Abstract：In order to study the effects of loading doses on the output pyrotechnic shock of a typical igniter, the output pressure was measured with a pressure sensor and the acceleration response was measured using piezoelectric accelerometers.The effects of loading doses on the output shock were analyzed with the shock response spectrum (SRS) calculated from acceleration-time histories.It is found that the relation between loading doses and peak pressure shows good agreement with the Nobel-Abel covolume equation of state (EOS); the difference value of SRSs shows a linear growth under different loading doses in the frequency range 1 000 Hz—10 000 Hz.
汪靖程1，李燕华1，温玉全1，李志良2，侯会民2. 典型点火器不同装药量下输出冲击试验与分析[J]. 振动与冲击, 2020, 39(2): 16-21.
WANG Jingcheng1，LI Yanhua1，WEN Yuquan1，LI Zhiliang2，HOU Huimin2. Test and analysis of the output shock under different loading doses of a typical igniter. JOURNAL OF VIBRATION AND SHOCK, 2020, 39(2): 16-21.
[1] Bement L J, Schimmel M L. A Manual for pyrotechnic design development and qualification[s]. NASA, 1995
[2] Himelblau H. Pyrotechnic devices and their applications[J]. Journal of the Acoustical Society of America, 2002, 111(5):2359-2359.
[3] Moening C J. Pyrotechnic shock flight failures [C]. Institute of Environmental Sciences Pyrotechnic Shock Tutorial Program, 31st Annual Technical Meeting, 1985.
[4] 张建华. 航天产品的爆炸冲击环境技术综述[J]. 导弹与航天运载技术, 2005(3): 30-36.
ZhANG Jianhua. Pyroshock environment of missiles and launch vehicles [J]. Missiles and space vehicles, 2005(3): 30-36.
[5] NASA-HDBK-7008. Spacecraft dynamic environments testing [S]. USA: National Aeronautics and Space Administration, 2014.
[6] 丁继锋，赵欣，韩增尧. 航天器火工冲击技术研究进展[J]. 宇航学报，2014，35(12): 1339-1349.
DING Jifeng, ZHAO Xin, HAN Zengrao. Research development of spacecraft pyroshock technique [J]. Journal of Astronautics, 2014, 35(12): 1339-1349.
[7] 张欢，刘天雄，李长江，等. 航天器火工冲击环境防护技术现状与应用[J]. 航天器工程，2014，23(2)：104-113.
ZHANG Huan, LIU Tian-xiong, LI Chang-jiang, et al. Status and application analysis of spacecraft pyroshock protection techniques [J]. Spacecraft Engineering, 2014, 23(2): 104-113.
[8] 张欢，刘海平，刘天雄,等. 航天器火工冲击载荷减缓设计及验证[J]. 装备环境工程，2015，12(3)：34-41.
ZHANG Huan, LIU Haiping, LIU Tianxiong, et al. Design and verification of pyrotechnic shock reduction scheme of spacecraft [J]. Equipment Environmental Engineering, 2015, 12(3): 34-41.
[9] 丁继锋. 星箭分离缓冲设计方法及试验验证研究[J]. 强度与环境，2016，43(2): 17-24.
Ding Jifeng. Shock isolation of satellite-rocket separation and its test verification[J]. Structure & Environment Engineering, 2016, 43(2): 17-24.
[10] 叶耀坤，严楠. 降低火工解锁螺栓分离冲击的技术研究[J]. 火工品，2011(1): 13-16.
YE Yaokun, Yan Nan. Study on the technology to low separation impact of pyrotechnic separator[J]. Initiators & Pyrotechnics, 2011(1): 13-16.
[11] 曹乃亮，徐宏，辛宏伟，等. 冲击载荷作用下火工分离保护装置的建模与分析[J]. 振动与冲击，2015(8)：20-25.
CAO Nailiang,XU Hong, XIN Hongwei,et al. Modeling and analysis of a pyrotechnics separation protecting device under explosion shock[J]. Journal of Vibration and Shock, 2015,34(8)：20-25.
[12] 蒋国伟，满孝颖，孔祥森，等. 卫星可展开附件的扁平式泡沫铝隔冲器研究[J]. 强度与环境，2018(1)：50-56.
JIANG Guowei, MAN Xiaoying, KONG Xiangsen, et al. Research on flat foam aluminum shock isolator of satellite deployable attachment[J]. Structure & Environment engineering, 2018(1): 50-56.
[13] Youn S H, Jang Y S, Han J H. Development of a three-axis hybrid mesh isolator using the pseudoelasticity of a shape memory alloy[J]. Smart Materials & Structures, 2011, 20(7):075017.
[14] 张忠凯，夏冬星，杨安民，等. 三种缓冲材料在某型爆炸螺栓降冲击中的应用研究[J]. 火工品，2018(2)：25-28.
ZHANG Zhongkai, Xia Dongxing, YANG Anmin, et al. Study on the Application of Three Cushioning Materials to An Explosive Bolt for impact reduction. Initiators & Pyrotechnics, 2018(2): 25-28.
[15] 白志富, 果琳丽, 陈岱松. 新型非火工星箭连接分离技术[J]. 导弹与航天运载技术, 2009(1): 31-37.
BAI Zhifu, GUO Linli, CHEN Daisong. Late-model non-pyrotechnic devices for separation of satellite-launching vehicle [J]. Missiles and space vehicles, 2009(1): 31-37.
[16] 王军评，毛勇建，黄含军. 点式火工分离装置冲击载荷作用机制的数值模拟研究[J]. 振动与冲击，2013，32(2): 9-13.
WANG Jun-ping, MAO Yong-jian. HUANG Han-jun. Numerical simulation for impulsively loading mechanism of a point pyrotechnic separation device [J]. Journal of vibration and shock, 2013, 32(2): 9-13.
[17] 韩晓健，焦安超，王睿. 包带低冲击装置冲击试验及数据分析[J]. 航天器环境工程，2007，24(5): 318-321.
HAN Xiaojian, JIAO Anchao, WANG Rui. Shock tests for low shock device of wrapping band related data processing [J]. Spacecraft Environment Engineering, 2007, 24(5): 318-321.
[18] Wang X, Qin Z, Ding J, et al. Finite element modeling and pyroshock response analysis of separation nuts[J]. Aerospace Science & Technology, 2017, 68:380-391
[19] NASA-STD-7003A. Pyroshock test criteria [S]. USA: National Aeronautics and Space Administration, 2011.
[20] MIL-STD-810G Method 517.1 [S]. USA: Department of defense test method standard, 2008.
[21] GJB 150.27-2009. 军用装备实验室环境试验方法 第27部分：爆炸分离冲击试验[S]. 北京：中国人民解放军总装备部，2009.
GJB 150.27-2009. Laboratory environmental test methods for military materiel-Part 27：Pyroshock test [S]. Beijing: The Chinese people’s liberation army （PLA） in the equipment department, 2009.
[22] Lee J R, Chen C C, Kong C W. Review of pyroshock wave measurement and simulation for space systems[J]. Measurement, 2012, 45(4):631-642.
[23] 毕文辉，刘爽，严楠. 密闭爆发器在做功火工品输出性能测试中的应用[J]. 计量与测试技术, 2008, 35(7): 1-3.
Application of Closed Bomb in Testing Output Performance for Explosive Actuated Devices[J]. Metrology & Measurement Technique, 2008, 35(7): 1-3.
[24] Piersol A G, Paez T L, Harris C M. Harris' Shock and Vibration Handbook, 6th edition[M]. New York: McGraw-Hill, 2010.
[25] IEST RP-DTE032.2-2009.Pyroshock Testing Techniques[S]. USA, Institute of Environmental Sciences and Technology, 2009.
[26] 高峰, 叶涛, 刘晓伟. 基于炸药力和余容的引信中雷管爆炸气体压力计算[J]. 弹箭与制导学报, 2015(1):82-85.
GAO Feng, YE Tao, LIU Xiao-wei. Study on Calculations of Exploding Gas Pressure of Detonators Based on Explosive Force and Covolume[J]. Journal of Projectiles Rockets Missiles & Guidance, 2015.
