内弹道稳定剂对中高燃速RDX-CMDB推进剂燃烧性能的影响

摘要

以一种中高燃速改性双基推进剂配方为基础配方,添加不同粒度的Al2O3及不同品种的内弹道稳定剂, 研究了6~20MPa下推进剂燃速和燃速压强指数的变化规律,并对其燃烧机理进行了分析.结果表明,添加Al2O3后推进剂的燃速降低,且随着压强的升高,燃速降低的幅度减小;不同品种的内弹道稳定剂对燃速及燃速压强指数降低和提高的幅度不同,TiO2提高了推进剂高压段的燃速,MgO几乎不影响推进剂燃速,而Al2O3、ZrO2均降低了推进剂的燃速.添加不同粒度的Al2O3后,均使燃烧表面的催化剂含量(浓度)降低,改变了催化剂的催化效率,从而导致添加芳香铅A催化剂的推进剂中Al2O3粒径分别为10μm和2.5μm时,燃速相应降低0.25mm/s和1.25mm/s.不同品种的内弹道稳定剂对燃烧表面催化剂含量、分散均匀性、催化活性的影响不同,TiO2、MgO的活性高于Al2O3和ZrO2,从而表现出添加TiO2、MgO的推进剂燃速高于添加Al2O3、ZrO2的推进剂.%The change rule of burning rate and pressure exponent of the propellant in the range of 6－20MPa was studied taking a kind of middle or high burning rate CMDB propellant as basic formula and adding Al2O3 with different particle size and different kinds of internal ballistics stabilizer.The combustion mechanism was analyzed. The results show that the burning rate decreases when Al2O3 is added. The reduction range of burning rate reduces with the pressure rising. The range of enhancement or reduction of different kinds of internal ballistics stabilizer to burning rate and pressure exponent is different. TiO2 increases the burning rate in high pressure stage and MgO does not affect the burning rate of propellant while Al2O3 and ZrO2 both decrease the burning rate of propellant. The catalyst content (or concentration) on the combustion surface decreases when different particle size of Al2O3 is added. The catalytic efficiency of catalyst is changed, which leads to 0.5mm/s and 1.25mm/s reduction on burning rate of propellant added aromatic lead A and Al2O3 with the particle size of 10μm and 2.5μm, respectively. The influence of internal ballistics stabilizer on catalyst content,dispersal uniformity and catalyst activity is different. The activity of TiO2 and MgO is higher than that added Al2O3 and ZrO2, which reflects that the burning rate of propellant added TiO2 or MgO is higher than that added Al2O3 and ZrO2.