新型智能飞片式电子雷管研究

张英豪; 孙昕语; 马宏昊; 沈兆武; 岳中文

doi:10.11883/bzycj-2025-0138

新型智能飞片式电子雷管研究

doi: 10.11883/bzycj-2025-0138

张英豪^{1, 2,},
孙昕语²,
马宏昊³,
沈兆武³,
岳中文^1, ,

1.
中国矿业大学（北京）力学与土木工程学院，北京 100083
2.
北京煋邦数码科技有限公司，北京 102433
3.
中国科学技术大学工程科学学院，安徽合肥 230027

详细信息

作者简介:
张英豪（1975－　），男，硕士，正高级工程师，zyhao1998@sina.com

通讯作者:
岳中文（1975－　），男，博士，教授,zwyue75@163.com

中图分类号: TD235.3
计量
- 文章访问数: 895
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- 被引次数: 0
出版历程
- 收稿日期: 2025-05-12
- 修回日期: 2025-08-15
- 网络出版日期: 2025-08-19

Research on new intelligent flyer-type electronic detonator

1.
School of Mechanics and Civil Engineering, China University of Mining and Technology (Beijing), Beijing 100083, China
2.
Beijing SinoBang Digital Technology Co., LTD., Beijing 102433, China
3.
School of Engineering Science, University of Science and Technology of China, Hefei 230027, Anhui, China

摘要

摘要: 针对工业电子雷管因使用敏感起爆药剂导致的意外爆炸风险，以及传统无起爆药雷管存在的安全与环保问题，为了通过飞片起爆技术提升炸药安全性和环保性能，提出一种新型智能飞片式电子雷管设计：通过理论分析确定飞片起爆临界参数，结合数值模拟优化飞片速度；采用高速摄影观测飞片运动特性，通过铅板穿孔试验评估轴向起爆能力;利用水下爆炸试验验证爆轰稳定性;并开展空气间隔殉爆试验测试安全距离。研究显示：主装药结构优化（一次药400 mg/1.56 g/cm³、二次药200 mg/1.41 g/cm³、三次药320 mg/散装）可实现稳定爆轰；飞片发生器收口直径5.6~5.7 mm时飞片速度达可靠起爆阈值，铅板试验显示轴向起爆能力优于传统无起爆药雷管；水下爆炸试验证实爆轰性能稳定，空气间隔殉爆距离不低于30 mm，满足40 mm生产工艺安全要求；创新性地取消四次药，简化生产工艺，兼具高安全性与绿色环保特性。研究结果表明：新型智能飞片式电子雷管通过飞片起爆技术彻底规避装填敏感起爆药剂，在起爆可靠性、安全距离及环保性能上显著优于传统结构，符合工业雷管安全化、绿色化发展趋势，为行业提供了创新解决方案。
- 电子雷管 /
- 飞片 /
- 结构设计 /
- 安全性
Abstract: To address the accidental explosion risks caused by sensitive primary explosives in industrial electronic detonators, as well as the safety and environmental issues associated with traditional no-primary detonators, a new intelligent flyer-type electronic detonator design was proposed to enhance the safety and environmental performance through flyer initiation technology. To achieve reliable initiation without sensitive primary explosives, a multi-dimensional approach combining experimental and numerical simulation methods is employed for the design and performance optimization of the new intelligent flyer-type electronic detonator. First, critical parameters for slapper initiation were determined through theoretical modeling of shock wave propagation and energy transfer. A finite element model of the flyer acceleration process was established to simulate the effects of different charge structures (e.g., confinement diameter, thickness) on flyer velocity, comprehensively considering material deformation, detonation wave interactions, and flyer fragmentation effects. Second, a high-speed camera (500 000 Hz) was used to synchronously record the detonation process, capturing the actual velocity, flight attitude, and deformation behavior of the flyer upon target impact. This data was used to validate the numerical model and optimize the structural design of the flyer generator. Third, the axial initiation capability was evaluated through standardized lead plate (5 mm thickness) penetration tests. The penetration depth and crater morphology were comparatively analyzed to quantify performance differences with traditional no-primary detonators. Fourth, an underwater explosion test system was utilized, with an array of pressure sensors measuring shock wave overpressure and bubble pulse energy to assess detonation stability and energy output efficiency. Fifth, donor/acceptor detonator arrays were set up at 10–50 mm intervals, and high-speed cameras were used to monitor sympathetic detonation phenomena, verifying compliance with the industrial safety standard of 40 mm minimum separation distance. Sixth, charge parameters were optimized through iterative testing: Primary charge (400 mg, compaction density 1.56 g/cm³) ,Secondary charge (200 mg, compaction density 1.41 g/cm³) , Tertiary charge (320 mg, loosely packed) ,The fourth charge layer was eliminated to simplify the production process while maintaining performance. This multi-scale methodology system provides systematic validation support for the reliability, safety, and environmental friendliness of the flyer initiation technology. The results were aquired as follows. Optimized main charge configuration (primary charge: 400 mg−1.56 g/cm³, secondary charge: 200 mg−1.41 g/cm³, tertiary charge: 320 mg-loosely packed) achieved stable detonation, achieve synergistic improvement of detonation performance and safety. When the slapper generator's necking diameter was 5.6-5.7 mm, the flyer velocity reached the reliable initiation threshold. Lead plate tests demonstrated superior axial initiation capability compared to traditional no-primary detonators. Underwater explosion tests confirmed stable detonation performance, with an air-gap sympathetic detonation distance ≥30 mm, meeting the 40 mm safety requirement for production processes. The innovative elimination of the fourth charge simplified the production process while maintaining high safety and environmental friendliness.The technical bottlenecks of traditional no-primary detonators has been broken. The results show that he new intelligent flyer-type electronic detonator completely avoids the use of sensitive primary explosives through flyer initiation technology. It significantly outperforms traditional designs in initiation reliability, safety distance, and environmental performance, aligning with the industry's trend toward safer and greener detonators. This study provides an innovative solution for the field.
- electronic detonator /
- flyer /
- structural design /
- safety

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图 1 爆轰传播过程示意图

Figure 1. Diagram of detonation propagation procedure

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图 2 电子引火元件组成

Figure 2. Composition of the electronic ignition element

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图 3 电子控制模块基本工作原理

Figure 3. Basic working principle of the electronic control module

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图 4 新型智能飞片式电子雷管结构图

Figure 4. Structure diagram of New intelligent flyer-type electronic detonator

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图 5 水下爆炸试验设备组成

Figure 5. Composition of underwater explosion test equipment

1. Initiation controller; 2. New intelligent flyer-type electronic detonator; 3. Plumb bob; 4. Sensor; 5. Steel frame; 6. Explosion cistern; 7. Oscilloscope

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图 6 冲击波压力时程曲线

Figure 6. Time course curve of shock wave pressure

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图 7 飞片高速摄影实拍图

Figure 7. High-speed photography of flyer

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图 8 飞片残片

Figure 8. Fly fragments

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图 9 数值计算模型图

Figure 9. Numerical calculation model

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图 10 飞片运动速度模拟曲线

Figure 10. Simulation curve of the flight plate motion speed

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图 11 近炸殉爆试验图

Figure 11. Near-explosion explosion test diagram

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表 1 不同二次压药密度下的铅板穿孔试验

Table 1. Lead plate perforation test at different second primary pressure density

ρ₂/(g·cm⁻³)	铅板穿孔直径/mm
ρ₂/(g·cm⁻³)	最大值	最小值	平均值	标准偏差
1.50	11.8	11.1	11.25	0.27
1.41	12.1	11.5	11.72	0.25
1.30	11.1	10.2	10.82	0.30

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表 2 不同收口直径下的铅板穿孔试验

Table 2. Lead plate perforation test with different bayonet diameters

收口直径/mm	铅板穿孔直径/mm	拒爆率
6.0～6.1	11.90, 11.42, 11.72, 11.56, ×，×，×，×，×，×	3/5
5.6～5.7	11.44, 11.68, 11.48, 11.90, 11.82, 11.24, 11.40, 11.62, 11.86, 11.28	0
注：“×”表示铅板未穿孔，说明雷管未完全爆轰。

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表 3 不同收口直径的冲击波峰值压力

Table 3. Shock wave peak pressure under different bayonet diameter

试验	一次装药量/mg	二次装药量/mg	三次装药量/mg	收口直径/mm	峰值压力/MPa
1	412	205	318	6.1	2.167
2	407	205	323	6.0	2.019
3	405	201	321	5.7	2.173
4	407	204	324	6.1	2.133
5	405	201	320	6.0	2.159

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表 4 PETN状态方程参数表

Table 4. PETN state equation parameters table

密度/ (g·cm⁻³)	E/GPa	D/ (km·s⁻¹)	CJ爆轰压力/GPa	A/GPa	B/GPa	R₁	R₂	ω
1.5	8.56	7.45	22	625.3	23.29	5.25	1.6	0.28

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表 5 空气介质状态方程参数表

Table 5. Air medium state equation parameter table

ρ₀/ (g·cm⁻³)	c/ (m·s⁻¹)	S₁	S₂	S₃	γ₀	a
1.29×10⁻³	340	0	0	0	0.14	0

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表 6 飞片Johnson-Cook本构方程计算参数

Table 6. Calculation parameters of Johnson-Cook constitutive equation for flying plates

密度/(g·cm⁻³)	n	m	A_JC/GPa	B_JC/GPa	C_JC	T_m/K	T_room/K
7.8	0.26	1.03	0.792	0.51	0.014	1793	294

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