Comparison between external store separation and buried store separation of fighter
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摘要:
为了研究弹体外挂投放与内埋投放的区别，利用基于Menter SST湍流模式的改进延迟分离涡模拟（IDDES）方法以及重叠网格技术，分别对亚声速和超声速来流条件下，同一弹体外挂投放和内埋投放进行了数值模拟，得到了亚声速和超声速条件下外挂投放与内埋投放弹体的下落规律。通过对比分析表明：亚声速和超声速来流条件下，内埋投放由于受舱体内强非定常流场以及舱体唇口剪切层的影响，弹体受很大的抬头力矩，弹体姿态角变化较大，投放特性劣于外挂投放。进一步研究表明：在弹射时给弹体一定的低头角速度，使弹体以低头姿态穿越剪切层，则可以大幅度降低剪切层带来的不利影响，提高内埋投放弹体分离品质。
Abstract:To analyze the difference between external store separation and buried store separation, several separation cases were simulated using the same missile under the conditions of both subsonic and supersonic inflow. Improved delayed detached eddy simulation (IDDES) method based on Menter SST turbulence model and overset mesh method were employed. Different trajectories of missile under different separation conditions were obtained. The results show that under both subsonic and supersonic inflow conditions, the buried missile is impacted by the strong unsteady flow field inside the cavity and shear layer at the cavity lip. It gives the missile big upward force moment which leads to obvious attitude angle variation. Compared with external store separation, the quality of buried store separation is much worse. If the missile is given a downward angular velocity and goes through the shear layer in pitch down angle, the side effects caused by shear layer can be substantially reduced. By using this launching method, the buried store separation quality is improved apparently.
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Key words:
- weapon separation /
- buried weapon bay /
- shear layer /
- detached eddy simulation /
- overset mesh method
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图 3 亚声速来流条件下弹体中心截面马赫数分布云图
Figure 3. Contours of Mach number distribution on central plane of missile for subsonic inflow
图 4 超声速来流条件下弹体中心截面马赫数分布云图
Figure 4. Contours of Mach number distribution on central plane of missile for supersonic inflow
图 5 亚声速来流条件下弹体竖直方向合力、速度和位移随时间变化曲线
Figure 5. Vertical force, velocity and displacement of missile versus time for subsonic inflow
图 6 亚声速来流条件下弹体俯仰力矩、俯仰角速度和俯仰角随时间变化曲线
Figure 6. Pitch moments, pitch angular velocity and pitch angle of missile versus time for subsonic inflow
图 7 亚声速来流条件下t=0.1 s外挂投放流场中心截面马赫数及弹体表面压力分布云图
Figure 7. Contours of Mach number distribution on flow field central plane and pressure distribution on missile surface for external store separation of subsonic inflow at t=0.1 s
图 8 亚声速来流条件下t=0.1 s外挂投放弹体表面不同周向位置处压力系数分布
Figure 8. Pressure coefficient distribution at different circumferential positions on missile surface for external store seperation of subsonic infolw at t=0.1 s
图 9 超声速来流条件下弹体竖直方向合力、速度和位移随时间变化曲线
Figure 9. Vertical force, velocity and displacement of missile versus time for supersonic inflow
图 10 超声速来流条件下弹体俯仰力矩、俯仰角速度和俯仰角随时间变化曲线
Figure 10. Pitch moments, pitch angular velocity and pitch angle of missile versus time for supersonic inflow
图 11 超声速来流条件下t=0.1 s外挂投放流场密度梯度等值面
Figure 11. Iso-surfaces of density gradient of external store separation for supersonic inflow at t=0.1 s
图 12 超声速来流条件下t=0.1 s外挂投放弹体表面压力分布云图及不同周向位置处压力系数分布
Figure 12. Pressure distribution contours on missile surface and pressure coefficient distribution at different circumferential positions for extemal store seperation of supersonic inflow at t=0.1 s
图 13 超声速来流条件下t=0.25 s外挂投放流场密度梯度等值面
Figure 13. Iso-surfaces of density gradient of external store separation for supersonic inflow at t=0.25 s
图 14 超声速来流条件下t=0.25 s外挂投放弹体表面压力分布云图及不同周向位置处压力系数分布
Figure 14. Pressure distribution contours on missile surface and pressure coefficient distribution at different circumferential positions for external store seperation of supersonic inflow at t=0.25 s
图 15 超声速来流条件下t=0.07 s时内埋投放流场中心截面马赫数及弹体表面压力分布云图
Figure 15. Contours of Mach number distribution on central plane and pressure distribution on missile surface for buried store seperation of supersonic inflow at t=0.07 s
图 16 超声速来流条件下t=0.07 s内埋投放弹体表面不同周向位置处压力系数分布
Figure 16. Pressure coefficient distribution at different circumferential positions on missile surface for buried store seperation of supersonic inflow at t=0.07 s
图 17 超声速来流条件下t=0.22 s时内埋投放流场中心截面马赫数及弹体表面压力分布云图
Figure 17. Contours of Mach number distribution on central plane and pressure distribution on missile surface for buried store seperation of supersonic inflow at t=0.22 s
图 18 超声速来流条件下t=0.22 s内埋投放弹体表面不同周向位置处压力系数分布
Figure 18. Pressure coefficient distribution at different circumferential positions on missile surface for buried store seperation of supersonic inflow at t=0.22 s
图 19 改进发射方式下弹体竖直方向速度、位移和俯仰角速度、俯仰角随时间变化曲线
Figure 19. Vertical velocity, displacement, pitch angular velocity and pitch angle of missile versus time for improved launch mode
表 1 计算工况
Table 1. Calculation conditions
工况 Ma 投放方式 弹射力A/N 弹射力B/N 弹射力合力/N 弹射力合力矩/(N·m) 1 0.85 内埋 -10 679 -42 717 -53 396 12 174 2 0.85 外挂 -10 679 -42 717 -53 396 12 174 3 1.35 内埋 -10 679 -42 717 -53 396 12 174 4 1.35 外挂 -10 679 -42 717 -53 396 12 174 5 0.85 内埋 -42 717 -10 679 -53 396 -4 165 6 1.35 外挂 -42 717 -10 679 -53 396 -4 165 
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表 2 投放前弹体受力对比
Table 2. Missile force comparison before launching
来流条件 投放方式 竖直方向气动力合力/N 俯仰力矩/(N·m) 亚声速 外挂 2 527 -3 393 内埋 23 -149 超声速 外挂 3 525 -7 698 内埋 -169 267
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