本SAE航空航天推荐规程（ARP）是与欧洲航空安全局（EASA）和美国联邦航空管理局（FAA）等监管机构的行业合作，旨在确定最坏情况下可信的热失控（TR）条件（释放的能量和最高温度）用于航空大型推进电池系统的设计，以定量验证TR，代替电池级RTCA DO-311A测试，禁用保护。ARP考虑了单元内TR的三个阶段，并定义了特定单元设计的两个临界温度。 这些温度是了解确定TR事件严重性所需的监测层的关键。可以使用不同的触发方法来量化作为时间函数的加热特性和由此产生的能量分布释放。结果显示，事件临界温度的三个一般阶段（见1.5）对应于石墨阳极的电池固体电解质界面（SEI）和电解质之间的反应，导致电池产生的热量而不是加速率量热计（ARC）提供的热量。电池的温度继续升高，直到隔板开始熔化。 临界温度2发生在隔板熔化和电极短路产生大量热量后，使电池温度迅速升高至377°C。这些温度是TR的关键前兆，与事件的长度和严重程度有关。了解这一关键信息对本文提出的方法至关重要。

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. Results show three general phases of the event critical temperature (see1.5) corresponding with the reaction between the cell’s solid electrolyte interphase (SEI) for graphite anodes and the electrolyte, resulting in heat generated by the cell rather than heat supplied from the accelerating rate calorimeter (ARC). The temperature of the cell continues to rise until the separator begins to melt. Critical Temperature 2 occurs after the separator melts and electrodes are shorted together to generate large amounts of heat, raising the cell temperature quickly to 377 °C. These temperatures are key precursors of TR, regarding the length and severity of an event. Understanding this key bit of information is vital to the approach presented herein.