# US 11,993,397 B1 · System and a method for preconditioning a power source of 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 11,993,397 B1 - Document ID: US11993397B1 - Status: Granted - Kind: B1 - Application number: 18/120,257 - Filed: 2023-03-10 - Granted: 2024-05-28 - Earliest claimed: 2023-03-10 - Assignees: Beta Air, LLC - Applicants: Beta Air, LLC - Inventors: John Charles Palombini - Web page: https://patentgrep.com/patent/US11993397B1 ## CPC - B64F 1/36: Other airport installations (ground installations for de-icing aircraft B64F5/20) - B60L 53/18: Cables specially adapted for charging electric vehicles - B60L 58/26: by cooling - B60L 2200/10: Air crafts - 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 - 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 ## Abstract A system and a method for preconditioning a power source of an electric aircraft are disclosed. The system may include a ground service equipment, wherein the ground service equipment may be configured to precondition a power source of an electric aircraft. The ground service equipment may include a positive pressure pump configured to pump a coolant into the power source and a negative pressure pump configured to pump the coolant out of the power source. The system may include a controller communicatively connected to the ground service equipment. The controller may be configured to control the positive pressure pump and control the negative pressure pump. ## Claims ### Claim 1 A system for preconditioning a power source of an electric aircraft, wherein the system comprises: a ground service equipment, wherein the ground service equipment is configured to precondition a power source of an electric aircraft and comprises: a positive pressure pump configured to pump a coolant into the power source; and a negative pressure pump configured to pump the coolant out of the power source; and a controller communicatively connected to the ground service equipment, wherein the controller is configured to: control the positive pressure pump to pump the coolant into the power source; and control the negative pressure pump to pump the coolant out of the power source. ### Claim 2 (depends on 1) The system of claim 1, wherein the power source of the electric aircraft comprises a cooling circuit configured to allow a coolant flow, wherein the positive pressure pump is further configured to pump the coolant into the cooling circuit of the power source. ### Claim 3 (depends on 2) The system of claim 2, wherein the negative pressure pump is further configured to pump the coolant out of the cooling circuit of the power source. ### Claim 4 (depends on 1) The system of claim 1, wherein the preconditioning the power source of the electric aircraft comprises precooling. ### Claim 5 (depends on 1) The system of claim 1, wherein the negative pressure pump comprises an entrapment pump. ### Claim 6 (depends on 1) The system of claim 1, wherein the negative pressure pump is configured to pull the coolant out of the power source after the positive pressure pump pumps the coolant into the power source of the electric aircraft. ### Claim 7 (depends on 1) The system of claim 1, wherein the controller is further configured to control a flow rate of the coolant. ### Claim 8 (depends on 1) The system of claim 1, wherein the ground service equipment further comprises a spent coolant reservoir. ### Claim 9 (depends on 1) The system of claim 1, wherein the ground service equipment further comprises a cable module, wherein the cable module comprises: a connector, wherein the connector is configured to mate with a port of the electric aircraft; a proximal end, wherein the proximal end is connected with the ground service equipment; and a cable configured to transmit the coolant from the proximal end to the connector. ### Claim 10 (depends on 9) The system of claim 9, wherein the system further comprises a user input device configured to receive a user input, wherein the connector of the cable module comprises the user input device. ### Claim 11 A method for preconditioning a power source of an electric aircraft, wherein the method comprises: receiving, using a controller, a user input from a user input device; receiving, using the controller, a temperature of a power source of an electric aircraft from at least a sensor communicatively connected to the power source; controlling, using the controller, a positive pressure pump of ground service equipment to pump a coolant into the power source of the electric aircraft as a function of the user input; and controlling, using the controller, a negative pressure pump of the ground service equipment to pump the coolant out of the power source of the electric aircraft of the ground service equipment as a function of the temperature of the power source. ### Claim 12 (depends on 11) The method of claim 11, wherein the power source of the electric aircraft comprises a cooling circuit configured to allow a coolant flow, wherein the positive pressure pump is further configured to pump the coolant into the cooling circuit of the power source. ### Claim 13 (depends on 12) The method of claim 12, further comprising: pumping, using the negative pressure pump, the coolant out of the cooling circuit of the power source. ### Claim 14 (depends on 11) The method of claim 11, wherein the preconditioning the power source of the electric aircraft comprises precooling the power source. ### Claim 15 (depends on 11) The method of claim 11, wherein the negative pressure pump comprises an entrapment pump. ### Claim 16 (depends on 11) The method of claim 11, further comprising: controlling, using the controller, a flow rate of the coolant. ### Claim 17 (depends on 16) The method of claim 16, further comprising: pulling, using the negative pressure pump, the coolant out of the power source after the positive pressure pump pumps the coolant into the power source of the electric aircraft. ### Claim 18 (depends on 11) The method of claim 11, wherein the ground service equipment comprises a spent coolant reservoir. ### Claim 19 (depends on 11) The method of claim 11, wherein the ground service equipment further comprises a cable module, wherein the cable module comprises: a connector, wherein the connector is configured to mate with a port of the electric aircraft; a proximal end, wherein the proximal end is connected with the ground service equipment; and a cable configured to transmit the coolant from the proximal end to the connector.