硬质隔板双脉冲发动机内流场仿真研究  

The Simulation Study of Inner Flow Field for Dual-Pulse Solid Rocket Motor with Rigrid Clapboard

作　　者：白涛涛[1] 莫展[1,2] 张跃峰[1] 房雷[1] 孙振华[1] 王虎干[1,2] 

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]航空制导武器航空科技重点实验室,河南洛阳471009

出　　处：《航空兵器》2015年第3期51-53,57,共4页Aero Weaponry

基　　金：国家自然科学基金资助项目(11402283)

摘　　要：基于脉冲隔板总开孔面积一定的情况下,研究了不同级间开孔形式对一脉冲壳体绝热层烧蚀和流动损失的影响,对带硬质隔板的双脉冲发动机进行了内流场数值计算。结果表明:隔板背壁区涡流会加重绝热层烧蚀,燃气再附着点附近烧蚀情况最严重;改变开孔形状和布局对隔板流动损失影响不大,但优化开孔倒角设计可改善隔板孔流通能力;减小隔板外缘孔径并加开隔板中心孔能有效减轻绝热层烧蚀。Studying on the influence of different interstage ports on the ablation of first-pulse＇s insulator and flow loss under the same total area of interstage ports,the numerical simulation of inner flow field is applied to dual-pulse solid rocket motor with rigrid clapboard. The results show that the backward eddys can enhance the ablation of insulator,and there is the worst ablation at reattachment point. The change of the shape and position of interstage ports have little effect on the flow loss of clapboard,but the optimal design can improve the intake capacity of interstage ports. Reducing the diameter of outer ports and increasing central port can weaken ablation effectively.

关 键 词：固体火箭发动机 双脉冲 硬质隔板 流场 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]