US 12,304,349 B2
Systems and methods for battery management for electric aircraft batteries
Braedon Lohe, Essex Junction, VT (US); Cullen Jemison, Winooski, VT (US); Andrew Giroux, Georgia, VT (US); and Tom Hughes, South Burlington, VT (US)
Assigned to BETA Air LLC, South Burlington, VT (US)
Filed by BETA AIR, LLC, South Burlington, VT (US)
Filed on May 8, 2023, as Appl. No. 18/144,561.
Application 18/144,561 is a continuation in part of application No. 17/878,003, filed on Jul. 31, 2022, granted, now 11,705,738.
Application 17/878,003 is a continuation in part of application No. 17/528,896, filed on Nov. 17, 2021, granted, now 11,476,676, issued on Oct. 18, 2022.
Prior Publication US 2023/0302961 A1, Sep. 28, 2023
Int. Cl. B60L 58/18 (2019.01); B60L 3/00 (2019.01); B60L 53/16 (2019.01); H01M 10/46 (2006.01); B64C 29/00 (2006.01); H01M 10/42 (2006.01)
CPC B60L 58/18 (2019.02) [B60L 3/0046 (2013.01); B60L 53/16 (2019.02); H01M 10/46 (2013.01); B60L 2200/10 (2013.01); B64C 29/0008 (2013.01); H01M 2010/4271 (2013.01); H01M 2010/4278 (2013.01); H01M 2220/20 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A system for battery management for electric aircraft batteries, the system comprising:
an energy storage system configured to provide energy to an electric aircraft using a power supply connection, the energy storage system comprising:
a battery pack;
a pack monitoring unit (PMU), wherein the PMU is configured to:
compare an operating condition of the battery pack to a threshold;
send a control signal as a function of the comparison; and
create a lock out flag as a function of the comparison; and
at least a contactor, wherein the at least a contactor comprises a first contactor with a first orientation relative to the electric aircraft and a second contactor with a second orientation relative to the electric aircraft, wherein the second orientation is at a non-zero angle relative to the first orientation, each of the first contactor and the second contactor having a closed position in which power is provided through the respective contactor and an open position in which power is not provided through the respective contactor, wherein the at least a contactor is configured to:
receive the control signal generated by the PMU; and
terminate the power supply connection between the battery pack and the electric aircraft responsive to as few as one of the first contactor or the second contactor being in the respective open position; and
a bus electrically connected to the at least a contactor.