US20230249840A1 - Aircraft comprising hydrogen storage tanks - Google Patents
Aircraft comprising hydrogen storage tanks Download PDFInfo
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- US20230249840A1 US20230249840A1 US18/187,830 US202318187830A US2023249840A1 US 20230249840 A1 US20230249840 A1 US 20230249840A1 US 202318187830 A US202318187830 A US 202318187830A US 2023249840 A1 US2023249840 A1 US 2023249840A1
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- Prior art keywords
- hydrogen storage
- cargo bay
- tanks
- storage tanks
- aircraft
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- 239000001257 hydrogen Substances 0.000 title claims abstract description 86
- 229910052739 hydrogen Inorganic materials 0.000 title claims abstract description 86
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 title claims abstract description 84
- 238000003860 storage Methods 0.000 title claims abstract description 71
- 125000004435 hydrogen atom Chemical group [H]* 0.000 claims description 2
- 239000000446 fuel Substances 0.000 description 9
- 230000005484 gravity Effects 0.000 description 7
- 230000007423 decrease Effects 0.000 description 3
- 239000002131 composite material Substances 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000011065 in-situ storage Methods 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 1
- 239000002828 fuel tank Substances 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000009420 retrofitting Methods 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/30—Fuel systems for specific fuels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/22—Other structures integral with fuselages to facilitate loading, e.g. cargo bays, cranes
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/04—Arrangement thereof in or on aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/02—Tanks
- B64D37/06—Constructional adaptations thereof
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C1/00—Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/01—Shape
- F17C2201/0104—Shape cylindrical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/03—Orientation
- F17C2201/035—Orientation with substantially horizontal main axis
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/05—Size
- F17C2201/054—Size medium (>1 m3)
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2201/00—Vessel construction, in particular geometry, arrangement or size
- F17C2201/05—Size
- F17C2201/056—Small (<1 m3)
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2205/00—Vessel construction, in particular mounting arrangements, attachments or identifications means
- F17C2205/01—Mounting arrangements
- F17C2205/0123—Mounting arrangements characterised by number of vessels
- F17C2205/013—Two or more vessels
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2221/00—Handled fluid, in particular type of fluid
- F17C2221/01—Pure fluids
- F17C2221/012—Hydrogen
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
- F17C2223/01—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the phase
- F17C2223/0107—Single phase
- F17C2223/0123—Single phase gaseous, e.g. CNG, GNC
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2223/00—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel
- F17C2223/03—Handled fluid before transfer, i.e. state of fluid when stored in the vessel or before transfer from the vessel characterised by the pressure level
- F17C2223/036—Very high pressure (>80 bar)
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F17—STORING OR DISTRIBUTING GASES OR LIQUIDS
- F17C—VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES
- F17C2270/00—Applications
- F17C2270/01—Applications for fluid transport or storage
- F17C2270/0186—Applications for fluid transport or storage in the air or in space
- F17C2270/0189—Planes
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
- Y02T90/40—Application of hydrogen technology to transportation, e.g. using fuel cells
Definitions
- the present disclosure relates to aircraft comprising hydrogen storage tanks, particularly hydrogen storage tanks containing gaseous hydrogen or suitable for containing gaseous hydrogen.
- Hydrogen in either gaseous or liquid form is of increasing interest as a fuel for a variety of transport applications, including aeronautical applications, due to an absence of CO 2 generation at the point of use.
- storage of gaseous hydrogen at high pressure presents a significant technical challenge and in particular requires a significant increase in the volume of stored fuel compared to that required for traditional fuel.
- Minimising the loss of useful space within an aircraft and maximising the amount of stored hydrogen are important considerations in relation to retro-fitting known aircraft with hydrogen storage tanks, or in designing new aircraft having conventional fuselage and wing forms.
- an aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks, and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system, the aircraft further comprising a fuselage having a cargo bay including one or more of the plurality of hydrogen storage tanks, the longitudinal axes of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis of the fuselage and lying in one or more planes extending across the width dimension of the cargo bay, and wherein the hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2 ⁇ R ⁇ 25.7.
- the aircraft has the format of one of number of known aircraft, for example a format like that of the Airbus® A 320 ®, the volume of the cargo bay which is occupied by the hydrogen storage tanks it contains is maximised or approximately maximised.
- the cargo bay may include exactly two hydrogen storage tanks having a common aspect ratio R in the range 4.2 ⁇ R ⁇ 7.7, each hydrogen storage tank being disposed on a respective lateral side of a vertical plane which passes through the central longitudinal axis of the fuselage and bisects the cargo bay.
- the hydrogen storage tanks may have a common diameter d in the range 1 . 0 m d 1 . 1 m.
- the cargo bay may be either a forward or rear cargo bay of the aircraft.
- the fuselage of the aircraft may have a forward cargo bay and rear cargo bay, each being bisected by a vertical plane passing through the central longitudinal axis of the fuselage, with the forward and rear cargo bays each including exactly one hydrogen storage tank, each hydrogen storage tank being located on a respective lateral side of the vertical plane and having an aspect ratio R in the range 4 . 2 ⁇ R ⁇ 7 . 7 .
- This allows the weight of the hydrogen storage tanks to be more evenly distributed along the length of the aircraft whilst keeping the centre of gravity of the tanks within or near the vertical plane passing through the central longitudinal axis of the fuselage.
- the hydrogen storage tanks may optionally also have a common diameter d in the range 1.0 m ⁇ d ⁇ 1.1 m.
- the cargo bay may include exactly seven like generally cylindrical hydrogen storage tanks arranged in a first set of three tanks and second set of four tanks, longitudinal axes of hydrogen storage tanks of the first and second sets lying in first and second planes respectively which extend across the width dimension of the cargo bay, the second plane being disposed vertically above the first plane, and the longitudinal axis of any given hydrogen storage tank of the first set having a position across the width of the cargo bay between the positions of the longitudinal axes of two adjacent hydrogen storage tanks of the second set.
- the hydrogen storage tanks may have a common aspect ratio R having a value in the range 7.5 ⁇ R ⁇ 15.4, and optionally also a common diameter d in the range 0.5 ⁇ d ⁇ 0 . 63 .
- the seven tanks within the cargo bay are preferably distributed symmetrically about a vertical plane which passes through the central longitudinal axis of the fuselage and bisects the cargo bay so that their centre of gravity lies in or near that plane.
- the cargo bay may include exactly thirteen like hydrogen storage tanks arranged in a first set of four tanks, a second set of five tanks and a third set of four tanks, the longitudinal axes of the hydrogen storage tanks of the first, second sets and third sets lying in first, second and third planes respectively which extend across the width dimension of the cargo bay, the second plane being disposed vertically above the first plane and the third plane being disposed vertically above the second plane, the longitudinal axis of any given hydrogen storage tank of the first and third sets having a position across the width of the cargo bay between the positions of the longitudinal axes of two adjacent tanks of the second set.
- the hydrogen storage tanks may have a common aspect ratio having a value R in the range 10.4 ⁇ R ⁇ 25.7 and optionally also a common diameter d in the range 0.3 ⁇ d ⁇ 0.44.
- the thirteen tanks within the cargo bay are distributed symmetrically about a vertical plane which passes through the central longitudinal axis of the fuselage and bisects the cargo bay, so the centre of gravity of the tanks lies in or near that plane.
- the conveying system preferably comprises a manifold system providing for one or more of the hydrogen storage tanks within a cargo bay to be removed from the cargo bay such that the remaining hydrogen storage tanks within the cargo bay remain operatively coupled to the hydrogen-fuelled propulsion system.
- This provides an aircraft in which the hydrogen fuel capacity and payload may be optimised for a given flight mission or flight profile.
- FIG. 1 is a side elevation of a first aircraft of a known type
- FIG. 2 is a longitudinal cross-section of the fuselage of the FIG. 1 aircraft
- FIG. 3 is a longitudinal cross-section of the fuselage of a second aircraft of a known type
- FIG. 4 is a transverse cross-section of a lower portion of the fuselage of the FIG. 1 aircraft;
- FIG. 5 is a side elevation of a third aircraft of a known type
- FIG. 6 is a transverse cross-section of a lower portion of the fuselage of a first example aircraft
- FIGS. 7 A-D show alternative distributions of a pair of hydrogen storage tanks within the first example aircraft
- FIG. 8 is a transverse cross-section of a lower portion of the fuselage of a second example aircraft.
- FIG. 9 is a transverse cross-section of a lower portion of the fuselage of a third example aircraft.
- an aircraft 100 of known type (e.g. an Airbus® A320® or similar aircraft) comprises a fuselage 180 having central longitudinal axis 101 .
- the 15 fuselage 180 is divided longitudinally into a passenger space (not shown) and a cargo space 150 located vertically below the passenger space.
- the cargo space 150 includes a forward cargo bay 102 and a rear cargo bay 104 located respectively fore and aft of the wing centre structure 103 of the aircraft 100 .
- a vertical plane 120 passing through the central longitudinal axis 101 of the fuselage 180 of the aircraft 100 divides each of the cargo spaces 102 , 104 into like lateral halves, each being on a respective lateral side of the plane 120 .
- the forward and rear cargo bays 102 , 104 have lengths of three and four standard pallets respectively.
- FIG. 3 shows a horizontal longitudinal cross-section through the fuselage 280 of a second aircraft 200 of a known type (e.g. an Airbus® A321® or similar aircraft).
- the fuselage 280 has central longitudinal axis 201 .
- the fuselage 280 is divided longitudinally into a passenger space and a cargo space located vertically below the passenger space.
- the cargo space has forward and rear cargo bays 202 , 204 respectively fore and aft of the wing centre structure 203 of the aircraft 200 .
- the forward and rear cargo bays 202 , 204 have lengths of four and five pallets respectively.
- FIG. 5 shows a side elevation of a third aircraft 300 of a known type (e.g. a Boeing® 737® or similar aircraft) having a fuselage 380 with a central longitudinal axis 301 , and forward and rear cargo bays 302 , 304 located respectively fore and aft of a wing centre structure 303 .
- Cargo bays of commercial aircraft such as 100 , 200 , 300 are typically in the region of 4.6 m to 7.7 m in length.
- FIG. 6 shows a transverse cross-section through a lower portion of the fuselage of a first example aircraft, the portion defining a cargo space 450 .
- the aircraft has a format similar to any of the aircraft 100 , 200 , 300 of FIGS. 1 , 3 and 5 respectively.
- the cross-section includes a forward cargo bay 402 containing two like, generally cylindrical hydrogen storage tanks 410 A, 410 B.
- the tanks 410 A, 410 B are cylindrical with domed (e.g. hemispherical) ends.
- a vertical plane 420 through the longitudinal axis 401 of the fuselage of the aircraft divides the forward cargo bay into two like lateral portions, each hydrogen storage tank 410 A, 41 B being located in a respective lateral portion.
- the longitudinal axes 411 A, 411 B of the hydrogen storage tanks 410 A, 410 B are generally parallel to the central longitudinal axis 401 of the fuselage of the aircraft and lie in a plane 495 which is orthogonal to the plane 420 and which extends across the with dimension (x) of the cargo bay 402 .
- the hydrogen storage tanks 410 A, 410 B are substantially identical, each having a diameter of 1.0 m or 1.1 m, or a diameter substantially equal to the height h of the cargo bay 402 .
- the aspect ratio R (i.e. length/diameter) of the hydrogen storage tanks 410 A, 410 B may be in the range 4.2 ⁇ R ⁇ 7.7 so that the length of the tanks may be equal to the length of the cargo bay 402 .
- FIG. 7 A shows a horizontal longitudinal cross-section through the cargo bay 402 in the plane 495 .
- the aircraft has a rear cargo bay 404 available for payloads such as baggage and freight.
- the aircraft comprises a hydrogen-fuelled propulsion system (for example one or more PEM fuel cells, one or more hydrogen-fuelled gas turbine engines or a combination of one or more fuel-cells and one or more gas turbine engines) and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the propulsion system.
- a hydrogen-fuelled propulsion system for example one or more PEM fuel cells, one or more hydrogen-fuelled gas turbine engines or a combination of one or more fuel-cells and one or more gas turbine engines
- a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the propulsion system.
- FIGS. 7 B — 7 D show alternative locations for the hydrogen fuel tanks in variants of the first example aircraft. Both tanks may be located in the rear cargo bay ( FIG. 7 B ), or alternatively one tank may be in the forward cargo bay and one in the rear cargo bay ( FIGS. 7 C and 7 D ), although in all cases each tank is located on a respective lateral side of the plane 420 .
- FIG. 8 shows a transverse cross-section through a lower portion of the fuselage of a second example aircraft, the portion defining a cargo space 550 which includes a forward cargo bay 502 .
- the aircraft has a general format similar to that of any of the aircraft 100 , 200 , 300 of FIGS. 1 , 3 and 5 .
- the forward cargo bay 502 contains seven hydrogen storage tanks 510 A-G, the longitudinal axes 511 A-G of the tanks being substantially parallel to the central longitudinal axis 501 of the fuselage of the aircraft.
- a first set of three tanks 510 A-C is arranged such the tanks' longitudinal axes 511 A-C lie in a first plane 595 extending across the width dimension (x) of the forward cargo bay 502 .
- a second set of four tanks 510 D-G is arranged such that the tanks' longitudinal axes 511 D-G lie in a second plane 597 extending across the width of the forward cargo bay 502 , the second plane 597 being disposed vertically above the first plane 595 .
- Any given tank of the first set has a longitudinal axis which has a position x across the width of the cargo bay 502 which is in between the positions of the longitudinal axes of two adjacent tanks in the second set.
- tank 510 A has a longitudinal axis 511 A located in the x direction between the positions of longitudinal axes 511 D, 511 E of tanks 510 D, 510 E respectively.
- the seven tanks 510 A-G within the forward cargo bay 502 have a common aspect ratio R in the range 7.5 ⁇ R ⁇ 15.4 and a common diameter d in the range 0.5 ⁇ d ⁇ 0.63.
- the length of the tanks may be equal to the length of the cargo bay 502 .
- the seven hydrogen storage tanks 510 A-G may be located in a rear cargo bay of the aircraft.
- the hydrogen storage tanks 510 A-G within the cargo bay 502 are distributed symmetrically about a vertical plane 520 passing through the central longitudinal axis 501 of the aircraft, so that their centre of gravity lies in or near the plane 520 .
- Further hydrogen storage tanks may be located elsewhere in or on the aircraft, the centre of gravity of any such tanks lying in the plane 520 .
- the aircraft comprises a hydrogen-fuelled propulsion system and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the propulsion system.
- the maximum width of the cargo bay 502 is 8 r and the height of the cargo bay 502 is 3 . 732 r, where r is the outer radius of the hydrogen storage tanks.
- FIG. 9 shows a transverse cross-section through a lower portion of the fuselage of a third example, the portion defining a cargo space 650 which includes a forward cargo bay 602 .
- the aircraft has a general format similar to that of any of the aircraft 100 , 200 , 300 of FIGS. 1 , 3 and 5 .
- the forward cargo bay 602 contains thirteen hydrogen storage tanks 610 A-M, the longitudinal axes 611 A-M of the tanks being substantially parallel to the central longitudinal axis 601 of the fuselage of the aircraft.
- a first set of four tanks 610 A-D is arranged such that the tanks' longitudinal axes 611 A-D lie in a plane 695 extending across the width dimension (x) of the forward cargo bay 602 .
- each of a second set of five tanks 610 E- 1 lie in a plane 697 which extends across the width dimension of the cargo bay 602 , the plane 697 being parallel to and vertically above the plane 695 .
- a third set of four tanks 610 J-M is arranged such the longitudinal axes 611 J-M of the tanks lie in a third plane 699 extending across the width dimension of the cargo bay 602 , the plane 699 being parallel to the planes 695 , 697 and vertically above the plane 697 .
- any given tank of the first or third sets of tanks has a longitudinal axis which has a position across the width dimension (x) of the cargo bay 602 which is in between the positions of the longitudinal axes of a pair of adjacent tanks in the second set.
- tanks 610 A, 610 J have respective longitudinal axes 611 A, 611 J located between the positions of the longitudinal axes 611 E, 611 F of tanks 610 E, 610 F of the second set of tanks.
- the thirteen hydrogen storage tanks may be located in a rear cargo bay of the aircraft.
- the hydrogen storage tanks within the cargo bay 602 are distributed symmetrically about a vertical plane 620 passing through the central longitudinal axis 601 of the aircraft so that the centre of gravity of the tanks lies in or near the plane 620 .
- the tanks 610 A-M may have an aspect ratio R in the range 10.4 ⁇ R ⁇ 25.7.
- the diameter d of the tanks 610 A-M may be in the range 0.3 ⁇ d ⁇ 0.44.
- the maximum width of the cargo bay 502 is 10 r and the height of the cargo bay 502 is 5 . 464 r, where r is radius of the hydrogen storage tanks.
- Tanks of the FIG. 6 arrangement have a larger diameter than those of the FIG. 8 arrangement, and tanks of the FIG. 8 arrangement have a larger diameter than those of the FIG. 9 arrangement for a given size of cargo bay.
- Tank packing fraction i.e. the fraction of cargo bay volume occupied by hydrogen storage tanks
- the volume of a cargo bay occupied by stored hydrogen may be increased further by taking advantage of the possibility of reduced tank wall thickness as tank diameter is reduced.
- overall tank stiffness decreases. A long, thin composite tank of relatively small wall thickness may therefore need to be supported to prevent tank flexing and resulting damage to the brittle matrix of the composite material of the tank.
- a further alternative embodiment of the invention employs an arrangement similar to that of FIG. 8 but with the tanks distributed differently between forward and rear cargo bays.
- the rear cargo bay may accommodate four tanks and the forward cargo bay accommodate three tanks.
- the distribution of the hydrogen tanks preferably remains symmetric with respect to the plane 520 .
- the arrangements of hydrogen storage tanks shown in FIGS. 8 and 9 may each include an in-situ or common manifold arrangement allowing the number of tanks to be varied simply by removing some of the hydrogen storage tanks, with the rest of the tanks remaining operatively coupled to the hydrogen-fuelled propulsion system of the aircraft. This allows for the respective volumes of a cargo bay occupied by fuel and luggage or freight to be adjusted or traded-off in order to meet the requirements of a particular flight mission or flight profile.
- An in-situ manifold arrangement allows tanks to be inserted or removed without making further adjustments to the fuel system of an aircraft and allows an optimum balance between range and payload to be achieved for a given flight mission.
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- General Engineering & Computer Science (AREA)
- Filling Or Discharging Of Gas Storage Vessels (AREA)
Abstract
An aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system. The aircraft further comprises a fuselage having a cargo bay (502) including one or more (510A-G) of the plurality of hydrogen storage tanks, the longitudinal axes (511A-G) of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis (501) of the fuselage and lying in one or more planes (595, 597) extending across the width dimension of the cargo bay. The hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2≤R≤25.7, allowing the volume of space with the cargo bay occupied by stored hydrogen to be maximised or approximately maximised.
Description
- This application is a divisional of U.S. patent application Ser. No. 17/562,775, filed on Dec. 27, 2021, which is based upon and claims the benefit of priority from British Patent Application No. 2100664.8, filed on Jan. 19, 2020, the entire contents of which are herein incorporated by reference.
- The present disclosure relates to aircraft comprising hydrogen storage tanks, particularly hydrogen storage tanks containing gaseous hydrogen or suitable for containing gaseous hydrogen.
- Hydrogen in either gaseous or liquid form is of increasing interest as a fuel for a variety of transport applications, including aeronautical applications, due to an absence of CO2 generation at the point of use. However, storage of gaseous hydrogen at high pressure presents a significant technical challenge and in particular requires a significant increase in the volume of stored fuel compared to that required for traditional fuel. Minimising the loss of useful space within an aircraft and maximising the amount of stored hydrogen are important considerations in relation to retro-fitting known aircraft with hydrogen storage tanks, or in designing new aircraft having conventional fuselage and wing forms.
- According an example, an aircraft comprises a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks, and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system, the aircraft further comprising a fuselage having a cargo bay including one or more of the plurality of hydrogen storage tanks, the longitudinal axes of the one or more hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis of the fuselage and lying in one or more planes extending across the width dimension of the cargo bay, and wherein the hydrogen storage tanks within the cargo bay have a common aspect ratio R in the range 4.2≤R≤25.7. Where the aircraft has the format of one of number of known aircraft, for example a format like that of the Airbus® A320®, the volume of the cargo bay which is occupied by the hydrogen storage tanks it contains is maximised or approximately maximised.
- The cargo bay may include exactly two hydrogen storage tanks having a common aspect ratio R in the range 4.2≤R≤7.7, each hydrogen storage tank being disposed on a respective lateral side of a vertical plane which passes through the central longitudinal axis of the fuselage and bisects the cargo bay. The hydrogen storage tanks may have a common diameter d in the range 1.0 m d 1.1 m. The cargo bay may be either a forward or rear cargo bay of the aircraft.
- The fuselage of the aircraft may have a forward cargo bay and rear cargo bay, each being bisected by a vertical plane passing through the central longitudinal axis of the fuselage, with the forward and rear cargo bays each including exactly one hydrogen storage tank, each hydrogen storage tank being located on a respective lateral side of the vertical plane and having an aspect ratio R in the range 4.2≤R≤7.7. This allows the weight of the hydrogen storage tanks to be more evenly distributed along the length of the aircraft whilst keeping the centre of gravity of the tanks within or near the vertical plane passing through the central longitudinal axis of the fuselage. The hydrogen storage tanks may optionally also have a common diameter d in the range 1.0 m≤d≤1.1 m.
- The cargo bay may include exactly seven like generally cylindrical hydrogen storage tanks arranged in a first set of three tanks and second set of four tanks, longitudinal axes of hydrogen storage tanks of the first and second sets lying in first and second planes respectively which extend across the width dimension of the cargo bay, the second plane being disposed vertically above the first plane, and the longitudinal axis of any given hydrogen storage tank of the first set having a position across the width of the cargo bay between the positions of the longitudinal axes of two adjacent hydrogen storage tanks of the second set. In this case, the hydrogen storage tanks may have a common aspect ratio R having a value in the range 7.5≤R≤15.4, and optionally also a common diameter d in the range 0.5≤d≤0.63. The seven tanks within the cargo bay are preferably distributed symmetrically about a vertical plane which passes through the central longitudinal axis of the fuselage and bisects the cargo bay so that their centre of gravity lies in or near that plane.
- The cargo bay may include exactly thirteen like hydrogen storage tanks arranged in a first set of four tanks, a second set of five tanks and a third set of four tanks, the longitudinal axes of the hydrogen storage tanks of the first, second sets and third sets lying in first, second and third planes respectively which extend across the width dimension of the cargo bay, the second plane being disposed vertically above the first plane and the third plane being disposed vertically above the second plane, the longitudinal axis of any given hydrogen storage tank of the first and third sets having a position across the width of the cargo bay between the positions of the longitudinal axes of two adjacent tanks of the second set. In this case the hydrogen storage tanks may have a common aspect ratio having a value R in the range 10.4≤R≤25.7 and optionally also a common diameter d in the range 0.3≤d≤0.44. Preferably, the thirteen tanks within the cargo bay are distributed symmetrically about a vertical plane which passes through the central longitudinal axis of the fuselage and bisects the cargo bay, so the centre of gravity of the tanks lies in or near that plane.
- The conveying system preferably comprises a manifold system providing for one or more of the hydrogen storage tanks within a cargo bay to be removed from the cargo bay such that the remaining hydrogen storage tanks within the cargo bay remain operatively coupled to the hydrogen-fuelled propulsion system. This provides an aircraft in which the hydrogen fuel capacity and payload may be optimised for a given flight mission or flight profile.
- Example aircraft are described below with reference to the accompanying drawings in which:
-
FIG. 1 is a side elevation of a first aircraft of a known type; -
FIG. 2 is a longitudinal cross-section of the fuselage of theFIG. 1 aircraft; -
FIG. 3 is a longitudinal cross-section of the fuselage of a second aircraft of a known type; -
FIG. 4 is a transverse cross-section of a lower portion of the fuselage of theFIG. 1 aircraft; -
FIG. 5 is a side elevation of a third aircraft of a known type; -
FIG. 6 is a transverse cross-section of a lower portion of the fuselage of a first example aircraft; -
FIGS. 7A-D show alternative distributions of a pair of hydrogen storage tanks within the first example aircraft; -
FIG. 8 is a transverse cross-section of a lower portion of the fuselage of a second example aircraft; and -
FIG. 9 is a transverse cross-section of a lower portion of the fuselage of a third example aircraft. - Referring to
FIGS. 1, 2 and 4 , anaircraft 100 of known type (e.g. an Airbus® A320® or similar aircraft) comprises afuselage 180 having centrallongitudinal axis 101. The 15fuselage 180 is divided longitudinally into a passenger space (not shown) and acargo space 150 located vertically below the passenger space. Thecargo space 150 includes aforward cargo bay 102 and arear cargo bay 104 located respectively fore and aft of thewing centre structure 103 of theaircraft 100. Avertical plane 120 passing through the centrallongitudinal axis 101 of thefuselage 180 of theaircraft 100 divides each of thecargo spaces plane 120. The forward andrear cargo bays -
FIG. 3 shows a horizontal longitudinal cross-section through thefuselage 280 of asecond aircraft 200 of a known type (e.g. an Airbus® A321® or similar aircraft). Thefuselage 280 has centrallongitudinal axis 201. Thefuselage 280 is divided longitudinally into a passenger space and a cargo space located vertically below the passenger space. The cargo space has forward andrear cargo bays wing centre structure 203 of theaircraft 200. The forward andrear cargo bays -
FIG. 5 shows a side elevation of athird aircraft 300 of a known type (e.g. a Boeing® 737® or similar aircraft) having afuselage 380 with a centrallongitudinal axis 301, and forward andrear cargo bays wing centre structure 303. Cargo bays of commercial aircraft such as 100, 200, 300 are typically in the region of 4.6 m to 7.7 m in length. -
FIG. 6 shows a transverse cross-section through a lower portion of the fuselage of a first example aircraft, the portion defining acargo space 450. The aircraft has a format similar to any of theaircraft FIGS. 1, 3 and 5 respectively. The cross-section includes aforward cargo bay 402 containing two like, generally cylindricalhydrogen storage tanks 410A, 410B. Thetanks 410A, 410B are cylindrical with domed (e.g. hemispherical) ends. Avertical plane 420 through thelongitudinal axis 401 of the fuselage of the aircraft divides the forward cargo bay into two like lateral portions, each hydrogen storage tank 410A, 41B being located in a respective lateral portion. Thelongitudinal axes 411A, 411B of thehydrogen storage tanks 410A, 410B are generally parallel to the centrallongitudinal axis 401 of the fuselage of the aircraft and lie in aplane 495 which is orthogonal to theplane 420 and which extends across the with dimension (x) of thecargo bay 402. Thehydrogen storage tanks 410A, 410B are substantially identical, each having a diameter of 1.0 m or 1.1 m, or a diameter substantially equal to the height h of thecargo bay 402. The aspect ratio R (i.e. length/diameter) of thehydrogen storage tanks 410A, 410B may be in the range 4.2≤R≤7.7 so that the length of the tanks may be equal to the length of thecargo bay 402.FIG. 7A shows a horizontal longitudinal cross-section through thecargo bay 402 in theplane 495. The aircraft has arear cargo bay 404 available for payloads such as baggage and freight. - The aircraft comprises a hydrogen-fuelled propulsion system (for example one or more PEM fuel cells, one or more hydrogen-fuelled gas turbine engines or a combination of one or more fuel-cells and one or more gas turbine engines) and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the propulsion system.
- The mass of hydrogen storage tanks is much greater than the mass of fuel they may contain, therefore such tanks need to be carefully located within an aircraft in order to ensure that the centre of gravity of the aircraft is not in an unsuitable position. Gaseous hydrogen fuel accounts for only 20% of the total mass of a full hydrogen storage tank.
FIGS. 7B —7D show alternative locations for the hydrogen fuel tanks in variants of the first example aircraft. Both tanks may be located in the rear cargo bay (FIG. 7B ), or alternatively one tank may be in the forward cargo bay and one in the rear cargo bay (FIGS. 7C and 7D ), although in all cases each tank is located on a respective lateral side of theplane 420. -
FIG. 8 shows a transverse cross-section through a lower portion of the fuselage of a second example aircraft, the portion defining acargo space 550 which includes aforward cargo bay 502. The aircraft has a general format similar to that of any of theaircraft FIGS. 1, 3 and 5 . Theforward cargo bay 502 contains seven hydrogen storage tanks 510A-G, thelongitudinal axes 511A-G of the tanks being substantially parallel to the centrallongitudinal axis 501 of the fuselage of the aircraft. A first set of three tanks 510A-C is arranged such the tanks'longitudinal axes 511A-C lie in afirst plane 595 extending across the width dimension (x) of theforward cargo bay 502. A second set of fourtanks 510D-G is arranged such that the tanks' longitudinal axes 511 D-G lie in asecond plane 597 extending across the width of theforward cargo bay 502, thesecond plane 597 being disposed vertically above thefirst plane 595. Any given tank of the first set has a longitudinal axis which has a position x across the width of thecargo bay 502 which is in between the positions of the longitudinal axes of two adjacent tanks in the second set. For example, tank 510A has alongitudinal axis 511A located in the x direction between the positions oflongitudinal axes tanks forward cargo bay 502 have a common aspect ratio R in the range 7.5≤R≤15.4 and a common diameter d in the range 0.5≤d≤0.63. The length of the tanks may be equal to the length of thecargo bay 502. In an alternative example aircraft of the invention, the seven hydrogen storage tanks 510A-G may be located in a rear cargo bay of the aircraft. The hydrogen storage tanks 510A-G within thecargo bay 502 are distributed symmetrically about avertical plane 520 passing through the centrallongitudinal axis 501 of the aircraft, so that their centre of gravity lies in or near theplane 520. - Further hydrogen storage tanks may be located elsewhere in or on the aircraft, the centre of gravity of any such tanks lying in the
plane 520. The aircraft comprises a hydrogen-fuelled propulsion system and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the propulsion system. - If the hydrogen storage tanks with the
cargo bay 502 are touching, with tanks of the second set (plane 597) spanning the maximum width of the cargo bay, and the first and second set of tanks in contact with the bottom and top of thecargo bay 502 respectively, then the maximum width of thecargo bay 502 is 8 r and the height of thecargo bay 502 is 3.732 r, where r is the outer radius of the hydrogen storage tanks. -
FIG. 9 shows a transverse cross-section through a lower portion of the fuselage of a third example, the portion defining acargo space 650 which includes aforward cargo bay 602. The aircraft has a general format similar to that of any of theaircraft FIGS. 1, 3 and 5 . Theforward cargo bay 602 contains thirteen hydrogen storage tanks 610A-M, thelongitudinal axes 611A-M of the tanks being substantially parallel to the centrallongitudinal axis 601 of the fuselage of the aircraft. A first set of four tanks 610A-D is arranged such that the tanks'longitudinal axes 611A-D lie in aplane 695 extending across the width dimension (x) of theforward cargo bay 602. The longitudinal axes 611 E-1 of each of a second set of fivetanks 610E-1 lie in aplane 697 which extends across the width dimension of thecargo bay 602, theplane 697 being parallel to and vertically above theplane 695. A third set of fourtanks 610J-M is arranged such thelongitudinal axes 611J-M of the tanks lie in athird plane 699 extending across the width dimension of thecargo bay 602, theplane 699 being parallel to theplanes plane 697. Any given tank of the first or third sets of tanks has a longitudinal axis which has a position across the width dimension (x) of thecargo bay 602 which is in between the positions of the longitudinal axes of a pair of adjacent tanks in the second set. For example,tanks 610A, 610J have respectivelongitudinal axes longitudinal axes tanks cargo bay 602 are distributed symmetrically about avertical plane 620 passing through the centrallongitudinal axis 601 of the aircraft so that the centre of gravity of the tanks lies in or near theplane 620. The tanks 610A-M may have an aspect ratio R in the range 10.4≤R≤25.7. The diameter d of the tanks 610A-M may be in the range 0.3≤d≤0.44. - If the hydrogen storage tanks are touching, with tanks of the second set (plane 697) spanning the maximum width of the cargo bay, and the first and third sets of tanks in contact with the bottom and top of the
cargo bay 602 respectively, then the maximum width of thecargo bay 502 is 10 r and the height of thecargo bay 502 is 5.464 r, where r is radius of the hydrogen storage tanks. - Tanks of the
FIG. 6 arrangement have a larger diameter than those of theFIG. 8 arrangement, and tanks of theFIG. 8 arrangement have a larger diameter than those of theFIG. 9 arrangement for a given size of cargo bay. As tank diameter decreases, hoop stress also decreases and therefore the wall thickness of the tanks may be reduced. Tank packing fraction (i.e. the fraction of cargo bay volume occupied by hydrogen storage tanks) increases moving from theFIG. 6 arrangement to theFIG. 8 arrangement, and from theFIG. 8 arrangement to theFIG. 9 arrangement due to decreasing tank diameter. The volume of a cargo bay occupied by stored hydrogen may be increased further by taking advantage of the possibility of reduced tank wall thickness as tank diameter is reduced. However, as tank wall thickness reduces at constant tank length, overall tank stiffness decreases. A long, thin composite tank of relatively small wall thickness may therefore need to be supported to prevent tank flexing and resulting damage to the brittle matrix of the composite material of the tank. - As the number of hydrogen storage tanks within a cargo bay increases, interconnection and manifolding of the tanks become more complex, adding weight to an aircraft of the invention. There may therefore be trade-off between the number of hydrogen storage tanks within a cargo bay and the overall weight of an aircraft of the invention.
- A further alternative embodiment of the invention employs an arrangement similar to that of
FIG. 8 but with the tanks distributed differently between forward and rear cargo bays. For example, the rear cargo bay may accommodate four tanks and the forward cargo bay accommodate three tanks. However, the distribution of the hydrogen tanks preferably remains symmetric with respect to theplane 520. - The arrangements of hydrogen storage tanks shown in
FIGS. 8 and 9 may each include an in-situ or common manifold arrangement allowing the number of tanks to be varied simply by removing some of the hydrogen storage tanks, with the rest of the tanks remaining operatively coupled to the hydrogen-fuelled propulsion system of the aircraft. This allows for the respective volumes of a cargo bay occupied by fuel and luggage or freight to be adjusted or traded-off in order to meet the requirements of a particular flight mission or flight profile. An in-situ manifold arrangement allows tanks to be inserted or removed without making further adjustments to the fuel system of an aircraft and allows an optimum balance between range and payload to be achieved for a given flight mission.
Claims (5)
1. An aircraft comprising a hydrogen-fuelled propulsion system, a plurality of like generally cylindrical hydrogen storage tanks, and a conveying system arranged to convey hydrogen from the hydrogen storage tanks to the hydrogen-fuelled propulsion system, wherein the aircraft further comprises a fuselage having a cargo bay containing exactly thirteen like generally cylindrical hydrogen storage tanks arranged in a first set of four tanks, a second set of five tanks and a third set of four tanks, the longitudinal axes of said thirteen hydrogen storage tanks within the cargo bay extending parallel to the longitudinal axis of the fuselage and the longitudinal axes of hydrogen storage tanks of the first, second sets and third sets lying in first, second and third planes respectively which extend across the width dimension of the cargo bay, the second plane being disposed vertically above the first plane and the third plane being disposed vertically above the second plane, and wherein the longitudinal axis of any given hydrogen storage tank of the first and third sets has a position across the width of the cargo bay between the positions of the longitudinal axes of two adjacent hydrogen storage tanks of the second set.
2. An aircraft according to claim 1 wherein the thirteen hydrogen storage tanks contained in the cargo bay have a common aspect ratio having a value R in the range 10.4≤R≤25.7.
3. An aircraft according to claim 2 wherein said hydrogen storage tanks have a common diameter d in the range 0.3 m≤d≤0.44 m.
4. An aircraft according to claim 1 wherein the thirteen tanks within the cargo bay are distributed symmetrically about a vertical plane which passes through the central longitudinal axis of the fuselage and bisects the cargo bay.
5. An aircraft according to claim 1 wherein the conveying system comprises a manifold system providing for one or more of the thirteen hydrogen storage tanks within the cargo bay to be removed from the cargo bay such that the remaining hydrogen storage tanks within the cargo bay remain operatively coupled to the hydrogen-fuelled propulsion system.
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US18/187,830 US20230249840A1 (en) | 2021-01-19 | 2023-03-22 | Aircraft comprising hydrogen storage tanks |
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GBGB2100664.8A GB202100664D0 (en) | 2021-01-19 | 2021-01-19 | Aircraft comprising hydrogen storage tanks |
US17/562,775 US11905028B2 (en) | 2021-01-19 | 2021-12-27 | Aircraft comprising hydrogen storage tanks |
US18/187,830 US20230249840A1 (en) | 2021-01-19 | 2023-03-22 | Aircraft comprising hydrogen storage tanks |
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CN115071951A (en) * | 2022-07-25 | 2022-09-20 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Three-airframe integrated airplane |
FR3138650A1 (en) * | 2022-08-03 | 2024-02-09 | Airbus Operations (S.A.S.) | Aircraft comprising a fuselage reinforced by a ventral beam and provided with at least one opening closed by a removable panel |
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US20040129836A1 (en) * | 2002-09-10 | 2004-07-08 | The Boeing Company | Liquid hydrogen fueled aircraft |
US7051979B2 (en) | 2004-01-29 | 2006-05-30 | The Boeing Company | Auxiliary fuel tank systems for aircraft and methods for their manufacture and use |
US7624946B2 (en) * | 2004-03-30 | 2009-12-01 | Airbus Deutschland Gmbh | Reservoir for cryogenic fuels and vehicles |
US7871042B2 (en) * | 2006-11-14 | 2011-01-18 | The Boeing Company | Hydrogen fueled blended wing body ring tank |
EP2224519A1 (en) * | 2009-02-16 | 2010-09-01 | HyET Holding B.V. | Hydrogen storage vessel and fuel cell apparatus comprising an ionic decompression cell |
US8851424B2 (en) | 2010-05-06 | 2014-10-07 | Embraer S.A. | Systems and methods to provide compliance with structural load requirements for aircraft with additional fuel tankage |
JP6363598B2 (en) * | 2012-07-26 | 2018-07-25 | ゾディアック エアロテクニクス | Removable storage for hydrogen mounted on passenger transport such as aircraft |
US10279921B2 (en) * | 2012-10-31 | 2019-05-07 | General Electric Company | Cryogenic tank |
US10800525B2 (en) | 2013-05-20 | 2020-10-13 | The Boeing Company | Efficient low carbon emission airplane integrating jet fuel and cryogenic fuel systems |
DE102014107316A1 (en) | 2014-05-23 | 2015-11-26 | Airbus Operations Gmbh | Tank system for the cryogenic storage of hydrogen and aircraft with a tank system for the cryogenic storage of hydrogen |
WO2016022334A1 (en) * | 2014-08-04 | 2016-02-11 | Washington State University | Vapor cooled shielding liner for cryogenic storage in composite pressure vessels |
CN107972877B (en) | 2017-12-26 | 2024-03-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Hydrogen fuel aircraft |
CN207712306U (en) | 2017-12-26 | 2018-08-10 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of hydrogen fuel aircraft |
FR3096029A1 (en) * | 2019-09-16 | 2020-11-20 | Airbus | AIRCRAFT CONTAINING HYDROGEN TANKS |
US11643204B2 (en) | 2019-12-09 | 2023-05-09 | Arizona Board Of Regents On Behalf Of Arizona State University | Unmanned aerial vehicle for low-pressure hydrogen transport |
AU2021273192A1 (en) | 2020-05-12 | 2023-02-02 | Universal Hydrogen Co. | Systems and methods for storing, transporting, and using hydrogen |
US11796132B2 (en) * | 2020-12-02 | 2023-10-24 | Green Grid Inc. | Hydrogen fuel storage and delivery system |
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