[an error occurred while processing this directive] [an error occurred while processing this directive] [an error occurred while processing this directive]
[an error occurred while processing this directive]

Journal of Projectiles, Rockets, Missiles and Guidance >

2022 , Vol. 42 >Issue 2: 89 - 93

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2022.02.016

Numerical Simulation of Ignition Reaction of HTPB Propellant Under Drop-weight Impact

  • LIU Zhaoheng ,
  • YU Hongtao ,
  • LIU Zhuo
Expand
  • School of Mechatronic Engineering, Xi’an Technological University, Xi’an 710021, China

Received date: 2021-09-30

  Online published: 2025-05-29

Fold

Abstract

In order to study the ignition mechanism of typical HTPB propellant under low pressure impact, a three-dimensional simulation model of drop-weight test of HTPB propellant was established based on hot spot theory. The drop-weight test of HTPB propellant was numerically simulated by finite element method and trinomial ignition growth reaction rate model, and the ignition response and dynamic mechanical response of HTPB propellant during the whole impact process were analyzed.The results show that during the whole impact process, due to the radial deformation of the propellant after the impact, the shear stress is concentrated on the edge of the upper and lower surface of the propellant, and the friction stress produces local heat concentration to form a hot spot, which causes the propellant to ignite and explode.It is calculated that when the falling height is 75 cm, the initiation threshold of 10 kg drop hammer impact HTPB propellant is 540.2 MPa2·s.

Key words： low pressure impact; HTPB propellant; drop weight test; ignition growth reaction rate model; numerical simulation

Cite this article

LIU Zhaoheng , YU Hongtao , LIU Zhuo . Numerical Simulation of Ignition Reaction of HTPB Propellant Under Drop-weight Impact[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2022 , 42(2) : 89 -93 . DOI: 10.15892/j.cnki.djzdxb.2022.02.016

[an error occurred while processing this directive]

References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
覃金贵. PBX炸药非冲击点火机制实验及数值模拟研究[D]. 长沙: 国防科技大学, 2014.

[2]
LONG B, CHANG X L, HU K, et al. Effects of temperature and strain rate on the dynamic fracture properties of HTPB propellant[J]. Propellants, Explosives, Pyrotechnics, 2015, 40(4): 479-483.

[3]
郁红陶, 何远航, 张庆明. 高压水射流冲击固体推进剂的温度效应实验研究[J]. 北京理工大学学报, 2008, 28(3):189-191.

[4]
HO S Y. High strain-rate constitutive models for solid rocket propellants[J]. Journal of Propulsion and Power, 2002, 18(5): 1106-1111.

[5]
袁俊明, 刘玉存, 曹文军. B炸药落锤撞击点火的数值模拟[J]. 含能材料, 2013, 21(1):30-34.

[6]
杨明, 黄卫东, 刘丙杰, 等. HTPB推进剂冲击发火判据的试验研究[J]. 火炸药学报, 2020, 43(1):85-89.

DOI

[7]
丁彪, 黄锋, 杨明, 等. 基于落锤试验的固体推进剂冲击发火判据研究[J]. 舰船电子工程, 2019, 39(11):187-189.

[8]
国防科学技术工业委员会. 中华人民共和国国家军用标准炸药实验方法:GJB 772A-1997[S]. 北京: 国防科工委军标出版社, 1997.

[9]
SO W, FRANCIS E C. Dynamic finite element analysis of solid propellant impact test[J]. Journal of Spacecraft & Rockets, 2012, 28(6):658-662.

Options
Outlines

/

〈 〉

[an error occurred while processing this directive]