自由装填式固体火箭发动机药柱低温点火结构完整性分析  

Analysis on structural integrity of a free loading solid propellant grains under ignition loading at low temperature

作　　者：邓康清[1] 张路 庞爱民[1] 余瑞 杨玲[1] 信培培 DENG Kangqing;ZHANG Lu;PANG Aimin;YU Rui;YANG Ling;XIN Peipei(Hubei Institute of Aerospace Chemotechnology,Xiangyang 441003,China)

机构地区：[1]湖北航天化学技术研究所,襄阳441003

出　　处：《固体火箭技术》2018年第4期428-434,共7页Journal of Solid Rocket Technology

摘　　要：利用三维有限元方法,通过热-机耦合,分析一种自由装填式固体火箭发动机药柱从药柱固化降温到低温点火整个过程中发动机的温度场、总位移、等效应力和等效应变的变化情况,得到了固化降温和点火升压过程中药柱/壳体有无粘接两种情况下发动机的受力情况的不同,并根据最大应变能理论,分析了两种情况发动机药柱的结构完整性;得出了在温度和压强双重载荷下,模量、泊松比、药柱/壳体粘接高度等参数对发动机药柱结构完整性的影响规律,表明该型发动机药柱/壳体粘接高度不宜超过40 mm。By using thermal-structure interaction method of three-dimension viscoelastic finite element software,change of temperature,displacement,Von Mises stress and Von Mises strain of a propellant grain was obtained from the curing temperature of the grain to its ignition pressurization at low temperature.A great difference of the stress-strain state of the grain with and without adhesion between grain/case was found.The integrity of the grain with and without adhesion between grain/case was also analyzed according to the theory of maximum strain energy.The influence of the parameters,include modulus,Poisson ratio,adhesion height of grain/case on the structural integrity of the free loading solid rocket propellant grain subjected to temperature and pressurization load was obtained.The results show that the adhesion height of grain/case should be no more than 40 mm.

关 键 词：固体火箭发动机 自由装填药柱 结构完整性 热-机耦合 仿真 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]