Rapid Analysis on Structural Integrity of Mixed Propellant and Internal Bore Burning Grain

ZHANG  Lu; YU  Jian; DENG  Kangqing; YU  Rui; YANG  Ling; PANG  Aimin

doi:10.15892/j.cnki.djzdxb.2018.06.016

Journal of Projectiles, Rockets, Missiles and Guidance >

2018 , Vol. 38 >Issue 6: 68 - 74,78

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2018.06.016

Rapid Analysis on Structural Integrity of Mixed Propellant and Internal Bore Burning Grain

ZHANG Lu ,
YU Jian ,
DENG Kangqing ,
YU Rui ,
YANG Ling ,
PANG Aimin

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Hubei Institute of Aerospace Chemotechnology, Hubei Xiangyang 441003, China

Received date: 2018-02-12

Online published: 2025-05-29

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Abstract

In order to rapidly analyze the structural integrity of mixed propellant and internal bore burning grain during cooling process after curing, a rapid assessment method of the structural integrity of propellant grain is introduced first. And then based on the assessment method, the evaluation operation interface for the structure integrity of propellant grain is developed by using the C language. In the evaluation interface a mixed propellant and internal bore burning grain is analyzed and the equivalent modulus of the grain and the equivalent stress of the dangerous position are obtained. Finally, the results are compared with the finite element simulation results based on the linear viscoelastic constitutive model. It is proven that they are in good agreement and the error is less than 6% and the calculation time is saved as well. The developed operation interface can be applied to rapid analysis on the structural integrity analysis of mixed propellant and internal bore burning grain.

Key words： curing and cooling; structural integrity analysis; equivalent modulus; operating interface; rapid analysis

Cite this article

ZHANG Lu , YU Jian , DENG Kangqing , YU Rui , YANG Ling , PANG Aimin . Rapid Analysis on Structural Integrity of Mixed Propellant and Internal Bore Burning Grain[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2018 , 38(6) : 68 -74,78 . DOI: 10.15892/j.cnki.djzdxb.2018.06.016

References

[1]	SCHAPERY R A. Models for damage growth and fracture in nonlinear viscoelastic particulate composites[C]// TheAmerican Society of Mechanical Engineering. Proceeding of Ninth US National Congress of Applied Mechanics. [S. l.:s. n.], 1982: 237-245.
[2]	SCHAPERY R A. Nonlinear viscoelastic and visco-plastic constitutive equations with growing damage[J]. International Journal of Fracture, 1999, 97(1/2/3/4): 33-66.
[3]	DARABI M K, ABU AL-RUB R K, MASAD E A, et al. A thermo-viscoelastic-viscoplastic-viscodamage constitutive model fo asphaltic materials[J]. International Journal of Solids ＆ Structures, 2011, 48(1): 191-207.
[4]	DARABI M K, ABU AL-RUB R K, MASAD E A, et al. Thermodynamic-based model for coupling temperature-dependent viscoelastic,viscoplastic,and viscodamage constitutive behavior of asphalt mixtures[J]. International Journal for Numerical and Analytical Methods in Geomechanics, 2012, 36(7): 817-854.
[5]	唐志平, 田兰桥, 朱兆禅, 等. 高应变率下环氧树脂的力学性能研究[C]//中国力学学会爆炸力学专业委员. 全国第二届爆炸力学学术会议论文集. 扬州: [出版者不祥],1981.
[6]	BURKE M A, WOYTOWITZ P J, REGGI G. Nonlinear viscoelastic constitutive model for solid propellant[J]. Journal of Propulsion and Power, 1992, 8(3): 586-591.
[7]	HINTERHOELZL R M, SCHAPERY R A. FEM Implementation of a Three-Dimensional Viscoelastic Constitutive Model for Particulate Composites with Damage Growth[J]. Mechanics of Time-Dependent Materials, 2004, 8(1): 65-94.
[8]	许进升. 复合推进剂热粘弹性本构模型试验及数值仿真研究[D]. 南京: 南京理工大学, 2013.
[9]	邓斌, 申志彬, 谢燕, 等. 含损伤粘弹性本构及其在有限元分析中的实现[J]. 推进技术, 2013, 34(5): 699-705.
[10]	唐国金, 邓斌, 申志彬. 基于推进剂复杂本构模型的药柱结构分析模块开发[J]. 固体火箭技术, 2014, 37(3): 336-341.
[11]	CHYUAN Shiang-Woei. Dynamic analysis of solid propellant grains subjected to ignition pressurization loading[J]. Journal of Sound and Vibration, 2003, 268(3): 465-483.
[12]	CHYUAN Shiang-Woei, Studies of poisson’s ratio variation for solid propellant grains under ignition pressure loading,International Journal of Pressure Vessels and Piping, 2003, 80(12): 871-877.
[13]	刘中兵, 周艳青, 张兵. 固体发动机低温点火条件下药柱结构完整性分析[J]. 固体火箭技术, 2015, 38(3): 351-355.
[14]	蒙上阳, 唐国金, 雷勇军. 材料性能对固体发动机结构完整性的影响[J]. 国防科技大学学报, 2002, 24(5): 10-15.
[15]	潘奠华, 胡明勇. 固化降温过程中固体火箭发动机材料参数的影响分析[J]. 烟台大学学报(自然科学与工程版), 2006, 19(1): 63-67.
[16]	徐新琦, 于胜春. 固化降温过程中推进剂药柱的瞬态响应分析[J]. 固体火箭技术, 2007, 27(3): 180-183.
[17]	王玉峰, 李高春, 刘著卿, 等. 变温环境下固体药柱的温度应力分析[J]. 宇航学报, 2010, 3(9): 2223-2230.
[18]	鲍福廷, 侯晓. 固体火箭发动机设计[M]. 北京: 宇航出版社, 2016: 400-403.

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