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学者姓名：王冰
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Abstract ：
A bistable composite cylindrical structure is a thin-walled shell, stable in its extended and coiled configurations, that offers large shape-morphing capabilities without structural damage. It has been successfully applied to deployable structures and launched into orbit. Smart-morphing designs provide new freedom and flexibility for space-deployable mechanics, reducing structural weight and complexity. Here, we present a novel magnetically activated bistable composite cylindrical structure, where the fundamentals of the critical magnetic driving boundaries are revealed for the first time to develop a reversed smart-morphing design principle. This is achieved by employing a magnetically responsive area within a bistable composite, where the NdFeB particles are co-cured directly with the carbon layups to ensure good bonding. Theoretical analysis of the magnetic driving principle was developed to reveal the interacting mechanics of a bistable structure subjected to magnetic actuation. The magnetic field distribution was characterized through experiments; a series of magnetic-responsive bistable composite cylindrical samples were produced and subjected to magnetic activation to determine the critical shape transition intensities. Their shape-changing processes were also evaluated through mechanical testing and compared to the magnetic driving mechanics. It is found that there is an optimal level of magnetic particle concentration to minimize the magnetically responsive time and input energy. The critical boundaries in terms of the current and air gap are established through theoretical analysis and verified through experimental observations. The magnetic driving mechanics are then discussed and concluded in detail. This provides a simple and effective alternative for smart actuation and morphing control of bistable composite structures, supporting their future applications in deep space exploration.
Keyword ：
bistable bistable composite composite driving driving magnetic magnetic mechanics mechanics
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| GB/T 7714 | Wang, Bing , Zhang, Shunnan , Guan, Chenglong et al. Magnetic driving mechanics of a bistable composite cylindrical structure [J]. | SMART MATERIALS AND STRUCTURES , 2025 , 34 (4) . |
| MLA | Wang, Bing et al. "Magnetic driving mechanics of a bistable composite cylindrical structure" . | SMART MATERIALS AND STRUCTURES 34 . 4 (2025) . |
| APA | Wang, Bing , Zhang, Shunnan , Guan, Chenglong , Zhong, Jianfeng , Zhong, Shuncong . Magnetic driving mechanics of a bistable composite cylindrical structure . | SMART MATERIALS AND STRUCTURES , 2025 , 34 (4) . |
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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 rapid development of aerospace technology has continuously promoted the demand for lightweight and systematic design of twisting structures, where advanced composites have drawn great expectations. A double helical structure has been developed to introduce large axial twistable capability, where thin-walled cured composite strips with a longitudinal curvature were prestressed or flattened to be employed as shape-changing units, and then assembled by using rigid spokes, pins, or webs; however, its twisting performance would be susceptible to thermal effects, and affected by the curvature variations induced by flattening and assembling of the precured curved strips. Here, we proposed a novel double helical structural design, where thin-walled curved tapes with transverse curvature were applied as the shape-changing units without prestressing. The double helical structures were produced and investigated with isotropic transverse curved tapes, orthotropic flat strips, as well as orthotropic transverse curved tapes, in order to reveal its geometric curvature effects-induced twisting mechanics. An inextensible shell model was formulated to analyse the shape-changing process, and expose the regulating mechanisms on structural stability. Experiments and finite element analysis were carried out to investigate the material and geometric curvature dependencies. It is found that the material orthotropy contributes to the bistability of the helical structure; geometric curvature promotes the stiffness and shape-changing stability of the double helix. The twisting mechanisms were then concluded in detail. These findings are expected to facilitate torsional structural design and application of deployable composite structures for aerospace engineering.
Keyword ：
Composite Composite Helical Helical Mechanics Mechanics Structure Structure Twisting Twisting
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| GB/T 7714 | Wang, Bing , Xu, Biao , Zhao, Chenmin et al. Geometric curvature effects-induced twisting mechanics of a double helical structure [J]. | INTERNATIONAL JOURNAL OF SOLIDS AND STRUCTURES , 2025 , 315 . |
| MLA | Wang, Bing et al. "Geometric curvature effects-induced twisting mechanics of a double helical structure" . | INTERNATIONAL JOURNAL OF SOLIDS AND STRUCTURES 315 (2025) . |
| APA | Wang, Bing , Xu, Biao , Zhao, Chenmin , Chen, Xiayu , Guan, Chenglong , Zhong, Jianfeng et al. Geometric curvature effects-induced twisting mechanics of a double helical structure . | INTERNATIONAL JOURNAL OF SOLIDS AND STRUCTURES , 2025 , 315 . |
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| GB/T 7714 | Wang, Bing , Zhan, Lihua , Guan, Chenglong . Advanced Polymer Composites and Applications [J]. | Polymers , 2025 , 17 (15) . |
| MLA | Wang, Bing et al. "Advanced Polymer Composites and Applications" . | Polymers 17 . 15 (2025) . |
| APA | Wang, Bing , Zhan, Lihua , Guan, Chenglong . Advanced Polymer Composites and Applications . | Polymers , 2025 , 17 (15) . |
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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 , 46 : S893-S907 . |
| MLA | Zhan, Lihua et al. "Curing simulation and experimental analysis of composite segmented tools for aerospace applications" . | POLYMER COMPOSITES 46 (2025) : S893-S907 . |
| 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 , 46 , S893-S907 . |
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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 , 46 (11) : 10604-10618 . |
| MLA | Wang, Bing et al. "Viscoelastic mechanics of a bistable composite cylindrical structure" . | POLYMER COMPOSITES 46 . 11 (2025) : 10604-10618 . |
| APA | Wang, Bing , Ye, Junjie , Zhang, Shunnan , Guan, Chenglong , Zhong, Jianfeng , Zhong, Shuncong . Viscoelastic mechanics of a bistable composite cylindrical structure . | POLYMER COMPOSITES , 2025 , 46 (11) , 10604-10618 . |
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Thermal residual stress generated during curing is known to be detrimental to mechanical performance of a carbon composite. Fiber prestressing technique has been developed for decades to counterbalance these negative effects. Although there have been some achievements in development of the prestress mechanisms, these are mainly based on the extrapolations from macroscopic mechanical characterizations, lack of direct evaluation of the in-situ in-plane strain or stress evolution mechanisms, in order to reveal the impact induced by different prestressing methods. Here, we investigated the in-situ strain evolution mechanisms in producing a prestressed carbon composite. Since clamping of the uncured prepreg is the most challenging, both the strain evolutions with and without precured prepreg edges were evaluated to reveal the underlying mechanisms induced by stress relaxation during fiber prestressing. Mechanical tests in terms of Charpy impact and three-point bending, as well as fractured morphology were carried out to evaluate the prestress effects. The underlying mechanisms were then proposed to reveal the fundamentals in producing a prestressed composite. These are expected to revolutionize industrial production and applications of prestressed polymeric composites, indicating detrimental mechanisms on precuring strip ends following conventional prestress procedures. Highlights There is an optimal prestrain level to maximize properties of a composite. Internal strain development is dependent on the fiber clamping methods. Stress relaxation is beneficial to induce compressive stress within a composite. In-situ strain evolution mechanics is revealed for prestressed carbon composite.
Keyword ：
curing curing polymeric composite polymeric composite prestress prestress residual/internal stress residual/internal stress strain strain
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| GB/T 7714 | Zhao, Chenmin , Wang, Bing , Lin, Xinyu et al. In-situ strain evolution mechanisms within a prestressed carbon composite [J]. | POLYMER COMPOSITES , 2024 , 45 (12) : 10826-10838 . |
| MLA | Zhao, Chenmin et al. "In-situ strain evolution mechanisms within a prestressed carbon composite" . | POLYMER COMPOSITES 45 . 12 (2024) : 10826-10838 . |
| APA | Zhao, Chenmin , Wang, Bing , Lin, Xinyu , Yu, Folian , Guan, Chenglong , Zhong, Shuncong . In-situ strain evolution mechanisms within a prestressed carbon composite . | POLYMER COMPOSITES , 2024 , 45 (12) , 10826-10838 . |
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Composite structures have been widely applied in aerospace. Their dimensional geometries and residual strength predictions in service are critical to ensure structural integrity and safety for aerospace applications. Composites are known to show significant viscoelasticity. In this research, we have established a theoretical model and investigated the creep behaviour of a polymeric carbon composite. A Weibull distribution function was fitted to establish the master curve based on the superposition principles in order to construct explore the service-life prediction model. The time-temperature boundary of the composite was created to benefit long-term creep predictions of the aerospace composite.
Keyword ：
Arrhenius Arrhenius Superposition principle Superposition principle Time-Temperature boundary Time-Temperature boundary Weibull distribution function Weibull distribution function
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| GB/T 7714 | Chen, Xiayu , Wang, Bing , Zhao, Chenmin et al. Long-term Creep Prediction of a Carbon Composite [J]. | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 , 2024 : 395-398 . |
| MLA | Chen, Xiayu et al. "Long-term Creep Prediction of a Carbon Composite" . | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 (2024) : 395-398 . |
| APA | Chen, Xiayu , Wang, Bing , Zhao, Chenmin , Guan, Chenglong , Zhong, Shuncong . Long-term Creep Prediction of a Carbon Composite . | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 , 2024 , 395-398 . |
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A bistable composite tape-spring (CTS) structure is stable in both extended and coiled configurations, which can be fully coiled or folded. Its bistable coiling feature has been employed in a Roll-Out Solar Array and successfully deployed in space; its foldable characteristics is analogous to a flexible mechanical hinge, showing great potential to be applied in an aircraft landing gear. Both the structural coiling and folding mechanics are dependent on tape geometry; whilst the correlated scale effect has not been investigated, which significantly constrains its foldable mechanical hinge designs and smart driving analysis in order to further reduce weight and complexity for conventional mechanical hinges. Here, we studied the folding stability mechanics of the CTS structure towards its full tape-length range, where novel stress and shape transitional mechanisms are revealed. This is achieved by investigating the quasi-static folding process of the CTS, where new stable shape features in terms of critical transitional length and stable folded angle are observed and identified through experimental observations, finite element model, as well as theoretical analysis. Theoretical criteria were then determined from the strain energy analysis in comparison to the predefined folded tape shape features. The folding stability mechanisms towards its full tape-length range were proposed in order to facilitate customized flexible hinge design and in-situ smart driving analysis in order to replace conventional mechanical hinges.
Keyword ：
Composite Composite Folding Folding Mechanism Mechanism Stability Stability Tape-spring Tape-spring
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| GB/T 7714 | Chen, Hui , Wang, Bing , Lin, Xueqi et al. Folding mechanics of a bistable composite tape-spring for flexible mechanical hinge [J]. | INTERNATIONAL JOURNAL OF MECHANICAL SCIENCES , 2024 , 272 . |
| MLA | Chen, Hui et al. "Folding mechanics of a bistable composite tape-spring for flexible mechanical hinge" . | INTERNATIONAL JOURNAL OF MECHANICAL SCIENCES 272 (2024) . |
| APA | Chen, Hui , Wang, Bing , Lin, Xueqi , Seffen, Keith A. , Zhong, Shuncong . Folding mechanics of a bistable composite tape-spring for flexible mechanical hinge . | INTERNATIONAL JOURNAL OF MECHANICAL SCIENCES , 2024 , 272 . |
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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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