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弹箭与制导学报 >

2019 , Vol. 39 >Issue 1: 21 - 24,30

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2019.01.005

复合材料多瓣易碎盖分离过程研究

  • 李文龙 ,
  • 周光明 ,
  • 蔡登安
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  • 1 中国飞行试验研究院, 西安 710089
    2 南京航空航天大学机械结构力学及控制国家重点实验室, 南京 210016

李文龙(1991-),男,陕西咸阳人,助理工程师,硕士研究生,研究方向:工程力学。

收稿日期: 2018-06-07

  网络出版日期: 2025-05-21

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Separation Process of a Composite Multi-part Fragile Cover

  • LI Wenlong ,
  • ZHOU Guangming ,
  • CAI Deng'an
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  • 1 Chinese Flight Test Establishment, Xi'an 710089, China
    2 State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2018-06-07

  Online published: 2025-05-21

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摘要

为减轻整体冲破式复合材料易碎盖分离体重量,对复合材料多瓣易碎盖进行设计,并采用数值模拟与试验两种方法对其分离过程进行了研究。首先,基于等强度设计原则,提出了一种复合材料多瓣易碎盖薄弱区结构设计方法;其次,对复合材料多瓣易碎盖分离过程进行了数值模拟;最后,对易碎盖进行冲破试验,验证了设计方法的有效性。结果表明,文中提出的复合材料多瓣易碎盖设计方法能保证易碎盖冲破时间短,并且分离体可沿预设轨迹飞出。

关键词： 复合材料; 多瓣易碎盖; 分离过程; 数值模拟

本文引用格式

李文龙 , 周光明 , 蔡登安 . 复合材料多瓣易碎盖分离过程研究[J]. 弹箭与制导学报, 2019 , 39(1) : 21 -24,30 . DOI: 10.15892/j.cnki.djzdxb.2019.01.005

Abstract

In order to reduce the weight of the fragile cover, the composite multi-part fragile cover was designed, and the separation process of the cover was studied by numerical simulation and experiment. Firstly, based on the equal-strength design principle, a design method for the weak zone structure of composite multi-part fragile cover was proposed. Secondly, the separation process of composite multi-part fragile cover was numerically simulated. Finally, the failure experiment was carried out to verify the effectiveness of the design method. The results show that the design method of composite multi-part fragile cover proposed in this paper can ensure the short breaking time, and the separator can fly out along the preset trajectory.

Key words： composite material; multi-part fragile cover; separation process; numerical simulation

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参考文献

[1]
姚昌仁, 张波. 火箭导弹发射装置设计[M]. 北京: 北京理工大学出版社, 1998: 217－222．
[2]
COPELAND R L, GREENE R F, BEELR D R, et al. Protective cover for a missile nose cone: US 3970006[P]. 1976－07－20．
[3]
BOEGLIN P H, CHIGOT C R. Plate-glass fitted with an explosion-cutting device: US 4333381 [P]. 1982 －06 －08．
[4]
BELL R E, REID W J T. Missile weapon system: US 5239909 [P]. 1993 －08 －31．
[5]
何东晓. 先进复合材料在航空航天的应用综述[J]. 高科技纤维与应用, 2006, 31(2): 9－11．
[6]
沈观林, 胡更开. 复合材料力学[M]. 北京: 清华大学出版社, 2006: 15－28．
[7]
DOANE W J. Frangible fly through diaphragm for missile launch canister: US 4498368[P]. 1985－02－12．
[8]
KAM T Y, WU J H, WANG W T. External failure pressure of a frangible laminated composite canister cover[J]. Composite Structures, 1999, 47(1 /2 /3 /4): 563－569．
[9]
WU J H, WANG W T, KAM T Y. Failure analysis of a frangible laminated composite canister cover[J]. Journal of Aerospace Engineering, 1999, 213(G3): 187－195．
[10]
周光明, 袁卓伟, 王新峰. 整体冲破式复合材料薄膜盖的设计与试验研究[J]. 宇航学报，2007，28(3): 707 －712．
[11]
钱元. 冲破式复合材料发射箱盖结构设计和试验研究 [D]. 南京: 南京航空航天大学, 2013．
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