Methods for a venting seal for battery modules in an electric aircraft

Abstract

A method for a venting seal for battery modules in an electric aircraft is presented. The method includes sealing off, by an independent seal, a battery module of a plurality of battery modules from a vent conduit during typical operation, unsealing, by independent seal, the vent conduit as a function of a thermal event, disengaging, by a contactor of an electrical bridging device, at least a catalyst battery module from the remaining plurality of battery modules, and transferring, by the electrical bridging device, electrical energy across the remaining plurality of battery modules.

What is claimed is: 
     
         1 . A method for a venting seal for battery modules in an electric aircraft, the method comprising:
 sealing off, by an independent seal, a battery module of a plurality of battery modules from a vent conduit during typical operation;   unsealing, by the independent seal, the vent conduit as a function of a thermal event;   disengaging, by a contactor of an electrical bridging device, at least a catalyst battery module from the remaining plurality of battery modules; and   transferring, by the electrical bridging device, electrical energy across the remaining plurality of battery modules.   
     
     
         2 . The method of  claim 1 , wherein method further comprises regulating, by the contactor, electrical connection to the plurality of battery modules. 
     
     
         3 . The method of  claim 1 , wherein disengaging the at least a catalyst battery module further comprises disengaging the at least a catalyst battery as a function of a thermal threshold. 
     
     
         4 . The method of  claim 1 , wherein the method further comprises disengaging, by the contactor, the at least a catalyst battery module as a function of a disconnect assembly. 
     
     
         5 . The method of  claim 1 , wherein each battery module further comprises a module monitor unit, the method further comprises:
 detecting, by a module monitor unit, a measured battery data; and   generating a thermal datum as a function of the measured battery data.   
     
     
         6 . The method of  claim 5 , wherein the method further comprises:
 determining, by a computing device communicatively connected to the module monitor unit, a thermal event for the at least a catalyst battery module as a function of the thermal datum and a thermal threshold; and   isolating the at least a catalyst battery module as a function of the contactor.   
     
     
         7 . The method of  claim 1 , wherein independent seal further comprises a plurality of mica materials. 
     
     
         8 . The method of  claim 1 , wherein the method further comprises reestablishing, by the contactor, an electrical connection as a function of breaking off the at least a catalyst battery module. 
     
     
         9 . The method of  claim 1 , wherein the method further comprises cooling, by the vent the at least a catalyst battery cell as a function of a cooling device. 
     
     
         10 . The method of  claim 9 , wherein the cooling device further comprises a cooling fin, the method comprising dissipating, by the cooling fin heat from the at least a catalyst battery module within the vent conduit. 
     
     
         11 . The method of  claim 1 , wherein each battery module of the plurality of battery modules comprises a vent conduit. 
     
     
         12 . The method of  claim 1 , wherein the battery module comprises at least a pouch cell. 
     
     
         13 . The method of  claim 1 , wherein the independent seal comprises mica. 
     
     
         14 . The method of  claim 1 , wherein the contactor is normally closed. 
     
     
         15 . The method of  claim 1 , further comprising powering an electric aircraft using the plurality of battery modules. 
     
     
         16 . The method of  claim 15 , wherein powering the electric aircraft further comprises powering at least a propulsor using the plurality of battery modules. 
     
     
         17 . The method of  claim 16 , wherein the propulsor is a lift propulsor. 
     
     
         18 . The method of  claim 16 , wherein the propulsor is a thrust propulsor. 
     
     
         19 . The method of  claim 15 , wherein the electric aircraft is an electric vertical take-off and landing (eVTOL) aircraft. 
     
     
         20 . The method of  claim 19 , wherein the eVTOL aircraft comprises at least a lift propulsor and at least a thrust propulsor.