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WO2024170958A1 - Drone fonctionnant à l'hydrogène - Google Patents

Drone fonctionnant à l'hydrogène Download PDF

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Publication number
WO2024170958A1
WO2024170958A1 PCT/IB2024/000089 IB2024000089W WO2024170958A1 WO 2024170958 A1 WO2024170958 A1 WO 2024170958A1 IB 2024000089 W IB2024000089 W IB 2024000089W WO 2024170958 A1 WO2024170958 A1 WO 2024170958A1
Authority
WO
WIPO (PCT)
Prior art keywords
hydrogen
propeller
hover
body portion
central body
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/IB2024/000089
Other languages
English (en)
Inventor
Ofer Rubin
Ran ALTMAN
Ido Baruchin
Orion CHASID
David MARKOVITS
Omri Sirkis
Nimrod NACHMIAS
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hevendrones Ltd
Original Assignee
Hevendrones Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hevendrones Ltd filed Critical Hevendrones Ltd
Publication of WO2024170958A1 publication Critical patent/WO2024170958A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/25—Fixed-wing aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0016—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers
    • B64C29/0025—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by free or ducted propellers or by blowers the propellers being fixed relative to the fuselage
    • 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
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • B64U10/10—Rotorcrafts
    • B64U10/13—Flying platforms
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U20/00—Constructional aspects of UAVs
    • B64U20/40—Modular UAVs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/10—Wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U30/00—Means for producing lift; Empennages; Arrangements thereof
    • B64U30/20—Rotors; Rotor supports
    • B64U30/21—Rotary wings
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/19—Propulsion using electrically powered motors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/30—Supply or distribution of electrical power
    • B64U50/32—Supply or distribution of electrical power generated by fuel cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U80/00—Transport or storage specially adapted for UAVs
    • 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
    • B64D41/00—Power installations for auxiliary purposes
    • B64D2041/005—Fuel cells

Definitions

  • the exemplary embodiments relate to autonomous airborne vehicles, commonly referred to as drones. More particularly, the exemplary embodiments relate to drones that are hydrogen-powered, or are hybrid-powered including hydrogen and batteries.
  • Drones are used for a wide variety of missions. To increase the utility of drones, it is desirable to increase their range, payload, cruising speed, maximum operational altitude, or more than one of the above.
  • an autonomous airborne vehicle includes a central body portion having a first lateral side and a second lateral side opposite the first lateral side, wherein the central body portion defines a longitudinal roll axis and a vertical yaw axis; a first wing extending from the first lateral side of the central body portion; a second wing extending from the lateral side of the central body portion; a first boom positioned on an underside of the first wing, wherein the first boom is oriented in a direction parallel to the longitudinal roll axis, and wherein the first boom has a first end and a second end opposite the first end; a second boom positioned on an underside of the second wing, wherein the second boom is oriented in a direction parallel to the longitudinal roll axis, and wherein the second boom has a first end and a second end opposite the first end of the second boom; a first hover propeller positioned at the first end of the first boom, wherein the first hover propeller is configured to provide thrust in
  • the first wing and the second wing are configured to be removable from the central body portion.
  • the first boom is configured to be removable from the first wing
  • the second boom is configured to be removable from the second wing.
  • the central body portion includes a payload area therein.
  • the hydrogen cylinder is positioned in a nose portion of the central body portion
  • the hydrogen fuel cell is positioned in a tail portion of the central body portion
  • the payload area is positioned between the hydrogen cylinder and the hydrogen fuel cell.
  • the autonomous airborne vehicle also includes a forward bulkhead positioned between the hydrogen cylinder and the payload area, and a rear bulkhead positioned between the hydrogen fuel cell and the payload area.
  • the first wing includes a first wing spar
  • the second wing includes a second wing spar
  • the first wing spar and the second wing spar are joined to the forward bulkhead.
  • the hydrogen cylinder is interchangeably received within the central body portion.
  • a nose of the central body portion is configured to be opened to allow the hydrogen cylinder to be interchanged.
  • the autonomous airborne vehicle also includes at least one air intake configured to capture air and deliver the captured air to the hydrogen fuel cell during forward flight to thereby cool the hydrogen fuel cell.
  • the autonomous airborne vehicle also includes at least one air exhaust configured to exhaust the captured air.
  • an aft-most point of the first wing is further aft than an aft- most point of the central body portion.
  • the central body portion lacks a tailplane.
  • the pusher propeller has a smaller diameter than the first hover propeller.
  • the pusher propeller has a diameter of between 22 inches and 30 inches, and the first hover propeller has a diameter of between 31 inches and 36 inches.
  • the pusher propeller has a smaller blade pitch than the first hover propeller.
  • the autonomous airborne vehicle has a maximum gross takeoff weight that is in a range of from 40 kilograms to 70 kilograms.
  • the autonomous airborne vehicle is configured to accommodate a payload having a weight that is in a range of from 2 kilograms to 20 kilograms.
  • Figure 1A shows a perspective view rendering of an exemplary embodiment of a hydrogen-powered drone.
  • Figure IB shows a top view rendering of the hydrogen-powered drone shown in Figure 1A.
  • Figure 2A shows an exemplary refueling system for a drone.
  • Figure 2B shows an exemplary refueling system for a hydrogen cylinder.
  • Figure 3 shows an exemplary hydrogen fuel cell-based power system for a drone.
  • Figure 4A shows a top view of an exemplary drone.
  • Figure 4B shows a side view of the exemplary drone shown in Figure 4A.
  • Figure 4C shows a disassembled view of the exemplary drone shown in Figure 4A, the drone being shown packed for transportation.
  • Figure 4D shows a perspective view of the exemplary drone shown in Figure 4A, the exterior of the drone being rendered transparently to show interior elements of the drone.
  • Figure 4E shows a top view of the exemplary drone shown in Figure 4A, the exterior of the drone being rendered transparently to show interior elements of the drone.
  • Figure 5A shows a perspective view of an exemplary drone that is similar to the exemplary drone shown in Figure 4A.
  • Figure 5B shows a top view of the exemplary drone shown in Figure 5A.
  • the exemplary embodiments relate to drones (e.g., autonomous airborne vehicles) that are powered by hydrogen fuel cells.
  • a drone includes a hybrid power system including a hydrogen fuel cell together with a battery.
  • the hydrogen fuel cell (together with the battery in hybrid embodiments) delivers electrical power to a plurality of rotors to thereby enable the drone to fly.
  • Figures 1 A and IB show a perspective view and a top view, respectively, of a hydrogen-powered drone 100.
  • a hydrogen-powered drone may have five times or more longer flight times as compared with a comparable battery-powered drone.
  • a hydrogen-powered drone may operate in more extreme conditions, as compared with a comparable battery-powered drone.
  • a hydrogen-powered drone may utilize sustainable energy, as compared with a comparable battery-powered drone.
  • a hydrogen-powered drone may have a reduced carbon footprint, as compared with a comparable battery-powered drone.
  • the use of one or more hydrogen fuel cells may allow for a drone design that is more efficient.
  • the use of hydrogen fuel cells may result in a light platform.
  • the use of hydrogen fuel cells may result in a safe platform.
  • the use of hydrogen fuel cells may be economical in terms of total cost of ownership.
  • the use of hydrogen fuel cells may be suitable for multiple tasks.
  • a hydrogen-powered drone may fly for a distance (e.g., have a range) of greater than 60 km, or greater than 100 km, or between 100 km and 200 km.
  • a hydrogen-powered drone may have a flight endurance of at least 100 minutes, or at least 200 minutes, or at least 300 minutes, or at least 400 minutes, or at least 500 minutes with a 5 kg payload.
  • a hydrogen-powered drone may have a maximum payload of at least 7 kg (e.g., between 7 kg and 20 kg).
  • a hydrogen-powered drone has a cruise speed of at least 15 meters per second (e.g., at least 30 meters per second).
  • a hydrogen-powered drone is configured to be refueled quickly and efficiently.
  • a hydrogen-powered drone may be refueled in less than 10 minutes, with enough fuel to fly for a time period of 2 hours, or for a time period of 5 hours, or for a time period of 8 hours, or for a time period of 10 hours.
  • the drone is configured to be coupled to a local hydrogen source (e.g., a hydrogen source and compressor) to thereby refuel the drone.
  • Figure 2A shows a drone 200 (e.g., which may be substantially similar to the drone 100 described above or any other exemplary drone described herein) coupled to a local hydrogen source 210 via a fueling hose 220.
  • the drone is configured to interchangeably receive a hydrogen tank that is configured to be coupled to a local hydrogen source (e.g., a hydrogen source and a compressor) to thereby refuel the drone.
  • a hydrogen tank 250 e.g., which may be received by the drone 100 or any other exemplary drone described herein
  • the local hydrogen source 210 and the local hydrogen source 260 are the same local hydrogen source.
  • a hydrogen-powered drone includes a hydrogen fuel cellbased power system.
  • Figure 3 shows selected elements of a power system 300.
  • the power system 300 includes a hydrogen cylinder 310.
  • the hydrogen cylinder 310 is configured to contain pressurized hydrogen therein.
  • the power system 300 includes a fuel cell 320.
  • the fuel cell 320 is operable to receive hydrogen (e.g., from the hydrogen cylinder 310) and oxygen (e.g., from ambient air) and react the hydrogen with the oxygen to produce electricity.
  • the power system 300 includes a regulator 330 coupled to the hydrogen cylinder 310 and to the fuel cell 320 to thereby control a flow of hydrogen from the hydrogen cylinder to the fuel cell.
  • the power system 300 is thereby operable to provide electrical power 340 to power a drone as described herein.
  • an exemplary drone is a multirotor drone.
  • the drone may be highly agile and capable of landing in poorly defined terrain (e.g., uneven ground, sloping ground, rocky ground, etc.), as well as designated landing spaces.
  • the drone may be operated by a remote control.
  • the drone may autonomously map out the most efficient route to its destination.
  • an exemplary drone is customizable to the unique goals of its commercial clients.
  • the drone is configured to receive different payloads interchangeably to fit the needs of different clients, different mission profiles, etc.
  • the drone may measure the nutrient levels of soil for farmers.
  • the drone may collect risk-assessment data for construction companies.
  • the drone may perform last-mile delivery.
  • the drone may identify real estate for reforestation projects.
  • the drone may aid emergency responders in risk assessment and delivery of supplies.
  • an exemplary drone is lightweight.
  • the drone may be programmed with a DMMS, a control system that contains multiple gyroscopes and supporting algorithms, which may significantly extend the operating boundary of stable flight.
  • a drone has an electrical system including epoxy casings for wiring thereof, thereby to reduce vibration experienced by one or more, or all of, the cylinder, fuel cell, and/or motor.
  • a relatively flexible wire may be used, a set of flexible wires may be intertwined, and or one or more crimping connections rather than soldering connections may be used.
  • a drone is configured to allow operation in rainy, dusty, and other environments.
  • a drone has aerodynamic body design.
  • the drone may have an integrated wing structure to provide additional lift.
  • the drone may use lightweight materials, including a custom cylinder.
  • Hydrogen cylinders generate heat.
  • Other vehicles that successfully employ hydrogen engines e g., buses and cars
  • a drone includes a cooling system for the hydrogen cylinder which integrates with a drone’s smaller form factor and aerodynamic requirements.
  • cooling may be achieved by switching tanks.
  • a drone is configured to be refueled autonomously, via a system for swapping hydrogen cylinders.
  • a drone is configured to provide improved performance (e.g., one or more, or all of, longer endurance, greater distance, more power for lift.
  • Hydrogen fuel cells may be limited in power (e.g., in terns of supply of continuous power in contrast to a battery).
  • a 30-kilogram drone needs 3000 watts to fly, but may not have enough engine power to get off the ground.
  • the drone’s aerodynamic may provide extra lift.
  • the aerodynamics of a drone are configured to provide a sufficient portion of the lift that is needed, thereby requiring less power (such that a hydrogen cell is sufficient).
  • a battery of the same weight as a comparable hydrogen system gives more power.
  • a battery may give more boost, but provide less storage; while hydrogen may give less boost, but provide more storage.
  • a hydrogen/battery hybrid system includes a battery to provide extra boost.
  • battery, payload, or other components is interchangeable on a drone.
  • a drone includes electrical connectors for a payload (e.g., generic connectors).
  • a hybrid drone allows for hovering at a heavier gross weight but for less time, as hovering requires more power than forward flight.
  • a drone is configurable such that, when the drone’s mission is mostly hovering, the drone’s wings may be removed because the drone does not need to be aerodynamic, and removing the wings saves weight.
  • a drone includes an algorithmically-controlled power distribution unit.
  • FIG. 4A shows a top view schematic rendering of an exemplary embodiment of a drone 400.
  • the drone includes a body 410 including a central body portion 415 and first and second wings 420 and 425 extending from opposite lateral sides of the central body portion 415.
  • the central body portion 415 defines a roll axis (e.g., a longitudinal axis) that generally defines a forward-flight direction of the drone 400.
  • the central body portion 415 defines a yaw axis Y (e.g., a vertical axis) that is perpendicular to the roll axis X and is oriented vertically when the drone 400 is level.
  • the wings 420 and 425 include an airfoil profile that is configured to provide lift during forward flight.
  • the central body portion 415 and the wings 420 and 425 are made from an aerospace composite (e.g., a polymer, such as an epoxy, containing one or more stiffening fibers, such as carbon fiber, glass fiber, or aramid fiber).
  • the drone 400 is configured to allow the wings 420 and 425 to be removed from the central body portion 415 for packing and shipment of the drone 400.
  • the first wing 420 includes a main wing spar 421 and the second wing 425 includes a main wing spar 426.
  • the main wing spars 421 and 426 provide structural support to the wings 420 and 425, respectively.
  • the drone 400 has a wingspan of between 4 meters and 6 meters, or between 4 meters and 5.5 meters, or between 4 meters and 5 meters, or between 4 meters and 4.5 meters, or between 4.5 meters and 6 meters, or between 4.5 meters and 5.5 meters, or between 4.5 meters and 5 meters, or between 5 meters and 6 meters, or between 5 meters and 5.5 meters, or between 5.5 meters and 6 meters, or between 4.75 meters and 5.25 meters, or between 4.8 meters and 5.2 meters, or between 4.9 meters and 5.1 meters, or about 4.5 meters, or 4.5 meters, or about 5 meters, or 5 meters, or about 5.5 meters, or 5.5 meters.
  • the central body portion 415 has a nose-to-tail length of between 1.5 meters and 2.5 meters, or between 1.5 meters and 2.25 meters, or between 1.5 meters and 2 meters, or between 1 .5 meters and 1 .75 meters, or between 1 .75 meters and 2.5 meters, or between 1.75 meters and 2.25 meters, or between 1.75 meters and 2 meters, or between 2 meters and 2.5 meters, or between 2 meters and 2.25 meters, or between 2.25 meters and 2.5 meters, or between 1.8 meters and 2.2 meters, or between 1.9 meters and 2.1 meters, or between 1.95 meters and 2.05 meters, or about 1.5 meters, or 1.5 meters, or about 1.75 meters, or 1.75 meters, or about 2 meters, or 2 meters, or about 2.25 meters, or 2.25 meters, or about 2.5 meters, or 2.5 meters.
  • the body 410 is shaped in a manner such that the drone 400 can be referred to as a “flying wing” type aircraft.
  • the body 410 is shaped in a manner such that it lacks a tail including vertical stabilizers, horizontal stabilizers, a rudder, or an elevator (e g., a tailplane).
  • the body 410 is shaped such that the aft-most points at the tips of the wings 420 and 425 are positioned further aft along the roll axis X than is the aft- most point at the rear of the central body portion 415, or are positioned at the same distance aft along the roll axis X as is the aft-most point at the rear of the central body portion 415.
  • the drone 400 includes booms 430 and 435.
  • each of the booms 430 and 435 is coupled to an underside of a respective one of the wings 420 and 425 in an orientation such that the booms 430 and 435 are oriented parallel to the roll axis X.
  • the booms 430 and 435 are formed from an aerospace composite as described above.
  • the booms 430 and 435 are removable from the wings 420 and 425 for packing and shipment of the drone 400.
  • FIG. 4C shows the drone 400 disassembled as described above for packing and shipment.
  • the drone 400 is disassembled into five main pieces, namely the central body portion 415, the wings 420 and 425, and the booms 430 and 435.
  • a drone 400 that is sized as described herein is capable of being packed into a container 401 that is 2.5 meters in length, 1.2 meters in width, and 0.9 meters in height.
  • the drone 400 includes a main landing gear 418 extending from the lower side of the central body portion 415.
  • the drone 400 includes side landing gear 431 and 436 (the side landing gear 431 being obscured by the side landing gear 436 in the side view shown in Figure 4B), each of which extends from the lower side of a respective one of the booms 430 and 435.
  • the drone 400 is configured such that, when positioned on level ground, the main landing gear 418 bears about 60% of the weight of the drone 400, and the side landing gear 431 and 436 each bear about 20% of the weight of the drone 400.
  • the side landing gear 431 and 436 are shaped to act as vertical stabilizers during forward flight.
  • each of the side landing gear 431 and 436 includes a rudder operable to provide flight control during forward flight.
  • the main landing gear 418 and the side landing gear 431 and 436 are sized to provide a ground clearance of about 0.5 meter when the drone 400 is positioned on level ground.
  • the drone 400 includes four hover propellers 432, 433, 437, and 438.
  • hover propeller includes encompasses both the propellers themselves (i.e., the rotating blades) and the motors (e.g., electric motors) that are coupled to the propellers so as to drive rotation.
  • the hover propellers 432 and 433 are positioned at opposite ends of the boom 430, and the hover propellers 437 and 438 are positioned at opposite ends of the boom 435.
  • the hover propellers 432, 433, 437, and 438 are operable to provide vertical lift (e.g., to provide thrust in a direction parallel to the yaw axis Y) so as to allow the drone 400 to hover.
  • the hover propellers 432, 433, 437, and 438 each have a diameter that is in a range of 30 inches to 36 inches (e g., in a range from 31 to 35 inches).
  • the hover propellers 432, 433, 437, and 438 have a blade pitch that is between 10° and 12.5° (e.g., that is 11°).
  • each of the hover propellers 432, 433, 437, and 438 includes a motor having a power that is between 1000 watts and 2000 watts. In some embodiments, each of the hover propellers 432, 433, 437, and 438 has a weight that is between 0.5 kilograms and 1.5 kilograms. In some embodiments, each of the hover propellers 432, 433, 437, and 438 is operable to generate a thrust that is between 8 kilograms and 30 kilograms. In some embodiments, each of the hover propellers 432, 433, 437, and 438 is configured that, when the drone 400 is operating at nominal conditions, each of the hover propellers 432, 433, 437, and 438 generates between 40% and 70% of its maximum thrust.
  • the drone 400 includes a pusher propeller 416.
  • the term “pusher propeller” includes encompasses both the propellers themselves (i.e., the rotating blades) and the motor (e.g., electric motor) that are is to the propellers so as to drive rotation.
  • the pusher propeller 416 is positioned at the rear of the central body portion 415 and is oriented so as to generate thrust along the roll axis X, thereby to enable forward flight of the drone 400.
  • the pusher propeller 416 has a diameter of 22 to 30 inches (e.g., a diameter of 25 to 27 inches).
  • the pusher propeller 416 has a smaller blade pitch than do the hover propellers 432, 433, 437, and 438. In some embodiments, the pusher propeller 416 has a blade pitch that is between 8.5° and 11.5° (e.g., that is 10°). In some embodiments, the pusher propeller 416 has a blade pitch that is between 8.5° and 11.5° (e g., that is 10°) and is less than the blade pitch of the hover propellers 432, 433, 437, and 438.. In some embodiments, the pusher propeller 416 includes a motor having a power that is between 900 and 2500 watts.
  • the pusher propeller 416 is operable to generate a thrust that is between 4 kilograms and 25 kilograms. In some embodiments, the pusher propeller 416 is configured that, when the drone 400 is operating at nominal conditions, the pusher propeller 416 generates between 40% and 70% of its maximum thrust.
  • the body 410 defines a body interior 450.
  • the body interior 450 contains various elements that are necessary for operation of the drone 400.
  • Figures 4D and 4E show a perspective view and a top view, respectively, of the drone 400 with the body 410 rendered partially transparent so as to show internal elements of the drone 400.
  • the body interior 450 includes suitable fittings (e.g., mounting points) that are configured to retain such elements.
  • the body interior 450 includes a forward bulkhead 452 and a rear bulkhead 454 that subdivide the body interior 450 into different areas.
  • the body 410 includes one or more doors 458 providing access to the body interior 450.
  • the forward bulkhead 452 is coupled to the wing spars 421 and 426 so as to join the wings 420 and 425 to one another.
  • the drone 400 includes a hydrogen cylinder 460 that is positioned forward of the forward bulkhead 452.
  • the hydrogen cylinder 460 is sized to contain between 13 and 34 liters of pressurized hydrogen, e.g., 13 liters, or 15 liters, or 20 liters, or 25 liters, or 30 liters, or 34 liters.
  • the hydrogen cylinder 460 has a length that is between 352 millimeters and 527 millimeters.
  • the hydrogen cylinder 460 has a diameter that is between 189 millimeters and 274 millimeters.
  • the hydrogen cylinder 460 has a safety factor of between 1.4 and 3.2.
  • the drone 400 is configured to removably and interchangeably receive the hydrogen cylinder 460.
  • one of the doors 458 is positioned (e.g., on the upper surface of the body 410 or on the nose of the body 410 to allow access to the hydrogen cylinder 460 for removal and replacement.
  • the drone 400 is configured to be able to receive hydrogen cylinders 460 of different sizes (e.g., 13 liters, 15 liters, 20 liters, 25 liters, 30 liters, 34 liters, etc.) in order to customize the drone 400 to different mission profiles.
  • the drone 400 includes a fuel cell 465 that is positioned aft of the rear bulkhead 454.
  • the fuel cell 465 is coupled to the hydrogen cylinder 460 in order to receive a supply of hydrogen therefrom, such as using a regulator in the manner described above with reference to Figure 3.
  • the fuel cell 465 is electrically coupled to the hover propellers 432, 433, 437, and 438 and the pusher propeller 416, thereby to deliver electricity to allow the hover propellers 432, 433, 437, and 438 and the pusher propeller 416 to operate.
  • the fuel cell 465 is operable to provide electrical power of between 2 kilowatts and 5 kilowatts.
  • the fuel cell 465 has a weight that is between 4 kilograms and 6 kilograms.
  • a payload area 456 is defined between the forward bulkhead 452 and the rear bulkhead 454.
  • the forward bulkhead 452 and the rear bulkhead 454 provide separation between a payload contained within the payload area 456 and the operational elements of the drone 400, such as the hydrogen cylinder 460 and the fuel cell 465.
  • the payload area 456 provides isolation (e.g., thermal isolation, vibrational isolation, etc.) to a payload contained therein.
  • the body includes one or more of the doors 458 that provides access to the payload area 456.
  • the drone 400 includes a winch 470.
  • the winch 470 is operable to allow a cargo to be lifted by the drone 400.
  • the drone 400 includes communications equipment 475.
  • the communications equipment 475 is configured to allow the drone 400 (including flight control hardware, payload, etc.) to communicate with external parties (e g., via cellular, satellite, or other wireless communication).
  • the drone 400 includes a battery 480.
  • the battery 480 together with the fuel cell 465, forms a hybrid power system that is capable of powering onboard elements of the drone 400 (e.g., the hover propellers 432, 433, 437, and 438 and the pusher propeller 416, a payload within the payload area 456, the winch 470, the communications equipment 475, flight control electronics, etc.) in a hybrid manner such that, at any given time, power is drawn from the fuel cell 465, the battery 480, or both, depending on the operational situation of the drone 400.
  • the hover propellers 432, 433, 437, and 438 and the pusher propeller 416 e.g., the hover propellers 432, 433, 437, and 438 and the pusher propeller 416, a payload within the payload area 456, the winch 470, the communications equipment 475, flight control electronics, etc.
  • the drone 400 includes air intakes 490 and 492, and an air exhaust 494.
  • the air intakes 490 and 492 are positioned at locations the body 410 that are near the fuel cell 465.
  • the air intakes 490 and 492 are oriented so as to capture air and direct the captured air toward the fuel cell 465 when the drone 400 is in forward flight.
  • capturing and directing air toward the fuel cell 465 allows the fuel cell 465 to be cooled.
  • the air intakes 490 and 492 are oriented so as to direct the captured air toward other elements of the drone 400 that require cooling (e g., electronic equipment, etc.).
  • capturing and directing air toward the fuel cell 465 allows for efficient operation of the fuel cell.
  • the air exhaust 494 allows the captured air to flow out of the drone 400, thereby facilitating cooling of the fuel cell 465.
  • the drone 400 has a maximum takeoff weight of at least 40 kilograms, or at least 45 kilograms, or at least 50 kilograms, or at least 55 kilograms, or at least 60 kilograms, or between 40 kilograms and 70 kilograms, or between 40 kilograms and 60 kilograms, or between 40 kilograms and 50 kilograms, or between 50 kilograms and 70 kilograms, or between 50 kilograms and 60 kilograms, or between 60 kilograms and 70 kilograms, or about 40 kilograms, or 40 kilograms, or about 45 kilograms, or 45 kilograms, or about 50 kilograms, or 50 kilograms, or about 55 kilograms, or 55 kilograms, or about 60 kilograms, or 60 kilograms, or 60 kilograms
  • the drone 400 is configured to accommodate a payload having a weight of between 2 kilograms and 20 kilograms, or between 2 kilograms and 15 kilograms, or between 2 kilograms and 10 kilograms, or between 2 kilograms and 5 kilograms, 5 kilograms and 20 kilograms, or between 5 kilograms and 15 kilograms, or between 5 kilograms and 10 kilograms, or between 10 kilograms and 20 kilograms, or between 10 kilograms and 15 kilograms, or between 15 kilograms and 20 kilograms.
  • Figures 5A and 5B show a perspective view and a top view, respectively, of an exemplary embodiment of a drone 500 that is substantially similar to the drone 400 described above.
  • the drone 500 includes a body 510 having a central body portion 515 and wings 520 and 525.
  • the drone 500 includes booms 530 and 535.
  • the drone 500 includes hover propellers 532, 533, 537, and 538, and a pusher propeller 516.
  • the central body portion 515 includes a nose 518 that can be opened to allow a hydrogen cylinder to be accessed and interchanged.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Transportation (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Fuel Cell (AREA)

Abstract

L'invention concerne un véhicule aérien autonome comprenant une portion de corps centrale ayant des premier et deuxième côtés latéraux ; des première et deuxième ailes s'étendant à partir des premier et deuxième côtés respectifs de la portion de corps centrale ; des première et deuxième flèches orientées longitudinalement positionnées sur les côtés inférieurs des première et deuxième ailes respectives ; des hélices de vol stationnaire positionnées à chaque extrémité de chaque flèche et configurées pour fournir une poussée dans une direction verticale ; une hélice de poussée positionnée au niveau d'une extrémité arrière de la portion de corps central et configurée pour fournir une poussée le long de l'axe de roulis ; une bouteille d'hydrogène contenant de l'hydrogène sous pression ; une pile à combustible à hydrogène couplée à la bouteille d'hydrogène de façon à recevoir de l'hydrogène de la bouteille d'hydrogène, configurée pour faire réagir l'hydrogène avec de l'oxygène pour générer de l'électricité, et couplée électriquement aux hélices de vol stationnaire et à l'hélice de poussée de façon à fournir de l'électricité à celles-ci, la portion de corps centrale ayant la forme d'une aile volante.
PCT/IB2024/000089 2023-02-14 2024-02-14 Drone fonctionnant à l'hydrogène Ceased WO2024170958A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US202363484919P 2023-02-14 2023-02-14
US63/484,919 2023-02-14

Publications (1)

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WO2024170958A1 true WO2024170958A1 (fr) 2024-08-22

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Citations (8)

* Cited by examiner, † Cited by third party
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US6170778B1 (en) * 1999-04-22 2001-01-09 Sikorsky Aircraft Corporation Method of reducing a nose-up pitching moment on a ducted unmanned aerial vehicle
US20060091258A1 (en) * 2004-10-29 2006-05-04 Chiu Tien S Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV)
US20160375997A1 (en) * 2015-03-03 2016-12-29 Amazon Technologies, Inc. Unmanned aerial vehicle with a tri-wing configuration
US20190337407A1 (en) * 2014-08-08 2019-11-07 SZ DJI Technology Co., Ltd. Systems and methods for uav battery exchange
CN111794880A (zh) * 2020-07-18 2020-10-20 河北柒壹壹玖工业自动化技术有限公司 一种基于氢动能发动机的储氢罐恒温装置
US20220052361A1 (en) * 2020-08-12 2022-02-17 Alakai Technologies Corporation Fuel cell oxygen delivery system, method and apparatus for clean fuel electric aircraft
US20220169371A1 (en) * 2019-03-25 2022-06-02 Lift Air Gmbh Aircraft
US20220194579A1 (en) * 2019-04-23 2022-06-23 Intelligent Energy Limited Uav having configurable fuel cell power system

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6170778B1 (en) * 1999-04-22 2001-01-09 Sikorsky Aircraft Corporation Method of reducing a nose-up pitching moment on a ducted unmanned aerial vehicle
US20060091258A1 (en) * 2004-10-29 2006-05-04 Chiu Tien S Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV)
US20190337407A1 (en) * 2014-08-08 2019-11-07 SZ DJI Technology Co., Ltd. Systems and methods for uav battery exchange
US20160375997A1 (en) * 2015-03-03 2016-12-29 Amazon Technologies, Inc. Unmanned aerial vehicle with a tri-wing configuration
US20220169371A1 (en) * 2019-03-25 2022-06-02 Lift Air Gmbh Aircraft
US20220194579A1 (en) * 2019-04-23 2022-06-23 Intelligent Energy Limited Uav having configurable fuel cell power system
CN111794880A (zh) * 2020-07-18 2020-10-20 河北柒壹壹玖工业自动化技术有限公司 一种基于氢动能发动机的储氢罐恒温装置
US20220052361A1 (en) * 2020-08-12 2022-02-17 Alakai Technologies Corporation Fuel cell oxygen delivery system, method and apparatus for clean fuel electric aircraft

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