摘要
为保证固体火箭发动机(Solid Rocket Motor,SRM)尾翼机构工作的可靠性,进行热防护设计以控制喷管外壁温度.基于三维有限元法对喷管工作时的温度场进行数值仿真,获取发动机喷管在温度和压力载荷联合作用下的温度场分布,结果表明原喷管的热防护不满足要求,通过对喷管各组成结构的重新设计,获得符合设计要求的喷管结构,并且发动机点火试验表明热防护设计满足要求,所得方法可为喷管的设计、试验和生产提供参考.
In order to ensure the reliability of Solid Rocket Motor （SRM） empennage machine, the heat protection design of the nozzle is carried out to control the outer wall temperature. Based on 3D finite element model, the temperature field of the nozzle is calculated under thermal loading and working pressure, and the results show that the heat protection design of original nozzle is not satisfy the requirement. Depending on the numerical results, the nozzle structure is redesigned. The appropriate structure of nozzle is achieved and validated by launching experiment. This method is available for design, experiment and manufacture of SRM nozzle.
出处
《计算机辅助工程》
2013年第A01期160-163,共4页
Computer Aided Engineering
关键词
固体火箭发动机
喷管
热防护设计
有限元法
solid rocket motor
nozzle
heat protection design
finite element method
