高压气体驱动二级轻气炮发射过程的数值模拟方法及应用

陈履坦; 何起光; 陈小伟

doi:10.11883/bzycj-2022-0054

高压气体驱动二级轻气炮发射过程的数值模拟方法及应用

doi: 10.11883/bzycj-2022-0054

陈履坦^1,,
何起光¹,
陈小伟^{2, 3, ,}

1.
北京理工大学机电学院，北京 100081
2.
北京理工大学爆炸科学与技术国家重点实验室，北京 100081
3.
北京理工大学前沿交叉科学研究院，北京 100081

基金项目: 国家自然科学基金（11627901）

详细信息

作者简介:
陈履坦（1996－　），男，博士研究生，3120205137@bit.edu.cn

通讯作者:
陈小伟（1967－　），男，博士，教授，chenxiaoweintu@bit.edu.cn

中图分类号: O313.4
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- PDF下载量: 148
- 被引次数: 0
出版历程
- 收稿日期: 2022-02-17
- 修回日期: 2022-08-30
- 网络出版日期: 2022-10-27
- 刊出日期: 2022-12-08

Numerical modeling on the launch process of a two-stage light gas gun using high-pressure gas as the driving source

CHEN Lütan^1
,,
HE Qiguang¹,
CHEN Xiaowei^{2, 3
, ,}

1.
School of Mechatronic Engineering, Beijing Institute of Technology, Beijing 100081, China
2.
State Key Laboratory of Explosion Science and Technology, Beijing Institute of Technology, Beijing 100081, China
3.
Advanced Research Institute of Multidisciplinary Science, Beijing Institute of Technology, Beijing 100081, China

摘要

摘要: 二级轻气炮是一种常见的超高速发射装置，多年来其数值研究大多采用简化一维模型，鲜有三维有限元模型。以14 mm口径高压气体驱动二级轻气炮为研究对象，采用耦合欧拉-拉格朗日（coupled Eulerian-Lagrangian, CEL）算法，根据膜片破裂与否，将二级轻气炮模型解耦为2个分级三维数值模型。为确定实验难以测得的参数（材料摩擦因数和膜片破膜压力），设计正交试验，拟合确定活塞与泵管间摩擦因数为0.82，弹丸与发射管摩擦因数为0.30和膜片破膜压力为11.73 MPa。正交结果表明，摩擦因数对计算结果影响较大，在高压气体驱动二级轻气炮的计算中不应忽略。通过上述方法建立数字化高压气体驱动二级轻气炮，完整复现气炮发射过程，计算的弹丸终速与实验结果吻合度高。选取验证工况详细分析了气炮发射过程内流场变化，并呈现关键时刻的压力云图。该气炮简化方法、分级思想和关键参数确认方法可推广应用于固体发射药驱动、爆轰驱动等其他驱动形式的二级/多级轻气炮。
- 二级轻气炮 /
- 正交试验 /
- 分级三维数值模型 /
- 耦合欧拉-拉格朗日算法
Abstract: A two-stage light gas gun is a common hypervelocity launcher. Over the years, most researchers adopted simplified one-dimensional models and rarely used three-dimensional finite element models. This paper used the coupled Eulerian-Lagrangian algorithm to calculate the gas-driven hydrodynamic field in a 14-mm-caliber two-stage light gas gun. The two-stage light gas gun was decoupled into two three-dimensional numerical models according to whether the diaphragm was broken. A three-factor four-level orthogonal test was carried out to get the material friction coefficient and the broken diaphragm pressure, which were difficult to measure in experiments. The ordinary least square method was used to calculate the orthogonal test data. The friction coefficient between the piston and the pump tube was 0.82, the friction coefficient between the projectile and the launch tube was 0.30, and the broken diaphragm pressure was 11.73 MPa. The orthogonal test showed that the friction coefficient and the broken diaphragm pressure significantly influenced the calculation results. The friction could not be ignored in calculating the launch process of the two-stage light gas gun. So keeping the gun body clean was necessary to improve the projectile velocity. The numerical model for the two-stage light gas gun was established based on the method mentioned above, which completely reproduced the launch process of the gas gun, and visually represented the change of the flow field. The velocities of the projectile were numerically obtained by the established model, which were highly consistent with the experimental results. In addition, the verification condition was selected to analyze the change of the flow field, and the pressure nephograms at the critical moments were given. It should be noted that the velocity range of the projectile was 3－5 km/s. The method is fully applicable for the projectile velocity below 3 km/s and is generalizable for the higher projectile velocity. The gas gun simplification method, grading idea and key parameter confirmation method can be extended to other two/multi-stage light-gas guns, such as solid propellant driven and detonation driven.
- two-stage light gas gun /
- orthogonal test /
- numerical model /
- coupled Eulerian-Lagrangian algorithm

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图 1 14 mm口径高压气体驱动二级轻气炮示意图

Figure 1. Schematics of a 14-mm-caliber two-stage light gas gun based on high-pressure gas driving

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图 2 14 mm口径高压气体驱动二级轻气炮二维模型

Figure 2. Two-dimensional models for the 14-mm-caliber two-stage light gas gun

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图 3 气炮模型

Figure 3. Light-gas gun models

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图 4 活塞模型

Figure 4. The piston model

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图 5 弹丸模型

Figure 5. The projectile model

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图 6 0～7.50 ms活塞前后压力云图

Figure 6. Pressure nephograms around the piston at 0−7.50 ms

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图 7 泵管和锥段35.30～37.70 ms压力云图

Figure 7. Pressure nephograms in the pump tube and the tapered section at 35.30−37.70 ms

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图 8 活塞的速度/位移-时间曲线

Figure 8. Velocity- and displacement-time curves of the piston

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图 9 膜片处的压力-时间曲线

Figure 9. Pressure-time curve at the diaphragm

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图 10 二级模型0～1.95 ms的压力云图

Figure 10. Pressure nephograms of the second-stage model at 0−1.95 ms

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图 11 活塞的速度和位移时间里程曲线

Figure 11. Velocity- and displacement-time curves of the piston

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图 12 弹丸尾部2.20～3.20 ms的压力云图

Figure 12. Pressure nephograms at the tail of the projectile at 2.20－3.20 ms

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图 13 弹丸时间-速度/弹尾压力曲线

Figure 13. Pressure-time curve at the tail of the projectile and velocity-time curve of the projectile

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图 14 等分均布观测点和弹丸弹尾的压力变化对比

Figure 14. Comparison of pressure changes between the evenly-distributed observation points and the projectile tail

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图 15 0～39.10 ms锥段气体温度曲线

Figure 15. Temperature-time curve of the gas in the tapered section at 0−39.10 ms

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图 16 36.90～37.70 ms锥段瞬态温度场

Figure 16. Transient temperature fields in the tapered section at 36.90−37.70 ms

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表 1 14 mm口径高压气体驱动二级轻气炮几何参数

Table 1. The geometrical parameters of the 14-mm-caliber two-stage light-gas gun

部件	长度/mm	内径/mm	入锥角度/(°)
高压气室	720	90
泵管	11820	60
发射管	6600	14
锥段	320	14～60	4.5

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表 2 14 mm高压气体驱动二级轻气炮的实验参数

Table 2. Experimental parameters of the 14-mm-caliber two-stage light-gas gun

实验	高压气室初始压力/MPa	泵管初始压力/MPa	活塞质量/g	弹丸质量/g	膜片厚度/mm	弹丸终速/（m·s⁻¹）
1	15.7	0.041	733	1.51	0.4	3 846
2	22.1	0.045	733	1.55	0.4	4 155
3	21.7	0.047	733	2.43	0.4	3 571

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表 3 Johnson-Cook模型材料参数^[20-21]

Table 3. Material parameters for the Johnson-Cook model^[20-21]

材料	密度/（kg·m⁻³）	泊松比	杨氏模量/GPa	初始屈服应力/MPa	硬化常数/MPa	应变硬化指数	温度系数	熔化温度/K
4340不锈钢	7900	0.33	200	280	802.5	0.622	1	1673
铝	2790	0.33	73.1	369	684	0.34	1.7	1000

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表 4 气体材料参数

Table 4. Material parameters for gases

气体	R/（J·（mol·K）⁻¹）	环境压力/Pa	比定容热容/（J·（kg·K）⁻¹）
氦气	2077	0	3116
氮气	298.3	0	743

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表 5 正交试验的因素及水平

Table 5. Factors and levels of orthogonal tests

水平	μ₁	μ₂	p/MPa
1	0.3	0.1	10
2	0.5	0.2	20
3	0.7	0.3	30
4	0.9	0.4	40

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表 6 正交工况及弹丸终速

Table 6. The orthogonal cases as well as the final velocities of projectiles

计算工况	μ₁	μ₂	p/MPa	v/（m·s⁻¹）			计算工况	μ₁	μ₂	p/MPa	v/（m·s⁻¹）
计算工况	μ₁	μ₂	p/MPa	试验1	试验2	试验3	计算工况	μ₁	μ₂	p/MPa	试验1	试验2	试验3
1	0.3	0.1	10	4517	4835	4183	9	0.7	0.1	30	3645	4428	4597
2	0.3	0.2	20	4751	4959	4243	10	0.7	0.2	40	4230	4279	4622
3	0.3	0.3	30	4797	5194	4142	11	0.7	0.3	10	3568	4036	3396
4	0.3	0.4	40	4782	5039	4180	12	0.7	0.4	20	3469	4019	3264
5	0.5	0.1	20	4453	4396	4184	13	0.9	0.1	40	4581	4755	3842
6	0.5	0.2	10	4081	4290	3611	14	0.9	0.2	30	4412	4550	4030
7	0.5	0.3	40	3997	4375	3887	15	0.9	0.3	20	4232	4451	3786
8	0.5	0.4	30	4197	4029	3720	16	0.9	0.4	10	3840	3843	3742

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表 7 正交试验结果分析

Table 7. Analysis of orthogonal test results

v/（m·s⁻¹）	试验 1			试验 2			试验 3
v/（m·s⁻¹）	μ₁	μ₂	p	μ₁	μ₂	p	μ₁	μ₂	p
k₁	4711.75	4299.00	4001.50	5006.75	4603.50	4251.00	4187.00	4201.50	3688.50
k₂	4182.00	4368.50	4226.25	4272.50	4519.50	4456.25	3850.50	4126.50	3869.25
k₃	3728.00	4148.50	4262.75	4190.50	4514.00	4550.25	3969.75	3802.75	4122.25
k₄	4266.25	4072.00	4397.50	4399.75	4232.50	4384.00	3805.50	3682.00	4132.75
R	983.75	296.50	396.00	816.25	371.00	299.25	381.50	519.50	444.25

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表 8 观测点的参数及波阵面平均速度

Table 8. Parameters for observation points and mean wavefront velocities at observation points

观测点	S/m	ΔS/m	t/ms	Δt/ms	c/(m·s⁻¹)	观测点	S/m	ΔS/m	t/ms	Δt/ms	c/(m·s⁻¹)
0	0		0			6	3.260	0.650	2.35	0.20	3250
1	0.018	0.018	0.05	0.05	360	7	3.900	0.640	2.50	0.15	4267
2	0.670	0.652	1.40	1.35	483	8	4.550	0.650	2.65	0.15	4333
3	1.310	0.640	1.75	0.35	1829	9	5.200	0.650	2.80	0.15	4333
4	1.960	0.650	1.95	0.20	3250	10	5.850	0.650	3.00	0.20	3250
5	2.610	0.650	2.15	0.20	3250	11	6.490	0.640	3.15	0.15	4267

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