旁泄间隙对燃气弹射内弹道特性影响

赵加鹏; 张磊; 佘湖清; 郭晋兵

doi:10.13224/j.cnki.jasp.20210389

旁泄间隙对燃气弹射内弹道特性影响

doi: 10.13224/j.cnki.jasp.20210389

中国船舶集团有限公司第七一〇研究所，湖北宜昌 443003

详细信息

作者简介:
赵加鹏（1981-），男，研究员，博士，主要从事水下发射总体技术研究

中图分类号: V553.1；TJ768
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- 被引次数: 0
出版历程
- 收稿日期: 2021-07-24
- 网络出版日期: 2023-08-16

Influence of bypass clearance on gas-ejection internal ballistic characteristics

710 Research Institute， China State Shipbuilding Corporation Limited，Yichang Hubei 443003，China

摘要

摘要:
为了研究旁泄间隙（发射筒与隔板的间隙）对燃气弹射内外流场及内弹道特性参数的影响，采用Realizable$ \kappa {\text{-}} \varepsilon $湍流模型，结合动态分层动网格及用户自定义函数（user defined function，UDF）技术，对燃气弹射过程进行了数值模拟，分析了旁泄间隙大小对燃气弹射性能的影响，并进行了地面发射试验。通过与试验数据对比，验证了燃气弹射仿真模型的有效性。仿真结果表明，在旁泄间隙出口附近形成明显漩涡，旁泄间隙的增大会导致低压室压力与加速度峰值减小，并使试验弹出筒时间延长、出筒速度降低，但变化趋势呈现非线性特征。旁泄间隙从2 mm增大到6 mm时，出筒时间延长7.7%，出筒速度降低16.3%，可认为在此范围内旁泄间隙的影响幅度相对较小；但此后旁泄间隙的影响会显著增强，当旁泄间隙从6 mm增大到8 mm时，出筒时间延长20%，出筒速度降低35.8%，当旁泄间隙增大到10 mm时，试验弹到筒口速度甚至降为0 m/s。本文研究结果为燃气弹射装置的设计与优化提供参考借鉴。
- 燃气弹射 /
- 旁泄间隙 /
- 内外流场 /
- 动态分层技术 /
- 内弹道
Abstract:
In order to study the influence of bypass clearance (the clearance between the launcher and the Missile pallet) on the flow fields and characteristic parameters of the gas ejection, realizable turbulence model, dynamic layered dynamic grid and user-defined function technology were used to simulate the process of gas ejection. And the influence of the bypass clearance size on the performance of gas ejection was analyzed. The ground launch test was carried out. Compared with the test data, the effectiveness of the gas ejection simulation model was verified. The simulation results showed that, obvious vortices were formed near the exit of the clearance. As the clearance increased, the pressure in the low-pressure chamber decreased, the acceleration peak decreased, the exit time of missile prolonged and the exit velocity decreased. When the clearance increased from 2 mm to 6 mm, the exit time was only extended by 7.7%, and the exit speed was reduced by 16.3%, the change of exit time and velocity was relatively small within this clearance range. When the clearance increased from 6 mm to 8 mm, the exit time was extended by 20%, and the exit velocity was reduced by 35.8%. When the clearance increased to 10 mm, the ejection of missile failed, and the exit time and velocity changed significantly within this clearance range. The research results provide an important guidance for the optimization design of gas ejection device.
- gas-ejection /
- bypass clearance /
- internal and external flow fields /
- dynamic layering technology /
- interior ballistic

HTML

图 1 燃气弹射装置示意图

Figure 1. Schematic diagram of gas-ejection device

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图 2 燃气弹射简化模型示意图

Figure 2. Schematic diagram of simplified model of gas-ejection

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图 3 计算模型及网格

Figure 3. Calculation model and mesh

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图 4 试验弹发射过程的时序图

Figure 4. Sequence diagram of launching process of test missile

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图 5 燃气发生器腔内压力

Figure 5. Pressure in the gas generator chamber

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图 6 计算值与试验结果的比较

Figure 6. Comparison of calculated and test values

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图 7 筒底和旁泄出口速度云图及流线图

Figure 7. Velocity distribution in the bottom and at the gap outlet

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图 8 不同时刻温度场分布云图及速度流线图

Figure 8. Contours of gas temperature and velocity streamlines at different moments

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图 9 试验弹位移

Figure 9. Displacement of test missile

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图 10 试验弹加速度

Figure 10. Acceleration of test missile

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图 11 试验弹速度

Figure 11. Velocity of test missile

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图 12 试验弹出筒速度

Figure 12. Exit velocity of test missile

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表 1 弹射系统的物理参数

Table 1. Physical parameters of ejection system

参数数值

m/kg 2000
D/m 0.825
L/m 7.9

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