某大型T800壳体结构精细化建模及损伤失效分析

喻琳峰; 任全彬; 宋学宇; 张爱华

doi:10.13224/j.cnki.jasp.20230097

某大型T800壳体结构精细化建模及损伤失效分析

doi: 10.13224/j.cnki.jasp.20230097

1.
中国航天科技集团有限公司西安航天动力技术研究所，西安 710025
2.
中国航天科技集团有限公司航天动力技术研究院，西安 710025

详细信息

作者简介:
喻琳峰（1997-），男，硕士生，主要从事固体火箭发动机壳体结构设计研究。E-mail：954770982@qq.com

中图分类号: V435
计量
- 文章访问数: 1082
- HTML浏览量: 301
- PDF量: 52
- 被引次数: 0
出版历程
- 收稿日期: 2023-02-21
- 网络出版日期: 2024-08-03

Refined modeling and damage failure analysis of a large T800 shell structure

1.
Xi’an Institute of Aerospace Propulsion Technology，China Aerospace Science and Technology Corporation，Xi’an 710025，China
2.
Aerospace Solid Propulsion Technology Institute，China Aerospace Science and Technology Corporation，Xi’an 710025，China

摘要

摘要:
利用Python对ABAQUS二次开发的方法，建立了精细化的壳体后封头结构模型。针对复合材料壳体封头纤维缠角及厚度不断变化的特点，编制计算程序，精确计算出封头部位每个纵向缠绕层缠绕角的大小以及缠绕层随半径变化的层厚，较真实地建立了固体火箭发动机复合材料壳体后封头结构的有限元分析模型，在一定内压载荷下对其应变情况进行了分析。将分析的结果与试验结果比较, 验证了该模型的准确性。使用UMAT（user-defined material）子程序，引入损伤失效准则对壳体结构进行了损伤失效分析，进一步获取了该结构在内压载荷逐渐增加时，其破坏位置，破坏形式，最终得出了该缠绕层结构的最终破坏形式为封头靠近赤道位置处的纤维断裂破坏，对今后的复合材料壳体结构设计提供了依据。
- 纤维缠绕 /
- 复合材料壳体 /
- 精细化模型 /
- 损伤力学 /
- 渐进损伤 /
- 破坏模式
Abstract:
Using the method of Python’s secondary development of ABAQUS, a refined shell back head structure model was established. According to the characteristics of the fiber winding angle and thickness of the composite shell head, the calculation program was compiled to accurately calculate the winding angle of each longitudinal winding layer and the thickness of the winding layer varying with the radius. The finite element analysis model of the rear head structure of the solid rocket motor composite shell was established, and the strain was analyzed under certain internal pressure load. The accuracy of the model was verified by comparing the analysis results with the experimental results. The UMAT （user-defined material） subroutine was used to introduce the damage failure criterion to analyze the shell structure, and the failure position and failure form of the structure were further obtained when the internal pressure load gradually increased. Finally, it was concluded that the final failure form of the winding layer structure was the fiber fracture failure near the equatorial position of the head, helping to provide a basis for the design of the composite shell structure in the future.
- filament wound /
- composite shell /
- refined model /
- damage mechanics /
- progressive damage /
- failure mode

HTML

图 1 UMAT子程序运行流程图

Figure 1. UMAT subroutine running flow chart

下载: 全尺寸图片幻灯片

图 2 试件模型结构示意图

Figure 2. Specimen model structure diagram

下载: 全尺寸图片幻灯片

图 3 弯曲试验加载机

Figure 3. Bending test loading machine

下载: 全尺寸图片幻灯片

图 4 弯曲试验结果

Figure 4. Bending test results

下载: 全尺寸图片幻灯片

图 5 仿真计算模型

Figure 5. Simulation calculation model

下载: 全尺寸图片幻灯片

图 6 试件纤维损伤云图

Figure 6. Specimen fiber damage cloud diagram

下载: 全尺寸图片幻灯片

图 7 试件基体损伤云图

Figure 7. Specimen matrix damage cloud diagram

下载: 全尺寸图片幻灯片

图 8 试验、仿真结果对比图

Figure 8. Comparison of test and simulation results

下载: 全尺寸图片幻灯片

图 9 部分单元局部坐标系

Figure 9. Partial element local coordinate system

下载: 全尺寸图片幻灯片

图 10 壳体后封头结构模型

Figure 10. Shell back head structure model

下载: 全尺寸图片幻灯片

图 11 壳体水压爆破后封头形貌

Figure 11. Water pressure burst appearance of shell rear head

下载: 全尺寸图片幻灯片

图 12 筒身环向应变

Figure 12. Circumferential strain of cylinder body

下载: 全尺寸图片幻灯片

图 13 筒身环向应变变化曲线

Figure 13. Curve of cylindrical circumferential strain change

下载: 全尺寸图片幻灯片

图 14 缠绕层赤道附近纤维损伤云图

Figure 14. Fiber damage cloud near the equator of the winding layer

下载: 全尺寸图片幻灯片

图 15 缠绕层赤道附近基体损伤云图

Figure 15. Matrix damage cloud near the equator of the winding layer

下载: 全尺寸图片幻灯片

图 16 缠绕层靠接头附近纤维损伤云图

Figure 16. Fiber damage cloud near the joint of winding layer

下载: 全尺寸图片幻灯片

图 17 缠绕层靠接头附近基体损伤云图

Figure 17. Damage cloud diagram of the winding layer near the joint matrix

下载: 全尺寸图片幻灯片

图 18 各内压载荷下基体失效因子分布情况

Figure 18. Distribution of matrix failure factor under internal pressure loads

下载: 全尺寸图片幻灯片

图 19 各内压载荷下纤维失效因子分布情况

Figure 19. Distribution of fiber failure factors under various internal pressure loads

下载: 全尺寸图片幻灯片

图 20 缠绕层靠近赤道位置纤维、基体失效因子变化情况

Figure 20. Change of failure factor of fiber and matrix near the equator of winding layer

下载: 全尺寸图片幻灯片

图 21 缠绕层靠近金属接头位置纤维、基体失效因子变化情况

Figure 21. Change of failure factor of fiber and matrix near the metal joint of winding layer

下载: 全尺寸图片幻灯片

表 1 试件材料性能参数

Table 1. Material performance parameters of specimen

材料	参数	数值
T800	拉伸模量/GPa	290
	拉伸失效应力/MPa	5820
	断裂延伸率/%	2.0
	体密度/（g/cm³）	1.8
	线密度/（g/km）	445.5
树脂	拉伸模量/GPa	3.33
	压缩模量/GPa	3.49
	弯曲模量/GPa	3.94
	切变模量/GPa	1.0
	拉伸失效应力/MPa	94.3
	压缩失效应力/MPa	150
	弯曲强度/MPa	155

下载: 导出CSV

表 2 T800碳/环氧复合材料性能参数

Table 2. Performance parameters of T800 carbon fiber/epoxy resin composites

参数		数值
拉伸模量/GPa	E₁₁	173
	E₂₂	11.4
	E₃₃	11.4
切变模量/GPa	G₁₂	1.91
	G₁₃	1.91
	G₂₃	1.91
泊松比	$ \mathrm{\nu } $₁₂	0.22
泊松比	$ \nu $₁₃	0.22
拉伸失效应力/MPa	X_t	3157
拉伸失效应力/MPa	Y_t	63.1
压缩失效应力/MPa	X_c	2525.5
压缩失效应力/MPa	Y_c	189.4
剪切失效应力/MPa		50
基体失效能/（MPa·mm^1/2）		1
纤维失效能/（MPa·mm^1/2）		12.5
黏性正则化系数		0.001

下载: 导出CSV

表 3 缠绕层工艺参数

Table 3. Winding layer process parameters

缠绕层	退移量/mm	起始位置/mm
纵向层1	0
环向层1～2		553
纵向层2	0
环向层3～4		553
纵向层3（退移）	25±5
环向层5～6		553
纵向层4	0
环向层7～8		553
纵向层5（退移）	30±5
环向层9～10		553
纵向层6	0
环向层11～12		553
纵向层7（退移）	50±5
环向层13～14		553
纵向层8（退移）	40±5
环向层15～16		553
纵向层9	0
环向层17～18		553
纵向层10	0
环向层19～20		553
纵向层11	0

下载: 导出CSV

表 4 接头、堵盖及弹性层材料性能参数

Table 4. Material properties of joint, gasket and closure

材料	参数	数值
铝	弹性模量/GPa	70
	泊松比	0.3
	密度/（g/cm³）	2.7
橡胶	弹性模量/GPa	0.08
橡胶	泊松比	0.48
钢	弹性模量/GPa	200
钢	泊松比	0.3

下载: 导出CSV

表 5 方向向量

Table 5. Direction vector

新坐标	方向向量
OX	$ -\dfrac{2{x}_{0}{y}_{0}}{{b}^{2}},\dfrac{2\left({{x}_{0}}^{2}+{{{\textit{z}}}}_{0}^{2}\right)}{{a}^{2}},-\dfrac{2{y}_{0}{{\textit{z}}}_{0}}{{b}^{2}} $
OY	$ {{\textit{\textit{z}}}}_{0},0,-{x}_{0} $
OZ	$ \dfrac{{2}{{x}}_{{0}}}{{{a}}^{{2}}}{,}\dfrac{{2}{{y}}_{{0}}}{{{b}}^{{2}}}{,}\dfrac{{2}{{{\textit{\textit{z}}}}}_{{0}}}{{{a}}^{{2}}} $
注：表中a、b、c为椭球形状参数。

下载: 导出CSV

表 6 壳体水压爆破实验结果

Table 6. Results of hydrostatic burst tests of composite cases

序号	压强/MPa	最大顺纤维应变	筒身最大环向应变
01	16.2	0.0100	0.0118

下载: 导出CSV

参考文献(19)

[1]	刘炳禹,张炜,王晓洁. 封头补强技术研究[J]. 固体火箭技术,1996,19(4): 57-61. LIU Bingyu,ZHANG Wei,WANG Xiaojie. Research on strengthening technology of head[J]. Journal of Solid Rocket Technology,1996,19(4): 57-61. (in Chinese LIU Bingyu, ZHANG Wei, WANG Xiaojie. Research on strengthening technology of head[J]. Journal of Solid Rocket Technology, 1996, 19(4): 57-61. (in Chinese)
[2]	LIU P F,CHU J K,HOU S J,et al. Numerical simulation and optimal design for composite high-pressure hydrogen storage vessel: a review[J]. Renewable and Sustainable Energy Reviews,2012,16(4): 1817-1827. doi: 10.1016/j.rser.2012.01.006
[3]	王明鉴,卢明章. 固体火箭发动机纤维缠绕壳体承载能力数值仿真[J]. 固体火箭技术,2011,34(2): 234-237. WANG Mingjian,LU Mingzhang. Numerical simulation of load-bearing capacity of solid rocket motor fiber winding composite case[J]. Journal of Solid Rocket Technology,2011,34(2): 234-237. (in Chinese WANG Mingjian, LU Mingzhang. Numerical simulation of load-bearing capacity of solid rocket motor fiber winding composite case[J]. Journal of Solid Rocket Technology, 2011, 34(2): 234-237. (in Chinese)
[4]	PARNAS L,KATIRCI N. Design of fiber-reinforced composite pressure vessels under various loading conditions[J]. Composite Structures,2002,58(1): 83-95. doi: 10.1016/S0263-8223(02)00037-5
[5]	杨眉,陈秀华,伍春波. 固体火箭发动机纤维缠绕复合材料壳体爆破渐进失效的数值模拟[J]. 机械工程材料,2012,36(11): 92-96. YANG Mei,CHEN Xiuhua,WU Chunbo. Numerical simulation for burst progressive failure of filament-wound composite case in solid rocket motor[J]. Materials for Mechanical Engineering,2012,36(11): 92-96. (in Chinese YANG Mei, CHEN Xiuhua, WU Chunbo. Numerical simulation for burst progressive failure of filament-wound composite case in solid rocket motor[J]. Materials for Mechanical Engineering, 2012, 36(11): 92-96. (in Chinese)
[6]	LIU K S,TSAI S W. A progressive quadratic failure criterion for a laminate[J]. Composites Science and Technology,1998,58(7): 1023-1032. doi: 10.1016/S0266-3538(96)00141-8
[7]	BASU S,WAAS A M,AMBUR D R. Prediction of progressive failure in multidirectional composite laminated panels[J]. International Journal of Solids and Structures,2007,44(9): 2648-2676. doi: 10.1016/j.ijsolstr.2006.08.010
[8]	常新龙,刘万雷,张晓军,等. 缠绕复合材料壳体爆破压强的预测[J]. 航空动力学报,2017,32(12): 2817-2823. CHANG Xinlong,LIU Wanlei,ZHANG Xiaojun,et al. Burst pressure prediction of filament wound composite shell[J]. Journal of Aerospace Power,2017,32(12): 2817-2823. (in Chinese CHANG Xinlong, LIU Wanlei, ZHANG Xiaojun, et al. Burst pressure prediction of filament wound composite shell[J]. Journal of Aerospace Power, 2017, 32(12): 2817-2823. (in Chinese)
[9]	王晓宏,张博明,刘长喜,等. 纤维缠绕复合材料压力容器渐进损伤分析[J]. 计算力学学报,2009,26(3): 446-452. WANG Xiaohong,ZHANG Boming,LIU Changxi,et al. Prpgressive failure analysis of composite overwrapped pressure vessels[J]. Chinese Journal of Computational Mechanics,2009,26(3): 446-452. (in Chinese WANG Xiaohong, ZHANG Boming, LIU Changxi, et al. Prpgressive failure analysis of composite overwrapped pressure vessels[J]. Chinese Journal of Computational Mechanics, 2009, 26(3): 446-452. (in Chinese)
[10]	CHAPELLE D,PERREUX D. Optimal design of a Type 3 hydrogen vessel: Part Ⅰ analytic modelling of the cylindrical section[J]. International Journal of Hydrogen Energy,2006,31(5): 627-638. doi: 10.1016/j.ijhydene.2005.06.012
[11]	XU P,ZHENG J Y,LIU P F. Finite element analysis of burst pressure of composite hydrogen storage vessels[J]. Materials & Design,2009,30(7): 2295-2301.
[12]	BERRO RAMIREZ J P,HALM D,GRANDIDIER J C,et al. Experimental study of the thermomechanical behavior of wound notched structures[J]. International Journal of Hydrogen Energy,2015,40(38): 13148-13159. doi: 10.1016/j.ijhydene.2015.05.156
[13]	付福超. 纤维缠绕复合材料结构刚度预测模型与力学分析方法研究[D]. 南京: 南京航空航天大学,2007. FU Fuchao. The mechanics research of filament wound composite shells[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2007. (in Chinese FU Fuchao. The mechanics research of filament wound composite shells[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2007. (in Chinese)
[14]	和欣辉,韩小平. 纤维缠绕复合材料起伏区域残余应力[J]. 材料工程,2016,44(4): 76-81. HE Xinhui,HAN Xiaoping. Residual stresses in local fiber undulations for filament-wound composites[J]. Journal of Materials Engineering,2016,44(4): 76-81. (in Chinese HE Xinhui, HAN Xiaoping. Residual stresses in local fiber undulations for filament-wound composites[J]. Journal of Materials Engineering, 2016, 44(4): 76-81. (in Chinese)
[15]	LINDE P,PLEITNER J,BOER H D,et al. Modelling and simulation of fibre metal laminates[C]//Proceedings of ABAQUS User’s Conference. Boston,US: [s. n. ],2004: 421-439.
[16]	ZHANG Qian,XU Hui,JIA Xiaolong,et al. Design of a 70 MPa type Ⅳ hydrogen storage vessel using accurate modeling techniques for dome thickness prediction[J]. Composite Structures,2020,236: 111915. doi: 10.1016/j.compstruct.2020.111915
[17]	DVH A,TNT A,VTL A,et al. Design of planar wound composite vessel based on preventing slippage tendency of fibers[J]. Composite Structures,2020,254: 112854. doi: 10.1016/j.compstruct.2020.112854
[18]	尤军峰,刘浩,王春光. 固体火箭发动机复合材料壳体细观力学仿真分析[J]. 固体火箭技术,2018,41(5): 549-555,579. YOU Junfeng,LIU Hao,WANG Chunguang. Mesomechanics simulation analysis of composite case structure of SRM[J]. Journal of Solid Rocket Technology,2018,41(5): 549-555,579. (in Chinese YOU Junfeng, LIU Hao, WANG Chunguang. Mesomechanics simulation analysis of composite case structure of SRM[J]. Journal of Solid Rocket Technology, 2018, 41(5): 549-555, 579. (in Chinese)
[19]	陈汝训,刘铭初,李志明. 固体火箭发动机设计与研究(下)[M]. 北京: 宇航出版社,1992. CHEN Ruxun,LIU Mingchu,LI Zhiming. The design and research of solid rocket motor: Part 2 [M]. Beijing: Astronautic Publishing House,1992. (in Chinese CHEN Ruxun, LIU Mingchu, LI Zhiming. The design and research of solid rocket motor: Part 2 [M]. Beijing: Astronautic Publishing House, 1992. (in Chinese)