一种新型大弧厚六翼星孔棒状发射药的燃烧特性

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/e_1=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/e_1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/e_1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32.5m处的弹丸初速分别提高0.28%和1.4%。

Combustion Characteristics of Seraph Star-hole Gun Propellant with Large Web Size

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 P_r 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 s/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 p_m 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.