含能材料燃速测试评价方法及其影响因素研究

菜单

摘要为了研究分析测试条件对发射药燃速测试结果的影响关系，以高能硝胺发射药为研究对象，采用密闭爆发器燃烧实验和数据处理分析方法，研究了不同药型结构、不同装填密度和不同点火强度与发射药燃速测试结果的关系，采用高压中止实验研究了18/1发射药的侵蚀燃烧与内孔长径比的关系。研究结果表明：63835

（1）药型结构对燃速测试结果影响较大。随着内孔长径比的增大，正比式燃速系数u1增大，燃速压力指数n减小，指数式燃速系数A相应地增大；在内孔长径比相同的条件下，随着发射药内孔数量的增加，正比式燃速系数u1减小，燃速压力指数n减小，指数式燃速系数A相应地增大。考虑到侵蚀燃烧和燃烧稳定性的影响，实验选用40mm的18/1发射药进行燃速的测试较好。

（2）装填密度对燃速测试结果影响较大，18/1发射药正比式燃速系数u1随着装填密度的增加而减小；6/19发射药的燃速压力指数n随着装填密度的增加而增大，指数式燃速系数A随着装填密度的增加而减小。考虑到测试样品燃烧的稳定性，实验选用0.20 g·cm-3装填密度进行燃速的测试较好。

（3）点火强度的大小对燃速测试结果有一定的影响，18/1和18/19发射药的正比式燃速系数u1随点火药量的增大而减小，目前的理论研究无法对其进行解释，实验现象有待进一步验证。

（4）发射药内孔长径比较大时，其燃烧与平行层燃烧规律产生偏差，并且侵蚀燃烧随内孔长径比的增大而增大。

毕业论文关键词发射药燃速测试药型结构装填密度点火强度

毕业设计说明书（论文）外文摘要

Title The burning rate test evaluation method of energetic materials and the research of its influence factors

Abstract In order to study the effect of test condition of propellant on burning rate test results, with high-energy nitroamine propellant as the research object, using the closed bomb experiments and data processing analysis method, studied the relation between different charge structure, different loading density, different ignition intensity and propellant burning rate test results. Using high pressure termination experimental study on the relation between erosive burning and the inner hole aspect ratio of 18/1 propellant . The results show that:

(1) Charge structure has great influence on the burning rate test results, proportional propellant burning rate coefficient u1 with the inner hole aspect ratio increased, the burning rate pressure exponent n with the inner hole aspect ratio decreased, index of burning rate coefficient A with the inner hole aspect ratio increased. Considering the erosive burning and combustion stability, it would be better to use the 40mm 18/1 propellant for the test.

(2) Loading density has great influence on the burning rate test results, 18/1 proportional propellant burning rate coefficient u1 decreases with increase of loading density; 6/19 propellant burning rate pressure exponent of n increases with the loading density, index of burning rate coefficient A decreases with increase of loading density. Considering the combustion stability of the sample, it would be better to choose the loading density of 0.20 g·cm-3.

(3) Ignition intensity size on the burning rate of the test results have a certain influence, the type of 18/1 and 18/19 proportional propellant burning rate coefficient u1 decreases with the ignition charge increases. Does not account for current theories research, experimental phenomena needs further validation.

(4) Propellant inner hole aspect ratio is larger, the regular pattern of combustion and parallel layer combustion produces deviation, and with the inner hole aspect ratio increases, the erosive burning increases.