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学者姓名：关成龙
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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 °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 °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 integrated manufacturing of aerospace composite cryogenic tanks is crucial for enhancing payload efficiency, reducing costs, and leading the aerospace industry upgrade. Composite segmented tool, which balances internal support and mold surface, must not only meet the requirements of disassembly and demolding but also ensure sufficient stiffness without deformation under loads like winding tension and curing shrinkage during tank formation. This article addresses the challenge faced by composite tool with uniformly thick ply stacking schemes, where the weight increases significantly with the rocket body diameter, rendering functions such as disassembly and demolding unfeasible. A global-local optimization approach aimed at achieving variable-thickness ply stacking designs for composite tooling was proposed. Starting with a defined segmented tool design for the phi 3.35 m tank, models for calculating winding tension under complex service conditions and finite element models for curing shrinkage were established. Optimization of ply shapes, dimensions, and sequences using OptiStruct was conducted, which achieved a weight reduction of 34.48% while ensuring that deformations under loading met design standards. Subsequently, the engineering trials for the composite melon petal and wallboard corresponding to the phi 600 mm tank were conducted based on the optimized scheme. The maximum deformations for the two components were 0.43 mm and 0.15 mm, respectively, meeting the manufacturing requirements for engineering applications. The results provide a lightweight, high-stiffness, and detachable tool design scheme for achieving the integrated manufacturing of extra-large (phi 10 m) composite tanks.Highlights The external load was analyzed through theoretical and simulation approaches. The weight of composite tool was significantly reduced after optimization. The engineering prototypes of the segmented tools were achieved. Structure design and optimization for composite tool of aerospace cryogenic tank. image
Keyword ：
aerospace cryogenic tank aerospace cryogenic tank composite segmented tool composite segmented tool curing kinetics curing kinetics finite element simulation finite element simulation ply stacking optimization ply stacking optimization
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| GB/T 7714 | Guan, Chenglong , Chi, Tongming , Zhan, Lihua et al. Service load analysis and ply stacking optimization for composite tool of aerospace cryogenic tank [J]. | POLYMER COMPOSITES , 2024 , 45 (8) : 6845-6860 . |
| MLA | Guan, Chenglong et al. "Service load analysis and ply stacking optimization for composite tool of aerospace cryogenic tank" . | POLYMER COMPOSITES 45 . 8 (2024) : 6845-6860 . |
| APA | Guan, Chenglong , Chi, Tongming , Zhan, Lihua , Yao, Shunming , Chen, Junhao , Xie, Liping et al. Service load analysis and ply stacking optimization for composite tool of aerospace cryogenic tank . | POLYMER COMPOSITES , 2024 , 45 (8) , 6845-6860 . |
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Abstract ：
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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Space deployable structures are able to be deployed from a folded state to a predetermined or desired configuration. They are superior in terms of spatial packaging ratio, controllability, and structural complexity, in order to solve the space limitations for aerospace vehicles. Therefore, they have been applied in structural designs and concepts for various aerospace missions, including space support booms, space deployable antennas, solar panels, as well as flexible solar sails. Recent development of advanced manufacturing technologies and applications of novel smart materials and structures, brings new degree of design freedom to space deployable mechanics, inspiring novel space deployable mechanisms, especially for smart driving and control strategies. Here, we present a review on development of mechanics and smart driving of space deployable structures. Advantages and limitations for various deployable mechanisms are also presented to reveal further insights. The trends and future deployable mechanics are directed by further advancements in terms of modularisation, intelligences, and deployment precision. Multi-disciplinary cross-integrations are leading the way for future breakthroughs in novel deployable mechanics and intelligent driving control for space explorations.
Keyword ：
Deployable Deployable Driving Driving Mechanics Mechanics Smart Smart Structure Structure
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| GB/T 7714 | Wang, Bing , Zhu, Juncheng , Zhong, Shuncong et al. Space deployable mechanics: A review of structures and smart driving [J]. | MATERIALS & DESIGN , 2024 , 237 . |
| MLA | Wang, Bing et al. "Space deployable mechanics: A review of structures and smart driving" . | MATERIALS & DESIGN 237 (2024) . |
| APA | Wang, Bing , Zhu, Juncheng , Zhong, Shuncong , Liang, Wei , Guan, Chenglong . Space deployable mechanics: A review of structures and smart driving . | MATERIALS & DESIGN , 2024 , 237 . |
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Abstract ：
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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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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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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A bistable composite tape-spring (CTS) is a thin-walled open slit tube, which can be coiled or folded into two stable configurations. The CTS has been applied to roll-out-solar-array and successfully launched to space station and micro-satellites based on their one-time deployment performance. There is growing interest on CTS to be applied in reversible deployable structures and foldable mechanical hinges; however, its high-cycle fatigue under large shape folding is still unknown. Here, we device a novel folding fatigue setup to investigate the foldingunfolding cyclic behaviour of the CTS. This is achieved by using a bespoke folding fatigue rig, where both the tape ends of the CTS were clamped separately on rotatable shafts to enable folding under cyclic axial displacements. Since stress concentration is more significant in the snapping fold region, analysis is focused on the peak fatigue stress. It is found that the folding peak stress decreases with the folding cycle: although progressive local damage is observed during 3000 to 100,000 cycles, the CTS is still functional and tends to be stablised after 300,000 folding cycles. The Basquin's law is applied to predict the fatigue life of the CTS, indicating a fatigue life of 1.4E11 folding cycles with a 40% decrease in peak folding stress. These findings are expected to facilitate the structural designs and applications of the CTS to flexible composite hinges.
Keyword ：
Bistable Bistable Composite Composite Folding fatigue Folding fatigue Functional Functional Structural Structural
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| GB/T 7714 | Chen, Xiayu , Du, Dongmei , Wang, Bing et al. High-cycle folding fatigue mechanics of a bistable composite tape-spring [J]. | MATERIALS LETTERS , 2024 , 368 . |
| MLA | Chen, Xiayu et al. "High-cycle folding fatigue mechanics of a bistable composite tape-spring" . | MATERIALS LETTERS 368 (2024) . |
| APA | Chen, Xiayu , Du, Dongmei , Wang, Bing , Jiang, Shihan , Guan, Chenglong , Zhong, Shuncong . High-cycle folding fatigue mechanics of a bistable composite tape-spring . | MATERIALS LETTERS , 2024 , 368 . |
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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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