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This SAE Aerospace Recommended Practice (ARP) is an industrial collaboration with regulatory bodies like the European Aviation Safety Agency (EASA) and the Federal Aviation Administration (FAA) to determine the worst-case credible thermal runaway (TR) condition (energy released and maximum temperature) for the design of an aviation large propulsion battery system to quantitatively verify TR in lieu of battery level RTCA DO-311A testing with protections disabled. The ARP considers the three stages of TR within a cell and defines the two critical temperatures for a specific cell design. These temperatures are key to understanding the layers of monitoring necessary to determine the severity of a TR event. Different trigger methods can be used to quantify the heating characteristics and resultant energy profile releases as a function of time.

The proposed AIR will detail power levels required for future electric aircraft applications and detail design considerations and use cases for megawatt and extreme fast charging for electric aircraft. The AIR will provide a mapping to other industry standard that may be have relevance as well as detail areas where technology gaps / future design considerations will need to be addressed.

This AIR provides basic background information and guidance for design and development of BMS architectures to be used in RLBs for aerospace applications. This guidance applies to batteries that are considered “installed” equipment and are intended to be part of the original or supplemental type certification or military airframe qualification.

This AIR is intended to provide a basic overview of methodologies that should be utilized when undertaking the design and development of rechargeable lithium battery systems for aerospace applications. The battery system includes the battery cells, monitoring and control electronics, and battery charger as applicable. The methodologies presented herein apply to “installed” equipment which would be part of the original or supplemental type certification or military airframe qualification.

Technical requirements related to the design and minimum performance requirements of connection set of conductive charging systems used for charging electrically powered aircraft.