[1]白龙,李月洁,周海霞,等.高低温对推进剂装药抗高过载能力影响研究[J].固体火箭技术,2019,42(03):372-376.[doi:10.7673/j.issn.1006-2793.2019.03.018]
 BAI Long,LI Yuejie,ZHOU Haixia,et al.Research on the influence of temperature on theantioverload performance of propellant grain[J].Journal of Solid Rocket Technology,2019,42(03):372-376.[doi:10.7673/j.issn.1006-2793.2019.03.018]
点击复制

高低温对推进剂装药抗高过载能力影响研究

参考文献/References:

[1]马伟华.高过载下固体推进剂装药结构完整性试验与仿真分析[D].北京:北京理工大学,2018.MA Weihua.Experimental and simulational analyses of structural integrity of solid propellant grain under high overload[D].Beijing:Beijing Institute of Technology,2018.[2]利凤祥,刘中兵,李越森,等.药柱结构对其抗轴向过载能力的影响[J].推进技术,2004,25(2):165-169.LI Fengxiang,LIU Zhongbing,LI Yuesen,et al.Effects of the structure of grains on their capability of resisting axial acceleration load[J].Journal of Propulsion Technology,2004,25(2):165-169.[3]武智慧,钱建平,刘荣忠,等.实际发射工况下底排药柱结构完整性的模拟计算[J].火炸药学报,2014,37(3):60-65.WU Zhihui,QIAN Jianping,LIU Rongzhong,et al.Simulation calculation on structure integrity of base bleed grains in launching process[J].Chinese Journal of Explosives & Propellants,2014,37(3):60-65.[4]Sun C,Xu J,Chen X,et al.Strain rate and temperature dependence of the compressive behavior of a composite modified double-base propellant[J].Mechanics of Materials,2015,89:35-46.[5]肖志平,张泽远,邢国强.星型药柱固化降温瞬态热力耦合分析[J].航空兵器,2014(1):40-43.XIAO Zhiping,ZHANG Zeyuan,XING Guoqiang.Thermo-Mechanical Coupling Analysis of Star Grain in the Course of Cooling Process After Curing[J].Aero Weaponry,2014(1):40-43. [6]Yclmaz O,Kuran B,zgen G O.Reliability assessment of solid-propellant rocket motors under storage and transportation loads[J].Journal of Spacecraft and Rockets,2017,54(6):1-11.[7]王海清,隋欣,丁娜仁花,等.某型炮射导弹膛内运动时期药柱的应力应变分析[J].弹箭与制导学报,2017,37(3):49-54.WANG Haiqing SUI Xin,DING Narenhua,et al.Stress and strain analysis of a gun-launched solid rocket motor propellant grain during the launching process[J].Journal of Projectiles,Rockets,Missiles and Guidance,2017,37(3):49-54.

相似文献/References:

[1]李恩奇,雷勇军,袁端才,等.某固体火箭发动机药柱的动力学分析 [J].固体火箭技术,2007,(6):486.
[2]段红珍,蔺向阳,徐磊,等.纳米Co粉在NC基高分子体系中的分散性[J].固体火箭技术,2007,(4):335.
[3]宋小兰,李凤生,张景林,等.粒度和形貌及粒度分布对RDX安全和热分解性能的影响[J].固体火箭技术,2008,(2):168.
[4]王永杰,鲁建英,陈林泉,等.固体火箭发动机撞击靶板安全性数值分析[J].固体火箭技术,2009,(03):274.
[5]宋小兰,李凤生,张景林,等.纳米AP/Fe2O3复合氧化剂的制备及其机械感度和热分解特性[J].固体火箭技术,2009,(03):306.
[6]菅晓霞,肖乐勤,黄求安,等.组分迁移特性表征方法的探索[J].固体火箭技术,2009,(03):314.
[7]王英红,张放利,闫松,等.推进剂发火温度测定方法的改进[J].固体火箭技术,2011,(05):663.
[8]邸克,杨月诚,张昆鹏.固体推进剂/衬层界面裂纹的界面层模型有限元分析[J].固体火箭技术,2012,(06):751.
[9]韩波,鞠玉涛,周长省.HTPB推进剂粘聚断裂研究[J].固体火箭技术,2013,(01):89.
[10]吴俊峰,李新田,田辉,等.固液火箭发动机推进剂组合能量特性分析[J].固体火箭技术,2013,(02):225.

更新日期/Last Update: 2019-07-11
PDF下载 分享