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学者姓名：关成龙
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Abstract ：
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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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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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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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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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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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 °.
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 | De-chao Zhang , Li-hua Zhan , Bo-lin Ma 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 | De-chao Zhang 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 | De-chao Zhang , Li-hua Zhan , Bo-lin Ma , Shun-ming Yao , Jin-zhan Guo , Cheng-long Guan 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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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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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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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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