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新媒体时代高职院校工匠精神培养策略和路径探讨

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新闻研究导刊 2024年第5期15卷 169-171页

作者：史亚运山西工程职业学院山西太原030009

随着新媒体技术的迅猛发展,信息传播的方式和速度发生了深刻变化,这为高职院校培养学生的工匠精神带来了新的机遇和挑战。新媒体时代,信息传播效率大幅提升、传播范围迅速扩大,高职院校可以更加便捷地获取和分享优质的教育资源,同时也... 详细信息

随着新媒体技术的迅猛发展,信息传播的方式和速度发生了深刻变化,这为高职院校培养学生的工匠精神带来了新的机遇和挑战。新媒体时代,信息传播效率大幅提升、传播范围迅速扩大,高职院校可以更加便捷地获取和分享优质的教育资源,同时也可以更加灵活地开展各式各样的教育教学活动。这也为高职院校培养学生的工匠精神提供了更加广阔的平台和更加多样化的途径。因此,高职院校需要认真思考如何在新媒体时代有效培养学生的工匠精神,以更好地促进学生的职业发展和社会进步。本研究深入探讨新媒体时代高职院校工匠精神的培养策略和路径,通过文献梳理,分析了工匠精神的内涵,为后续研究提供了理论支撑。在此基础上,阐述了工匠精神培养对于高职院校的重要性,包括提升学生职业竞争力、促进学生全面发展、推动高职院校改革创新、促进产教融合和校企合作等。通过对比不同文献的观点和研究结果,提出了高职院校在新媒体时代培养学生工匠精神的具体策略和建议,包括整合线上线下资源、创新教学方式方法、加强师资队伍建设以及深化产教融合等。本研究旨在为高职院校在新媒体时代更好地培养学生的工匠精神提供有益借鉴和参考,以促进学生的全面发展。

关键词：工匠精神高职院校新媒体就业职业

Oscillation quenching and physical explanation on freeplay-based aeroelastic airfoil in transonic viscous flow

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Chinese Journal of Aeronautics 2023年第10期36卷 124-136页

作者： yayun shi Shun HE Gaowei CUI Gang CHEN Yan LIU State Key Laboratory for Strength and Vibration of Mechanical Structures School of Aerospace EngineeringXi’an Jiaotong UniversityXi’an 710049China School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Beijing Institute of Structure and Environment Engineering Beijing 100076China Shenyang Aircraft Design Institute Shenyang 110036China

Limit Cycle Oscillation(LCO)quenching of a supercritical airfoil(NLR 7301)considering freeplay is investigated in transonic viscous *** Fluid Dynamics(CFD)based on Navier-Stokes equations is implemented to calculate transonic aerodynamic forces.A loosely coupled scheme with steady CFD and an efficient graphic method are developed to obtain the aerodynamic *** quenching phenomenon is observed from the nonlinear dynamic aeroelastic response obtained by using time marching *** the airspeed increases,LCO appears then quenches,forming the first LCO *** the quenching region,LCO occurs again and sustains until the divergence of the response,forming the second LCO *** quenching of LCOs was addressed physically based on the aerodynamic preload and the linear flutter ***“island”of stable region is observed in the flutter boundary,*** flutter speed versus the mean Angle of Attack(AoA).The LCO quenches when the aerodynamic preload crosses this stable region with the increasing of *** LCO quenching of this model in transonic flow is essentially induced by destabilizing effect from aerodynamic preload,since the flutter speed is sensitive to AoA due to aerodynamic nonlinearity.

关键词： Freeplay Nonlinear aeroelasticity Supercritical airfoil Transonic flutter Unsteady flow

Adjoint-based robust optimization design of laminar flow wing under flight condition uncertainties

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Chinese Journal of Aeronautics 2023年第6期36卷 19-34页

作者： Yifu CHEN Hanyue RAO Yiju DENG Tihao YANG yayun shi Junqiang BAI School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China The First Aircraft Design and Research Institute Xi’an 710089China State Key Laboratory for Strength and Vibration of Mechanical Structures School of Aerospace EngineeringXi’an Jiaotong UniversityXi’an 710049China

It is an inherent uncertainty problem that the application of laminar flow technology to the wing of large passenger aircraft is affected by flight *** order to seek a more robust natural laminar flow control effect,it is necessary to develop an effective optimization design ***,attention must be given to the impact of crossflow(CF)instability brought on by the sweep *** paper constructs a robust optimization design framework based on discrete adjoint methods and non-intrusive polynomial *** prediction is implemented by coupled Reynolds-Averaged Navier-Stokes(RANS)and simplified e^(N)method,which can consider both Tollmien-Schlichting(TS)wave and crossflow vortex *** have performed gradient enhancement processing on the general Polynomial Chaos Expansion(PCE),which is advantageous to reduce the computational cost of single uncertainty *** processing takes advantage of the gradient information obtained by solving the coupled adjoint equations considering *** statistical moment gradient solution used for the robust optimization design also uses the derivatives of coupled adjoint *** framework is applied to the robust design of a 25°swept wing with infinite span in transonic *** uncertainty quantification and sensitivity analysis on the baseline wing shows that the uncertainty quantification method in this paper has high accuracy,and qualitatively reveals the factors that dominate in different flow field *** the robust optimization design,the mean and standard deviation of the drag coefficient can be reduced by 29%and 45%,respectively,and compared with the deterministic optimization design results,there is less possibility of forming shock waves under flight condition *** optimization results illustrate the trade-off between the transition delay and the wave drag reduction.

关键词： Adjoint method Gradient-based optimization Laminar-turbulent transition Robust design Uncertainty propagation

Engineering Sodium Metal Anode with Sodiophilic Bismuthide Penetration for Dendrite-Free and High-Rate Sodium-Ion Battery

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Engineering 2022年第4期8卷 87-94页

作者： Wanyu Zhao Min Guo Zhijun Zuo Xiaoli Zhao Huanglin Dou Yijie Zhang shiying Li Zichen Wu yayun shi Zifeng Ma Xiaowei Yang Key Laboratory of Advanced Civil Engineering Materials of Ministry of Education School of Materials Science and EngineeringTongji UniversityShanghai 201804China School of Chemistry and Chemical Engineering Shaoxing UniversityShaoxing 312000China Key Laboratory of Coal Science and Technology of Ministry of Education and Shanxi Province Taiyuan University of TechnologyTaiyuan 030024China Shanghai Electrochemical Energy Devices Research Center School of Chemistry and Chemical EngineeringShanghai Jiao Tong UniversityShanghai 200240China

Sodium(Na)metal batteries with a high volumetric energy density that can be operated at high rates are highly ***,an uneven Na-ion migration in bulk Na anodes leads to localized deposition/dissolution of sodium during high-rate plating/stripping behaviors,followed by severe dendrite growth and loose ***,we engineer the Na hybrid anode with sodiophilic Na_(3)Bi-penetration to develop the abundant phase-boundary ionic transport *** to intrinsic Na,the reduced adsorption energy and ion-diffusion barrier on Na_(3)Bi ensure even Na^(+)nucleation and rapid Na^(+)migration within the hybrid electrode,leading to uniform deposition and dissolution at high current ***,the bismuthide enables compact Na deposition within the sodiophilic framework during cycling,thus favoring a high volumetric ***,the obtained anode was endowed with a high current density(up to 5 mA∙cm^(−2)),high areal capacity(up to 5 mA∙h∙cm^(−2)),and long-term cycling stability(up to 2800 h at 2 mA∙cm^(−2)).

关键词： Sodium metal anode Dendrite-free Compact electrodeposition Sodiophilic bismuthide Ion diffusion barrier

Numerical analysis and optimization of boundary layer suction on airfoils

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Chinese Journal of Aeronautics 2015年第2期28卷 357-367页

作者： shi yayun Bai Junqiang Hua Jun Yang Tihao School of Aerodynamics Northwestern Polytechnical University Chinese Aeronautical Establishment

Numerical approach of hybrid laminar flow control （HLFC） is investigated for the suc- tion hole with a width between 0.5 mm and 7 mm. The accuracy of Menter and Langtry＇s transition model applied for simulating the flow with boundary layer suction is validated. The experiment data are compared with the computational results. The solutions show that this transition model can pre- dict the transition position with suction control accurately. A well designed laminar airfoil is selected in the present research. For suction control with a single hole, the physical mechanism of suction control, including the impact of suction coefficient and the width and position of the suc- tion hole on control results, is analyzed. The single hole simulation results indicate that it is favor- able for transition delay and drag reduction to increase the suction coefficient and set the hole position closer to the trailing edge properly. The modified radial basis function （RBF） neural net- work and the modified differential evolution algorithm are used to optimize the design for suction control with three holes. The design variables are suction coefficient, hole width, hole position and hole spacing. The optimization target is to obtain the minimum drag coefficient. After optimization, the transition delay can be up to 17% and the aerodynamic drag coefficient can decrease by 12.1%.

关键词： Active control Hybrid laminar flow control(HLFC) Neural network Optimization Radial basis function (RBF)Transition prediction

Transition prediction and sensitivity analysis for a natural laminar flow wing glove flight experiment

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Chinese Journal of Aeronautics 2021年第8期34卷 34-47页

作者： Tihao YANG Hai ZHONG Yifu CHEN yayun shi Junqiang BAI Feifei QIN Northwestern Polytechnical University Xi'an 710072China Chinese Flight Test Establishment Xi'an 710089China Xi’an Jiaotong University Xi'an 710049China ETH Zürich(Swiss Federal Institute of Technology in Zurich) Zurich 8093Switzerland

Natural laminar flow technology can significantly reduce aircraft aerodynamic drag and has excellent technical appeal for transport aircraft development with high aerodynamic *** and efficiently predicting the laminar-to-turbulent transition and revealing the maintenance mechanism of laminar flow in a transport aircraft’s flight environment are significant for developing natural laminar flow *** this research,we carry out natural laminar flow flight experiments with different Reynolds numbers and angles of *** critical N-factor is calibrated as 9.0 using flight experimental data and linear stability theory from a statistical perspective,which makes sure that the relative error of transition location is within 5%.We then implement a simplified e^(N) transition prediction method with a similar accuracy compared with linear stability *** compute the sensitivity information for the simplified eN method with an adjointbased method,using the automatic differentiation technique(ADjoint).The impact of Reynolds numbers and pressure distributions on TS waves is analyzed using the sensitivity *** the sensitivity analysis,we find that:favorable pressure gradients not only suppress the development of TS waves but also decrease their sensitivity to Reynolds numbers;there exist three special regions which are very sensitive to the pressure distribution,and the sensitivity decreases as the local favorable pressure gradient *** proposed sensitivity analysis method enables robust natural laminar flow wings design.

关键词： e^(N)method Flight experiment Natural laminar flow Sensitivity analysis Transition prediction

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设计主导下当代土家织锦生产的问题与风险

艺术设计研究 2022年第2期 74-78,34页

作者：石雅云刘晓春中山大学中文系中山大学中国非物质文化遗产研究中心

当代土家织锦的生产正经历着设计者与制作者相分离的重要转变。设计者通过“降低工艺难度”“剔除手工性”“增强故事性”的方式,不断弱化织造工艺和织造群体的价值,并就此获得了织锦生产的主导权。服务于商业资本逻辑的设计主导生产后... 详细信息

当代土家织锦的生产正经历着设计者与制作者相分离的重要转变。设计者通过“降低工艺难度”“剔除手工性”“增强故事性”的方式,不断弱化织造工艺和织造群体的价值,并就此获得了织锦生产的主导权。服务于商业资本逻辑的设计主导生产后,手工艺人对技艺和本土文化的所有权遭到剥夺,由此带来了“去技艺化”“去主体化”“去意义化”的风险。设计的助推与动力作用不应以遮蔽手工艺人群体的创作力与文化主体性为代价。正视设计主导当代传统手工艺生产可能产生的问题,才能更好地探索传统手工艺当代传承与发展的路径。

关键词：土家织锦设计主导技艺的话语权

Optimization and Analysis of Hybrid Laminar Flow Control Wings Based on Infinite Span Wings

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Optimization and Analysis of Hybrid Laminar Flow Control Win...

2016年航空科学与技术全国博士生学术论坛

作者： Yang Tihao Bai Junqiang shi yayun Northwestern Polytechnical University

The optimizations of hybrid laminar flow control（HLFC） wings are parametrically studied with variations in sweep angles, different coefficients and different Reynolds number. The influence of transition induced by crossflow has been included. A CFD solver with the linear stability theory code has been implemented and coupled into an optimization framework. The comparison between the computational results and the experiment data of NLF（2）-0415 wing proves that the transition model is capable of predicting accurate transition location. Then, HLFC wings are optimized with target of minimum drag. Design results shown that, large leading edge sweep angles and high value of the Reynolds number accelerate the instability of CF and TS disturbance waves. But suction control can efficient suppress the development of disturbance waves near theleading edge. And laminar flow can be obtained with suitable pressure distributions. The best pressure distributions have a gentle negative pressure gradient near the leading edge and a small favorable pressure gradient behind it. Nose down pitching moment coefficients may limit the further extending of laminar flow. The optimum HLFC wing with minimum drag coefficients is a balance of friction drag, pressure drag and trim drag.

关键词： Hybrid laminar flow control Optimization design Active control Transonic flow FFD

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基于离散伴随的层流翼优化设计方法

航空学报 2022年第12期43卷 230-249页

作者：杨体浩王一雯王雨桐史亚云周铸西北工业大学航空学院西安710072 西北工业大学无人系统技术研究院西安710072 西安交通大学航天学院西安710049 中国空气动力研究与发展中心绵阳621000

层流技术是未来发展绿色航空的核心技术,可处理大规模设计变量的高效、鲁棒的优化设计方法是推动层流技术工程应用转化的关键环节之一。基于高可信度RANS求解器,结合准三维层流边界层方程、Drela-Giles和C1准则,建立了可同时捕捉Tollmie... 详细信息

层流技术是未来发展绿色航空的核心技术,可处理大规模设计变量的高效、鲁棒的优化设计方法是推动层流技术工程应用转化的关键环节之一。基于高可信度RANS求解器,结合准三维层流边界层方程、Drela-Giles和C1准则,建立了可同时捕捉Tollmien-Schlichting(TS)和Crossflow(CF)不稳定性的转捩预测方法,与典型风洞和飞行试验对比,验证了该方法的可靠性。通过严格物面插值、获得准确的间歇因子函数以剔除气动力计算引入的数值噪声,精确推导了考虑转捩的耦合伴随方程,并结合无矩阵存储技术、链式求导法则、反向混合自动微分及Coupled Krylov(CK)算法发展了耦合伴随方程高效求解方法,最终建立了基于离散伴随的层流翼梯度优化设计方法。针对典型客机翼身组合体构型的气动优化显著推迟了转捩,获得了10.48%的减阻收益。优化结果表明,建立的层流翼梯度优化方法能够有效处理多种转捩机制并存的复杂三维层流翼优化问题。

关键词：离散伴随层流转捩减阻梯度优化流向转捩横流转捩