WO2017143431A1

WO2017143431A1 - Air transportable fuel cell power system

Info

Publication number: WO2017143431A1
Application number: PCT/CA2017/000034
Authority: WO
Inventors: Thomas David Jones; Michel Meyer Bitton
Original assignee: Energyor Technologies Inc.
Priority date: 2016-02-23
Filing date: 2017-02-22
Publication date: 2017-08-31
Also published as: CA3050754A1

Abstract

Disclosed herein is a system for delivering a power source to a remote location. The system includes an unmanned aerial vehicle (UAV) with a primary power system connected to it to fly the UAV to the remote location. The UAV is autonomously controlled. The primary power system is capable of being converted to a secondary power system to provide a power source at the remote location. A controller in communication with the UAV is used to operate the UAV and fly the UAV to the remote location.

Description

AIR TRANSPORTABLE FUEL CELL POWER SYSTEM

TECHNICAL FIELD

[0001] The present generally concerns fuel cell powered unmanned aerial vehicles (UAVs), and more particularly to using such UAVs as air transportable power systems for remote field use.

BACKGROUND

[0002] The commercial market for small UAVs, or drones, used in civil applications is expected to increase dramatically over the next few years. In addition to military applications, many new uses for UAVs are being announced regularly. Currently, well-known uses include parcel delivery, disaster response, hydro and rail line inspections, flare stack inspections, precision agriculture, search and rescue missions, and film production. However, it is well known that battery powered UAVs have very limited flight times due to the relatively low specific energy (Watt-hours/kg) of existing rechargeable battery technologies.

[0003] Fuel cell systems for UAV applications offer much higher specific energies than lithium polymer (LiPo) batteries and therefore provide a significant increase in flight endurance for small, electrically powered UAVs. Indeed, fuel cell systems can provide up to 3 to 4 times the specific energy of LiPo batteries when using compressed hydrogen gas as fuel. Even higher specific energy is available using other forms of hydrogen fuel.

[0004] The inventors are unaware of any UAV fuel cell system, which can also be used for a practical ground power source that is air transportable. Moreover, if additional hydrogen fuel could be made available or carried to the field by the user, the overall system specific energy available at the remote onsite location would increase dramatically.

[0005] Thus, there is an unmet need for an easily transportable energy source to remote locations such that in combination with a fuel supply located at the remote location, substantially increased energy can be provided for a prolonged period. BRIEF SUMMARY

[0006] We have addressed the aforesaid problems by developing a new and unobvious system and method, which significantly reduces the weight burden of a field power source by eliminating the need to carry it. This advantageously provides sufficient onsite power and energy to make it practical for field use. In essence, our air transportable fuel cell power system can fly to a specific remote location, land, and then be configured by the user to supply power on the ground. When the power system is no longer needed in the field, it is then reconfigured to provide power to fly the UAV, which can then move to the next location or return to base. Our system substantially reduces, or essentially eliminates, the weight burden of a field power supply by providing an air transportable power source. This dramatically increases specific energy compared to rechargeable batteries, which allows significantly longer run times in the field.

[0007] Accordingly, in one embodiment there is provided a system for delivering a power source to a remote location, the system comprising:

[0008] an unmanned aerial vehicle (UAV) having a primary power system connected thereto for flying the UAV to the remote location, the UAV being autonomously controlled, the primary power system being capable of being converted to a secondary power system to provide a power source at the remote location; and

[0009] a controller in communication with the UAV to operate the UAV and to fly the UAV to the remote location.

[00010] In one example, a fuel source with an amount of fuel is delivered to the remote location so as to be connected to the secondary power source. The fuel source is gaseous hydrogen. The fuel source is liquid hydrogen. The fuel source is a chemical hydride. The fuel source is a metal hydride. The fuel source is generated at the remote location.

[00011] In one example, the fuel source includes about 8 kg energy storage mass in the form of a hydrogen fuel source, the 8 kg providing about 480 grams of usable hydrogen. A 50% fuel cell system efficiency (typical) with the specific energy of hydrogen fuel being 33,410 Wh/kg, the energy available would be 0.480 kg ^* 33,410 Wh/kg * 0.5 = 8018.4 Wh,

[00012] Accordingly, in another embodiment, there is provided a method for delivering a power source to a remote location, the method comprising:

[00013] receiving a signal from a controller;

[00014] flying an unmanned aerial vehicle (UAV), having a primary power system connected thereto, for powering the UAV to the remote location, the UAV being autonomously controlled; and

[00015] converting the primary power system into a secondary power system for providing a power source at the remote location.

[00016] In one example, a fuel source with an amount of a fuel is delivered to the remote location so as to be connected to the secondary power source. The fuel source is gaseous hydrogen. The fuel source is liquid hydrogen. The fuel source is a chemical hydride. The fuel source is a metal hydride. The fuel source is generated at the remote location.

[00017] In one example, the fuel source includes about 8 kg energy storage mass in the form of a hydrogen fuel source, the 8 kg providing about 480 grams of usable hydrogen. A 50% fuel cell system efficiency (typical) with the specific energy of hydrogen fuel being 33,410 Wh/kg, the energy available would be 0.480 kg * 33,410 Wh/kg ^* 0.5 = 8018.4 Wh,

[00018] Accordingly, in yet another embodiment, there is provided an apparatus for autonomously powering a UAV to a remote location, the apparatus comprising;

[00019] a lightweight frame;

[00020] landing gear connected to the frame;

[00021] a propulsion system connected to the frame;

[00022] a primary power source connected to the propulsion system, the primary power system being capable of being converted to a secondary power system to provide a power source at the remote location; and [00023] an integrated field power system to receive therein the secondary power system, the integrated field power system being in communication with the propulsion system.

[00024] In one example, the system described above further includes an integrated field power system to receive therein the secondary power system, the integrated field power system being in communication with the propulsion system.

[00025] Accordingly, in another embodiment, there is provided a method of actively deploying one or more unmanned aerial vehicles (UAVs) using a non-transitory computer readable medium having stored therein instructions that are executable to cause a controller to activate deployment of one or more unmanned aerial vehicles (UAVs), the method comprising:

[00026] receiving, via an integrated field power system interface of an air transportable fuel cell power system, a first input that corresponds to a first request for a first power source, which first power source is capable of being converted to a second power source and in which the first power source is needed by a requester at a first location remote from a first UAV fuelling station; and

[00027] in response to receipt of the first input, sending, via a network interface, the first request for the first power source to a network of the one or more UAVs that are adapted to carry the first_power source based on the requester located at the first remote location, the requester notifying the controller of a need for the first power source at the first remote location, the requester having a requester account, wherein the first request for the first power source includes: a. a unique electronic identifier for the air transportable fuel cell power system, wherein the unique electronic identifier is indicated by the requester account;

b. an indication of the type of power source needed at the first location: and

[00028] a request for delivery of the first power source by the one or more UAVs to the remote location associated with the unique electronic identifier according to the requester account. BRIEF DESCRIPTION OF THE DRAWINGS

[00029] These and other features of that described herein will become more apparent from the following description in which reference is made to the appended drawings wherein:

[00030] FIG. 1 is a perspective view of an embodiment of an air transportable fuel cell power system;

[00031] FIG. 2 is a front view of the air transportable fuel cell power system of FIG. 1 showing detail of the integrated field power system interface;

[00032] FIG. 3 is a perspective top view of the air transportable fuel cell power system of FIG. 1 , showing an alternative integrated field power system interface connected to an external power manager;

[00033] FIG. 4 is a perspective top view of the external power manager of FIG. 3, connected to number of pieces of field equipment;

[00034] FIG. 5 is a perspective top view of a fixed wing UAV for carrying air transportable power system for remote field use;

[00035] FIG. 6 is a perspective top view of a hybrid vertical take-off and landing (VTOL) fixed wing UAV for carrying the air transportable power system; and

[00036] FIG. 7 is simplified block diagram showing a communications network.

DETAILED DESCRIPTION

Definitions

[00037] Unless otherwise specified, the following definitions apply:

[00038] The singular forms "a", "an" and "the" include corresponding plural references unless the context clearly dictates otherwise. [00039] As used herein, the term "comprising" is intended to mean that the list of elements following the word "comprising" are required or mandatory but that other elements are optional and may or may not be present.

[00040] As used herein, the term "consisting of is intended to mean including and limited to whatever follows the phrase "consisting of. Thus, the phrase "consisting of indicates that the listed elements are required or mandatory and that no other elements may be present.

[00041] As used herein, the term "unmanned aerial vehicle (UAV)" is intended to mean either an autonomous or a semi-autonomous vehicle capable of flight without a physically present human pilot. Examples of flight-related functions include, but are not limited to, sensing the UAV's environment or operating in the air without a need for input from an operator. In the case of a semi-autonomous vehicle, a remote human operator could control some functions, while other functions are carried out autonomously. Also, a UAV may be configured to allow a remote operator to take over functions that can otherwise be controlled autonomously by the UAV. Certain functions may be controlled remotely in one instance and performed autonomously in another instance. For example, a remote operator could control high level navigation decisions for a UAV, such as by specifying that the UAV should travel from one location to another, while the UAV's navigation system autonomously controls more fine-grained navigation decisions, such as the specific route to take between the two locations, specific flight controls to achieve the route and avoid obstacles while navigating the route, and so on.

[00042] A UAV can be of various forms. For example, a UAV may take the form of a rotorcraft such as a helicopter or multi-copter; a fixed-wing aircraft, a hybrid VTOL fixed wing aircraft, a jet aircraft, a ducted fan aircraft; a lighter-than-air dirigible such as a blimp or steerable balloon; a tail-sitter aircraft, a glider aircraft, or an ornithopter. The term "UAV" may also include the terms "drone", "unmanned aerial vehicle system" ("UAVS"), or "unmanned aerial system" ("UAS").

[00043] Referring now to FIG. 1 , a system for delivering a power source, such as hydrogen fuel cell, to a location that is remote from a fueling station (not shown) is shown generally at 10. The system 10 is, in essence, an air transportable fuel cell power system. Broadly speaking, the air transportable fuel cell power system 10 comprises a fuel cell system 12, a hydrogen power source 14; a UAV 11 , which includes a UAV airframe 16, a propulsion system 18, and a landing gear 20; and an integrated field power system interface 21. In one example, the air transportable fuel cell power system 10 can travel autonomously. During flight from the fuelling station to the remote location, the fuel cell system 12 uses the hydrogen source 14 as fuel. The energy produced by the hydrogen fuel cell powers the propulsion system 18 so that the UAV 11 transports its own power source to a specific location remote from the fuelling station. Upon arrival, the UAV 11 lands using the landing gear 20 and is then reconfigured to provide power through the integrated field power system interface 21. The ability to transport an otherwise bulky and heavy power source from a starting point to a finishing point remote therefrom is particularly advantageous. One particularly desirable use example contemplated by the inventors would be the delivery of a power source to a soldier operating in the field. The use of the system 10 would negate the soldier having to carry a bulky and heavy power source, usually on his back, to a remote location.

[00044] Referring now to FIG. 2, the air transportable fuel cell power system 10 is shown providing more detail of the integrated field power system interface 21. Upon arrival at its destination, the air transportable fuel cell power system 10 can be reconfigured to provide auxiliary power through the integrated field power system interface 21. Desirable power sources may include, but are not limited to, alternating current (AC) power through AC power receptacle 22, direct current (DC) power at various voltages such as 5V, 12V and 24V through DC power receptacle 24 which could use a multitude of connector configurations, and a USB connection for charging various electronic devices, known to those skilled in the art, at a USB receptacle 26.

[00045] Referring now to FIG. 3, an alternative air transportable fuel cell power system 50 is illustrated and includes a different integrated field power system interface 21 with a plurality of connections 52, which can interface through an electrical interface cable 54 to an external portable power manager 56. The external portable power manager 56, also known as a soldier power manager, or squad power manager, is used extensively in the military. This permits a number of military applications, and has the following advantages:

- Manages and prioritizes battery usage

- Powers man-packable gear and man-worn gear

- Recharges military and commercial batteries

- Optimizes solar/alternative power sources

- Monitors power sources and loads, alerting war fighter to problems

- Dynamically adjusts to changing mission needs

- Fully submergible for use in all weather

- Data logging for mission analysis and planning

[00046] Referring now to FIG. 4, a soldier's equipment configuration is shown generally at 100. As described above, the external portable power manager 56 is located at the centre of the configuration 100 and is electrically connected to the air transportable fuel cell power system 50 (not shown in FIG. 4), drawing power from fuel cell system 12 through the integrated field power system interface connections 52 as best illustrated in FIG. 3. The external portable power manager 56 can power and charge field equipment including, but not limited to, VHF radio 102, Multiband Inter/lntra Team Radio (MBITR) 104, Defense Advanced GPS Receiver (DAGR) 106, infrared night vision goggles 108, and various military battery configurations such as a rechargeable lithium-ion battery BB-2590 1 10, or a rechargeable lithium- ion battery BB-2557 1 12.

[00047] Referring now to FIG. 5, an alternative UAV aircraft configuration for the air transportable fuel cell power system is shown generally at 50. In this example, the UAV is a fixed wing UAV and includes a UAV fuselage 152 that houses the fuel cell 12 and the integrated field power system interface 21 (not shown). UAV wings 154, to which are attached two winglets 156, are also connected to the UAV fuselage 152. A propulsion system 158 is located rearwardly to drive the aircraft forwards.

[00048] Referring now to FIG. 6, in which another alternative UAV aircraft configuration for the air transportable fuel cell power system is shown generally at 200. This aircraft is a hybrid VTOL fixed wing UAV. The UAV fuselage 202 houses the fuel cell 12 and the integrated field power system interface such as 21 (not shown). The UAV wings 204, attached to winglets 206, are also fastened to UAV fuselage 202. The aircraft is driven forward using the propulsion system 208. For a vertical take-off, the propulsion system 210, attached to UAV wings 204, lifts the aircraft vertically to a safe height whereby the aircraft transitions to straight and level flight using thr propulsion system 208. Similarly for a vertical landing, the propulsion system 210, attached to the UAV wings 204, lowers the aircraft vertically in order to land the UAV.

[00049] Referring to FIG. 7, is a simplified block diagram illustrating components of a UAV request communications network 300, an integral part being a non-transitory computer readable medium having stored therein instructions that are executable to cause the controller to activate deployment of one or more of the unmanned aerial vehicles (UAVs) 312. In operation, the integrated field power system interface 302 of an air transportable fuel cell power system, receives a first input that corresponds to a request for a first power source, in which first power source is capable of being converted to a second power source and in which the first power source is needed by a requester, such as a soldier located remote from the UAV fuelling station. The requester has a requester account and a unique electronic identifier, known collectively as user data 308. Once the first input is received, the system sends via a network interface 304, the first request for the first power source to dispatcher 306 and then to a deployment system 310 which triggers deployment of the one or more UAVs 312 that are adapted to carry the firstjDower source based on the requester located at the first remote location. The requester indicates the type of power source needed at the first location and requests delivery of the first power source by the one or more UAVs to the remote location associated with the unique electronic identifier according to the requester account.

[00050] In one example, an air transportable fuel cell power system, like the ones described above, may include one or more UAVs located either at a single station or distributed over a wide geographic area. A controller communicates with the system to activate same at short notice. Controllers such as hand-held electronic devices such as mobile phones, tablets and the like can be operated either by the person located remote from the station, and in need of power, or by others. Depending on the power needs at the remote location, the system can dispatch an appropriate UAV or UAVs to the remote location in order to provide power.

[00051] In particular, in a military operation where power might be needed for communications or logistics, a power system may include a fleet or "swarm" with a number of different types of UAVs, which are configured for different power needs. For instance, some UAVs may be configured with fuel cells. In particular, the fuel cells may themselves be further configured with various military connector interfaces for equipment such as a soldier power manager previously described, or to attach directly to the soldier's equipment itself to power or charge as required.

[00052] Due to their size and maneuverability, UAVs may be able to reach the remote location and provide energy more quickly than traditional responses.

[00053] Typically, the equivalent specific energy levels over 1000 Wh/kg are achievable, and even higher depending on how much hydrogen fuel can be carried to the field.

[00054] As an example taken from the military, a typical soldier must carry up to 8 kg of lithium ion batteries on a mission in order to power communication equipment, sensors, optics, targeting devices, and the like. The specific energy of a typical lithium ion battery is about 200 Wh/kg, which therefore provides a total of 1600 Wh of useable energy to the soldier.

[00055] For comparison, an air transportable fuel cell power system may have 1800 Wh on board to provide energy for propulsion. With this energy, a multirotor aircraft can fly over 3 hours and 30 minutes. At a flight speed of 10 m/s (36 km/h), which is typical for this type of UAV, it would travel almost 120 km. This is significantly further than most soldier missions, and therefore would not be a limitation on how far the soldier could travel before restocking his or her supplies. Further, since the UAV can travel autonomously, it would not have to follow the soldier directly thereby maintaining the soldier's safety by protecting their location. If a fixed wing, or hybrid VTOL fixed wing UAV configuration was used, even greater distances could be travelled (up to 600 km) with higher amounts of energy available on the ground.

[00056] If the soldier carried the same 8 kg energy storage mass as hydrogen fuel storage (i.e. compressed gas cylinder), where the typical weight storage capacity of 6% is common, this would provide 480 grams of usable hydrogen. With a 50% fuel cell system efficiency (typical) and where the specific energy of hydrogen fuel is 33,410 Wh/kg (lower heating value; room temperature), the energy available would be 0.480 kg ^* 33,410 Wh/kg ^* 0.5 = 8018.4 Wh, more than five times that available from lithium ion batteries.

[00057] Alternatively, for the same energy available from lithium ion batteries, the soldier could carry a reduced mass of 1600 Wh / 8018.4 Wh ^* 8 kg = 1.6 kg of hydrogen fuel storage.

[00058] Alternatively, if the soldier did not need to travel 120 km, no energy storage mass would need to be carried at all and the residual energy from the air transportable fuel cell power system could be used on the ground. This is especially true if a fixed wing or hybrid VTOL fixed wing UAV configuration was implemented.

[00059] The air transportable fuel cell power system could also be used in emergency response situations or for disaster relief, providing an autonomous power source which could be sent to a pinpoint location via its autopilot and global positioning system (GPS), thereby providing emergency power for communications equipment, lighting, cell towers, etc.

[00060] Because the UAV functions via fuel cell, it could also provide some amounts of heat and water to disaster victims, as byproducts of the fuel cell reaction.

[00061] The air transportable fuel cell power system could be used to provide emergency power to a disabled personal watercraft or sailing vessel located at sea.

[00062] The hydrogen used as fuel for the air transportable fuel cell power system could be generated remotely onsite via chemical reaction (i.e. chemical or metal hydride), electrolysis via solar or other power source, solar using photoelectrochemical cells (PECs), etc. thereby increasing the available energy from the fuel cell system by orders of magnitude.

[00063] Other UAV platforms than multirotor could be used including fixed-wing aircraft and hybrid fixed-wing/vertical takeoff and landing (VTOL) aircraft. The later platform would offer the greatest potential for the air transportable fuel cell power system since it could take off and land vertically, while flying with increased efficiency and reduced energy consumption during straight and level flight, thereby providing the potential for more energy available at the remote field location.

[00064] The air transportable fuel cell power system could be configured to carry a very lightweight shelter or insulating material, which could be assembled at a remote location by a disaster victim, and connected to the fuel cell system to use the available power, heat and water which would increase the chances of survival while the victim is waiting for a conventional rescue method to arrive.

[00065] Thus, we have now developed a new and unobvious system in which a fuel cell powered unmanned aerial vehicle can be reconfigured to provide an air transportable field power source of very high specific energy for operation in remote areas. An integrated field power system can interface with receptacles for one or more power sources, such as a hydrogen fuel cell, where the fuel is in particular hydrogen gas, liquid hydrogen, metal hydrides or chemical hydrides. The specific energy of the overall approach and therefore the available energy in the field are increased dramatically by the fact that the user must only transport hydrogen fuel, and not the actual power source. Our system can be applied to all applications which require a lightweight source of energy in a remote field location.

Other Embodiments

[00066] From the foregoing description, it will be apparent to one of ordinary skill in the art that variations and modifications may be made to the embodiments described herein to adapt it to various usages and conditions.

Claims

CLAIMS We claim:

1. A system for delivering a power source to a remote location, the system comprising:

- an unmanned aerial vehicle (UAV) having a primary power system connected thereto for flying the UAV to the remote location, the UAV being autonomously controlled, the primary power system being capable of being converted to a secondary power system to provide a power source at the remote location; and

- a controller in communication with the UAV to operate the UAV and to fly the UAV to the remote location.

2. The system, according to claim 1 , in which a fuel source with an amount of a fuel is delivered to the remote location so as to be connected to the secondary power source.

3. The system, according to claim 2, in which the fuel source is gaseous hydrogen.

4. The system, according to claim 2, wherein the fuel source is liquid hydrogen.

5. The system, according to claim 2, in which the fuel source is a chemical hydride.

6. The system, according to claim 2, wherein the fuel source is a metal hydride.

7. The system, according to claim 1 , in which the fuel source is generated at the remote location.

8. The system, according to claim 2, in which the fuel source includes about 8 kg energy storage mass in the form of a hydrogen fuel source, the 8kg providing about 480 grams of usable hydrogen.

9. The system, according to claim 8, in which with a 50% fuel cell system efficiency (typical) with the specific energy of hydrogen fuel being 33,4 0 Wh/kg, the energy available would be 0.480 kg ^* 33,410 Wh/kg ^* 0.5 = 8018.4 Wh,

10. A method for delivering a power source to a remote location, the method comprising:

- receiving a signal from a controller;

- flying an unmanned aerial vehicle (UAV), having a primary power system connected thereto, for flying the UAV to the remote location, the UAV being autonomously controlled; and

- converting the primary power system into a secondary power system for providing a power source at the remote location.

11. The method, according to claim 10, in which a fuel source with an amount of fuel is delivered to the remote location so as to be connected to the secondary power source.

12. The method, according to claim 1 1 , in which the fuel source is gaseous hydrogen.

13. The method, according to claim 11 , wherein the fuel source is liquid hydrogen.

14. The method, according to claim , in which the fuel source is a chemical hydride.

15. The method, according to claim 1 1 , wherein the fuel source is a metal hydride.

16. The method, according to claim 1 1 , in which the fuel source is generated at the remote location.

17. The method, according to claim 1 1 , in which the fuel source includes about 8 kg energy storage mass in the form of a hydrogen fuel source, the 8kg providing about 480 grams of usable hydrogen.

18. The method, according to claim 17, in which with a 50% fuel cell system efficiency (typical) with the specific energy of hydrogen fuel being 33,410 Wh/kg, the energy available would be 0.480 kg ^* 33,410 Wh/kg ^* 0.5 = 8018.4 Wh.

19. An apparatus for autonomously powering a UAV to a remote location, the apparatus comprising;

- a lightweight frame;

- landing gear connected to the frame;

- a propulsion system connected to the frame;

- a primary power source connected to the propulsion system, the primary power system being capable of being converted to a secondary power system to provide a power source at the remote location; and

- an integrated field power system to receive therein the secondary power system, the integrated field power system being in communication with the propulsion system.

20. The apparatus, according to claim 19, further includes an integrated field power system to receive therein the secondary power system, the integrated field power system being in communication with the propulsion system.

21. A method of actively deploying one or more unmanned aerial vehicles (UAVs) using a non-transitory computer readable medium having stored therein instructions that are executable to cause a controller to activate deployment of one or more unmanned aerial vehicles (UAVs), the method comprising:

receiving, via an integrated field power system interface of an air

transportable fuel cell power system, a first input that corresponds to a first request for a first power source, which first power source is capable of being converted to a second power source and in which the first power source is needed by a requester at a first location remote from a first UAV fuelling station; and

in response to receipt of the first input, sending, via a network interface, the first request for the first power source to a network of the one or more UAVs that are adapted to carry the first power source based on the requester located at the first remote location, the requester notifying the controller of a need for the first power source at the first remote location, the requester having a requester account, wherein the first request for the first power source includes:

c. a unique electronic identifier for the air transportable fuel cell power system, wherein the unique electronic identifier is indicated by the requester account;

d. an indication of the type of power source needed at the first location: and

e. a request for delivery of the first power source by the one or more UAVs to the remote location associated with the unique electronic identifier according to the requester account.