基于推进剂发火温度测试的需求,针对国军标测试方法和现有技术的发展,根据推进剂燃烧产生气体的基本性质,建立了推进剂点火温度测试方法和测试装置,测得定容燃烧器中压强突增点对应的温度为推进剂的发火温度。试验表明,以承压较高的金属容器作为试验器,增加了试验的安全性;以压强的骤增点作为推进剂样品的点燃点,可以实现点火温度的准确、一致判定,还可实现隔离试验,试验操作更人性化;温度、压强和时间的对应关系均很容易通过计算机记录,使整个试验数据的记录和采集智能化,并可重现。最后,比较了一般中能复合推进剂和含硼富燃料推进剂的发火温度。 Based on the requirements of the propellant ignition temperature test, according to the national military standard test method and the development of the existing technology, according to the basic properties of the propellant combustion gas, the ignition temperature test method and the test device of the propellant are established. The pressure corresponding to the sudden increase in pressure is the ignition temperature of the propellant. Experiments show that the higher pressure of the metal container as a test device to increase the safety of the test; the pressure surge point as the ignition point of the propellant sample, ignition temperature can be achieved accurately and consistently, but also to achieve isolation Test, test operation more humane; temperature, pressure and time of the correspondence are very easy to record by computer, so that the entire test data recording and acquisition intelligence and reproducibility. Finally, the firing temperatures of typical medium-energy composite propellants and boron-rich fuel-based propellants were compared.