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Semisynthesis of homogeneous spike RBD glycoforms from SARS-CoV-2 for profiling the correlations between glycan composition and function

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National Science Review 2024年第2期11卷 145-154页

作者： Farong Ye Cheng Li Feng-Liang Liu Xinliang Liu Peng Xu Rong-Hua Luo wenping song Yong-Tang Zheng Tianlei Ying Biao Yu Ping Wang Center for Chemical Glycobiology Frontiers Science Center for Transformative Molecules Zhangjiang Institute for Advanced Study School of Chemistry and Chemical Engineering Shanghai Jiao Tong University MOE/NHC/CAMS Key Laboratory of Medical Molecular Virology Shanghai Frontiers Science Center of Pathogenic Microorganisms and Infection Shanghai Institute of Infectious Disease and BiosecurityShanghai Engineering Research Center for Synthetic ImmunologySchool of Basic Medical Sciences Shanghai Medical College Fudan University Key Laboratory of Animal Models and Human Disease Mechanisms of Chinese Academy of Sciences/Key Laboratory of Bioactive Peptides of Yunnan Province Center for Biosafety Mega-Science Kunming Institute of ZoologyChinese Academy of Sciences State Key Laboratory of Bioorganic and Natural Products Chemistry Center for Excellence in Molecular Synthesis Shanghai Institute of Organic Chemistry Chinese Academy of Sciences Shenzhen Research Institute of Shanghai Jiao Tong University

Vaccines have been the primary remedy in the global fight against coronavirus disease 2019（COVID-19）.The receptor-binding domain（RBD） of the spike protein, a critical viral immunogen, is affected by the heterogeneity of its glycan structures and relatively low immunogenicity. Here, we describe a scalable synthetic platform that enables the precise synthesis of homogeneously glycosylated RBD, facilitating the elucidation of carbohydrate structure–function relationships. Five homogeneously glycosylated RBDs bearing biantennary glycans were prepared, three of which were conjugated to T-helper epitope(Tpep) from tetanus toxoid to improve their weak immune response. Relative to natural HEK293-derived RBD, synthetic RBDs with biantennary N-glycan elicited a higher level of neutralising antibodies against SARS-CoV-2 in mice. Furthermore, RBDs containing Tpepelicited significant immune responses in transgenic mice expressing human angiotensin-converting enzyme 2. Our collective data suggest that trimming the N-glycans and Tpepconjugation of RBD could potentially serve as an effective strategy for developing subunit vaccines providing efficient protection.

关键词： peptide ligation glycosylation glycoprotein

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不同级别宫颈鳞状上皮内病变患者宫颈分泌物各指标检测情况及其临床意义

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中国微生态学杂志 2024年第1期36卷 85-89页

作者：程小萍潘琳宋文萍北京市和平里医院妇科北京100013

目的探讨不同级别宫颈鳞状上皮内病变(SIL)患者宫颈分泌物各指标检测情况及其临床意义,为该类患者的治疗提供参考。方法选取北京市和平里医院妇科2022年3月至2023年5月164例SIL患者为研究对象,根据病理检查结果将患者分为宫颈低度鳞状... 详细信息

目的探讨不同级别宫颈鳞状上皮内病变(SIL)患者宫颈分泌物各指标检测情况及其临床意义,为该类患者的治疗提供参考。方法选取北京市和平里医院妇科2022年3月至2023年5月164例SIL患者为研究对象,根据病理检查结果将患者分为宫颈低度鳞状上皮内病变(LSIL)组(n=72)和宫颈高度鳞状上皮内病变(HSIL)组(n=92),另纳入宫颈癌患者21例为宫颈癌组、健康女性60例为健康组。统计4组受试者阴道白细胞酯酶(LE)、N-乙酰基氨基半乳糖苷酶(NAG)、唾液酸苷酶(SNA)、过氧化氢(H_(2)O_(2))阳性率及pH值;观察4组受试者阴道滴虫感染情况及需氧菌性阴道炎(AV)、细菌性阴道病(BV)阳性率;评估4组受试者阴道清洁度;观察4组受试者HPV感染情况并通过Spearman分析评估宫颈病变程度与阴道微环境、HPV感染的相关性。结果LSIL组、HSIL组、宫颈癌组患者阴道LE、NAG、SNA、H_(2)O_(2)阳性率及pH值均显著高于健康组(均P<0.05),且随着宫颈病变程度的加重,阴道LE、NAG、SNA、H_(2)O_(2)阳性率及pH值均呈上升趋势(均P<0.05)。LSIL组、HSIL组、宫颈癌组患者滴虫感染率及AV、BV阳性率均显著高于健康组(均P<0.05),且随着宫颈病变程度的加重,滴虫感染率及AV、BV阳性率均呈上升趋势(均P<0.05)。LSIL组、HSIL组、宫颈癌组阴道清洁度Ⅰ~Ⅱ级患者占比低于健康组,Ⅲ~Ⅳ级患者占比高于健康组(均P<0.05),且随着宫颈病变程度的加重,阴道清洁度越来越差(均P<0.05)。LSIL组、HSIL组、宫颈癌组高危型HPV感染患者占比、HPV感染总发生率均高于健康组(均P<0.05),随着宫颈病变程度的加重,高危型HPV感染、HPV感染总发生率均呈上升趋势(均P<0.05)。经相关性分析,宫颈病变程度与滴虫感染、AV、BV、LE、NAG、SNA、H_(2)O_(2)、pH值、阴道清洁度、HPV感染均呈正相关(均P<0.05)。结论SIL患者宫颈微生态处于显著失衡状态,宫颈病变程度与分泌物各指标具有显著相关性。

关键词：宫颈鳞状上皮内病变宫颈分泌物微生态宫颈癌

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高速共轴刚性旋翼非定常流动高精度数值模拟

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航空学报 2024年第9期45卷 169-188页

作者：韩少强宋文萍韩忠华许建华四川大学计算机学院天府工程数值模拟与软件创新中心成都610065 西北工业大学航空学院气动与多学科优化设计研究所西安710072

高速共轴刚性旋翼在前飞状态下会产生复杂的非定常涡干扰流动结构及较强的激波,对高速直升机的气动、噪声及振动特性有着重要的影响,这些流动现象的高分辨率捕捉是高速直升机CFD研究中的难点之一。发展了可在大规模并行计算中实现负载... 详细信息

高速共轴刚性旋翼在前飞状态下会产生复杂的非定常涡干扰流动结构及较强的激波,对高速直升机的气动、噪声及振动特性有着重要的影响,这些流动现象的高分辨率捕捉是高速直升机CFD研究中的难点之一。发展了可在大规模并行计算中实现负载均衡的运动嵌套网格系统,提出了能够在人工边界上保持高阶精度的高效嵌套关系辨识及插值方法;在嵌套网格上应用了发展的谱特性自适应优化的五阶非多项式重构WENO格式(WENO-K)和改进的延迟脱体涡模拟(IDDES)方法,从而提高对非定常多尺度流动结构的空间数值分辨率及时间保持能力。针对简单四桨共轴旋翼及X-2验证机的八桨共轴旋翼,进行了非定常涡流场高精度数值模拟,研究了高速共轴刚性旋翼桨尖涡结构的生成、发展、演化过程及涡干扰机制。计算结果表明,高阶格式结合IDDES方法能够显著降低数值耗散并提高多尺度湍流结构的分辨率,捕捉到了桨尖涡的高速发展演化过程及桨-涡干扰现象,并能够分辨出桨叶后缘生成的马蹄状的精细涡面结构,有利于高速共轴旋翼涡流场干扰机制及气动噪声的深入研究。

关键词：高速直升机共轴刚性旋翼高阶格式 IDDES 非定常流动桨尖涡

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基于空间嵌套径向基函数的高效并行网格变形方法

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航空学报 2024年第15期45卷 206-217页

作者：路宽宋文萍郭恒博叶坤王跃韩忠华西北工业大学航空学院气动与多学科优化设计研究所西安710072 中国航空工业集团沈阳飞机设计研究所沈阳110035 飞行器基础布局全国重点实验室西安710072

高效的网格变形方法可以大幅提高流固耦合数值模拟、基于高精度计算流体动力学(CFD)分析的气动外形优化设计等问题的计算效率。常规的基于径向基函数(RBF)的网格变形方法在变形控制点增多时,会引起网格变形计算量激增,而采用减少变形控... 详细信息

高效的网格变形方法可以大幅提高流固耦合数值模拟、基于高精度计算流体动力学(CFD)分析的气动外形优化设计等问题的计算效率。常规的基于径向基函数(RBF)的网格变形方法在变形控制点增多时,会引起网格变形计算量激增,而采用减少变形控制点的方法减小计算量,会带来拟合精度的损失。针对已有RBF网格变形方法计算效率与计算精度不能两全的现状,提出了一种空间嵌套径向基函数模型(SN-RBF),发展了基于SN-RBF模型的高效网格变形方法,在保证网格变形精度的同时大幅度提高了网格变形效率。发展的SN-RBF模型采用多个物理空间相互重叠的子模型代替样本点较多的径向基函数模型,大幅度缩短了径向基函数法网格变形的建模时间。鉴于其便于并行的优良特性,还发展了基于该网格变形方法的并行建模方法与并行网格变形方法,使得网格变形效率得到进一步提升。测试算例表明,建模样本点越多,网格变形效率提升越显著。其中CRM翼身组合体算例,建模效率提升高达16947倍,网格变形效率提升高达5218倍。

关键词：径向基函数空间嵌套径向基函数网格变形并行建模

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企业应对产品技术合规风险的策略与实践

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质量与认证 2024年第7期 75-78页

作者：宋文平深圳创维数字技术有限公司

在经济全球化和技术快速发展的背景下,企业面临着日益复杂的产品技术合规风险。这些风险不仅涉及产品安全、环保标准和知识产权保护,还可能受到多变的国际贸易规则的影响。技术合规风险的管理对于保障企业持续运营、维护企业声誉和避免... 详细信息

在经济全球化和技术快速发展的背景下,企业面临着日益复杂的产品技术合规风险。这些风险不仅涉及产品安全、环保标准和知识产权保护,还可能受到多变的国际贸易规则的影响。技术合规风险的管理对于保障企业持续运营、维护企业声誉和避免法律后果至关重要[1]。本文旨在探讨企业如何通过建立有效的合规管理体系,并对其进行细致的合规风险评估,以应对产品技术合规风险,确保企业可持续发展和市场竞争力。

关键词：技术合规风险风险管理风险评估内部控制应急计划

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Multi-infill strategy for kriging models used in variable fidelity optimization

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Chinese Journal of Aeronautics 2018年第3期31卷 448-456页

作者： Chao song Xudong YANG wenping song National Key Laboratory of Science and Technology on Aerodynamic Design and Research Northwestern Polytechnical University

In this paper, a computationally efficient optimization method for aerodynamic design has been developed. The low-fidelity model and the multi-infill strategy are utilized in this ***-fidelity data is employed to provide a good global trend for model prediction, and multiple sample points chosen by different infill criteria in each updating cycle are used to enhance the exploitation and exploration ability of the optimization approach. Take the advantages of lowfidelity model and the multi-infill strategy, and no initial sample for the high-fidelity model is needed. This approach is applied to an airfoil design case and a high-dimensional wing design *** saves a large number of high-fidelity function evaluations for initial model construction. What＇s more, faster reduction of an aerodynamic function is achieved, when compared to ordinary kriging using the multi-infill strategy and variable-fidelity model using single infill criterion. The results indicate that the developed approach has a promising application to efficient aerodynamic design when high-fidelity analyses are involved.

关键词： Aerodynamics Infill criteria Kriging models Multi-infill Optimization

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Aerodynamic performance of owl-like airfoil undergoing bio-inspired flapping kinematics

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Chinese Journal of Aeronautics 2021年第5期34卷 239-252页

作者： Xinyu LANG Bifeng song Wenqing YANG wenping song School of Aeronautics Northwestern Poly technical UniversityXi'an 710072China Research&Development Institute of Northwestern Polytechnical University in Shenzhen Shenzhen 518057China Yangtze River Delta Research Institute of Northwestern Polytechnical University Taicang 215400China

Natural flyers have extraordinary flight skills and their prominent aerodynamic performance has attracted a lot of ***,the aerodynamic mechanism of birds’flapping wing kinematics still lacks in-depth *** this paper,the aerodynamic performance of owl-like airfoil undergoing bio-inspired flapping kinematics extracted from a free-flying owl wing has been numerically *** overset mesh technique is used to deal with the large range movements of flapping *** bio-inspired kinematics consist of plunging and pitching movement.A pure sinusoidal motion and a defined motion composed of plunging of sinusoidal motion and pitching of the bio-inspired kinematics are selected for *** other two NACA airfoils are also selected to figure out the advantages of the owl-like *** is found that the cambered owl-like airfoil can enhance lift during the *** bio-inspired kinematics have an obvious advantage in lift generation with a presence of higher peak lift and positive lift over a wider proportion of the flapping ***,the bio-inspired motion is more economical for a lower power consumption compared with the sinusoidal *** sinusoidal flapping motion is better for thrust generation for a higher peak thrust value in both upstroke and downstroke,while the bio-inspired kinematics mainly generate thrust during the downstroke but produce more drag during the *** defined motion has similar lift performance with the bio-inspired kinematics,while it consumes more energy and generates less *** unsteady flow field around airfoils is also analyzed to explain the corresponding *** research in this paper is helpful to understand the flight mechanism of birds and to design a micro air vehicle with higher performance.

关键词： Aerodynamic performance Bio-inspired kinematics Flapping airfoils Low Reynolds number Micro aerial vehicles

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A novel high-order scheme for numerical simulation of wake flow over helicopter rotors in hover

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Chinese Journal of Aeronautics 2022年第5期35卷 260-274页

作者： Shaoqiang HAN wenping song Zhonghua HAN Institute of Aerodynamic and Multidisciplinary Design Optimization National Key Laboratory of Science and Technology on Aerodynamic Design and ResearchSchool of AeronauticsNorthwestern Polytechnical UniversityXi’an 710072China

Accurate prediction of tip vortices is crucial for predicting the hovering performance of a helicopter rotor.A new high-order scheme(we call it WENO-K)proposed by our research group is employed to minimize numerical dissipation and extended to numerical simulation of unsteady compressible viscous flows dominated by tip vortices over hovering ***-K is referred to as an adaptively optimized WENO scheme with Gauss-Kriging reconstruction,and its advantage is to reduce dissipation in smooth regions of flow while preserving high-resolution around *** WENO-K scheme is adopted to reconstruct left and right state values within the Roe Riemann solver updating the inviscid fluxes on a structured dynamic overset *** minimize the accuracy loss for high-order reconstruction on artificial boundaries of overset grid,a method of multilayer fringes is proposed to carry out interpolation between background grid and blade *** parallel computing considering automatic load balance on averagely partitioned overset grid is developed to reduce the wall-clock time of an unsteady *** results for Caradonna-Tung(C-T)rotor in hover at the conditions of subsonic and transonic tip Mach numbers show that the thrust coefficient error for the result of WENO-K scheme is no more than 3%.Compared with WENO-JS scheme,WENO-K scheme achieves about 40%improvement on accuracy of predicting rotor thrust with only 4.1%extra computational *** importantly,WENO-K scheme can capture more sophisticated unsteady flow structures and resolve tip vortices to a larger wake age with an increment of about 270°compared to WENO-JS scheme.

关键词： Dynamic overset grid Helicopter rotors High-order scheme Unsteady flow Vortex flow WENO scheme

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Far-field sonic boom prediction considering atmospheric turbulence effects: An improved approach

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Chinese Journal of Aeronautics 2022年第9期35卷 208-225页

作者： Jianling QIAO Zhonghua HAN Liwen ZHANG wenping song Bifeng song Institute of Aerodynamic and Multidisciplinary Design Optimization School of AeronauticsNorthwestern Polytechnical UniversityXi'an 710071China National Key Laboratory of Science and Technology on Aerodynamic Design and Research School of AeronauticsNorthwestern Polytechnical UniversityXi'an710071China

Accurate prediction of sonic boom is one of key challenges for the design of a low-boom supersonic aircraft. For most of available far-field prediction methods, the effect of atmospheric turbulence appearing in the planetary boundary layer cannot be considered, which results in remarkable inaccuracy of predicting ground-level sonic boom waveform. Although some efforts have been made to overcome the shortcoming, the turbulence effects are not yet well described so far. This article proposes an improved method by extending the two-dimensional Heterogeneous One-Way Approximation for the Resolution of Diffraction(HOWARD) equation to account for the axial and transverse convections of wind fluctuation as well as the effect of temperature fluctuation. The proposed method is validated by comparing the predictions with the flight-test data of JAXA D-SEND#1 LBM, which shows that the result of the proposed method is in better agreement with the flight-test data than that of the method without considering atmospheric turbulence ***, distortion mechanism of sonic boom waveforms caused by atmospheric turbulence is analyzed by using the proposed method. It is indicated that the effect of turbulent convection makes uniform sonic-boom wavefronts irregular, which creates the condition of diffraction effect to perturb waveforms. Finally, the proposed method is applied to investigate the behavior of two types of waveforms given by the sonic boom minimization theory. Results show that a far-field waveform with a weaker initial shock is more beneficial for low-boom design of a supersonic aircraft.

关键词： Atmospheric turbulence Augmented Burgers equation HOWARD equation Sonic boom Supersonic transport

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Aerodynamic performance enhancement forflapping airfoils by co-flow jet

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Chinese Journal of Aeronautics 2020年第10期33卷 2535-2554页

作者： Tao WU Bifeng song wenping song Wenqing YANG Zhonghua HAN School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Yangtze River Delta Research Institute Northwestern Polytechnical UniversityTaicang 215400China Research&Development Institute Northwestern Polytechnical University in ShenzhenShenzhen 518057China

Introducing active flow control into the design of flapping wing is an effective way to enhance its aerodynamic *** this paper,a novel active flow control technology called Co-Flow Jet(CFJ)is applied to flapping *** effect of CFJ on aerodynamic performance of flapping airfoils at low Reynolds number is numerically investigated using Unsteady Reynolds Averaged Navier-Stokes(URANS)simulation with Spalart-Allmaras(SA)turbulence *** methods are validated by a NACA6415-based CFJ airfoil case and a S809 pitching airfoil *** NACA6415 baseline airfoil and NACA6415-based CFJ airfoil with jet-off and jet-on are simulated in flapping motion,with Reynolds number 70,000 and reduced frequency *** a result,CFJ airfoils with jet-on generally have better lift and thrust characteristics than baseline airfoils and jet-off airfoil when Cμgreater than 0.04,which results from the CFJ effect of reducing flow separation by injecting high-energy fluid into boundary ***,typical kinematic and geometric parameters,including the reduced frequency and the positions of the suction and injection slot,are systematically studied to figure out their influence on aerodynamic performance of the CFJ *** a variable Cμjet control strategy is proposed to further improve effective propulsive *** with using constant Cμ,an increase of effective propulsive efficiency by22.6%has been achieved by using prescribed variable CμNACA6415-based CFJ airfoil at frequency *** study may provide some guidance to performance enhancement for Flapping wing Micro Air Vehicles(FMAV).

关键词： Aerodynamic performance Co-flow jet Flapping airfoils Flow control Propulsive efficiency

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