摘要
以某自由装填式发动机为例,采用三维粘弹性有限元方法,获取不同长径比发动机药柱在高温(+60℃)和低温(-40℃)时的结构响应,探讨不同长径比自由装填式固体火箭发动机药柱在温度载荷作用下的位移、应力和应变场变化规律。研究结果表明,对自由装填式固体火箭发动机长径比对位移场的影响最为显著,长径比分别为14.5和8.0时,发动机药柱的最大轴向位移高温时减小44.1%、低温时减小43.9%。大长径比自由装填式固体火箭发动机重点关注点火具安装及药柱支撑方式设计。
A SRM with large aspect ratio free loading grain was taken as an example to investigate the displacement,stress and strain of large aspect ratio free loading solid rocket motor（SRM） grain under extreme temperature loading.The structure response in various aspect ratio of SRM was calculated by three-dimension viscoelastic finite element method.The changes of displacement,stress and strain fields in diffenent aspect ratios were obtained under high temperature（＋60℃） and low temperature（-40℃） loading.The results showed that the displacement of free loading grain was mainly affected by aspect ratio.Thus the methods of installing ignition instrument and supporting grain were very important in SRM design of large aspect ratio free loading grain.
出处
《广西科学》
CAS
2011年第2期144-147,共4页
Guangxi Sciences
基金
国防预研支撑项目(40404)
总装科研创新团队基金资助
关键词
固体火箭
发动机
温度载荷
有限元方法
solid rocket
motor
temperature loading
finite element method
