固体发动机喷管热结构耦合数值仿真研究  

Study of numerical analysis upon thermal structure of nozzlefor solid rocket motor

作　　者：龚建良[1] GONG Jianliang(Xi’an Modern Chemistry Research Institute,Xi’an 710065,China)

机构地区：[1]西安近代化学研究所,西安710065

出　　处：《兵器装备工程学报》2024年第5期145-150,共6页Journal of Ordnance Equipment Engineering

摘　　要：针对在热载荷与内压联合作用下,固体火箭发动机潜入式喷管的热结构耦合数值仿真问题,采用流体仿真软件与结构计算软件,展开了数值模拟。在流体仿真软件中,计算了潜入式喷管工作过程的内部稳态流场,提取了高温燃气流动参数与固体壁面对流换热系数。在有限元结构计算平台内,编写了非均布壁面压力载荷与非均布对流换热系数子程序,耦合求解了喷管热结构耦合问题,获取了热防护材料内部温度场与应力场分布。研究表明,热载荷是引起喉衬应力的主要原因。喉衬环向压应力与拉应力随时间呈现先增大后减小的过程。经地面喷管结构完整性热试车试验验证,该热结构耦合数值仿真方法可用于喷管结构完整性与安全性分析,为喷管结构设计提供合理指导。The coupling thermal and mechanical effect on submerged nozzles is important in the design of modern rockets upon thermal loading and aerodynamic pressure.A simulation of the subroutine of non-uniform pressure and non-uniform heat transfer coefficient was conducted by CFD and FEM software to study the thermo-structural response of a submerged nozzle.Both the aerodynamic parameters and heat coefficients were obtained through analyzing the flow field.It was found that the thermal loading had an important influence on stress of throat insert for the solid rocket motor(SRM),both the hoop compressive stress and the hoop tensile stress increase at first and then decrease with the increase of time for the throat insert.The experimental results of the ground hot firing test of SRM with submerged nozzle showed that:the present method is reasonable for nozzle structural integrity and safety analysis,which can be applied to study the thermo-structural response of submerged nozzle for SRM.

关 键 词：固体火箭发动机 潜入式喷管 有限元方法 热结构 热应力 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]