US 11,897,599 B2
System and a method for a battery power management system for an electric aircraft
Stuart Denson Schreiber, South Burlington, VT (US); Nicholas Moy, South Burlington, VT (US); and Collin Freiheit, South Burlington, VT (US)
Assigned to Beta Air, LLC, South Burlington, VT (US)
Filed by BETA AIR, LLC, South Burlington, VT (US)
Filed on Mar. 31, 2023, as Appl. No. 18/129,366.
Application 18/129,366 is a continuation in part of application No. 17/515,124, filed on Oct. 29, 2021, granted, now 11,679,867.
Application 17/515,124 is a continuation in part of application No. 18/114,478, filed on Feb. 27, 2023.
Application 17/515,124 is a continuation of application No. 17/349,631, filed on Jun. 16, 2021.
Application 17/349,631 is a continuation in part of application No. 17/197,427, filed on Mar. 10, 2021, granted, now 11,142,333, issued on Oct. 12, 2021.
Application 18/114,478 is a continuation of application No. 17/524,901, filed on Nov. 12, 2021, granted, now 11,623,738, issued on Apr. 11, 2023.
Prior Publication US 2023/0234698 A1, Jul. 27, 2023
This patent is subject to a terminal disclaimer.
Int. Cl. B64C 13/50 (2006.01); B64C 13/16 (2006.01); H04W 4/40 (2018.01); H04W 72/566 (2023.01); B64C 29/00 (2006.01)
CPC B64C 13/16 (2013.01) [B64C 13/503 (2013.01); H04W 4/40 (2018.02); H04W 72/569 (2023.01); B64C 29/0033 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A system for a battery power management system for an electric aircraft, wherein the system comprises:
at least a flight component of an electric aircraft;
at least a battery, wherein the at least a battery is configured to power the at least a flight component of the electric aircraft;
at least a sensor communicatively connected to the at least a battery; and
a controller communicatively connected to the at least a sensor, wherein the controller is configured to:
receive sensor data from the at least a sensor;
identify a battery status as a function of the sensor data and a battery threshold; and
control the power from the at least a battery to the at least a flight component of the electric aircraft as a function of the battery status, wherein controlling the power from the at least a battery to the at least a flight component comprises reducing a torque to the at least a flight component.