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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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Abstract ：
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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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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Abstract ：
Glass Fiber-Reinforced Polymer (GFRP) finds extensive applications in the high-end equipment manufacturing industry owing to its advantages of light weight, high strength, and corrosion resistance. Since the residual stress in GFRP builds up during the curing process and affect its mechanical properties and service life, the characterization of the residual stress in GFRP is crucial. In this study, we establish a theoretical model based on the anisotropic stress-optics law for the orthorhombic crystalline system to describe the terahertz-elasticity of GFRP and calibrate the stress optical coefficients of GFRP. First, the residual stress in GFRP at different curing temperatures are measured by fiber Bragg grating sensors. Then, the refractive index of GFRP with different residual stress are obtained based on transmission-type THz-TDS. Finally, based on the proposed photoelastic model of GFRP, the stress optical coefficients of GFRP are measured by combining the measurement results of residual stress and refractive index. The experimental results show that the refractive index of GFRP decreases with the increase of residual stress; the stress optical coefficients of GFRP are determined as q11 = -5.612 x 10-9 Pa- 1, q12 = -2.548 x 10-9 Pa- 1, q21 = -1.305 x 10- 8 Pa- 1, q22 = -1.408 x 10-9 Pa- 1. The modeling of terahertz photoelasticity in GFRP and the determination of stress optical coefficients provide a basis for characterizing residual stress in GFRP by THz-TDS.
Keyword ：
GFRP GFRP Photoelastic model Photoelastic model Residual stress Residual stress Terahertz Terahertz
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| GB/T 7714 | Lin, Huisheng , Shi, Tingting , Huang, Yi et al. Measurement of stress optical coefficients for GFRP based on terahertz time-domain spectroscopy [J]. | OPTICAL MATERIALS , 2024 , 157 . |
| MLA | Lin, Huisheng et al. "Measurement of stress optical coefficients for GFRP based on terahertz time-domain spectroscopy" . | OPTICAL MATERIALS 157 (2024) . |
| APA | Lin, Huisheng , Shi, Tingting , Huang, Yi , Zhong, Shuncong , Wang, Bing , Zhang, Zhenghao et al. Measurement of stress optical coefficients for GFRP based on terahertz time-domain spectroscopy . | OPTICAL MATERIALS , 2024 , 157 . |
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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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Abstract ：
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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Thermal residual stress generated during curing is known to be detrimental to mechanical performance of a fibre reinforced composite. Elastic fibre prestressing has been developed to reduce the negative effects induced by the curing generated thermal residual stress, but the acting mechanisms of prestrain on dynamic interfacial strengthening within the composite is still unknown. In this paper, a bespoke fibre prestressing device was developed to apply biaxial stretching to a plain-weave carbon fibre reinforced epoxy prepreg with different prestrain levels. The effects of prestrain were then investigated by carrying out dynamic thermomechanical analysis. It is found that fibre prestraining is able to improve the fibre-matrix interface strength, and there is an optimal prestrain level to maximise the prestrain benefits. The prestrain mechanisms are then presented based on these observations. The prestrain composite can effectively improve its negative impact due to thermal residual stress, thereby improving its industrial applications.
Keyword ：
Interface Interface Mechanism Mechanism Prestrain Prestrain Thermodynamic Thermodynamic
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| GB/T 7714 | Zhao, Chenmin , Wang, Bing , Chen, Xiayu et al. Interfacial Strengthening Mechanics within a Prestrained Composite [J]. | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 , 2024 : 390-394 . |
| MLA | Zhao, Chenmin et al. "Interfacial Strengthening Mechanics within a Prestrained Composite" . | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 (2024) : 390-394 . |
| APA | Zhao, Chenmin , Wang, Bing , Chen, Xiayu , Guan, Chenglong , Zhong, Shuncong . Interfacial Strengthening Mechanics within a Prestrained Composite . | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 , 2024 , 390-394 . |
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Reducing structural weight and improving the efficiency of the structure are the eternal themes of the spacecraft. The cryogenic tank accounts for more than 60% of the dry weight of the whole vehicle, which directly determines the overall lightweight level of the vehicle. Compared with metal tanks, carbon fiber reinforced resin matrix composite tanks could achieve a structural weight reduction of more than 20%, which is the key to improve the efficiency of transportation and lead the upgrade of the aerospace industry. In this paper, aiming at the problems of unknown deformation/performance evolution law and difficult determination of process parameters in the curing process of composite tank under the constraints of large size and complex structure, the variations of thermophysical parameters of aerospace composite materials with temperature and curing degree is found out, and the simulation prediction models of temperature field and deformation field in the whole curing process of components is established. The effective prediction of the deformation and quality of tank wallboard is realized, which provides theoretical and methodological support for the high-quality forming of aerospace composite components.
Keyword ：
Composite cryogenic tank Composite cryogenic tank Deformation-performance synergetic manufacturing Deformation-performance synergetic manufacturing Finite element simulation Finite element simulation
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| GB/T 7714 | Guan, Chenglong , Chen, Junhao , Zhan, Lihua et al. Simulation Analysis for Deformation and Performance Evolution of Aerospace Composite Tank During Curing Process [J]. | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 , 2024 : 210-215 . |
| MLA | Guan, Chenglong et al. "Simulation Analysis for Deformation and Performance Evolution of Aerospace Composite Tank During Curing Process" . | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 (2024) : 210-215 . |
| APA | Guan, Chenglong , Chen, Junhao , Zhan, Lihua , Chi, Tongming , Wang, Bing , Zhong, Shuncong . Simulation Analysis for Deformation and Performance Evolution of Aerospace Composite Tank During Curing Process . | PROCEEDINGS OF THE 2024 3RD INTERNATIONAL SYMPOSIUM ON INTELLIGENT UNMANNED SYSTEMS AND ARTIFICIAL INTELLIGENCE, SIUSAI 2024 , 2024 , 210-215 . |
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