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学者姓名：关成龙
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Abstract ：
Bistable composite cylindrical structures have been developed over the last four decades, and show great potential for shape morphing applications, especially in aerospace. Their bistabilities are known to be induced by unsymmetric composite layups, while the governing factors on shape geometries and viscoelastic mechanics remain an enigma. Here, we investigated the intricate relationship between structural geometry and stable mechanics of a bistable unsymmetric composite cylindrical structure. A polylactic acid (PLA)-based carbon composite laminate was prepared through 3D printing, which released design freedom on structural fiber volume fraction that could be controlled by modulating hatch spacing between the composite yarns. This strategic adjustment allowed the regulation of grid density, hence the in-plane stress level, which dominates the bistable geometries. The cylindrical composite samples were produced with hatch spacing changed from 1.25 to 5 mm, corresponding to a fiber volume fraction ranged from 24.2% to 6.6%, where the structural curvature was also changed by up to 50% difference and gradually became viscoelastic dependent. It is found that the internal stress difference in thickness direction dominates the structural bistability, and there is a threshold value on the stress difference magnitude to essentially maintain the bistable configurations. These findings are expected to facilitate reversed structural design and manufacturing of the bistable cylindrical shells with tailorable stability, and promote their viscoelastic-based large shape morphing fatigue life predictions.Highlights Bistable composite cylindrical shells were produced with various grid density. A theoretical model was established to predict the time-dependent bistability. Stress difference in thickness direction dominates the structural curvature. Stress contour reveals the viscoelastic-dependent bistable mechanics.
Keyword ：
analytical modeling analytical modeling multifunctional composites multifunctional composites residual/internal stress residual/internal stress viscoelastic mechanics viscoelastic mechanics
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| GB/T 7714 | Wang, Bing , Ye, Junjie , Zhang, Shunnan et al. Viscoelastic mechanics of a bistable composite cylindrical structure [J]. | POLYMER COMPOSITES , 2025 . |
| MLA | Wang, Bing et al. "Viscoelastic mechanics of a bistable composite cylindrical structure" . | POLYMER COMPOSITES (2025) . |
| APA | Wang, Bing , Ye, Junjie , Zhang, Shunnan , Guan, Chenglong , Zhong, Jianfeng , Zhong, Shuncong . Viscoelastic mechanics of a bistable composite cylindrical structure . | POLYMER COMPOSITES , 2025 . |
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Metamaterials (MMs) have become increasingly prominent in terahertz flexible devices. However, bending deformation often alters the structure of the unit, which affects the response performance and stability of MMs. Here, a metal-aperture metamaterial (MA-MM) utilizing the strong coupling effect induced by two resonance modes is innovatively proposed to address the mentioned limitations. Specifically, it is found that the coupling state between multiple resonance modes remains consistent at different bending angles. Under these circumstances, the generated Rabi splitting peak presents stable response performance even under low resonance intensity caused by excessive deformation. The experimental results demonstrate that despite the amplitude of two resonant peaks decreasing significantly by 87.6%, the Q-factor of the Rabi splitting only reduced by 14.8%. Furthermore, armed with the response mode of the Rabi splitting being unaffected by plasma excitation range, the designed MA-MMs are able to maintain constant Q-factors and frequencies on curved surfaces of varying sizes. These findings exhibit the characteristics of electromagnetic response for multi-mode resonance-coupled MAMMs on different curved surfaces, presenting a novel design approach for terahertz flexible functional devices. (c) 2024 Chinese Laser Press
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| GB/T 7714 | Zeng, Qiuming , Shi, Tingting , Huang, Yi et al. Freestanding metamaterial with constant coupling response for terahertz flexible functional devices [J]. | PHOTONICS RESEARCH , 2025 , 13 (1) . |
| MLA | Zeng, Qiuming et al. "Freestanding metamaterial with constant coupling response for terahertz flexible functional devices" . | PHOTONICS RESEARCH 13 . 1 (2025) . |
| APA | Zeng, Qiuming , Shi, Tingting , Huang, Yi , Zhong, Shuncong , Sun, Fuwei , Guan, Chenglong et al. Freestanding metamaterial with constant coupling response for terahertz flexible functional devices . | PHOTONICS RESEARCH , 2025 , 13 (1) . |
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A bistable composite tape-spring (CTS) structure is a thin-walled open slit tube with fibres oriented at +/- 45 degrees, which is stable at both the extended and fully coiled configurations. Owning to its positive Gaussian curvature deformation mechanics and high stowage-to-pack ratio, it has been successfully applied and launched to International Space Station and microsatellites to construct deployable solar sails. Intelligent driving designs of the CTS-based deployable structures are becoming more and more important to further reduce weight and complexities for space applications. Here, we presented novel findings on the passive thermal driving mechanics of the bistable CTS structure. This is achieved by exploring the thermal energy-induced microstructural expansion and contraction, which would change the structural curvature, and thus regulating the strain energy within the CTS. An analytical model on the strain energy evolution under thermal effects was established to predict the minimum stable shape transition paths, as well as to determine the critical boundary conditions for thermal driving. Both experiments and finite element model were then carried out to reveal underlying mechanisms. It is found that a CTS is able to be passively deployed under thermal energy, there is a minimum energy constraint to initiate the shape morphing process, and the critical boundaries are dependent on the thermal expansion of the structural material. These findings provide a novel low cost, simple and reversed smart morphing design principle of the CTS structure, enriching the theoretical analysis and deployable control of the bistable composites to benefit future deep space explorations.
Keyword ：
Bistable Bistable Composite Composite Mechanism Mechanism Strain energy Strain energy Thermal driving Thermal driving
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| GB/T 7714 | Peng, Yulin , Zhu, Juncheng , Wang, Bing et al. Passive thermal driving mechanics of a bistable composite tape-spring [J]. | THIN-WALLED STRUCTURES , 2025 , 210 . |
| MLA | Peng, Yulin et al. "Passive thermal driving mechanics of a bistable composite tape-spring" . | THIN-WALLED STRUCTURES 210 (2025) . |
| APA | Peng, Yulin , Zhu, Juncheng , Wang, Bing , Guan, Chenglong , Zhong, Jianfeng , Zhong, Shuncong . Passive thermal driving mechanics of a bistable composite tape-spring . | THIN-WALLED STRUCTURES , 2025 , 210 . |
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The composite segmented tools, used as the internal mandrel, are crucial in the integrated curing process of aerospace composite tanks. Their precise manufacturing demands stringent curing process requirements. Current studies lack reports on the curing simulation and process optimization of the segmented tools, making it challenging to provide effective guidance for the high-quality manufacturing of aerospace composite tanks. This study focuses on the composite segmented tools for a Phi 3.35 m liquid oxygen tank. The curing kinetics equations and thermophysical properties of T800/epoxy composites were tested and fitted. Finite element prediction models for the temperature and deformation evolution during the curing process were constructed. Based on the orthogonal experimental design, the curing parameters were optimized, and an engineering trial of the composite panel was completed. The results indicate that the heating rate has the most significant impact on the curing deformation of segmented tools, while the curing temperature has the greatest effect on curing uniformity. Under the optimized process parameters, the curing deformation of the composite panel obtained by the finite element model only has a 6.67% error compared to the experimental results, which not only validates the accuracy of the simulation models but also achieves precise manufacturing of the composite segmented tools.
Keyword ：
aerospace composite tank aerospace composite tank curing deformation simulation curing deformation simulation process optimization process optimization segmented tools segmented tools
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| GB/T 7714 | Zhan, Lihua , Yao, Shunming , Guan, Chenglong et al. Curing simulation and experimental analysis of composite segmented tools for aerospace applications [J]. | POLYMER COMPOSITES , 2025 . |
| MLA | Zhan, Lihua et al. "Curing simulation and experimental analysis of composite segmented tools for aerospace applications" . | POLYMER COMPOSITES (2025) . |
| APA | Zhan, Lihua , Yao, Shunming , Guan, Chenglong , Zhang, Dechao , Wang, Bing , Zhong, Shuncong . Curing simulation and experimental analysis of composite segmented tools for aerospace applications . | POLYMER COMPOSITES , 2025 . |
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The vibration pretreatment-microwave curing process is an efficient, low energy consumption, and high-quality out-of-autoclave curing process for carbon fiber resin matrix composites. This study aims to investigate the impact of vibration pretreatment temperature on the fiber weight content, microscopic morphology and mechanical properties of the composite laminates by using optical digital microscopy, universal tensile testing machine and thermogravimetric analyzer. Additionally, the combined mode of Bragg fiber grating sensor and temperature measurement fiber was employed to explore the effect of vibration pretreatment on the strain process during microwave curing. The study results revealed that the change in vibration pretreatment temperature had a slight impact on the fiber weight content when the vibration acceleration remained constant. The metallographic and interlaminar strength of the specimen formed at a vibration pretreatment temperature of 80 °C demonstrated a porosity of 0.414% and a 10.69% decrease in interlaminar shear strength compared to autoclave curing. Moreover, the introduction of the vibration energy field during the microwave curing process led to a significant reduction in residual strain in both the 0° and 90° fiber directions, when the laminate was cooled to 60 °. (Figure presented.) © Central South University 2024.
Keyword ：
curing strain curing strain interlaminar shear strength interlaminar shear strength microwave curing microwave curing porosity porosity thermo-gravimetric analysis thermo-gravimetric analysis vibration vibration
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| GB/T 7714 | Zhang, D.-C. , Zhan, L.-H. , Ma, B.-L. et al. Experimental investigation of vibration pretreatment-microwave curing process for carbon fiber reinforced resin matrix composites; [碳纤维增强树脂基复合材料振动预处理-微波固化工艺的实验研究] [J]. | Journal of Central South University , 2024 , 31 (6) : 1838-1855 . |
| MLA | Zhang, D.-C. et al. "Experimental investigation of vibration pretreatment-microwave curing process for carbon fiber reinforced resin matrix composites; [碳纤维增强树脂基复合材料振动预处理-微波固化工艺的实验研究]" . | Journal of Central South University 31 . 6 (2024) : 1838-1855 . |
| APA | Zhang, D.-C. , Zhan, L.-H. , Ma, B.-L. , Yao, S.-M. , Guo, J.-Z. , Guan, C.-L. et al. Experimental investigation of vibration pretreatment-microwave curing process for carbon fiber reinforced resin matrix composites; [碳纤维增强树脂基复合材料振动预处理-微波固化工艺的实验研究] . | Journal of Central South University , 2024 , 31 (6) , 1838-1855 . |
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Abstract ：
The vibration pretreatment-microwave curing process is an efficient, low energy consumption, and high-quality out-of-autoclave curing process for carbon fiber resin matrix composites. This study aims to investigate the impact of vibration pretreatment temperature on the fiber weight content, microscopic morphology and mechanical properties of the composite laminates by using optical digital microscopy, universal tensile testing machine and thermogravimetric analyzer. Additionally, the combined mode of Bragg fiber grating sensor and temperature measurement fiber was employed to explore the effect of vibration pretreatment on the strain process during microwave curing. The study results revealed that the change in vibration pretreatment temperature had a slight impact on the fiber weight content when the vibration acceleration remained constant. The metallographic and interlaminar strength of the specimen formed at a vibration pretreatment temperature of 80 degrees C demonstrated a porosity of 0.414% and a 10.69% decrease in interlaminar shear strength compared to autoclave curing. Moreover, the introduction of the vibration energy field during the microwave curing process led to a significant reduction in residual strain in both the 0 degrees and 90 degrees fiber directions, when the laminate was cooled to 60 degree celsius.
Keyword ：
curing strain curing strain interlaminar shear strength interlaminar shear strength microwave curing microwave curing porosity porosity thermo-gravimetric analysis thermo-gravimetric analysis vibration vibration
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| GB/T 7714 | Zhang, De-chao , Zhan, Li-hua , Ma, Bo-lin et al. Experimental investigation of vibration pretreatment-microwave curing process for carbon fiber reinforced resin matrix composites [J]. | JOURNAL OF CENTRAL SOUTH UNIVERSITY , 2024 , 31 (6) : 1838-1855 . |
| MLA | Zhang, De-chao et al. "Experimental investigation of vibration pretreatment-microwave curing process for carbon fiber reinforced resin matrix composites" . | JOURNAL OF CENTRAL SOUTH UNIVERSITY 31 . 6 (2024) : 1838-1855 . |
| APA | Zhang, De-chao , Zhan, Li-hua , Ma, Bo-lin , Yao, Shun-ming , Guo, Jin-zhan , Guan, Cheng-long et al. Experimental investigation of vibration pretreatment-microwave curing process for carbon fiber reinforced resin matrix composites . | JOURNAL OF CENTRAL SOUTH UNIVERSITY , 2024 , 31 (6) , 1838-1855 . |
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A bistable composite cylindrical shell is a thin-walled structure that can change shape between two stable configurations under small energy input, showing great potential to be applied to space deployable mechanics. The internal stress level within a cylindrical shell plays a vital role in determining its morphing mechanics, whilst tailoring the internal stress is tricky for traditional composite manufacturing methods. In this paper, we devise a novel biaxial elastic fibre prestressing (EFP) method to systematic design and produce prestrained carbon-based composite cylindrical shells, with tailorable bistability and morphing mechanics, as well as improved loadcarrying capabilities. A biaxial fibre stretching rig was devised to apply tensions on both directions of a plainweave carbon prepreg simultaneously; prestrained cylindrical shell samples were produced with various prestrain levels to fully evaluate the fibre prestraining effects; a finite element model was established and showed good agreement with experimental observations. The fibre prestraining mechanisms were then proposed. It is found that EFP is effective in tailoring the internal strain/stress level within a composite cylindrical shell, which in turn altering the structural morphing mechanics, and able to significantly lower the maximum tensile strain during shape-changing, thus improve the load-carrying capability. These findings are expected to facilitate structural design of the deployable composite structures and flexible mechanical hinges, by allowing further design freedoms in terms of morphing mechanics and load-carrying capability.
Keyword ：
Bistable composite Bistable composite Morphing mechanics Morphing mechanics Prestress Prestress Residual/internal stress Residual/internal stress Strain Strain
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| GB/T 7714 | Zhao, Chenmin , Wang, Bing , Chen, Xiayu et al. On tailoring morphing mechanics of a bistable composite cylindrical shell through elastic fibre prestressing [J]. | THIN-WALLED STRUCTURES , 2024 , 207 . |
| MLA | Zhao, Chenmin et al. "On tailoring morphing mechanics of a bistable composite cylindrical shell through elastic fibre prestressing" . | THIN-WALLED STRUCTURES 207 (2024) . |
| APA | Zhao, Chenmin , Wang, Bing , Chen, Xiayu , Guan, Chenglong , Zhong, Shuncong . On tailoring morphing mechanics of a bistable composite cylindrical shell through elastic fibre prestressing . | THIN-WALLED STRUCTURES , 2024 , 207 . |
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Abstract ：
A composite tape-spring (CTS) structure is a thin-walled open slit tube with fibres oriented at +/- 45, which is stable in both extended and coiled configurations. The governing factors of its bistability include composite constitutive behaviour, initial geometrical proportions, and geometrically non-linear structural behaviour. Its bistable principle can be employed to produce a flexible multistable hinge structure with tailorable stability. This is achieved by introducing variable stiffness design within a cylindrical shell structure, where folding stability is dependent on central functional patch region, and then connected to linking ploy regions. Thus, a novel multistable composite hinge structure can be designed with positive Gaussian curvature deformation, and its multistability is highly tailorable: a lengthy one-dimensional mechanical arm can be designed to coil and fold multiple times to enable large folding ratio. An analytical model was established based on the strain energy principle, in order to determine effects from functional tape length; the typical structural stability and stable configurations were then predicted with respect to regional length of the functional layer. It is found that the stability of a multistable composite hinge structure is dependent on geometry and combination of both the functional patch region, and connecting ploy region; the stable criteria are then proposed and show good agreement with experimental observations and FE analysis. These enrich the diversities of functional deployable structures to benefit novel requirements for various deployable mechanisms, and enable customised design, as well as smart driving for flexible and multifunctional mechanical composite hinge applications.
Keyword ：
Composite Composite Hinge Hinge Mechanics Mechanics Multistable Multistable
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| GB/T 7714 | Zhao, Chenmin , Lin, Xinyu , Wang, Bing et al. A multistable composite hinge structure [J]. | THIN-WALLED STRUCTURES , 2024 , 198 . |
| MLA | Zhao, Chenmin et al. "A multistable composite hinge structure" . | THIN-WALLED STRUCTURES 198 (2024) . |
| APA | Zhao, Chenmin , Lin, Xinyu , Wang, Bing , Zhu, Juncheng , Guan, Chenglong , Zhong, Shuncong . A multistable composite hinge structure . | THIN-WALLED STRUCTURES , 2024 , 198 . |
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Bistable composite structures have attracted growing interest in morphing applications to aerospace industry. Here, we device a novel prestrained bistable composite gridded structure, consisting pairs of prestrained composite strips on both sides and oriented in 90°. This is achieved by employing the elastic fibre prestressing (EFP) technique, where a plain-weave carbon prepreg was stretched in two directions at a constant strain level, and the tensile strain was maintained throughout the curing process to produce a prestrained composite trip. Upon load removal, recovery from the prestrained carbon fibres generates compressive stresses and interacts with thermal residual stresses, which in turn changing the in-plane stress level within a composite structure and induce out-of-plane deflections. Therefore, the bistability is generated from the pairs of the oriented prestrained composite strips, their deflections give opposite cylindrical configurations to the mid-plane. Here, we presented further details on the biaxial fibre straining rig; samples were produced with different prestrain levels, in order to reveal the underlying mechanisms from the fibre prestraining. These results provide valuable insights for the design of aerospace deployable structures. © The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd. 2024.
Keyword ：
Bistable Bistable Composite Composite Gridded structure Gridded structure Prestrain Prestrain
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| GB/T 7714 | Zhao, C. , Wang, B. , Chen, X. et al. A Prestrained Bistable Composite Gridded Structure [未知]. |
| MLA | Zhao, C. et al. "A Prestrained Bistable Composite Gridded Structure" [未知]. |
| APA | Zhao, C. , Wang, B. , Chen, X. , Lin, X. , Guan, C. , Zhong, S. . A Prestrained Bistable Composite Gridded Structure [未知]. |
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Polymers and composites have been widely applied in many industries, especially in aerospace. There are growing demands for understanding their natural viscoelastic performance, especially in aerospace applications, where precise dimensional control and prediction of the residual strength and modulus are vital for the success of an aerospace vehicle. The existing superposition principles mainly focus on the well-known WLF-based horizontal shift to predict the long-term behaviour through short-term experimental tests in terms of creep or stress relaxation. Whilst the intrinsic microstructural changes or damages within a polymeric material due to viscoelastic deformation are not considered, which may lead to large differences for long-term predictions. Here, we look into the very fundamentals of the existing superposition principles, aiming to develop towards a unified theory to better predict the long-term relaxation modulus or creep of a polymeric solid. This is achieved by considering both the free volume theory-based horizontal shift factors and activation energy-based shift factors; microstructural changes or damages induced vertical shift factors are then coupled to improve the prediction accuracy of the superposition methods. These will facilitate long-term predictions and accelerated aging tests for viscoelastic solids. © The Author(s), under exclusive license to Springer Nature Switzerland AG 2024.
Keyword ：
Accelerated Aging Accelerated Aging Arrhenius Arrhenius Shift Factor Shift Factor Superposition Principle Superposition Principle WLF Equation WLF Equation
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| GB/T 7714 | Chen, X. , Wang, B. , Zhao, C. et al. Towards a Unified Theory on the Superposition Principles [未知]. |
| MLA | Chen, X. et al. "Towards a Unified Theory on the Superposition Principles" [未知]. |
| APA | Chen, X. , Wang, B. , Zhao, C. , Du, D. , Guan, C. , Zhong, S. . Towards a Unified Theory on the Superposition Principles [未知]. |
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