] Antenna 13 is positioned in the top region of the top section R, ensuring a clear line of sight for different satellite constellations. The antenna is protected from external impacts by skin 16, the surface of which faces away from antenna 13 forming part of the outer surface of fuselage 101, particularly part of the outer surface of the top section R. The outer surface of skin 16 is arranged flush with its surroundings; therefore, neither the antenna nor the skin protrudes from the outer surface of the fuselage. This avoids aerodynamic drag on the antenna and the risk of bird strikes (and consequently, antenna loss). To allow signal transmission, skin 16 is made of fiberglass-reinforced plastic (invisible).

[0045] In its current state, opening O1 provides passage from the environment of fuselage 101 to the unpressurized rear portion A of the fuselage. Specifically, opening O1 is positioned above gap I, which is located between tanks 11 and 12. This, in particular, facilitates easy access to the two hydrogen tanks 11 and 12 and the associated distribution system (not shown), such as for maintenance operations. Therefore, panel 151 serves multiple functions beyond simply holding antenna 13.

[0046] Figure 2 and Figure 3 Relevant portions of a hydrogen-powered aircraft 1002 according to a second embodiment of the present invention and a hydrogen-powered aircraft 1003 according to a third embodiment of the present invention are shown respectively. Figure 2 In this case, antenna 13 is embedded in panel 152, which releasably closes opening O2 formed in housing 142 of fuselage 102. Similarly, in Figure 3 In this case, the antenna 13 is embedded in the panel 153, which can be releasably closed by the opening O3 formed in the housing 143 of the fuselage 103.

[0047] and Figure 1 The embodiments shown are the opposite. Figure 2 and Figure 3 In the embodiment shown, openings O2 and O3 are each configured for selectively extracting or installing the tank ports of the at least one hydrogen tank 11, 12. Opening O2 extends to the bottom portion B of the fuselage 102 (thus facilitating lateral tank installation and tank extraction), and antenna 13 is located in the edge region of panel 152.

[0048] In comparison, Figure 3 The opening O3 shown is completely upward (and is therefore designed for attaching / removing the can from above). While in Figure 3 While not visible in the center, opening O3 is preferably symmetrical about a plane extending along the longitudinal central axis of fuselage 103 in the xz direction, such that the view from the other side (in the other direction) is identical to that obtained from the plane. Figure 3 The view provided is reversed laterally. In this embodiment, the antenna 13 can therefore be positioned in the central region of the panel 153.

[0049] exist Figure 4 The image shows a portion of a hydrogen-powered aircraft 1004 according to a fourth embodiment of the present invention. Similar to... Figure 3 In the embodiment depicted, antenna 13 is embedded in panel 154, which releasably closes opening O4, which is formed in housing 144 of body 104 and serves as a can port for can loading and unloading from above.

[0050] Among them, with Figure 3 The embodiments shown are the opposite. Figure 4 In the embodiment depicted, the antenna 13 is embedded in a sub-panel 18 included in the panel 154. The sub-panel 18 is made of glass fiber reinforced plastic, allowing signals from or transmitted to the antenna 13 to pass through. Other components 19 of the panel 154 are preferably at least partially made of different materials, such as aluminum and / or carbon fiber reinforced plastic. This allows for high strength of the panel 154, particularly in terms of its size. In particular, this embodiment thus implements the concept of a panel within a panel.

[0051] Sub-panel 18 may be completely surrounded by other components 19 of panel 154 (and not visible due to viewing angle).

[0052] Figure 5 The illustration shows a portion of a hydrogen-powered aircraft 1005 according to a fifth embodiment of the invention. In this case, the top portion R of the fuselage 105 includes a radome 30 covering the antenna 13 and a portion of the outer shell 145 of the fuselage 105. The radome 30 is preferably made at least partially of glass fiber reinforced plastic, particularly in the region above the antenna 13. Thus, the radome 30 can form a skin covering the antenna 13 and made of glass fiber reinforced plastic, thereby allowing signals to pass through.

[0053] As from Figure 5 It is further evident that the top section R includes a pipe 17b of a hydrogen distribution system 17, which further includes a tank operating system 17a connected to tanks 11 and 12 respectively.

[0054] Pipe 17b can advantageously extend through the corresponding channel C, such as Figure 6 The figure shown illustrates a hydrogen-powered aircraft 1006 according to another embodiment of the invention in a cross section orthogonal to the longitudinal direction of the fuselage 106 of the aircraft 1006 (and thus in the yz plane).

[0055] In this configuration, antenna 13 is arranged between channels C, each channel including at least a portion of a corresponding tube 17b positioned between the fairing 30 and the outer shell 146 of the fuselage 106. In the region covering the channels C, the fairing 30 may advantageously have vents (not shown) to provide a leakage safety system for the channels C; the provision of such tubes within such channels covered by fairings with vents is known from documents US2023 / 0086167A1 and US2023 / 0382551 A1, as mentioned above. In this embodiment, the inventive positioning of antenna 13 between channels C facilitates a particularly compact arrangement of the aircraft.

[0056] A hydrogen-powered aircraft 1001, 1002, 1003, 1004, 1005, and 1006 is disclosed, comprising fuselages 101, 102, 103, 104, 105, and 106, the fuselage having an unpressurized rear portion A that includes or is configured to include at least one hydrogen tank 11, 12. A top portion R of the fuselage 101, 102, 103, 104, 105, and 106 at least partially covers the unpressurized rear portion A and integrates an antenna 13 for satellite internet access from within the aircraft.

[0057] Figure Labels

[0058] 101, 102, 103, 104, 105, 106 fuselage

[0059] 11 hydrogen tanks

[0060] 12 hydrogen tanks

[0061] 13 Antennas for satellite internet access

[0062] 141, 142, 143, 144, 145, 146 Outer shell

[0063] Panels 151, 152, 153, and 154

[0064] 16 fiberglass reinforced plastic skin

[0065] 17 Hydrogen Distribution System

[0066] 17a Tank Operating System

[0067] 17b Hydrogen Transport Pipe

[0068] 18 Sub-panels made of fiberglass reinforced plastic

[0069] 20 pressure chamber wall

[0070] 30 fairing

[0071] Aircraft 1001, 1002, 1003, 1004, 1005, and 1006

[0072] A Unpressurized Rear Section

[0073] Channel C

[0074] D specifies the flight direction

[0075] The gap between cans

[0076] L Cargo Area

[0077] O1, O2, O3, and O4 are open.

[0078] P passenger cabin

Claims

1. A hydrogen-powered aircraft (1001, 1002, 1003, 1004, 1005, 1006) comprising a fuselage (101, 102, 103, 104, 105, 106), said fuselage having an unpressurized rear portion (A) comprising or configured to comprise at least one hydrogen tank (11, 12), in, Antenna (13) for satellite internet access from within the aircraft is integrated in the top section (R) of the fuselage (101, 102, 103, 104, 105, 106), which at least partially covers the unpressurized rear section (A).

2. The hydrogen-powered aircraft according to claim 1, wherein, The antenna (13) is at least partially or completely buried in the top part (R).

3. The hydrogen-powered aircraft according to any one of claims 1 or 2, wherein, The antenna (13) is covered at least partially by a skin (16, 30) made of glass fiber reinforced plastic.

4. The hydrogen-powered aircraft according to any one of the preceding claims, wherein, The antenna is integrated in the panel (151, 152, 153, 154), which can be releasably closed by the openings (O1, O2, O3, O4) of the fuselage (101, 102, 103, 104).

5. The hydrogen-powered aircraft according to claim 4, wherein, The openings (O1, O2, O3, O4) provide access to the at least one hydrogen tank (11, 12) and / or a fuel distribution system (17) configured to supply hydrogen from the at least one hydrogen tank (11, 12) to the combustion chamber of the engine or the fuel cell of the aircraft.

6. The hydrogen-powered aircraft according to any one of claims 4 or 5, wherein, The openings (O2, O3, O4) are configured as tank ports for selectively extracting or installing the at least one hydrogen tank (11, 12).

7. The hydrogen-powered aircraft according to any one of claims 4 to 6, wherein, The unpressurized rear portion (A) includes two hydrogen tanks (11, 12) with a gap (I) therebetween, the gap (I) being at least partially covered by the panel (151).

8. The hydrogen-powered aircraft according to any one of claims 4 to 7, wherein, The antenna (13) is at least partially attached to and / or at least partially embedded in the sub-panel (18), the sub-panel being made of glass fiber reinforced plastic and included in the panel (154).

9. The hydrogen-powered aircraft according to any one of claims 4 to 8, wherein, The outer surface of the top portion (R) is wholly or at least partially formed by a portion of the outer shell (141, 142, 143, 144), which is fastened to a reinforcing structure of the fuselage (101, 102, 103, 104).

10. The hydrogen-powered aircraft according to any one of the preceding claims, wherein, The top section (R) includes a fairing (30) made at least partially of fiberglass reinforced plastic and at least partially covers a portion of the outer shell (145, 146) of the antenna (13) and the fuselage (105, 106).

11. The hydrogen-powered aircraft according to claim 10, wherein, The top section (R) further includes at least a portion of a hydrogen distribution system (17) and / or a ventilation system disposed between the fairing (30) and the outer casing (145, 146).

12. The hydrogen-powered aircraft according to claim 11, wherein, At least a portion of the antenna is arranged between two channels (C), which are at least partially formed in the top section (R) and respectively contain a corresponding hydrogen transport pipe (17b) of the distribution system (17) and / or at least a portion of the ventilation system.

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