一种高精度水下武器发射内弹道计算方法

杨春; 李开福; 陈炜彬; 李录甜; 李银龙

doi:10.11993/j.issn.2096-3920.2023-0123

一种高精度水下武器发射内弹道计算方法

doi: 10.11993/j.issn.2096-3920.2023-0123

1.
中国船舶集团有限公司第七〇五研究所, 云南昆明, 650101
2.
昆明欧迈科技有限公司, 云南昆明, 650106

详细信息

作者简介:
杨春：杨　春(1996-), 男, 硕士, 工程师, 主要研究方向为发射装置技术

通讯作者:
李开福(1987-), 男, 硕士, 高级工程师, 主要研究方向为发射技术

中图分类号: TJ630.32; U674
计量
- 文章访问数: 150
- HTML全文浏览量: 48
- PDF下载量: 10
- 被引次数: 0
出版历程
- 收稿日期: 2023-10-12
- 修回日期: 2024-06-02
- 录用日期: 2024-06-17
- 网络出版日期: 2024-08-13

A High-Precision Calculation Method for Internal Trajectory of Underwater Weapon Launch

1.
The 705 Research Institute, China State Shipbuilding Corporation Limited, Kunming 650101, China
2.
Kunming Optics-Mechanics-Electricity Technology Corporation Limited, Kunming 650106, China

摘要

摘要: 针对水下武器气动发射系统，提出了一种高精度内弹道计算方法。该方法将高精度理论推导和计算流体力学滑移技术相耦合, 对发射过程中的高压气体域运用四阶Runge-Kutta法进行求解, 对水域部分采用滑移网格进行单自由度武器发射仿真, 从而实现对内弹道的高精度计算, 可弥补理论计算误差偏大和流体仿真成本高的缺陷。对比试验数据可知, 通过该方法得到的武器出管速度平均误差为5.6%, 发射气瓶截止压力平均误差为4.0%，证明了该方法的准确性。
- 水下武器; 计算流体力学 /
- 内弹道 /
- 气动发射系统
Abstract: A high-precision calculation method for internal trajectory was proposed for the pneumatic launch system of underwater weapons. The method combined high-precision theoretical derivation with computational fluid mechanics slip technique and used the fourth-order Runge-Kutta method to solve the high-pressure gas domain during the launch process. The sliding grid was used to simulate the single degree of freedom weapon launch in the water area, so as to realize the high-precision calculation of internal trajectory, which could make up for the defects of large theoretical calculation error and high cost of fluid simulation. Through comparison with the test data, it can be seen that the average error of the discharge velocity of the weapon and the average error of the cutoff pressure of the posterior cavity obtained by this method are 5.6% and 4.0%, which proves the accuracy of this method.
- underwater weapon; computational fluid mechanics /
- internal trajectory /
- pneumatic launch system

HTML全文

图 1 气动不平衡式发射装置原理图

Figure 1. Schematic diagram of pneumatic unbalanced launch device

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图 2 气动不平衡式发射装置模型

Figure 2. Model of pneumatic unbalanced launch device

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图 3 模型网格划分

Figure 3. Model grid division

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图 4 武器非结构网格加密

Figure 4. Unstructured mesh refinement of weapons

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图 5 网格剖视图

Figure 5. Sectional view of mesh

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图 6 发射活塞运动计算流程

Figure 6. Calculation process for the motion of the launch piston

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图 7 CFD计算与理论计算耦合过程

Figure 7. Coupling process of CFD and theoretical calculation

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图 8 气瓶压力随时间变化曲线

Figure 8. Curves of gas cylinder pressure versus time

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图 9 气瓶质量流量随时间变化曲线

Figure 9. Curves of gas cylinder mass flow versus time

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图 10 后腔气压随时间变化曲线

Figure 10. Curves of rear chamber air pressure versus time

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图 11 网格无关性验证

Figure 11. Verification of grid independence

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图 12 发射过程不同时刻速度云图

Figure 12. Velocity contour of weapon for different moments

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图 13 不同深度下武器速度

Figure 13. The velocity of weapon in different deeps

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表 1 计算结果与试验对比

Table 1. Comparison between calculation results and experiments

发射深度/m	发射指标	理论-流体耦合计算值	试验值	误差/%
50	截止气压/MPa	7.15	6.8	5.1
50	武器速度/(m/s)	9.65	10.0	3.5
75	截止气压/MPa	6.83	6.7	1.9
75	武器速度/(m/s)	8.78	8.3	5.8
100	截止气压/MPa	6.56	6.2	5.8
100	武器速度/(m/s)	8.96	8.5	5.4
125	截止气压/MPa	6.70	6.5	3.1
125	武器速度/(m/s)	9.04	8.6	3.5
150	截止气压/MPa	6.66	6.4	4.1
150	武器速度/(m/s)	10.23	9.7	5.5

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参考文献(7)

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