固体火箭发动机点火过程力学响应数值仿真

Numerical Simulation of Mechanical Response of Ignition Transient on Solid Rocket Motor

针对发动机结构研究,在点火瞬态过程中的内压载荷与轴向过载共同作用下,使发动机结构安全性受到影响,为确保安全,推进剂药柱采用线性粘弹性模型,对固体火箭发动机进行了三维有限元分析。通过CAE软件的参数化设计语言编程,实现不同的轴向过载情况与改变药柱的局部结构,分别对发动机在点火瞬态过程中的应力、应变及位移场进行数值仿真,并明确以上各因素对药柱结构完整性的影响,为发动机的结构可靠性分析与寿命预估提供了一定的参考。结果表明,开缝式包覆层能有效地降低头部应力集中。

The three-dimensional finite element analysis of the solid rocket motor is operated under internal pressure loading and axial acceleration loading of ignition transient,with the grain using the linear viscoelastic model.Different axial acceleration loading and partial changing the structure of the grain are realized via the program of parametric design language of CAE software.The numerical simulations of the stress,strain and displacement fields of the motor on ignition transient are calculated respectively,and the influence on structure integrity for grain is discussed.The reference is available for the structure reliability analysis and life prediction of acceleration solid grains.The results show that gapping-style cladding of grain is able to lessen the stress intensity of its forehead effectively.