复合材料回转体网格结构热矫形机理及仿真模型研究

张鹏; 祁国成; 付平俊; 李健芳; 王乐辰; 左小彪; 孙宏杰; 王荣; 张博明

复合材料回转体网格结构热矫形机理及仿真模型研究

张鹏¹,
祁国成^1, ,,
付平俊^{2, 3},
李健芳^{2, 3},
王乐辰^{2, 3},
左小彪^{2, 3},
孙宏杰^{2, 3},
王荣^{2, 3},
张博明^{4, 5}

1.
北京交通大学物理科学与工程学院, 北京 100044
2.
航天材料及工艺研究所, 北京 100076
3.
功能性碳纤维复合材料国家工程研究中心, 北京 100076
4.
北京航空航天大学材料科学与工程学院, 北京 100191
5.
山东产业技术研究院先进材料院, 济南 250102

基金项目: 国家自然科学基金(12302162)

详细信息

通讯作者:
祁国成，博士，副教授，硕士生导师，研究方向为复合材料力学　E-mail: gchqi@bjtu.edu.cn

计量
- 文章访问数: 71
- HTML全文浏览量: 20
- 被引次数: 0
出版历程
- 收稿日期: 2024-05-08
- 修回日期: 2024-06-06
- 录用日期: 2024-06-24
- 网络出版日期: 2024-07-11

Research on hot sizing mechanism and simulation model of composite cylindrical grid structures

ZHANG Peng¹,
QI Guocheng^{1
, ,},
FU Pingjun^{2, 3},
LI Jianfang^{2, 3},
WANG Lechen^{2, 3},
ZUO Xiaobiao^{2, 3},
SUN Hongjie^{2, 3},
WANG Rong^{2, 3},
ZHANG Boming^{4, 5}

1.
School of Physical Science and Engineering, Beijing Jiaotong University, Beijing 100044, China
2.
Aerospace Research Institute of Materials & Processing Technology, Beijing 100076, China
3.
National Engineering Research Center of Functional Carbon Composite, Beijing 100076, China
4.
School of Materials Science and Engineering, Beihang University, Beijing 100191, China
5.
Institutes of Advanced Materials, Shandong Institutes of Industrial Technology, Jinan 250102, China

Funds: National Natural Science Foundation of China (12302162)

摘要

摘要: 复合材料回转体网格结构呈现多特征复杂结构属性，工艺固化变形限制了结构的制造装配精度。基于双马树脂的粘弹性，开展航天802双马树脂高温蠕变拉伸测试，证实双马树脂蠕变卸载后存在不可恢复的粘性流动应变，揭示了可以通过热矫形减少大型复合材料网格结构工艺变形的微观组分材料机理。推导建立复合材料网格结构的应变能增量理论，模拟复合材料网格结构热矫形荷载施加、松弛以及回弹过程，确定网格结构矫形回弹轮廓，与实验结果对比验证应变能理论模型有效性。分析复合材料网格结构热矫形内应力失效、矫形点个数、基于时温等效的工艺条件等影响因素，形成了复合材料网格舱段结构热矫形变形控制工艺变形仿真方法。
- 复合材料 /
- 网格结构 /
- 高温蠕变 /
- 热矫形 /
- 有限元分析
Abstract: The composite cylindrical grid structures exhibit quite a few features and complex structural characteristics, and its precision in manufacturing is restricted due to the curing deformation. Based on the viscoelasticity of the bismaleimide resin, high temperature creep tensile testing of the aerospace 802 bismaleimide resin was performed, confirming the existence of unrecoverable viscous flow strain after the unloading of the bismaleimide resin creep. The micro component material mechanism was revealed to reduce the process curing deformation of large composite grid structures through hot sizing. The deformation energy increment theory for composite grid structures was derived and established. The process of hot sizing load application, relaxation, and rebound of composite grid structures was simulated. The correction rebound profile of grid structures was determined, comparing with experimental results to verify the effectiveness of the deformation energy increment theory. The failure of internal stress, number of correction points and process conditions based on time temperature equivalence of hot sizing composite grid structure was analyzed. A complete process for the deformation simulation method of hot sizing deformation control for composite grid structures formed.
- composite /
- grid structure /
- high temperature creep /
- hot sizing /
- finite element analysis

HTML全文

图 1 树脂基复合材料结构热矫形机理

Figure 1. Mechanism of hot sizing of polymer matrix composite structures

U—Displacement imposed by the correction; T—Temperature imposed by the correction; $ {{ \varepsilon }}_{\text{1}} $—General elastic deformation; $ {{ \varepsilon }}_{\text{2}} $—High elastic deformation; $ {{ \varepsilon }}_{\text{3}} $—Viscous flow deformation; E—Modulus of elasticity; $ \eta $—Coefficient of viscous flow

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图 2 复合材料网格结构热矫形全过程轮廓变化

Figure 2. Profile changes throughout the entire process of hot sizing of composite gird structures

$ {\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {u } _1} $—Field of change of applied corrective displacement; $ {\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {u } _2} $—Field of displacement change when deformation rebound occurs in the interstage segment; $ {\overset{\lower0.5em\hbox{$\smash{\scriptscriptstyle\rightharpoonup}$}} {u } _3} $—Difference between the residual deformation and the initial deformation displacement field after the cabin segment has undergone creep

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图 3 802双马树脂在210℃不同应力水平下的高温蠕变及恢复过程中的应变-时间关系

Figure 3. Strain and time relationships of 802 bismaleimide resin during high temperature creep and recovery under different stress at 210℃

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图 4 802双马树脂高温蠕变应变曲线拟合

Figure 4. Strain curve fitting of 802 bismaleimide resin for high temperature creep

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图 5 TG800/802双马树脂复合材料网格结构热矫形模拟流程图

Figure 5. Flow chart for hot sizing simulation of TG800/802 bismaleimide resin composite grid structures

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图 6 圆度定义(a)、TG800/802双马树脂复合材料网格舱段结构(b)、TG800/802双马树脂复合材料网格舱段固化变形预报结果((c)、(d))

Figure 6. Definition of roundness (a), TG800/802 bismaleimide resin composite grid interstage segment (b), predicted results of curing deformation of TG800/802 bismaleimide resin composite grid interstage segment ((c), (d))

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图 7 TG800/802双马树脂复合材料网格舱段16点矫形位移载荷大小

Figure 7. Magnitude of displacement loads at 16 sizing points in the TG800/802 bismaleimide resin composite grid interstage segment

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图 8 TG800/802双马树脂复合材料网格舱段热矫形全过程应变能变化

Figure 8. Changes in strain energy during hot sizing of TG800/802 bismaleimide resin composite grid inter-stage segment

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图 9 TG800/802双马树脂复合材料网格舱段“固化变形-矫形荷载施加后-残留变形”轮廓

Figure 9. Profiles of “curing deformation, application of corrective load, and residual deformation”of TG800/802 bismaleimide resin composite grid interstage segment

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图 10 TG800/802双马树脂复合材料网格舱段热矫形内应力云图：(a)S₂₂；(b)最大主应力；(c)S₁₂；(d)S₁₃

Figure 10. Internal stress distribution of hot sizing of TG800/802 bismaleimide resin composite grid interstage segment: (a) S₂₂; (b) Max principle; (c) S₁₂; (d) S₁₃

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图 11 不同矫形点个数下的TG800/802双马树脂复合材料网格舱段轮廓

Figure 11. Contours of TG800/802 bismaleimide resin composite grid interstage segment with different number of corrective points

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图 12 TG800/802双马树脂复合材料网格舱段热矫形后残留横向拉应力S₂₂：(a)树脂模量衰减5%；(b)树脂模量衰减9%

Figure 12. Residual transverse tensile stress after hot sizing of TG800/802 bismaleimide resin composite grid interstage segment S₂₂:(a) Resin modulus attenuation by 5%; (b) Resin modulus attenuation by 9%

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表 1 TG800/802双马树脂复合材料室温力学性能

Table 1. TG800/802 bismaleimide resin composite properties at room temperature

E₁₁/MPa	E₂₂/MPa	G₁₂/MPa	G₂₃/MPa	$ {\mu }_{\text{12}} $	$ {\sigma }_{\text{11}}\text{/MPa} $	$ {\sigma}_{\text{22}}\text{/MPa} $	ILSS/MPa	$ {\sigma}_{\text{12}}\text{/MPa} $
164000	9310	5690	3280	0.38	2482	59	101	88
Notes: E—Modulus of elasticity; G—Modulus of shear; μ—Poisson’s ratio; σ—Intensity of stress; ILSS—Interlaminar shear strength.

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表 2 TG800/802复合材料平板及舱段结构铺层

Table 2. Plying of TG800/802 composite laminate and grid interstage segment

Composite	Ply
Skin	[45/−45/0/90/0/0/90/0/−45/45]
End frame	[45/−45/0/90/0/0/90/0/−45/45]₃
Thickened zone	[45/0/−45/0/15/0/−15/0/15/90]₆

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表 3 网格舱段层合板单元失效指数

Table 3. Failure index of grid interstage segment laminate unit

Failure mode	Hashin
Fiber tensile failure	0.008
Fiber compression failure	0.000
Matrix tension failure	0.889
Matrix compression failure	0.157

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表 4 树脂模量等效衰减程度对应残留应力水平

Table 4. Equivalent attenuation degree of resin modulus corresponding to residual stress

Decay of resin modulus	Internal stress/MPa
Decay of resin modulus	Maximum principal stress	S₂₂	S₁₂	S₁₃
5%	194.7	17.1	6.9	19.6
6%	227.4	19.8	8.1	22.9
9%	410.8	33.2	18.6	40.5

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