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[1]孙 迪,马 亮,甘晓松,等.嵌金属丝两级药柱掺混燃烧下的内弹道计算[J].火箭推进,2019,45(03):59-63.
　SUN Di,MA Liang,GAN Xiaosong,et al.Internal ballistics calculation under mixing combustion of two-stage grain with embedded wire[J].Journal of Rocket Propulsion,2019,45(03):59-63.
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嵌金属丝两级药柱掺混燃烧下的内弹道计算

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 45 期数: 2019年03期 页码: 59-63 栏目: 研究与设计 出版日期: 2019-06-30
Title:
Internal ballistics calculation under mixing combustion of two-stage grain with embedded wire
文章编号:
1672-9374(2019)03-0059-05
作者:
孙 迪; 马 亮; 甘晓松; 郭运强
(西安航天动力技术研究所, 陕西 西安 710025)
Author(s):
SUN Di;  MA Liang;  GAN Xiaosong;  GUO Yunqiang
(Xi'an Institute of Aerospace Propulsion Technology, Xi'an 710025, China)
关键词:
固体火箭发动机;  嵌金属丝;  单室双推力;  掺混燃烧;  内弹道
Keywords:
solid rocket motor;  embedded wire;  single-chamber dual-thrust;  mixing combustion;  internal ballistics
分类号:
V435
文献标志码:
A
摘要:
为了预示嵌金属丝端燃药柱和后翼柱药柱掺混燃烧条件下单室双推力发动机的内弹道性能,首先对高压段和低压段燃烧过程中的复杂燃面变化进行分析,获得不同增速比对应的燃面与基准燃面之间的关系。然后,考虑压强转级对增速比的影响,获得过渡段二者的关系,从而实现了整个燃烧过程增速比的无级变速,进而获得燃面退移规律,据此计算了这种类型装药发动机的内弹道性能。结果表明:计算值与试验曲线吻合良好,计算误差小于5%,证明了计算模型的合理性和程序的可靠性。该方法可用于此类型发动机的内弹道计算与分析。
Abstract:
In order to predict the internal ballistics performance of a single-chamber dual-thrust motor under the mixing combustion condition of end-burning grain with embedded wire and rear wing grain, the changes of complex combustion surface during the combustion process of the high pressure stage and the low pressure stage were first analyzed.The relationship between the combustion surface and the reference combustion surface corresponding to different speed increasing ratio was obtained.Then, considering the effect of pressure transfer on the speed increasing ratio, the relationship between them in the transition stage was obtained.Thereby, its stepless variable speed during the entire combustion process was realized, and the law of burning surface regression was obtained.Accordingly, the internal ballistic performance of this type of motor was calculated.The results show that the calculated values agree well with the experimental curves, and the calculation error is less than 5%, which proves the rationality of the calculation model and the reliability of the program.The method can be used for the internal ballistic calculation and analysis of this type of motor.

参考文献/References:

[1] 于剑桥, 文仲辉, 梅跃松.战术导弹总体设计[M].北京:北京航空航天大学出版社,2010.
[2] 王文平, 余利风, 张鸿涛.单室双推力固体火箭发动机两级推力的最佳选择[J].推进技术, 1992, 13(3):16-19.
[3] 赵庆华, 王莉莉, 刘欣.固液混合火箭发动机在武器与航天领域的应用[J].火箭推进,2014,40(6):59-63. ZHAO Q H, WANG L L, LIU X.Application of hybrid rocket engine in the fields of weapons and space launching[J].Journal of Rocket Propulsion,2014,40(6):59-63.
[4] 李越森, 王谨, 利凤祥.单燃速单室双推力三维药柱的工程设计[J].推进技术, 1998,19(6):32-35.
[5] 龚建良, 樊学忠, 李宏岩, 等.单室双推力发动机装药的瞬态结构完整性分析[J].弹箭与制导学报,2016,36(6):78-82.
[6] 张有为, 王晓宏, 杨举贤.嵌金属丝端燃药柱燃烧过程的数值研究[J].推进技术,2007,28(1):4-8.
[7] 马亮, 杨德敏, 王瑾, 等.基于Pro/E的含金属丝双推力药柱燃面计算方法[J].弹箭与制导学报,2008,28(2):143-145.
[8] GOSSANT B, GODFROY F, ROBERT P.Theoretical calculus of burning rate ratio in grains with embedded metal wires[C]//24th Joint Propulsion Conference,Virigina:American Institute of Aeronautics and Astronautics, 1988.
[9] 熊文波, 刘宇, 杨劲松.某嵌金属丝药柱主要装药设计参数的影响[J].固体火箭技术,2008,31(1):38-42.
[10] 肖志平, 韩波, 张亮, 等.嵌银丝端燃装药耦合传热的内弹道数值分析[J].固体火箭技术,2016,39(2):188-193.
[11] MERRILL K.Analytical modeling of effects of wires on solid motor ballistics[J].Journal of Propulsion & Power,2015,7(3):312-321.
[12] 肖志斌, 王家鑫, 王继.嵌金属丝端燃装药方案绝热层设计方法[J].上海航天,2010,27(2):61-64.
[13] 黄麟.AP低温热分解性能对嵌金属丝推进剂燃速的影响[J].推进技术, 1986,7(6):59-65.
[14] KUBOTA N, FUJISAWA T, ICHIDAT M.Combustion processes of propellants with embedded metal wires [J].AIAA Journal, 1982,20(1):116-121.
[15] 张明, 熊波, 涂四华, 等.嵌金属丝串装双燃速药柱燃烧分析及发动机内弹道计算[J].固体火箭技术,2016,39(1):36-38.
[16] 魏然, 鲍福廷, 刘旸.嵌金属丝推进剂燃烧起始阶段增速特性研究[J].固体火箭技术,2015,38(1):55-60.

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备注/Memo

收稿日期:2018-01-14
基金项目:国家自然科学基金(11702205)
作者简介:孙 迪(1989—),女,硕士,工程师,研究领域为固体火箭发动机设计

更新日期/Last Update: 2019-06-30