内弹道稳定剂对中高燃速RDX-CMDB推进剂燃烧性能的影响

发布时间：2019-04-16 00:08

【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Al_2O_3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Al_2O_3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Al_2O_3、ZrO_2均降低了推进剂的燃速。添加不同粒度的Al_2O_3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Al_2O_3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,TiO_2、MgO的活性高于Al_2O_3和ZrO_2,从而表现出添加TiO_2、MgO的推进剂燃速高于添加Al_2O_3、ZrO_2的推进剂。
[Abstract]:Based on a medium and high burning rate modified double base propellant formulation, adding different particle size of Al_2O_3 and different kinds of internal ballistic stabilizers, the change rule of burning rate and burning rate pressure index of propellant under 6~20MPa was studied. The combustion mechanism was analyzed. The results show that the burning rate of propellant decreases with the addition of Al_2O_3, and the decrease of burning rate decreases with the increase of pressure. The burning rate and burning rate pressure index of different kinds of internal ballistic stabilizers are different. TiO2 increases the burning rate of propellant at high pressure. MgO has little effect on the burning rate of propellant, while Al_2O_3, has little effect on the burning rate of propellant. The burning rate of propellant was reduced by ZrO_2. After adding different particle size of Al_2O_3, the content (concentration) of catalyst on combustion surface was decreased, and the catalytic efficiency of catalyst was changed. As a result, when the particle size of Al_2O_3 is 10 渭 m and 2.5 渭 m respectively, the burning rate of propellant with aromatic lead A catalyst decreases 0.25mm/s and 1.25 mm respectively. The effects of different kinds of internal ballistic stabilizers on catalyst content, dispersion uniformity and catalytic activity of combustion surface were different. The activity of TiO_2,MgO was higher than that of Al_2O_3 and ZrO_2, which showed that TiO_2, was added to the combustion surface. The burning rate of MgO propellant is higher than that of Al_2O_3,ZrO_2.
【作者单位】：西安近代化学研究所;宜宾北方川安化工有限公司;
【基金】：国防科工局基础产品创新科研项目(SJQC1510)
【分类号】：V512

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