GB2589445A - Hybrid unmanned aerial vehicle - Google Patents

Hybrid unmanned aerial vehicle Download PDF

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Publication number
GB2589445A
GB2589445A GB2014638.7A GB202014638A GB2589445A GB 2589445 A GB2589445 A GB 2589445A GB 202014638 A GB202014638 A GB 202014638A GB 2589445 A GB2589445 A GB 2589445A
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United Kingdom
Prior art keywords
air flow
heated air
uav
dedicated space
deflector frame
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GB2014638.7A
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GB2589445B (en
GB202014638D0 (en
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Robert Lindberg Ronald
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
    • B60L50/60—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by batteries
    • B60L50/66—Arrangements of batteries
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
    • B60L50/70—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using power supplied by fuel cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L50/00—Electric propulsion with power supplied within the vehicle
    • B60L50/50—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells
    • B60L50/75—Electric propulsion with power supplied within the vehicle using propulsion power supplied by batteries or fuel cells using propulsion power supplied by both fuel cells and batteries
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L58/00—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
    • B60L58/10—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
    • B60L58/24—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries
    • B60L58/26—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries by cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
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    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L58/00—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles
    • B60L58/10—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries
    • B60L58/24—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries
    • B60L58/27—Methods or circuit arrangements for monitoring or controlling batteries or fuel cells, specially adapted for electric vehicles for monitoring or controlling batteries for controlling the temperature of batteries by heating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C39/00—Aircraft not otherwise provided for
    • B64C39/02—Aircraft not otherwise provided for characterised by special use
    • B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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    • 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
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/24—Aircraft characterised by the type or position of power plants using steam or spring force
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B64D33/10—Radiator arrangement
    • 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
    • B64U20/90—Cooling
    • B64U20/98—Cooling using liquid, e.g. using lubrication oil
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U50/00—Propulsion; Power supply
    • B64U50/10—Propulsion
    • B64U50/11—Propulsion using internal combustion piston engines
    • 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
    • B64U50/33—Supply or distribution of electrical power generated by combustion engines
    • 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
    • B64U50/34—In-flight charging
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/60—Heating or cooling; Temperature control
    • H01M10/61—Types of temperature control
    • H01M10/617—Types of temperature control for achieving uniformity or desired distribution of temperature
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/60—Heating or cooling; Temperature control
    • H01M10/62—Heating or cooling; Temperature control specially adapted for specific applications
    • H01M10/625—Vehicles
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M10/00—Secondary cells; Manufacture thereof
    • H01M10/60—Heating or cooling; Temperature control
    • H01M10/66—Heat-exchange relationships between the cells and other systems, e.g. central heating systems or fuel cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2240/00—Control parameters of input or output; Target parameters
    • B60L2240/40—Drive Train control parameters
    • B60L2240/54—Drive Train control parameters related to batteries
    • B60L2240/545—Temperature
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60L—PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES; SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL; MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES
    • B60L2240/00—Control parameters of input or output; Target parameters
    • B60L2240/60—Navigation input
    • B60L2240/66—Ambient conditions
    • B60L2240/662—Temperature
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01M—PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY
    • H01M2220/00—Batteries for particular applications
    • H01M2220/20—Batteries in motive systems, e.g. vehicle, ship, plane
    • 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
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E60/00—Enabling technologies; Technologies with a potential or indirect contribution to GHG emissions mitigation
    • Y02E60/10—Energy storage using batteries
    • 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
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/70—Energy storage systems for electromobility, e.g. batteries
    • 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
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/60—Other road transportation technologies with climate change mitigation effect
    • Y02T10/72—Electric energy management in electromobility
    • 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
    • Y02T90/10—Technologies relating to charging of electric vehicles
    • Y02T90/16—Information or communication technologies improving the operation of electric vehicles
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Sustainable Development (AREA)
  • Sustainable Energy (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Power Engineering (AREA)
  • Transportation (AREA)
  • Manufacturing & Machinery (AREA)
  • Electrochemistry (AREA)
  • General Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Remote Sensing (AREA)
  • Oil, Petroleum & Natural Gas (AREA)
  • Electric Propulsion And Braking For Vehicles (AREA)

Abstract

A hybrid unmanned aerial vehicle (UAV) 100 comprises a body with at least one battery 120 disposed in a dedicated space of the body and at least one electrical motor for operating at least one propeller 110 of the UAV. The at least one electrical motor is configured to operate on the energy provided by the at least one battery. The UAV comprises a liquid or gaseous fuel powered, and liquid cooled power generator for charging the at least one battery. A coolant circulator pump circulates liquid coolant of the power generator and a radiator 115 is configured to transfer thermal energy from the liquid coolant to air passing through the radiator. The UAV further comprises a configurable deflector frame 170 disposed adjacent to the radiator and configured to deflect the heated air flow from the radiator. The deflector frame is selectively configurable for deflecting said heated air flow away from the body of the UAV when ambient temperature is in a first temperature range in which performance of the at least one battery is at or near nominal, and for deflecting said heated air flow towards said dedicated space for warming up the at least one battery when ambient temperature is in a second temperature range in which performance of the at least one battery would otherwise become lowered, wherein the second temperature range is below said first temperature range.

Description

HYBRID UNMANNED AERIAL VEHICLE
FIELD OF THE DISCLOSURE
The present disclosure relates to a hybrid unmanned aerial vehicle, and particularly to an improvement that enables increased flight time capacity of the hybrid unmanned aerial vehicle. The present disclosure further concerns a method to increase flight time capacity of the hybrid unmanned aerial vehicle.
BACKGROUND OF THE DISCLOSURE
Operation times of unmanned aerial vehicles, UAVs, also known as unmanned aerial systems, UAS, remotely piloted aircraft systems (RPAS) or as drones are rather limited.
Modern UAVs often operate on electrical power, which is stored in one or more batteries carried by the UAV during flight.
An improvement for operation times of UAVs has been achieved by incorporating a power generator in the UAV for producing energy for the one or more batteries as on-flight electrical energy source so that high energy density of gasoline can be utilized for energy production. Electricity obtained from the one or more batteries is utilized by the hybrid UAV for operating the electrical motors for flight energy. Such hybrid arrangement enables reducing amount of batteries needed for extended operation times.
A problem with prior art solutions is that in cold temperatures, battery capacity is deprived. This problem has been solved for example by preheating the battery pack before operation when ambient temperature is cold, or by introducing a dedicated electrical heater to keep the battery or batteries warm, which consumes electrical energy, thus reducing operation time. To some extent, charging and re-charging the battery produces some heating effect in the battery itself. However, in cold temperatures this heating effect is not sufficient to maintain the battery in a temperature that ensures its proper operation, and there are also limits for allowed charging temperature of the battery.
Another problem is that avionics, in other words electronic equipment fitted in the aircraft may also be sensitive to temperatures, for example hot or cold.
BRIEF DESCRIPTION OF THE DISCLOSURE
An object of the present disclosure is to provide an unmanned aerial vehicle, UAV with improved flight times independently from ambient temperature. An object is also to provide a method for solving the above problem.
The object of the disclosure is achieved by a specifically designed heat deflecting frame structure of an UAV and a method characterized by what is stated in the independent claims. The preferred embodiments of the disclosure are disclosed in the dependent claims.
The disclosure is based on the idea of utilizing heat energy expelled from an onboard radiator of the onboard power generator used for battery recharging for warming up cold sensitive parts, such as a one or more batteries and optionally for example avionics in cold temperatures. The air deflecting arrangement and the method are configurable so that when the UAV is operated in ambient temperatures that correspond those of the nominal operating temperatures of the battery, the battery and other optional cold sensitive parts are not heated, since excess heat may also cause harm to the battery.
With cold temperatures or "winter" conditions we refer to temperatures in which in which performance of the battery is lowered due to temperature. Modern, relatively light, rechargeable batteries such as lithium polymer (LiPo) batteries often used in mobile devices and UAVs, as well as other common rechargeable battery types such as lithium-ion batteries are sensitive to extremely hot and cold temperatures. We use here a LiPo battery as a non-limiting example. Typical nominal operation temperature ranges for use of a LiPo battery may be for example between +10°C and +55°C. When temperature of the battery is below the given nominal operation temperature range due to low ambient temperature, the battery may discharge in a fraction of time from what is expected within the nominal operation temperature range and thus capacity of the battery is deprived. Other battery types may have different nominal operation temperature ranges and may thus be able to provide shorter or longer life cycles and poorer or better performance in lower ambient temperatures than a LiPo battery. Thus, it is obvious to a skilled person that the applicable temperature ranges depend on the battery type used in the UAV and the nominal operation temperatures thereof, as well as on variation of the capacity of the battery over temperature. In one embodiment, the temperature of the at least battery is maintained above freezing point (0°C).
An advantage of the arrangement and the method of the disclosure is that in comparison to both pre-heating the battery and applying a dedicated electrical heater to the battery, energy is saved by utilizing excess heat energy of the power generator engine that would otherwise be wasted. In case of the dedicated heater, the benefit of saved energy is even higher, since any energy consumed during flight also reduces available flight time of the UAV. Also, pre-heated batteries will likely cool down during flight operation in cold weather, which may eventually cause exhausting the batteries sooner. Further, deflection of heated air may be implemented with a very simple and lightweight mechanical arrangement, which does not significantly add weight of the UAV, and thus have no significant negative effect on the available flight time.
As a result of the disclosed improvement, flight time of the UAV is not negatively affected due to ambient temperatures that fall below the nominal or recommended operating temperatures of the battery, and similar UAV operation times may be reached independent of ambient temperature.
A further benefit achieved through using the at least one battery as the main power source for operating the rotors is that if the power generator runs out of fuel, the batteries provide sufficient amount of energy that allows landing the UAV safely before it totally runs out of energy. While the invention ensures that the batteries operate within their recommended temperature range, the arrangement can further ensure that the fully or nearly fully charged at least one battery is capable of providing the energy required for such emergency landing, thus improving safety of both the UAV itself and the possibly sensitive and/or fragile payload carried by the UAV.
According to a first aspect, hybrid unmanned aerial vehicle (UAV) is provided comprising a body, at least one battery disposed in a dedicated space of the body, and at least one electrical motor for operating at least one propeller of the UAV. The at least one electrical motor is configured to operate on the energy provided by the at least one battery. The UAV also comprises a liquid or gaseous fuel powered, and liquid cooled power generator for charging the at least one battery, a coolant circulator pump for circulating liquid coolant of the power generator in a closed circulation loop configured to conduct heat away from the power generator, and a radiator configured to transfer thermal energy from the liquid coolant to air passing through the radiator.
The UAV further comprises a configurable deflector frame disposed adjacent to the radiator and configured to deflect the heated air flow from the radiator, wherein the configurable deflector frame is selectively configurable for deflecting said heated air flow away from the body of the UAV when ambient temperature is in a first temperature range in which performance of the at least one battery is at or near nominal, and for deflecting said heated air flow towards said dedicated space for warming up the at least one battery when ambient temperature is in a second temperature range in which performance of the at least one battery would otherwise become lowered, wherein the second temperature range is below said first temperature range.
According to a second aspect, the dedicated space further comprises avionics such that when the deflector frame is configured to deflect said flow towards the dedicated space, it also warms up the avionics.
According to a third aspect, said configurable deflector frame comprises a plurality of fixed walls and at least two removably attachable walls configured to be manually removably attached on at least two different sides of the deflector frame. The at least two different sides of the deflector frame are essentially open such that when a first removably attachable wall is attached at a first side of the deflector frame, the first removably attachable wall closes the initially open first side of the deflector frame for disabling the heated air flow from flowing towards the dedicated space and causes, together with at least some of the fixed walls, deflecting the heated air flow away from the body of the UAV via an open second side of the deflector frame, and when a second removably attachable wall is attached at the second side of the deflector frame, the second removably attachable wall closes the initially open second side of the deflector frame for disabling the heated air flow from flowing away from the body of the UAV via the second side of the deflector frame and causes, together with at least some of the fixed walls, deflecting the heated air flow via the open first side of the deflector frame towards the dedicated space.
According to a fourth aspect, said configurable deflector frame comprises a plurality of fixed walls and at least one manually or automatically adjustable wall configured to be adjusted into at least two different positions, such that when the at least one adjustable wall is disposed on a first side of the deflector frame, the at least one adjustable wall closes the otherwise open first side of the deflector frame for disabling the heated air flow from flowing towards the dedicated space and causes, together with at least some of the fixed walls, deflecting the heated air flow away from the body of the UAV via an open second side of the deflector frame, and when the at least one adjustable wall is disposed on the second side of the deflector frame, the at least one adjustable wall closes the otherwise open second side of the deflector frame for disabling the heated air flow from flowing away from the body of the UAV via the open second side of the deflector frame and causes, together with at least some of the fixed walls, deflecting the heated air flow via the open first side of the deflector frame towards the dedicated space.
According to a fifth aspect, said at least one adjustable wall is configured to be adjusted using a servo motor.
According to a sixth aspect, the configurable deflector frame is further configurable to deflect a predetermined fraction of said heated air flow towards said dedicated space and to deflect remaining part of said heated air flow away from the body of the UAV, when ambient temperature is between a first temperature threshold within the first temperature range and an upper temperature threshold of the second temperature range.
According to a seventh aspect, said at least two removably attachable walls are configured to deflect the predetermined fraction of said heated air flow towards the dedicated space by one or more of: partially closing the initially open first side of the deflector frame with a third removably attachable wall for deflecting the predetermined fraction of the heated air flow towards the dedicated space and for disabling the remaining part of the heated air flow from flowing towards the dedicated space, providing the at least first removably attachable wall with one or more air scoops for deflecting the predetermined fraction of the heated air flow towards the dedicated space, providing one or more holes in the at least first removably attachable wall for deflecting the predetermined fraction of the heated air flow towards the dedicated space, and providing at least one adjustable flap in the first wall, wherein opening the adjustable flap partially or fully is configured to cause the predetermined fraction of the heated air flow to be deflected towards the dedicated space.
According to an eighth aspect, said at least one adjustable wall is further configured to be adjusted into at least one third position, in which the at least one adjustable wall is configured to be inclined relative to the deflecting frame and to the heated air flow for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space and the remaining part of the heated air flow to be deflected outside the body of the UAV, or the ad least one adjustable wall comprises at least one adjustable flap in the at least one adjustable wall disposed on the first side of the deflector frame, wherein partially or entirely opening the at least one adjustable flap causes the predefined fraction of the heated air flow to flow towards the dedicated space.
According to a ninth aspect, said at least one adjustable wall is configured to be adjusted automatically based on a measured ambient temperature.
According to a tenth aspect, capacity of the at least one battery is sufficient for safe landing of the UAV when no electrical power is received from the power generator.
According to a first method aspect, a method for operating a hybrid unmanned aerial vehicle (UAV) comprising a body and at least one battery disposed in a dedicated space of the body. The method comprises operating one or more propellers of the UAV using at least one electrical motor, wherein the at least one electrical motor is configured to operate on the energy provided by the at least one battery, charging the at least one battery with
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a liquid or gaseous fuel powered, and liquid cooled power generator, circulating liquid coolant of the power generator in a closed circulation loop with a coolant circulator pump for conducting heat away from the power generator, transferring thermal energy from the liquid coolant to air with a radiator and causing an air flow through the radiator for passing thermal energy from the liquid coolant to the air flow, wherein the air flow is heated while passing through the radiator. The method further comprises deflecting the heated air flow from the radiator with a configurable deflector frame disposed adjacent to the radiator. Said deflecting the heated air flow with the configurable deflector frame comprises deflecting said heated air flow away from the body of the UAV when ambient temperature is in a first temperature range in which performance of the battery is at or near nominal, or deflecting said heated air flow towards said dedicated space for warming up the battery when ambient temperature is in a second temperature range in which performance of the battery would otherwise become lowered, wherein the second temperature range is below said first temperature range.
According to a second method aspect, dedicated space further comprises avionics, such that warming up the heated air flow deflected towards said dedicated space also warms up the avionics.
According to a third method aspect, said configurable deflector frame comprises a plurality of fixed walls and at least two manually removably attachable walls configured to be removably attached on at least two different sides of the deflector frame, and the method comprises disabling the heated air flow from flowing towards the dedicated space and deflecting the heated air flow away from the body of the UAV via an open second side of the deflector frame by attaching at least one first removably attachable wall at a first side of the deflector frame, whereby the at least one first removably attachable wall closes the otherwise open first side of the deflector frame or disabling the heated air flow from flowing away from the body of the UAV via the second side of the deflector frame and deflecting the heated air flow towards the dedicated space via the open first side of the deflector frame by attaching at least one second removably attachable wall at the second side of the deflector frame, wherein the at least one second removably attachable wall closes the otherwise open second side of the deflector frame.
According to a fourth method aspect, said configurable deflector frame comprises a plurality of fixed walls and at least one adjustable wall configured to be manually or automatically adjusted into at least two different positions, and the method comprises disabling the heated air flow from flowing towards the dedicated space and deflecting the heated air flow away from the body of the UAV via an open second side of the deflector frame by disposing the at least one adjustable wall on a first side of the deflector frame, whereby the at least one adjustable wall closes the otherwise open first side of the deflector frame, or disabling the heated air flow from flowing away from the body of the UAV via the second side of the deflector frame and deflecting the heated air flow via the open first side of the deflector frame towards the dedicated space by disposing the at least one adjustable wall on the second side of the deflector frame, whereby the at least one adjustable wall closes the otherwise open second side of the deflector frame.
According to a fifth method aspect, the method further comprises adjusting said least one adjustable wall with a servo motor.
According to a sixth method aspect, the method further comprises deflecting a fraction of said heated air flow towards said dedicated space and deflecting remaining part of said heated air flow away from the body of the UAV, when ambient temperature is between a first temperature threshold within the first temperature range and an upper temperature threshold of the second temperature range.
According to a seventh method aspect, said deflecting the predetermined fraction of said heated air flow towards the dedicated space is achieved by any of: partially closing the initially open first side of the deflector frame with a third wall for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space and for disabling the remaining part of the heated air flow from flowing towards the dedicated space, providing one or more air scoops provided in the first wall for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space, providing one or more holes in the first wall for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space, and providing at least one adjustable flap in the first wall, wherein opening the at least one adjustable flap partially or fully causes deflecting of the predetermined fraction of the heated air flow to be deflected towards the dedicated space.
According to an eighth method aspect, said deflecting the predetermined fraction of said heated air flow towards the dedicated space is achieved by any of: tilting the at least one adjustable wall with respect to the deflective frame and the heated air flow for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space and the remaining part of the heated air flow to be deflected outside the body of the UAV, and partially or fully opening a flap in the at least one adjustable wall disposed on the first
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side of the deflector frame for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space.
According to a ninth method aspect, the method further comprises adjusting said at least one adjustable wall automatically on basis of a measured ambient temperature.
BRIEF DESCRIPTION OF THE DRAWINGS
In the following the disclosure will be described in greater detail by means of preferred embodiments with reference to the accompanying drawings, in which Figure 1 illustrates a first perspective view of an exemplary UAV according to the disclosure; Figure 2 illustrates a second perspective view of the exemplary UAV according to the
disclosure;
Figure 3 shows a first schematic illustration of the disclosed solution; Figure 4 shows a second schematic illustration of the disclosed solution; Figure 5 shows a third schematic illustration of the disclosed solution; Figure 6 shows a fourth schematic illustration of the disclosed solution; Figure 7 illustrates an exemplary embodiment of the invention in summer configuration; and Figure 8 illustrates an exemplary embodiment of the invention in winter configuration.
DETAILED DESCRIPTION OF THE DISCLOSURE
In context of this application, directions may be defined on basis of dominant balanced position of the UAV when in operation. Thus, the term "down" refers to direction towards ground, in direction approximately aligned with gravitation affecting on a flying UAV, the term "front" refers to direction of predominant flying direction of the UAV and terms "back" and "rear" refers to the opposite direction. It should be noticed, however, that although more traditional types of UAVs have a clear predominant flying direction like airplanes, a multirotor UAV is typically capable of moving in any lateral direction. The term "lateral" refers to directions in a plane that is orthogonal with the direction "down".
Figures 1 and 2 illustrate two different perspective views of an exemplary UAV (100), designed as a quadcopter, i.e. a multirotor helicopter propelled by a plurality of rotors (110) run by a plurality of electrical engines. The invention is equally applicable to any multirotor helicopter independent of number of rotors (110), but also to other known types of UAVs. Operating power for the electrical engines powering the rotors (110) is received from at least one battery (120) disposed within a dedicated space (220) within the body (200) of the UAV. A power generator (130) is attached to the body (200) for generating electrical energy for charging the at least one battery (120). The power generator (130) operates on liquid or gaseous fuel, preferably with gasoline, which has high energy density. Alternatively, or additionally, other known types of liquid or gaseous fuels may be consumed by the electric power generator (130). The power generator (130) may be for example a combustion engine, or it may employ fuel cell technology. The power generator is preferably liquid cooled. A coolant circulator pump (not shown) is provided in a closed circulation loop for circulating liquid coolant of the power generator (130) in the closed circulation loop for conducting excess heat energy away from the power generator (130). The liquid coolant is circulated through a radiator (not shown) that is configured to transfer thermal energy from the liquid coolant to ambient air. Preferably, one or more fans (160) blow air through the radiator such that the air heats while passing through the radiator (115) and thus thermal energy is passed from the liquid coolant to the air flow passing through the radiator. Alternatively, the radiator may be located under airstream of one or more rotors or, in a fixed wing UAV configuration, an air scoop extending into the airstream caused by the moving UAV may provide air flow used for cooling the radiator. Fuel for operating the power generator during flight is stored in at least one fuel tank (140).
Advantageously layout of the functional parts of the UAV is such that weights of the functional parts are mutually balanced. This facilitates stability and ease of control of the UAV. Preferably, the power generator (130) is disposed near the outer circumference of the body (200). In the exemplary device, the body (200) of the UAV may have a shape of an elongated flat box having greater lateral dimensions than vertical dimensions (a.k.a.
thickness) and the power generator (130) is advantageously disposed at or near one end of the elongated body, whereas a dedicated space (220) comprising the at least one battery (120) and optionally at least part of avionics is disposed near the opposite end of the body. In one embodiment, the power generator (130) is disposed at the front of the UAV and the dedicated space (220) is disposed towards the rear end of the UAV. The dedicated space (220) is preferably at least partially enclosed by one or more walls of the body (200) and/or removably attached covers or shields (230) that provide protection for the parts disposed within the dedicated space (220). Fuel tanks (140), which have significant contribution to the weight when filled, are preferably disposed on two opposite sides of the body (200). In the disclosed embodiment, two fuel tanks (140) are attached to legs (250) of the landing feet for facilitating good balance of the UAV body. However, any other, preferably symmetrical placement of the fuel tanks (140) is applicable. The body (200) itself provides a surface under it on which payload may be attached. One or more radiators and one or more fans (160) producing air flow through the one or more radiators are preferably disposed within the body (200) between the power generator (130) and the dedicated space (220). A deflecting frame (170) is disposed adjacent to the radiator. Preferably, the one or more fans (160) are disposed above the radiator, on top of it, for providing a downward air flow of ambient air through the radiator. A downward air flow outlet is preferred, since it does not affect negatively to the lifting power provided with the propellers. Further, the deflecting frame (170) is preferably disposed adjacent to the radiator, but on the opposite side of the one or more fans (160), such that air flow received through the radiator passes through the deflecting frame (170).
The electrical power capacity of the one or more batteries (120) may be dimensioned only to be enough for ensuring that they are capable of providing power needed for an emergency landing. This way size of the batteries and in particular secondary load caused by the batteries may be minimized. The UAV may be designed for operation time of a few hours with a few litres of fuel, while the batteries may only be capable of providing a few minutes of operation time if used as the sole energy source of the UAV. For optimal performance, the electrical power capacity of the one of more batteries may be less or equal to 10%, more preferably less or equal to 5% of the total operation time of the UAV.
In a more specific example, operating time (flight time) of the UAV may be two to four hours depending on the amount of payload carried, whereas capacity of the batteries only enables flight time of about five minutes. It is important to have immediate electrical energy available for the avionics, in particular for an auto pilot, which reacts to position changes of the UAV within microseconds. For such immediate operation, electrical motors driving the propellers require immediately available electrical energy from the battery.
The exemplary UAV implementation shown in the figures 1 and 2 has a maximum take-off weight of 27 kg. Energy needed for this device for hovering is about 3750 W. A relatively small LiPo battery capable of producing 1 Ah, providing 44.4 V thus providing 44.4 Wh of energy is sufficient for this purpose in the exemplary UAV illustrated in the figures 1 and 2. However, for improved security, higher energy capacity is preferred, for example 6 Ah providing 266.4 Wh of energy. This battery allows an initial theoretical failsafe flight time with energy provided by the battery only 266.4/3750=0.07104 h=4.2624 min with the takeoff weight, which represents less than 4% of the total flight time available with maximum take-off weight. With failsafe flight time we refer to time needed for the UAV to be safely landed when no electrical power is provided by the power generator, but the UAV is operated on the energy provided by the battery only.
Since the fuel load and thus weight of the UAV changes during flight, a skilled person understands that the actual failsafe flying time will vary depending on the mass of the UAV at the time of failsafe engagement, in other words at the time that the power generator stops producing electrical energy for any reason. Selection of the desired battery capacity in comparison to total flight time is a design option, in which the failsafe flying time and the weight of the battery are optimized for desired operation characteristics of the UAV, including at least the maximum flight time and the failsafe time requirements.
Figures 3, 4, 5 and 6 illustrate schematically a cross-section of the main functional parts according to the invention in four different configurations. For simplicity, we will refer in these schematic presentations to just one battery (120), one fan (160), one radiator (115) and one configurable wall (270), but it is clear to a skilled person, that the invention applies to any selected number of these functional elements. Figure 3 shows a first configuration, suitable for "summer" operation, in other words for operating the UAV in temperatures in which capacity of the battery (120) is not negatively affected by ambient temperatures below its nominal operation temperature. Figure 4 illustrates a second configuration, suitable for "winter" operation, in other words for operating the UAV in temperatures in which capacity of the battery (120) would be negatively affected by ambient temperatures below its nominal operation temperature, if the invented solution was not applied.
Each of figures 3, 4, 5 and 6 show the body (200) of the UAV (100), into which the liquid cooled power generator (130) is attached. Liquid coolant is circulated in a closed circuit with a coolant circulator pump (330) such that hot coolant flows towards the radiator (115) in which its heat energy is passed to air flowing through the radiator (115). Air is preferably provided from outside the body using a fan (160). Instead of the preferred solution of providing the UAV with one or more fans (160), any other suitable method for providing sufficient air flow through the radiator (115) may be applied. For example, a radiator (115) may be disposed under one of the propellers (110) or an air scoop may be provided that deflects ambient air into the radiator (115) when the UAV is moving. Hot coolant flows (331) towards the radiator (115) and the cooled coolant flows back (332) to the power generator (130). The power generator (130) may be implemented as a combustion engine, in which the coolant heats while absorbing heat energy and the heated coolant flows (331) in the circulation for transferring heat energy away from cylinder heads of the combustion engine, and after passing heat away in the radiator, the cooled coolant is pumped back (332) with the coolant circulator pump (330) towards the combustion engine. A skilled person knows cooling arrangements also in other types of engines applicable as a power generator, such as fuel cells. Air flow (350) of ambient air sucked in by the fan (160) is illustrated with arrows towards the fan. Air heats up while absorbing heat energy from the liquid coolant while passing through the radiator (155) and the heated air flow (360) is flows through the radiator (115) to the deflecting frame (170) disposed on the side of the radiator (115) opposite to that of the fan (160). A battery (120) and avionics (125) are disposed within a dedicated space (220) within the body (200).
In the "summer" configuration shown in the figure 3, a configurable wall (270) of the deflecting frame (170) is disposed in a position that disables the heated air flow (360) from flowing into the dedicated space (220) by closing an open side of the deflection frame (170). At the same time, another side of the deflection frame (170) remains open, thus allowing the heated air flow (360) to be passed outside the body (200) of the UAV (100).
The configurable wall (270) thus forms, together with further fixed walls (275) of the deflection frame (170) a duct for the heated air from the radiator (110) to outside the body (200).
In the "winter" configuration shown in the figure 4, the configurable wall (270) of the deflecting frame (170) is disposed in a position that enables the heated air flow (360) to flow into the dedicated space (220) by closing the side of the deflection frame (170) that was left open in the "summer" configuration. Since the side of the deflection frame (170) towards the dedicated space (220) remains open, this allows the heated air flow (360) to be passed into the dedicated space (220) for heating up the dedicated space (220) and in particular the battery (120) and the optional avionics (125) in it. The configurable wall (270) thus forms, together with further fixed walls (275) of the deflection frame (170) a duct for the heated air from the radiator (110) to the dedicated space (220).
The configurable wall (270) may be turned about an axis with a hinge (280) for configuring the system into either one of the "summer" or the "winter" setting. A latch mechanism may be provided for securing the configurable wall (270) in either of its intended positions.
The figure 5 illustrates a third exemplary configuration, in which the configurable wall (270) is configured for deflecting a predefined fraction of the heated air flow towards the dedicated space (220). For example, the configurable wall may have a predefined number of inclination steps in relation to the deflective frame and the heated air flow (360) received from the radiator (115) for providing variable share of the heated air flow (360) towards the dedicated space, or inclination thereof may be gradually adjustable, such that it may be used for causing any selected fraction of the heated air flow (360) to enter the dedicated space (220), depending on ambient temperature. With a fraction we refer to for example x% of the entire heated air flow, wherein the remaining part corresponds to essentially (100-x) % of the heated air flow. A servo motor may be used for adjusting the configurable wall (270).
In the exemplary configuration of the figure 5 for example 20%, of the heated air flow (360) may be deflected towards the dedicated space (220) in +5°C for improving capacity of the battery, while the rest of the heated air flow (360) is deflected outside the body of the UAV.
This way, the dedicated space (220) may be warmed up in cool ambient temperatures that reside within the nominal operation range of the battery, but would in practice decrease the capacity of the battery (120) and/or performance of the avionics (125) somewhat, but without risk of causing overheating due to too much heating energy. If the nominal "summer" operation temperature range of the battery is defined as a first range and the "winter" operation temperature range is defined being below said nominal operation temperature range, such partial deflection of heated air flow may be advantageous in temperatures that still belong to the nominal operation range but in which the capacity of the battery would be in practice somewhat affected by the lower temperatures. Thus, it may be defined that if ambient temperature is less or equal to one or more predefined threshold temperature values within a first temperature range (nominal operation temperature range of the battery), partial deflection of the heated air flow towards the dedicated space is applied, and if the ambient temperature falls into the second temperature range below the first temperature range, the entire heated air flow is preferably deflected into the dedicated space (220). A plurality of temperature threshold values may be defined that correspond to various settings in which different fractions of the heated air flow (360) is to be deflected towards the dedicated space (220).
In an alternative embodiment, one or more configurable walls (270) may be removably attached to a wireframe defining respective sides of the deflecting frame (170) without a hinge. Such removably attachable walls (270) are preferably manually attached and removed in dependence of the ambient temperature. However, it is not necessary, that the deflective frame has openings with different size that can be closed with the same configurable wall. In such case, the selected open side of the deflecting frame (170) may be entirely or partially closed using one or more separate removably attachable walls of different sizes or types, which walls may be manually attached to the wireframe for covering selected side of the deflecting frame (170) fully or partially. By enclosing open sides only partially for example with a removably attachable wall smaller than the opening in the deflective frame (170), or applying a removable attachable wall having holes, flaps or air scoops for allowing a fraction of the heated air flow to be deflected towards the dedicated space (220), any selected fraction of the heated air flow (360) may be deflected towards the dedicated space for warming up the battery, while the remaining part of the heated air flow (360) is deflected outside the body of the UAV.
Figure 6 discloses a further embodiment, in which a configurable wall (170) comprises at least adjustable flap (271) for adjusting fraction of the heated air flow (360) that is deflected towards the dedicated space (220). The at least one adjustable flap may be configured to be opened in its entirety or only partially. In yet another alternative embodiment, the configurable wall (270) may comprise one or more holes that allow a fraction of the heated air (360) to flow towards the dedicated space (220).
Figures 7 and 8 show a perspective view of an exemplary embodiment of the invention in two different configurations. The body of the UAV has been omitted for clarity.
These illustrations show the pipes (531, 532) of the cooling system in which the coolant is circulated between the power generator (130) and the radiator (115) using the coolant circulator pump (330).
For facilitating air flow from the radiator towards the deflecting frame (170), face (171) of the deflecting frame towards the radiator is preferably essentially open, as illustrated in the figures 7 and 8 with the black bottom face (171) of the radiator (115) visible through the deflecting frame (170). The shape of the outer walls of the deflecting frame (170) preferably corresponds to the shape of the radiator (115) such that at least some fixed outer walls (275) of the deflecting frame (170) extend from the outer circumferential edges of the radiator (115). Preferably, fixed outer walls (275) of the deflective frame are aligned with the dominant direction of the air flow caused by the one or more fans (160) and received in the deflective frame (170) through the radiator (115) via the face (171) of the deflecting frame (170) that is adjacent to the radiator (115). This facilitates effective air flow through an assembly comprising the fan (160), at least part of the radiator (115) and at least part of the deflective frame (170).
In some embodiments, the deflecting frame may have one or more partition walls (275). Like the outer walls (275), these one or more partition walls (275') are preferably aligned with the dominant direction of the air flow caused by the one or more fans (160) and received in the deflective frame (170) through the radiator (115). Such one or more partition walls (275') facilitate for example mechanical stability to the deflecting frame (170) while also participating in deflection of the air flow passing through the deflecting frame. In some embodiments, the deflecting frame (170) may be divided by the partition walls (275') into at least two parts (170a, 170b) each of which pass air flow caused by respective one of at least two fans (160).
In addition to the essentially open side (171) towards the radiator (115), the deflecting frame (170) should preferably be open on at least two other sides. Shape of the deflecting frame on the open sides is preferably defined with a wireframe or some equivalent structure that allows either selectively attaching removably attachable walls (270a, 270b) into the deflecting frame or moving, for example rotating or translating, one or more adjustable walls (270) within the deflecting frame for selectively closing fully or partially at least one of the open sides with one or more removably attachable (270a, 270b) or adjustable walls (270). Any suitable means for removable attachment may be used for attaching the one or more removably attachable walls (270a, 270b). For example, the wireframe may comprise suitable slots into which an the removably attachable wall (270a, 270b) may be slid, or screws may be used for attaching the removably attachable walls to the deflecting frame (170) or hook-and-loop fastener known also as "velcro'', or removably attachable adhesive may be used for selectively attaching the removably attachable walls (270a, 270b) to the deflecting frame (170).
One or more adjustable walls (270) may be provided with a hinge mechanism enabling turning each of the adjustable walls between at least two alternative positions and any suitable type of latch mechanism for locking the adjustable wall in the selected position. Further, or additionally, for enabling deflection of the entire heated air flow or a predefined fraction of the heated air flow towards the dedicated space (220), the adjustable wall may comprise an adjustable flap (271) that can be automatically opened or closed either in its entirety or partially, as disclosed in the figure 6. Further, a servo motor may be provided onboard for enabling automated or remote-controlled configuration of the at least one adjustable wall in any applicable configuration. The servo motor may be used to set the position of the adjustable wall (270) and/or the adjustable flap (271) thereof for allowing variable configurations. In a fully automated configuration, a controller controls the servo motor to adjust the adjustable wall automatically on basis of temperature, for example on basis of measured ambient temperature or a temperature measured within the dedicated space (220). In a remote-controlled configuration, the servo motor may be controlled remotely by a user using wireless communication and a controller onboard for adjusting the adjustable wall into a wanted configuration.
In the preferred embodiment, at least one of the initially open sides of the deflecting frame (170) is directed down, towards outside the body of the UAV, and at least one of the initially open sides of the deflecting frame is directed towards the dedicated space (220) into which the at least one battery (120) and the optional avionics (125) are disposed, within the body of the UAV. The deflecting frame (170) may be configurable by selectively attaching one or more removably attachable walls (270a, 270b) or by turning one or more adjustable walls (270a, 270b) for closing the deflecting frame (170) on one of these initially open sides such, that the fixed walls (275, 275') and the at least one removably attachable or adjustable walls together define a path for passing the incoming air heated in the radiator (1 1 5).
When ambient temperature belongs to a range that has no significant negative effect on the performance of the battery (120), the deflecting frame (170) is preferably configured to pass the heated air flow away from the body of the UAV. This functionality is achieved by closing the initially open side of the deflecting frame that is directed towards the dedicated space (220) with at least one wall (270a), as shown in the figures 3 and 7, thus disabling any heated air from flowing into the dedicated space (220), and leaving the side of the deflecting frame open that is directed towards outside the body of the UAV. This way the heated air, which may for example have temperatures between +35°C and +55°C is passed away from the body via the duct formed by the deflecting frame (170). In warm ambient temperatures, such heated air, if passed towards the dedicated space could even cause the battery (120) or the avionics (125) in the dedicated space (220) to overheat. Thus, closing the open sides of the deflective frame (170) towards the dedicated space (220) with the wall (270a) also protects the devices disposed within the dedicated space (220) from overheating.
The battery (120) shown in the figures 7 and 8, although divided in two physical blocks, may be functionally considered as a single battery (120) comprising a plurality of battery cells coupled in series. Preferably, the battery (120) is considered as a single functional entity, which is preferably warmed/heated up in unison for maximum performance.
However, the invention is not limited to any number of batteries or battery cells that may need to be warmed up within the dedicated space (220). The embodiment shown in the figures 7 and 8 shows two extremes of the positions of the configurable wall or walls (270a, 270b), equivalent to "summer" and "winter" configurations. Figure 7 discloses the summer configuration in which the heated air flow is directed away from the UAV body. Figure 8 illustrates the winter configuration, in which the heated air flow is deflected into the dedicated space (220). In the embodiment shown in the figures 7 and 8, partial deflection of the heated air flow may be implemented for example by covering one or more openings in the deflecting frame (170) with walls that cover any of the initial openings only partially or by using attachable walls with suitable holes, air scoops and/or adjustable flaps that cause part of the heated air flow to be deflected towards the dedicated space (220).
When ambient temperature belongs to a range that would negatively affect performance of the at least one battery (120), in other words temperatures that are near, equal or below the lower threshold of the nominal operation temperature of the at least one battery (120), the deflecting frame (170) is preferably configured to deflect the heated air flow from the radiator (115) towards the dedicated space (220), thus heating up the at least one battery (120) and the optional avionics (125) disposed in the dedicated space (220). This functionality is achieved by entirely closing the initially open side of the deflecting frame (170) towards outside the body with a wall or walls (270b), and leaving the open side of the deflecting frame open that is directed towards the dedicated space (220), as shown in the figure 8. This way the heated air, which may have for example temperatures between +35°C and +55°C is passed towards the dedicated space (220) for warming it up, while the installed at least one wall (270b) disables the heated air flow from being passed directly out from the body of the UAV. The dedicated space (220) may be only partially enclosed by the body (200) and optionally with one or more further covers or shields, so that the dedicated space (200) has openings that allow air to flow out from the dedicated space in order to ensure good circulation of the incoming warm air about the devices disposed within the dedicated space (220).
Test flights performed in winter weather, with ambient temperature of about -20°C have shown that with such configurable deflecting frame (170) arrangement, temperature of the dedicated space (220) and the at least one battery (120) was maintained in about +15°C even after hours of flying, which temperature is sufficient for ensuring proper operation of the battery within its nominal temperature range.
In one embodiment, the user makes decision on whether to configure the deflecting frame (170) to deflect air away from the body of the UAV or into the dedicated space (220). On basis of this decision, the user either installs selected at least one removably attachable wall (270a, 270b) in the deflecting frame or selects a position of at least one adjustable wall (270).
In one alternative embodiment, at least one adjustable wall (270) may be automatically controlled in dependence of information on at least one of a measured ambient temperature, a measured temperature inside the dedicated space, a measured temperature of the battery and a measured temperature of the avionics disposed in the dedicated space. In such case, a temperature threshold value is preferably defined, and the measured temperature is compared to the temperature threshold value. If the measured temperature is below the threshold, the at least one adjustable wall is automatically turned into a position that causes air flow to be passed towards the dedicated space (220), and in other cases the at least one adjustable wall is disposed such that air flow is passed away from the body of the UAV. As understood by a skilled person, the exact temperature threshold value depends at least on the nominal operation temperature range of the battery, but it may also depend on other factors such as variation of the operation efficiency of the battery within the temperature range, structure of the body of the UAV and in particular that of the dedicated space and the temperature of the air flow received from the radiator, which depends for example on the type of the power generator, fuel and characteristics of the closed cooling loop. Preferably, a temperature threshold is defined that ensures optimal battery performance for the current ambient conditions. Recommended ambient temperature threshold value information may also be provided for a user for manually adjusting at least one adjustable wall, or for instructing the user to manually assemble at least one removably attachable or configurable wall before operating the UAV.
The above examples and embodiments are provided for enabling disclosure of the main principles of the invention. The scope of protection is not limited to any particular example but is defined by the scope of the claims.

Claims (19)

  1. CLAIMS1. A hybrid unmanned aerial vehicle (UAV), comprising - a body; - at least one battery disposed in a dedicated space of the body: -at least one electrical motor for operating at least one propeller of the UAV, wherein the at least one electrical motor is configured to operate on the energy provided by the at least one battery; - a liquid or gaseous fuel powered, and liquid cooled power generator for charging the at least one battery; -a coolant circulator pump for circulating liquid coolant of the power generator in a closed circulation loop configured to conduct heat away from the power generator; and - a radiator configured to transfer thermal energy from the liquid coolant to air passing through the radiator; characterized in that the UAV further comprises a configurable deflector frame disposed adjacent to the radiator and configured to deflect the heated air flow from the radiator, wherein the configurable deflector frame is selectively configurable for deflecting said heated air flow away from the body of the UAV when ambient temperature is in a first temperature range in which performance of the at least one battery is at or near nominal; and - for deflecting said heated air flow towards said dedicated space for warming up the at least one battery when ambient temperature is in a second temperature range in which performance of the at least one battery would otherwise become lowered, wherein the second temperature range is below said first temperature range.
  2. 2. The UAV according to claim 1, wherein - the dedicated space further comprises avionics such that when the deflector frame is configured to deflect said flow towards the dedicated space, it also warms up the avionics.
  3. 3. The UAV according to any of claims 1 to 2, wherein said configurable deflector frame comprises a plurality of fixed walls and at least two removably attachable walls configured to be manually removably attached on at least two different sides of the deflector frame, wherein the at least two different sides of the deflector frame are essentially open such that - when a first removably attachable wall is attached at a first side of the deflector frame, the first removably attachable wall closes the initially open first side of the deflector frame for disabling the heated air flow from flowing towards the dedicated space and causes, together with at least some of the fixed walls, deflecting the heated air flow away from the body of the UAV via an open second side of the deflector frame; and -when a second removably attachable wall is attached at the second side of the deflector frame, the second removably attachable wall closes the initially open second side of the deflector frame for disabling the heated air flow from flowing away from the body of the UAV via the second side of the deflector frame and causes, together with at least some of the fixed walls, deflecting the heated air flow via the open first side of the deflector frame towards the dedicated space.
  4. 4. The UAV according to any of claims 1 or 2, wherein said configurable deflector frame comprises a plurality of fixed walls and at least one manually or automatically adjustable wall configured to be adjusted into at least two different positions, such that - when the at least one adjustable wall is disposed on a first side of the deflector frame, the at least one adjustable wall closes the otherwise open first side of the deflector frame for disabling the heated air flow from flowing towards the dedicated space and causes, together with at least some of the fixed walls, deflecting the heated air flow away from the body of the UAV via an open second side of the deflector frame; and -when the at least one adjustable wall is disposed on the second side of the deflector frame, the at least one adjustable wall closes the otherwise open second side of the deflector frame for disabling the heated air flow from flowing away from the body of the UAV via the open second side of the deflector frame and causes, together with at least some of the fixed walls, deflecting the heated air flow via the open first side of the deflector frame towards the dedicated space.
  5. 5. The UAV according to claim 4, wherein said at least one adjustable wall is configured to be adjusted using a servo motor.
  6. 6. The UAV according to any of claims 1 to 5, wherein the configurable deflector frame is further configurable - to deflect a predetermined fraction of said heated air flow towards said dedicated space and to deflect remaining part of said heated air flow away from the body of the UAV, when ambient temperature is between a first temperature threshold within the first temperature range and an upper temperature threshold of the second temperature range.
  7. 7. The UAV according to claim 6 in combination with claim 3, wherein said at least two removably attachable walls are configured to deflect the predetermined fraction of said heated air flow towards the dedicated space by one or more of: - partially closing the initially open first side of the deflector frame with a third removably attachable wall for deflecting the predetermined fraction of the heated air flow towards the dedicated space and for disabling the remaining part of the heated air flow from flowing towards the dedicated space; - providing the at least first removably attachable wall with one or more air scoops for deflecting the predetermined fraction of the heated air flow towards the dedicated space; - providing one or more holes in the at least first removably attachable wall for deflecting the predetermined fraction of the heated air flow towards the dedicated space; and - providing at least one adjustable flap in the first wall, wherein opening the adjustable flap partially or fully is configured to cause the predetermined fraction of the heated air flow to be deflected towards the dedicated space.
  8. 8. The UAV according to claim 6 in combination with claim 4 or 5, wherein said at least one adjustable wall is further configured to be adjusted into at least one third position, in which the at least one adjustable wall is configured to: - be inclined relative to the deflecting frame and to the heated air flow for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space and the remaining part of the heated air flow to be deflected outside the body of the UAV; or - comprise at least one adjustable flap in the at least one adjustable wall disposed on the first side of the deflector frame, wherein partially or entirely opening the at least one adjustable flap causes the predefined fraction of the heated air flow to flow towards the dedicated space.
  9. 9. The UAV according to any of claims 4, 5 or 8, wherein said at least one adjustable wall is configured to be adjusted automatically based on a measured ambient temperature.
  10. 10. The UAV according to any of the preceding claims, wherein capacity of the at least one battery is sufficient for safe landing of the UAV when no electrical power is received from the power generator.
  11. 11. A method for operating a hybrid unmanned aerial vehicle (UAV) comprising - a body; and -at least one battery disposed in a dedicated space of the body; wherein the method comprises - operating one or more propellers of the UAV using at least one electrical motor, wherein the at least one electrical motor is configured to operate on the energy provided by the at least one battery; -charging the at least one battery with a liquid or gaseous fuel powered, and liquid cooled power generator; - circulating liquid coolant of the power generator in a closed circulation loop with a coolant circulator pump for conducting heat away from the power generator; - transferring thermal energy from the liquid coolant to air with a radiator; - causing an air flow through the radiator for passing thermal energy from the liquid coolant to the air flow, wherein the air flow is heated while passing through the radiator; characterized in that the method further comprises - deflecting the heated air flow from the radiator with a configurable deflector frame disposed adjacent to the radiator, wherein said deflecting the heated air flow with the configurable deflector frame comprises - deflecting said heated air flow away from the body of the UAV when ambient temperature is in a first temperature range in which performance of the battery is at or near nominal; or - deflecting said heated air flow towards said dedicated space for warming up the battery when ambient temperature is in a second temperature range in which performance of the battery would otherwise become lowered, wherein the second temperature range is below said first temperature range.
  12. 12. The method according to claim 11, wherein the dedicated space further comprises avionics, such that the heated air flow deflected towards said dedicated space also warms up the avionics.
  13. 13. The method according to any of claims 11 or 12, wherein said configurable deflector frame comprises a plurality of fixed walls and at least two manually removably attachable walls configured to be removably attached on at least two different sides of the deflector frame, and the method comprises - disabling the heated air flow from flowing towards the dedicated space and deflecting the heated air flow away from the body of the UAV via an open second side of the deflector frame by attaching at least one first removably attachable wall at a first side of the deflector frame, whereby the at least one first removably attachable wall closes the otherwise open first side of the deflector frame; or - disabling the heated air flow from flowing away from the body of the UAV via the second side of the deflector frame and deflecting the heated air flow towards the dedicated space via the open first side of the deflector frame by attaching at least one second removably attachable wall at the second side of the deflector frame, wherein the at least one second removably attachable wall closes the otherwise open second side of the deflector frame.
  14. 14. The method according to any of claims 11 or 12, wherein said configurable deflector frame comprises a plurality of fixed walls and at least one adjustable wall configured to be manually or automatically adjusted into at least two different positions, and the method comprises - disabling the heated air flow from flowing towards the dedicated space and deflecting the heated air flow away from the body of the UAV via an open second side of the deflector frame by disposing the at least one adjustable wall on a first side of the deflector frame, whereby the at least one adjustable wall closes the otherwise open first side of the deflector frame; or - disabling the heated air flow from flowing away from the body of the UAV via the second side of the deflector frame and deflecting the heated air flow via the open first side of the deflector frame towards the dedicated space by disposing the at least one adjustable wall on the second side of the deflector frame, whereby the at least one adjustable wall closes the otherwise open second side of the deflector frame.
  15. 15. The method according to claim 14, the method further comprising adjusting said at least one adjustable wall with a servo motor
  16. 16. The method according to any of claims 11 to 15, wherein the method further comprises -deflecting a fraction of said heated air flow towards said dedicated space and deflecting remaining part of said heated air flow away from the body of the UAV, when ambient temperature is between a first temperature threshold within the first temperature range and an upper temperature threshold of the second temperature range.
  17. 17. The method according to claim 16 in combination with claim 13, wherein said deflecting the predetermined fraction of said heated air flow towards the dedicated space is achieved by any of: - partially closing the initially open first side of the deflector frame with a third wall for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space and for disabling the remaining part of the heated air flow from flowing towards the dedicated space; - providing one or more air scoops provided in the first wall for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space; - providing one or more holes in the first wall for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space; and - providing at least one adjustable flap in the first wall, wherein opening the at least one adjustable flap partially or fully causes deflecting of the predetermined fraction of the heated air flow to be deflected towards the dedicated space.
  18. 18. The method according to claim 16 in combination with one of claims 14 or 15, wherein said deflecting the predetermined fraction of said heated air flow towards the dedicated space is achieved by any of: - tilting the at least one adjustable wall with respect to the deflective frame and the heated air flow for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space and the remaining part of the heated air flow to be deflected outside the body of the UAV; and - partially or fully opening a flap in the at least one adjustable wall disposed on the first side of the deflector frame for causing the predetermined fraction of the heated air flow to be deflected towards the dedicated space.
  19. 19. The method according to any of claims 14, 15 or 18, further comprising adjusting said at least one adjustable wall automatically on basis of a measured ambient temperature.
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