利用初始冲击波超压完成前后盖开启过程的贮运发射箱已得到广泛应用。为研究含尾喷管堵盖的冲击波超压形成过程及对后易碎盖的作用效果，应用有限元方法并结合动网格技术建立了导弹点火后堵盖的运动模型，并通过实验方法对仿真结果进行了验证。结合计算结果可清晰地看到尾焰流场的形成过程，并得到了冲击波超压在后易碎盖表面的随时间变化曲线。研究表明：受堵盖的影响，冲击波超压首先形成并冲击后易碎盖，燃气由堵盖的边缘向中心汇聚形成主流，在对后易碎盖的冲击时间和作用位置上与冲击波作用有明显的不同；后易碎盖主要受到冲击波超压作用实现碎裂变形，在堵盖运动的投影区域首先达到最大受力，瞬时峰值达5×105 Pa.
Abstract
The overpressure of shock wave is widely used in opening the launching canister. In order to study the formation of shock wave and its effect on the fragile lid with a nozzle closure, a simulation model is established by using a numerical method, in which a dynamic mesh technique is used to update the meshes of flow field. The simulation results are verified with the experimental results. The formation process of jet flow is shown clearly and the changing curves of the overpressure on the back lid with time are obtained from the analysis results. The research results show that the overpressure of shock wave forms on the nozzle closure and then impact the fragile lid. The gas converges from the edge of nozzle closure to the center to form a mainstream. The effects of the mainstream and the shock wave on the back fragile lid are obviously different in impact time and position. The back fragile lid is brittlely deformed under the action of overpressure of shock wave. In the projection area of the nozzle closure, the instantaneous peak first reaches to the maximum value of 5×105 Pa.
关键词
兵器科学与技术 /
尾喷管堵盖 /
冲击波 /
易碎盖 /
数值仿真
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Key words
ordnance science and technology /
nozzle closure /
shock wave /
fragile lid /
numerical simulation
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