US 12,255,343 B2
Battery pack for failure safety
Sean Richard Donovan, Richmond, VT (US); and Sam Wagner, Westford, VT (US)
Assigned to BETA AIR LLC, South Burlington, VT (US)
Filed by BETA AIR, LLC, South Burlington, VT (US)
Filed on Jun. 17, 2022, as Appl. No. 17/843,708.
Application 17/843,708 is a continuation of application No. 17/319,201, filed on May 13, 2021, granted, now 11,394,078.
Prior Publication US 2022/0393287 A1, Dec. 8, 2022
This patent is subject to a terminal disclaimer.
Int. Cl. H01M 50/242 (2021.01); H01M 10/42 (2006.01); H01M 50/204 (2021.01); H01M 50/218 (2021.01); H01M 50/227 (2021.01); H01M 50/579 (2021.01); H01M 10/653 (2014.01); H01M 50/249 (2021.01); H01M 50/298 (2021.01)
CPC H01M 50/242 (2021.01) [H01M 10/425 (2013.01); H01M 50/204 (2021.01); H01M 50/218 (2021.01); H01M 50/227 (2021.01); H01M 50/579 (2021.01); H01M 10/653 (2015.04); H01M 50/249 (2021.01); H01M 50/298 (2021.01); H01M 2220/20 (2013.01)] 17 Claims
OG exemplary drawing
 
1. An electric aircraft with a battery pack for failure safety, the electric aircraft comprising:
a fuselage having a longitudinal axis; and
a battery pack disposed within the fuselage, wherein the battery pack comprises:
a pack casing mounted to the fuselage, wherein the pack casing comprises an inner lining;
a crush zone positioned parallel to the longitudinal axis beneath a battery module, wherein the crush zone comprises an energy absorbing material configured to compress as a function of a crash force;
a battery module connection that attaches the battery module to the pack casing, and wherein the battery module connection is configured to disconnect in response to the crash force; and
a secondary crush zone that is located between a top of the battery module and an upper wall, wherein the secondary crush zone increases in thickness as the battery module is guided downward towards the crush zone;
wherein the inner lining is configured to guide the battery module towards the crush zone when the battery module connection is disconnected.