US 12,227,097 B2
Electric charging station for an electric vehicle and a method for its use
John Charles Palombini, South Burlington, VT (US); Nathan Ward, South Burlington, VT (US); Richard Donnelly, South Burlington, VT (US); Jake Pill, South Burlington, VT (US); and Edward Hall, South Burlington, VT (US)
Assigned to BETA Air LLC, South Burlington, VT (US)
Filed by BETA AIR, LLC, South Burlington, VT (US)
Filed on Apr. 3, 2023, as Appl. No. 18/130,064.
Application 18/130,064 is a continuation of application No. 17/751,870, filed on May 24, 2022, granted, now 11,654,787.
Prior Publication US 2023/0382250 A1, Nov. 30, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. B60L 53/302 (2019.01); B60L 53/18 (2019.01); B60L 58/24 (2019.01); B64C 29/00 (2006.01); B64F 1/36 (2024.01); H02J 7/00 (2006.01)
CPC B60L 53/302 (2019.02) [B60L 53/18 (2019.02); B60L 58/24 (2019.02); B64F 1/362 (2013.01); H02J 7/0042 (2013.01); B60L 2200/10 (2013.01); B64C 29/0008 (2013.01)] 20 Claims
OG exemplary drawing
 
1. An electric charging station for an electric aircraft, wherein the electric charging station comprises:
a charging connector, wherein the charging connector is configured to couple with an electric vehicle port of an electric aircraft for charging a battery of the electric aircraft;
a charging cable electrically connected to the charging connector, wherein the charging cable is configured to carry electricity;
an energy source, wherein the energy source is electrically connected to the charging cable;
a first fluidic connector, wherein the first fluidic connector is configured to couple with at least the electric vehicle port;
a battery temperature regulating element thermally connected to at least the battery of the electric aircraft through at least the electric aircraft vehicle port and comprising at least a coolant flow path;
a coolant temperature sensor, wherein the coolant temperature sensor is configured to generate a coolant temperature datum as a function of a coolant temperature; and
a computing device communicatively connected to the battery temperature regulating element and the coolant temperature sensor, wherein the computing device is configured to:
receive the coolant temperature datum from the coolant temperature sensor;
regulate the coolant temperature; and
modify a battery temperature of the battery of the electric aircraft using the battery temperature regulating element as a function of coolant flow.