镍基合金薄板不同温度下的弹道冲击行为

刘焦; 郑百林; 杨彪; 俞晓强; 张锴; 史同承

doi:10.11868/j.issn.1005-5053.2018.000045

镍基合金薄板不同温度下的弹道冲击行为

doi: 10.11868/j.issn.1005-5053.2018.000045

刘焦¹,
郑百林^1, ,,
杨彪¹,
俞晓强¹,
张锴¹,
史同承²

1.
同济大学航空航天与力学学院，上海 200092
2.
中国航发商用航空发动机有限责任公司设计研发中心，上海 201100

基金项目: 上海市航空发动机领域联合创新计划项目（AR905）

详细信息

通讯作者:
郑百林（1966—），男，博士，教授，主要从事固体力学、冲击力学、金属材料的力学行为研究，（E-mail）blzheng@tongji.edu.cn

中图分类号: TG146.1⁺5
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出版历程
- 收稿日期: 2018-04-23
- 修回日期: 2018-05-30
- 网络出版日期: 2019-01-21
- 刊出日期: 2019-02-01

Ballistic impact behavior of thin nickel-base alloy plates at different temperatures

1.
School of Aerospace Engineering and Applied Mechanics, Tongji University, Shanghai 200092，China
2.
AECC Commercial Aircraft Engine Co., Ltd, Design Research Center, Shanghai 201100，China

摘要

摘要: 为研究航空发动机机匣在高温下的包容性能力，通过实验和数值模拟研究25 ℃和600 ℃下GH4169合金薄板受球型子弹冲击后的变形行为。弹道冲击实验通过轻气炮实施，子弹以不同初始速率冲击靶板。分析温度和冲击速率对靶板的变形、临界击穿速率、破坏变形模式以及能量吸收的影响。结果表明：高温下靶板的变形更大，靶板被击穿所吸收的能量更小，临界击穿速率更小；高温下靶板被穿透后由弯曲作用引起的花瓣状变形更明显。数值模拟研究通过有限元软件LS-DYNA实施，数值模拟中选用Johnson-Cook本构模型。采用高温分离式霍普金森压杆（SHPB）实验技术对GH4169高温合金进行测试，获得了材料在高温高应变率下的力学特性并拟合了Johnson-Cook本构模型参数。数值模拟研究的结果和实验结果进行了对比，显示了良好的一致性。
- 弹道冲击实验 /
- 数值模拟 /
- 温度 /
- Johnson-Cook模型 /
- 破坏变形模式 /
- 临界击穿速率
Abstract: To study the aeroengine containment capability in high temperature, experiments and numerical simulations of the spherical nosed projectile impacting thin plate under 25 ℃ and 600 ℃ were performed. Experiments were conducted by using a gas gun. Target plates were impacted by bullets with different initial velocities. The effect of temperature and initial velocity on the deformation, failure pattern and energy absorption of the plate were analyzed. The results show that at higher temperature, the deformation of the target plates is greater, the energy absorbed by the target plates is smaller and the critical ballistic velocities are smaller . The petal deformation of the target plate caused by bending is more obvious under 600 ℃. Numerical simulations of the impact were conducted by using an explicit dynamics FE code (LS-DYNA). The Johnson-Cook material model was used to carry out the analysis. The Johnson-Cook material model parameters were obtained by the separated Hopkinson pressure bar (SHPB) experiment at high temperature. The results obtained from the numerical simulations were compared with those from the experiments. Good correlation is found between experiments and numerical simulations.
- ballistic impact experiments /
- numerical simulation /
- temperatures /
- Johnson-Cook model /
- failure patterns /
- critical ballistic velocity

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图 1 实验装置示意图

Figure 1. Schematic diagram of experimental setup

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图 2 GH4169合金靶板弹道冲击V_r 与 V_i

Figure 2. Ballistic impact V_i and V_r of GH4169 alloy plate

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图 3 GH4169合金靶板弹道冲击V_i与E_a

Figure 3. Ballistic impact V_i and E_a of GH4169 alloy plate

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图 4 25 ℃下GH4169合金靶板变形图（V_i = 148.9 m/s）　（a）正面；（b）反面

Figure 4. Deformation diagrams of GH4169 alloy plate at 25 ℃（V_i = 148.9 m/s）　（a）front；（b）back

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图 5 600 ℃下GH4169合金靶板变形图（V_i = 141.3 m/s）　（a）正面；（b）反面

Figure 5. Deformation diagrams of GH4169 alloy plate at 600 ℃（V_i = 141.3 m/s）　（a）front；（b）back

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图 6 带同步系统的高温霍普金森压杆实验装置

Figure 6. Experiment device of high temperature Hopkinson pressure bar with synchronous system

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图 7 GH4169合金Johnson-Cook本构方程拟合结果

Figure 7. Fitting results with Johnson-Cook constitutive equation of GH4169 alloy　（a）（25 ℃，200 ℃，400 ℃）/1500 s^–1；（b）（25 ℃，200 ℃，400 ℃）/3000 s^–1；（c）（600 ℃，700 ℃）/1500 s^–1；（d）（600 ℃，700 ℃）/3000 s^–1

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图 8 数值模拟研究球型子弹以不同冲击速率垂直撞击GH4169合金靶板V_i与V_r关系图

Figure 8. Relation between V_i and V_r by numerical simulation of GH4169 alloy plate impacted by spherical bullets with different velocities

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图 9 数值模拟研究冲击GH4169合金材料靶板E_a和h_t与V_i的关系

Figure 9. Relation of E_a and h_t versus V_i of impacting GH4169 alloy plate by numerical simulation　（a）600 ℃ ；（b）25 ℃

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图 10 实验和数值模拟研究冲击GH4169合金材料靶板V_r随V_i变化的关系图

Figure 10. Relation between V_r and V_i by experimental and numerical simulation of impacting GH4169 alloy plate

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图 11 实验和数值模拟研究冲击GH4169合金材料靶板V_d随V_i变化的关系图

Figure 11. Relation between V_d and V_i by experimental and numerical simulation of impacting GH4169 alloy plate　（a）600 ℃；（b）25 ℃

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图 12 25 ℃室温下GH4169合金材料靶板变形过程图（V_i = 148.9 m/s）

Figure 12. Deformation process of GH4169 alloy plate at 25 ℃（V_i = 148.9 m/s）　（a）50 μs；（b）100 μs；（c）200 μs

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图 13 600 ℃高温下GH4169合金材料靶板变形过程图（V_i = 141.3 m/s）

Figure 13. Deformation process of GH4169 alloy plate at 600 ℃（V_i = 141.3 m/s）　（a）50 μs；（b）100 μs；（c）200 μs

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表 1 GH4169合金靶板的弹道冲击实验测试结果

Table 1. Testing results of ballistic impact experiment of GH4169 alloy

Temperature/℃	V_i/（m·s^–1）	V_r/（m·s^–1）	V_d/（m·s^–1）	E_a/J	h_t/mm
25	128.9	0	128.9	58.627	6.9
25	137.5	0	137.5	66.711	7.6
25	142	0	142	71.149	8.5
25	143.87	66.3	77.57	51.677	10.5
25	146.86	77.8	69.06	54.745	10.2
25	146.9	79.7	67.2	53.73	10.3
25	148.9	86.2	62.7	52.013	9.7
25	171.15	124.5	46.65	48.665	9
25	187	142.9	44.1	51.335	8.6
600	110.43	0	110.43	43.029	7
600	114.7	0	114.7	46.421	7.2
600	123.66	0	123.66	53.957	8.3
600	124.6	40.1	84.5	49.107	11.5
600	127.48	59.7	67.78	44.766	11.3
600	129.3	63	66.3	44.987	10.9
600	134.9	83.3	51.6	39.728	10.1
600	141.3	105.3	36	31.324	10.1
600	158.1	123.2	34.9	34.641	9.8
600	176.2	142.1	34.1	38.298	9.4

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表 2 GH4169合金在不同温度下的基本参数^[18]

Table 2. Basic parameters of GH4169 alloy at different temperatures^[18]

Temperature/℃	E/GPa	ν	ρ/（kg·m^–3）	T_m/℃	T_r/℃	C_p/（J·kg^–1·K^–1）
25	205.0	0.321	8.24×10³	1800	25	440
600	150.8	0.350	8.24×10³	1800	25	539

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表 3 不同温度下GH4169合金的Johnson-Cook 本构模型参数

Table 3. Parameters of Johnson-Cook constitutive model of GH4169 alloy at different temperatures

Temperature/℃	A/MPa	B/MPa	C	n	m	$\mathop {{\varepsilon _0}}\limits^ {\!\! \cdot} $/s^–1
25	1290	1100	0.01	0.510	1.05	1500
600	1063.5	681.1	0.104	0.508	2.5	1500

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表 4 GH4169合金Johnson-Cook失效模型参数

Table 4. Parameters of Johnson-Cook damage model of GH4169 alloy

D₁	D₂	D₃	D₄	D₅
0.02	0.75	–1.1	0.0255	–0.275

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表 5 GH4169 合金Gruneisen状态方程参数

Table 5. Gruneisen equation of state parameters of GH4169 alloy

c/（m·s^–1）	S₁	S₂	S₃	γ	α
4578	1.33	0	0	1.67	0.43

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表 6 实验与数值模拟预测25 ℃和600 ℃下的临界击穿速率

Table 6. Tested and predicted critical ballistic velocities（V_c）at 25 ℃ and 600 ℃

Temperature/℃	V_c/（m·s^–1）		Deviation/%
Temperature/℃	Experimental	Numerical	Deviation/%
25	143	146.3	2.31
600	124	131.9	6.37

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