超音速射流对发射筒底箱的冲击流场计算

FLOW FIELD CALCULATION OF SUPERSONIC JET IMPINGEMENT ON CANISTER-LAUNCHED PLENUM

关键词:  垂直发射  发射装置  超音速射流  计算空气动力学

Key words:  Vertical launehing  Launching device  Spersonic jet  Computationalaerodynamics

摘要:

本文计算分析了导弹垂直发射系统中增压箱的内部流场.计算采用守恒型格式的FLIC方法,加入显式人工粘性,捕获了超音速射流冲击流场中的激波.计算结果表明:流场中的最大压力值在射流对称中心线上,并沿径向压力逐渐减小,这一规律与Bouslog,Stanley A.等人的实验结果相吻合.

Abstract:

In this paper the analysis calculation of jet internal flow field of the plenum in the missile vertical launching system is presented.By FLIC method with conservation from scheme and the exlicit artificial viscosity, the normal shock is captured in supersonic jet impingement flow field.The calculation results indicate that the maximun static pressure in the flow field locats at the axisymmetric center line of the jet aad decreases continuously in the radial direction, which is in accordance well with the experimental data by Bouslog, S.A.et al.