一种高能固体推进剂定压燃烧温度的确定方法

A Method for Determining the Constant Pressure Combustion Temperature of High Energy Solid Propellant

根据推进剂爆热与燃烧温度的正相关性,提出高能固体推进剂实际定压燃烧温度的确定方法;阐述并明确了爆热末态产物为准稳态非绝对稳态(自由能最小)的事实;根据高温燃烧产物降温到298 K确定了爆热末态燃烧产物,计算了推进剂理论定压爆热;测试不同样品质量的推进剂爆热,得到最大爆热值作为推进剂的实际定容爆热;通过测试定容爆热实验末状态的实际温度和压强,建立了定容爆热末状态燃气摩尔数的测试方法,获得了实际最大定压爆热。结果表明,根据爆热效率得到某高能推进剂在6.86 MPa、10 MPa、15 MPa和20 MPa下的实际能达到的最大定压燃烧温度分别为3598.02 K、3636.40 K、3675.54 K和3702.82 K,20 MPa下的温度误差最大为252.28 K,该值低于传统测温技术的误差。因此通过爆热间接确定高能固体推进剂的实际定压燃烧温度是合理的。

According to the positive correlation between propellant explosion heat and combustion temperature,a method for determining the actual constant pressure combustion temperature of high energy solid propellant was proposed.The fact that the final product of explosion heat is quasi-steady state and non-absolute steady state(minimum free energy)was expounded and clarified.According to the high temperature combustion products cooled down to 298 K,the final combustion products were determined,and the theoretical constant pressure explosion heat of the propellant was calculated.The maximum explosion heat value of propellant was obtained by testing the propellant explosion heat of different sample mass and is used as the actual constant volume explosion heat of propellant.By testing the actual temperature and pressure of the final state of the constant volume explosion heat experiment,a test method of the molar number of gas in the final state of the constant volume explosion heat experiment was established,and the actual maximum constant pressure explosion heat was obtained.The results show that the actual maximum constant pressure combustion temperatures of the high energy solid propellant at 6.86 MPa,10 MPa,15 MPa and 20 MPa,are 3598.02,3636.40,3675.54 and 3702.82 K,respectively,according to the explosion heat efficiency.The maximum temperature error at 20 MPa is 252.28 K,which is lower than the error of traditional temperature measurement technology.Therefore,it is reasonable to determine the actual constant pressure combustion temperature of high energy solid propellants indirectly through explosion heat.