# US 2023/0066433 A1 · Apparatuses and methods for charging an electric aircraft > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2023/0066433 A1 - Document ID: US20230066433A1 - Status: Published application - Kind: A1 - Application number: 17/575,358 - Filed: 2022-01-13 - Published: 2023-03-02 - Earliest claimed: 2021-08-20 - Assignees: Beta Air, LLC - Applicants: Beta Air, LLC - Inventors: Herman Wiegman - Web page: https://patentgrep.com/patent/US20230066433A1 ## CPC - B60L 58/26: by cooling - B60L 3/0046: {relating to electric energy storage systems, e.g. batteries or capacitors} - B60L 50/60: using power supplied by batteries (in combination with fuel cells B60L50/75) - B60L 53/16: Connectors, e.g. plugs or sockets, specially adapted for charging electric vehicles - B60L 53/18: Cables specially adapted for charging electric vehicles - B60L 53/62: in response to charging parameters, e.g. current, voltage or electrical charge - B60L 58/21: having the same nominal voltage - B64D 27/34: All-electric aircraft - B64D 31/16: for electric power plants - B64F 1/35: for supplying electrical power to stationary aircraft - B64U 50/37: Charging when not in flight - H02J 7/42: with electronic devices having internal batteries, e.g. mobile phones - H02J 7/751: {concerning the insertion or the connection of the batteries} - H02J 7/82: Control of state of charge [SOC] - H02J 7/933: {the cycle being controlled or terminated in response to electric parameters} - B60L 2200/10: Air crafts - B60L 2240/545: Temperature - B60L 2240/70: Interactions with external data bases, e.g. traffic centres - B60L 2250/12: by confirmation, e.g. of the input - H01R 13/5202: {Sealing means between parts of housing or between housing part and a wall, e.g. sealing rings} - H01R 2201/26: for vehicles - H02J 2105/32: {for aircrafts} - Y02T 10/70: Energy storage systems for electromobility, e.g. batteries - Y02T 10/7072: Electromobility specific charging systems or methods for batteries, ultracapacitors, supercapacitors or double-layer capacitors - Y02T 90/12: Electric charging stations - Y02T 90/14: Plug-in electric vehicles - B60L: PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES (arrangements or mounting of electrical propulsion units or of plural diverse prime-movers for mutual or common propulsion in vehicles B60K1/00, B60K6/20; arrangements or mounting of electrical gearing in vehicles B60K17/12, B60K17/14; preventing wheel slip by reducing power in rail vehicles B61C15/08; dynamo-electric machines H02K; control or regulation of electric motors H02P); SUPPLYING ELECTRIC POWER FOR AUXILIARY EQUIPMENT OF ELECTRICALLY-PROPELLED VEHICLES (electric coupling devices combined with mechanical couplings of vehicles B60D1/64; electric heating for vehicles B60H1/00); ELECTRODYNAMIC BRAKE SYSTEMS FOR VEHICLES IN GENERAL (control or regulation of electric motors H02P); MAGNETIC SUSPENSION OR LEVITATION FOR VEHICLES; MONITORING OPERATING VARIABLES OF ELECTRICALLY-PROPELLED VEHICLES; ELECTRIC SAFETY DEVICES FOR ELECTRICALLY-PROPELLED VEHICLES - B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT - B64F: GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR - B64U: UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR - H02J: ELECTRIC POWER NETWORKS; CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY - H01R: ELECTRICALLY-CONDUCTIVE CONNECTIONS; STRUCTURAL ASSOCIATIONS OF A PLURALITY OF MUTUALLY-INSULATED ELECTRICAL CONNECTING ELEMENTS; COUPLING DEVICES; CURRENT COLLECTORS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A system for charging an electric aircraft. The system includes an electric aircraft port, at least a current conductor, a power supply circuit and a controller. The electric aircraft port is configured to mate with a charging connector. At least a portion of the at least a current conductor is at the electric aircraft port. The at least a current conductor is configured to conduct a charging current to at least an energy source of the electric aircraft. The power supply circuit is electrically connected to the at least a current conductor. The power supply circuit is configured to regulate the charging current supplied to the at least an energy source. The controller is communicatively connected to the power supply circuit. The controller is configured to control operation of the power supply circuit as a function of a power threshold. A method for charging an electric aircraft is also provided. ## Claims ### Claim 1 An apparatus for charging an electric aircraft, comprising: an electric aircraft port of an electric aircraft, wherein the electric aircraft port is configured to mate with a charging connector; at least a current conductor, wherein at least a portion of the at least a current conductor is at the electric aircraft port, wherein the at least a current conductor is configured to conduct a charging current to at least an energy source of the electric aircraft; a power supply circuit electrically connected to the at least a current conductor, wherein the power supply circuit is configured to regulate the charging current supplied to the at least an energy source; and a controller communicatively connected to the power supply circuit, wherein the controller is configured to control operation of the power supply circuit as a function of a power threshold. ### Claim 2 (depends on 1) The system of claim 1, wherein the electric aircraft port is configured to mate with a coupling mechanism of the charging connector. ### Claim 3 (depends on 1) The system of claim 1, wherein the at least a current conductor comprises at least a direct current (DC) conductor. ### Claim 4 (depends on 1) The system of claim 1, wherein the at least an energy source comprises at least a battery. ### Claim 5 (depends on 1) The system of claim 1, wherein the power supply circuit is further configured to regulate a charging voltage supplied to the at least an energy source. ### Claim 6 (depends on 1) The system of claim 1, wherein the controller is further configured to terminate communication between the electric aircraft and the charging connector as a function of the power threshold. ### Claim 7 (depends on 1) The system of claim 1, wherein the controller is further configured to terminate the charging current supplied to the at least an energy source as a function of the power threshold. ### Claim 8 (depends on 1) The system of claim 1, wherein the controller is further configured to terminate the charging current supplied to the at least an energy source as a function of a failed charge event. ### Claim 9 (depends on 1) The system of claim 1, wherein the power threshold comprises a current threshold. ### Claim 10 (depends on 1) The system of claim 1, wherein the power threshold comprises a voltage threshold. ### Claim 11 A method for charging an electric aircraft, comprising: mating an electric aircraft port of an electric aircraft with a charging connector; conducting, by at least a current conductor, a charging current to at least an energy source of the electric aircraft, wherein at least a portion of the at least a current conductor is at the electric aircraft port; regulating, by a power supply circuit electrically connected to the at least a current conductor, the charging current supplied to the at least an energy source; and controlling, by a controller communicatively connected to the power supply circuit, operation of the power supply circuit as a function of a power threshold. ### Claim 12 (depends on 11) The method of claim 11, wherein mating the electric aircraft port further comprises mating the electric aircraft port with a coupling mechanism of the charging connector. ### Claim 13 (depends on 11) The method of claim 11, wherein the at least a current conductor comprises at least a direct current (DC) conductor. ### Claim 14 (depends on 11) The method of claim 11, wherein the at least an energy source comprises at least a battery. ### Claim 15 (depends on 11) The method of claim 11, wherein the method further comprises regulating, by the power supply circuit, a charging voltage supplied to the at least an energy source. ### Claim 16 (depends on 11) The method of claim 11, wherein controlling operation of the power supply circuit further comprises terminating communication between the electric aircraft and the charging connector as a function of the power threshold. ### Claim 17 (depends on 11) The method of claim 11, wherein controlling operation of the power supply circuit further comprises terminating the charging current supplied to the at least an energy source as a function of the power threshold. ### Claim 18 (depends on 11) The method of claim 11, wherein controlling operation of the power supply circuit further comprises terminating the charging current supplied to the at least an energy source as a function of a failed charge event. ### Claim 19 (depends on 11) The method of claim 11, wherein the power threshold comprises a current threshold. ### Claim 20 (depends on 11) The method of claim 11, wherein the power threshold comprises a voltage threshold.