纤维增强形状记忆聚合物复合材料及其航天应用

张豆; 刘彦菊; 冷劲松

doi:10.13801/j.cnki.fhclxb.20201224.002

纤维增强形状记忆聚合物复合材料及其航天应用

doi: 10.13801/j.cnki.fhclxb.20201224.002

张豆¹,
刘彦菊^1, ,,
冷劲松^{1, 2, ,}

1.
哈尔滨工业大学　航天科学与力学系，哈尔滨 150001
2.
哈尔滨工业大学　复合材料与结构研究所，哈尔滨 150001

基金项目: 国家自然科学基金(11632005；11672086)

详细信息

通讯作者:
刘彦菊，博士，教授，博士生导师，研究方向为复合材料电热性能　 E-mail：yj-liu@hit.edu.cn

冷劲松，博士，教授，博士生导师，研究方向为智能复合材料　 E-mail：libei@whut.edu.cn

中图分类号: TB332
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- 被引次数: 0
出版历程
- 收稿日期: 2020-10-15
- 录用日期: 2020-12-05
- 网络出版日期: 2020-12-25
- 刊出日期: 2021-03-15

Fiber reinforced shape memory polymer composites and their applications in aerospace

ZHANG Dou¹,
LIU Yanju^{1
, ,},
LENG Jinsong^{1, 2
, ,}

1.
Department of Astronautical Science and Mechanics, Harbin Institute of Technology, Harbin 150001, China
2.
Center for Composite Materials and Structures, Science Park of Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 形状记忆聚合物(SMP)是一种能够保持临时形状，并在外界刺激下自发回复到其初始形状的智能材料，具有高形状固定率、高形状回复率、转变温度可调、变形能力强、质量轻等优点，但其应用受到响应方式单一和承载能力差的限制，通过向聚合物中添加功能颗粒或增强纤维制成形状记忆聚合物复合材料(SMPC)，可有效解决这一问题。首先介绍了SMP形状记忆效应的原理，然后阐述了纤维增强型SMPC有限变形过程中纤维的微屈曲行为。最后对可变形结构在航天领域的应用进行了论述。
- 形状记忆聚合物复合材料 /
- 纤维 /
- 后屈曲 /
- 可变形结构 /
- 航天应用
Abstract: Shape memory polymer (SMP) is a kind of smart materials that can maintain a temporary shape and recover its initial configuration under external stimuli. Its advantages of high shape fixation rate, high shape recovery rate, adjustable transition temperature, high deformation ability and light weight makes it suitable to design and fabricate deformable structures. However, its application is restricted by limited response modes and poor bearing capacity. These problems can be effectively solved by adding functional particles or enhanced fibers to the polymer matrix to obtain shape memory polymer composites (SMPC). This article first introduces the shape memory mechanism of SMP and gives its actuation methods. Then, fiber microbuckling behavior of unidirectional fiber reinforced SMPC is discussed. Finally, applications of deformable structures in aerospace are presented.
- shape memory polymer composites /
- fibers /
- post microbuckling /
- deformable structures /
- aerospace applications

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图 1 应力-应变-温度的3D热-力学循环过程示意图^[12]

Figure 1. 3D diagram of stress-strain-temperature thermal-mechanical cycling process^[12]

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图 2 碳纤维增强形状记忆聚合物复合材料(SMPC)受压纤维的微屈曲^[18]

Figure 2. Microbuckling of carbon fibre reinforced shape memory polymer composite (SMPC)^[18]

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图 3 弯曲变形时纤维微屈曲示意图^[21]

Figure 3. Schematic diagram of fiber microbuckling during bending deformation^[21]

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图 4 弹性基体中一个杆在压缩载荷下屈曲变形^[31]

Figure 4. A bar on an elastic foundation^[31]

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图 5 压缩载荷下两种纤维屈曲失效方式: (a)拉伸模式; (b)剪切模式^[32]

Figure 5. Two failure modes of fiber buckling under compression load: (a) Tension mode; (b) Shearing mode^[32]

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图 6 纤维增强形状记忆复合材料的弯曲变形示意图^[35]

Figure 6. Bending deformation structure of fiber reinforced shape memory composites^[35]

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图 7 功能梯度材料弯曲变形示意图^[37]

Figure 7. Deformation of functionally graded plates under pure bending^[37]

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图 8 Tembo^®EMC铰链: (a)展开状态; (b)折叠状态; (c)EMC铰链在TacSat-2飞行试验中的安装位置^[41]

Figure 8. Tembo^®EMC hinge: (a) Deployable configuration; (b) Folded configuration; (c) Installment of EMC hinge in TacSat-2 mission^[41]

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图 9 SMPC铰链: (a)铰链回复过程^[42]; (b)铰链驱动太阳能帆板回复过程^[42]; (c)混杂智能铰链组成示意图^[43]; (d)一体化铰链回复过程^[44]

Figure 9. SMPC hinge: (a) Recovery process of SMPC hinge^[42]; (b) Recovery process of solar array driven by SMPC hinge^[42]; (c) Hybrid intelligent hinge^[43]; (d) Recovery process of integrated hinge^[44]

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图 10 SMPC套筒式分离装置: (a) 莲花型^[45]; (b)八爪型^[45]; (c) 竹节型^[45]; (d)凹痕型^[46]

Figure 10. SMPC telescope-feed release mechanism: (a) Lotus type^[45]; (b) Eight-paw type^[45]; (c) Bamboo type^[45]; (d) Groove type^[46]

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图 11 “钩子型”释放机构在立方星上的应用^[47]

Figure 11. “Hook” type on a CubeSat^[47]

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图 12 FalconSAT-3卫星上的可展开重力梯度杆(a)及EMC片层折叠方式(b)^[48]

Figure 12. Deployable gravity gradient boom in FalconSAT-3 (a) and folded configuration of EMC (b)^[48]

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图 13 桁架结构: (a)可展开桁架展开过程^[49]; (b)三纵梁桁架结构^[50]

Figure 13. Truss: (a) Deployable process of the truss^[49]; (b) Diagram and modal of three-longeron truss^[50]

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图 14 大承载可展开桁架结构: (a)收拢状态; (b)展开状态^[51]

Figure 14. Deployable truss with large carrying capacity: (a) Packaged configuration; (b) Deployable configuration^[51]

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图 15 柔性太阳翼在轨飞行照片: (a)~(b)发射13天后; (c)~(d)发射8个月后^[53]

Figure 15. Pictures of a flexible solar wing in orbit: (a)–(b) 13 days after launching; (c)–(d) 8 months after launching^[53]

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图 16 SMPC豆荚杆作为柔性太阳翼基板: (a)收拢状态; (b)展开状态^[54]

Figure 16. SMPC LCCT’s potential application as deployable solar wing: (a) Packaged configuration; (b) Deployed configuration^[54]

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图 17 搭载SJ20同步卫星的可展开柔性太阳能电池阵列系统(SMPC-FSAS) 2020年1月5日在轨展开过程: (a), (b)解锁过程; (c)–(f)展开过程^[55]

Figure 17. On-orbit releasing and deployment demonstration of SMPC-FSAS flight hardware which was performed on SJ20 Geostationary Satellite on 5 Jan., 2020: (a), (b) Unlocking process in space; (c)–(f) Deploying process in space^[55]

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纤维增强形状记忆聚合物复合材料及其航天应用

doi: 10.13801/j.cnki.fhclxb.20201224.002

通讯作者:
刘彦菊，博士，教授，博士生导师，研究方向为复合材料电热性能　 E-mail：yj-liu@hit.edu.cn

冷劲松，博士，教授，博士生导师，研究方向为智能复合材料　 E-mail：libei@whut.edu.cn

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Fiber reinforced shape memory polymer composites and their applications in aerospace

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留言板

纤维增强形状记忆聚合物复合材料及其航天应用

doi: 10.13801/j.cnki.fhclxb.20201224.002

通讯作者: 刘彦菊，博士，教授，博士生导师，研究方向为复合材料电热性能 E-mail：yj-liu@hit.edu.cn 冷劲松，博士，教授，博士生导师，研究方向为智能复合材料 E-mail：libei@whut.edu.cn

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Fiber reinforced shape memory polymer composites and their applications in aerospace

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出版历程

目录

通讯作者:
刘彦菊，博士，教授，博士生导师，研究方向为复合材料电热性能　 E-mail：yj-liu@hit.edu.cn

冷劲松，博士，教授，博士生导师，研究方向为智能复合材料　 E-mail：libei@whut.edu.cn