# US 2022/0285758 A1 · Battery cooling device and method for cooling a battery cell of an electrically powered aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2022/0285758 A1 - Document ID: US20220285758A1 - Status: Published application - Kind: A1 - Application number: 17/686,498 - Filed: 2022-03-04 - Published: 2022-09-08 - Earliest claimed: 2021-03-05 - Assignees: Volocopter GmbH - Applicants: Volocopter GmbH - Inventors: Nils ZIEGLER - Web page: https://patentgrep.com/patent/US20220285758A1 ## CPC - H01M 10/6556: Solid parts with flow channel passages or pipes for heat exchange (closed pipes H01M10/6552) - H01M 10/44: Methods for charging or discharging (circuits for charging H02J7/00) - H01M 10/613: Cooling or keeping cold - H01M 10/625: Vehicles - H01M 10/653: characterised by electrically insulating or thermally conductive materials - H01M 10/6554: Rods or plates - H01M 10/6568: characterised by flow circuits, e.g. loops, located externally to the cells or cell casings - H01M 10/658: by thermal insulation or shielding - H01M 10/659: by heat storage or buffering, e.g. heat capacity or liquid-solid phase changes or transition - H01M 50/213: adapted for cells having curved cross-section, e.g. round or elliptic (H01M50/209, H01M50/216 take precedence) - H01M 50/249: specially adapted for aircraft or vehicles, e.g. cars or trains (constructional details of batteries specially adapted for electric vehicles B60L50/64) - H01M 10/0525: Rocking-chair batteries, i.e. batteries with lithium insertion or intercalation in both electrodes; Lithium-ion batteries - H01M 10/643: Cylindrical cells - H01M 2220/20: Batteries in motive systems, e.g. vehicle, ship, plane - Y02E 60/10: Energy storage using batteries - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - H01M: PROCESSES OR MEANS, e.g. BATTERIES, FOR THE DIRECT CONVERSION OF CHEMICAL ENERGY INTO ELECTRICAL ENERGY - Y02E: REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A battery cooling device (6) for cooling at least one battery cell (5) of an electrically operated aircraft is provided, the battery cooling device (6) having a first cooling device (7, 8) configured for absorbing a first amount of heat at least from the battery cell (5) in an electrical discharging process and thereby cooling it. The first cooling device has at least one latent heat storage unit with a variable state of aggregation. The battery cooling device (6) also includes a second cooling device (9), which is configured for absorbing a second amount of heat from the battery cell (5) and the first cooling device in an electrical charging process, the second cooling device (9) being able to be filled with and flowed through by a coolant (13). Furthermore, the invention relates to a method for cooling a battery cell of an electrically powered aircraft. ## Claims ### Claim 1 A battery cooling device (6) for cooling at least one battery cell (5) of an electrically operated aircraft (1), the battery cooling device (6) comprising: a first cooling device (7, 8) configured for absorbing a first amount of heat (10) at least from the battery cell (5) in an electrical discharging process, the first cooling device (7, 8) comprising at least one latent heat storage unit with a variable state of aggregation, and a second cooling device (9) configured for absorbing a second amount of heat (12) from the battery cell (5) and the first cooling device (7, 8), the second cooling device (9) being able to be filled with and flowed through by a coolant (13). ### Claim 2 (depends on 1) The battery cooling device (6) as claimed in claim 1, wherein the second cooling device (9) has at least one of a flexible hose or a cooling plate, which is fillable with and flowed through by a coolant (13). ### Claim 3 (depends on 2) The battery cooling device (6) as claimed in claim 2, wherein the flexible hose is configured for indirectly or directly exerting a pressing pressure on the battery cell (5) and the first cooling device (7, 8) when the coolant (13) flows through. ### Claim 4 (depends on 1) The battery cooling device (6) as claimed in claim 1, wherein the second cooling device (9) is connected in a thermally conducting manner to the battery cell (5) by a first intermediate layer (23) and the first intermediate layer (23) is electrically insulating. ### Claim 5 (depends on 4) The battery cooling device as claimed in claim 4, wherein the second cooling device (9) is connected in a thermally conducting manner to the first intermediate layer (23) by a second intermediate layer (24) and the second intermediate layer (24) has a higher mechanical load-bearing capacity, than the first intermediate layer (23). ### Claim 6 (depends on 1) A battery module (3) comprising the battery cooling device (6) according to claim 1, and at least one battery cell (5). ### Claim 7 (depends on 6) The battery module as claimed in claim 6, further comprising a fire protection material (19), which at least partially encloses the battery cell (5) or the plurality of battery cells (5). ### Claim 8 (depends on 6) The battery module as claimed in claim 6, further comprising a busbar, and the battery cell is connected to the busbar in an electrically conductive manner by at least one wire bond. ### Claim 9 (depends on 6) The battery module as claimed in claim 6, wherein the at least one battery cell comprises at least two battery cells (5) which are in each case configured as a cylindrical round cell with a negatively poled end face (N) and with a positively poled end face (P), the round cells being arranged parallel to one another and the negatively poled end faces (N) of all of the battery cells (5) being arranged on a first side of the battery module (3) and the positively poled end faces (P) of all of the battery cells (5) being arranged on a second side of the battery module (3). ### Claim 10 (depends on 6) A vertical takeoff and landing, electrically powered aircraft (1), comprising a battery module (3) as claimed in claim 6. ### Claim 11 (depends on 10) The vertical takeoff and landing, electrically powered aircraft (1) as claimed in claim 10, further comprising a connector configured to connect the battery module (3) mechanically and electrically to drive units of the aircraft in an operating state, the connector being releasably configured in order to disconnect the battery module (3) from the aircraft (1) for a charging process. ### Claim 12 (depends on 10) A battery charging system (25) comprising: the vertical takeoff and landing aircraft (1) as claimed in claim 10 and a ground charging station (26), the ground charging station (26) has an electrical charging device for the battery cell and a cooling unit and is configured for electrically contacting the battery module (3) for the charging process of the battery cell (5) and for connecting the second cooling system (9) of the battery cooling device (6) to a stationary coolant circuit (27) of the cooling unit in a thermally conducting manner. ### Claim 13 A method for cooling a battery cell (5) of an electrically powered aircraft (1), the method comprising providing a battery cooling device (6) with a first cooling device (7, 8) with a latent heat storage unit, the first cooling device (7, 8) in a method step A absorbing a first amount of heat (10) which the battery cell (5) dissipates, and in a method step B, a second cooling device (9) of the battery cooling device absorbing a second amount of heat (12) from at least one of the battery cell (5) or the first cooling device (7, 8). ### Claim 14 (depends on 13) The method as claimed in claim 13, wherein method step B is carried out at least one of before, during, or after a charging process of the battery cell (5), a coolant (13) is pumped into the second cooling device (9) of the battery cooling device and the coolant of the second cooling device (9) absorbs the second amount of heat (12) from at least one of the battery cell (5) or the first cooling device (7, 8). ### Claim 15 (depends on 13) The method as claimed in claim 13, wherein during the absorption of the first amount of heat (10), the latent heat storage unit of the first cooling device (7, 8) changes its state of aggregation from solid to liquid/viscous and, during dissipation of the second amount of heat (12), changes its state of aggregation from liquid/viscous to solid. ### Claim 16 (depends on 13) The method as claimed in claim 13, further comprising removing a battery module (3), comprising the battery cooling device (6) and at least one battery cell (5), from the electrically powered aircraft (1) before the charging process of the battery cell (5), carrying out the charging process at a ground charging station (26), after completion of a reverse reaction for restoration of a functional capability of the latent heat storage unit, pumping the coolant (13) out of the second cooling device (9) and fitting the battery module (3) again into the electrically operated aircraft (1).