摘要：
A new seraph star-hole stick gun propellant with large web size was designed and prepared.The combustion characteristics of the star-hole stick gun propellants with different ratios of length to diameter(L/D=1,2,6) and different sealing layer thicknesses/gun propellant web size ratios (s/e1 =0,0.05,0.1) were studied by closed bome and combined with a large caliber gun,the experimental verification was performed.Results show that the combustion of the star-hole propellant is stable,revealing a parallel layer combustion.When the L/D increases from 1 to 6,the progressive combustion factor Pr increases by 56.8％ from 0.285 to 0.447,and the maximum pressure point delays.The L-B curves of end plane plugging propellants display obvious low initial combustion activity and hole breaking combustion.When the 5/e1 increases from 0 to 0.05 and 0.1,the initial gas generaation quantity of the star-hole stick gun propellant were reduced by about 1/2,and the hole breaking times were between the burning time needed to burn 10％ to 20％ (burned fraction) propellants.Selecting appropriate thicknesses of the plugging layers can realize the controllable regulation of the gas generation law of the propellants.When the s/e1 increases from 0 to 0.05 and 0.1,the maximum bore pressure Pm decreases by 1.39％ and 3.59％ respectively,however,the initial speed of projectile at 32.5 m from gun muzzle increases by 0.28％ and 1.4％,respectively.%设计并制备了一种新型大弧厚六翼星孔棒状发射药,利用密闭爆发器研究了不同长径比(L/D=1,2,6)、不同端面封堵层厚度/发射药弧厚比(s/e1=0,0.05,0.1)的星孔棒状发射药燃烧特性,并结合某大口径火炮进行了试验验证.结果表明,星孔棒状发射药燃烧稳定,呈平行层燃烧.长径比L/D由1增加至6时,燃烧渐增性因子Pr由0.285增加至0.447,增加了56.8％,而且最大压力点滞后.端面封堵发射药的L-B曲线显示了明显的降低起始燃烧活性和燃烧破孔特征.s/e1由0增加至0.05、0.1时,星孔棒状发射药的起始气体生成量降低了约1/2,破孔时间介于燃烧10％ ～20％(已燃份数)发射药所需燃烧时间之间.选择合适封堵层厚度,可实现发射药燃气生成规律的可控调节.s/e1由0增加至0.05、0.1时,最大膛压Pm分别下降1.3％和3.5％,而离炮口32.5 m处的弹丸初速分别提高0.28％和1.4％.
