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QIAN LEI 한국서예학회 2018 서예학연구 Vol.32 No.-
商周时期是中国古代铜器发展的鼎盛时期,西周中期铜器文字既承袭西周中期之遗风,又不断创新,构建出其独特的时代特征。学术界对西周中期铜器的研究,成果丰硕。本文在前人研究的基础上,对西周中期铜器文字书刻发展的历史特征分析研究,并进行相关历史文化的探讨。 本文的研究主要分为三个部分。 第一部分:对西周中期铜器铭文的发展与功用进行阐述,笔者从祭祀、征伐战功、赏赐策命、追孝与颂扬祖先、约剂类五个方面来分析其文字内容。 第二部分:分析了西周中期铜器文字书刻发展的历史特征。分析铜器铭文的产生与发展,然后对穆王、恭王、懿王、孝王时期铜器文字发展作出分析并进行分期。 结论部分:对文章的内容作出总结,探讨西周中期铜器文字书刻发展的历史特征。
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QIAN LEI 한국동양예술학회 2019 동양예술 Vol.45 No.-
《金膺显书学思想及其对中国书法交流刍议》一文主要论述了韩国近现代书坛的代表人物金膺显的生平及其书学思想及其对中国书法交流活动的分析,从金膺显先生的学书背景和学书历程的考察中,可以探察到金膺显的思想和艺术世界。通过对金膺显艺术精神上深厚的感性笔法论和人品论。结合他所处的时代背景。探索其作品中所蕴含的思想和哲学,需要充分理解他的书法观。因为实践出自思想。通过对其作品特征以及其作品对时代所产生影响的分析,定位他在书法史上的地位和位置。最后,通过对金先生与中国书法交流展览与研讨会,来探讨金膺显先生对中韩书法交流的贡献与意义。本篇论文将依照上述体系,通过对金膺显书法世界的研究,展示其在韩国现代书法史上所留下的足迹,以及通过对其作品世界的深入探究,对金膺显进行再次评价,这就是本篇论文的写作目的。并对金膺显先生对推动中韩书法交流的影响作出分析。
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QIAN LEI 한국동양예술학회 2020 동양예술 Vol.47 No.-
本文主要论述了朝鲜后半期受狂狷书风影响,书坛形成了独特的朝鲜书风,最具有代表性的便是“圆峤书学”与“东国真体”等,在书风形成的过程中与中国书法的关系密不可分。本文在考察在朝鲜后半期中韩书法交流的史实基础上,着重把握朝鲜书风形成的过程及其根源。探索朝鲜风形成过程中所蕴含的思想和哲学,这不仅仅是停留在分析朝鲜后半期书法的面貌,更重要的是对探索中韩书法交流、流变具有一定的意义,这也是本文的写作目的。
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QIAN LEI,이재우 한국동양예술학회 2018 동양예술 Vol.41 No.-
韩国三国时期的中韩书法文化交流》一文主要论述韩国三国时期(包括统一新罗)与中国的书法文化交流,本文共有四章内容。第一章为序论,主要介绍了论文写作的有关内容,包括研究意义、研究现状与学术评述、研究思路与方法、资料来源等。第二章为“韩国三国时期中韩文化交流的历史背景”,分别按照韩国三国时期的不同地域。来论述中韩文化交流的历史背景,进而探讨新罗与中国唐文化交流的重要途径是派遣大量留学生和学问僧入唐求学求法。第二章内容,一方面可以作为韩国三国时期中韩艺术交流的背景,另一方面又引出了第三章的内容,即“韩国三国时期中韩书法文化交流”。第三章为“韩国三国时期中韩书法文化交流”。分别论述了韩国三国时期与中国的书法文化交流。本章一方面充分利用了文献资料,另一方面又搜集了考古资料,从而增强了文章的科学性和说服力。第四章为“韩国三国时期中韩书法文化交流的特征”,在前几章论述的基础上,对韩国韩国三国时期中韩书法文化交流的特征进行分析。首先,韩国三国时期中韩书法文化交流具有广泛性,不仅是地域的广泛,更有领域上的广泛性。其次,该时期的书法文化交流的同时伴随着宗教文化的交流,并对其美学思想进行分析。第五章为本文作出结论,论述了古代中韩文化交流的意义,读史明智,这对今天的中韩文化交流依然具有借鉴意义,从而使本文的写作具有了现实意义。
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Maneuverable Aircraft Flight Control Using Nonlinear Dynamic Inversion
Qianlei Jia,Weiguo Zhang,Jingping Shi,Jiayue Hu 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10
Feedback linearization is a mature and highly applied control method in aerospace and other industrial applications. The designed control inputs are used to cancel the nonlinear terms using negative feedback of these terms. This paper focuses on designing a fight simulation model for F-16 fighter jet in responding to diverse sharp maneuvers. F-16 model is expressed by fixed-mass rigid-body six-degree-of freedom (6-DOF) equations of motion, which include the detailed aerodynamic coefficients, the engine model and the actuator models that have lags and limits. The two-time scaled concept of dynamic inversion method divides the aircraft states into groups according to their rate of response. Dynamic Inversion (DI) control law is designed for the fast variables using the aerodynamic control surfaces as inputs. Next, DI is applied to the control of the slow states using the outputs of the fast loop as inputs. Simulation results for the nonlinear flight control system have proved the validity and rationality of the proposed technique .
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Ehab Safwat,Weiguo Zhang,Mei Wu,Yongxi Lyu,Qianlei Jia 제어로봇시스템학회 2018 제어로봇시스템학회 국제학술대회 논문집 Vol.2018 No.10
This paper focuses on autonomous path-following flight under uncertainty and external disturbances. Integrated UAV waypoints guidance scheme based on carrot chasing guidance law is presented. In order to follow a desired path a Virtual Track Point (VTP) is introduced on the path and make the UAV chase it. The UAV updates its heading direction toward the VTP. As time progresses, the UAV will move toward the path and asymptotically follow the path. Nonlinear Dynamic Inversion (NDI) awards the flight control system researchers a straight forward method of deriving control laws for nonlinear systems. The control inputs are used to cancel unwanted terms in the equations of motion using negative feedback of these terms. The two-timescale assumption that separates the fast dynamics which are the three angular rates of the aircraft from the slow dynamics which include the angle of attack, side-slip angle, and bank angle is adopted. NDI control law is designed for the fast variables using the deflection of aerodynamic control surfaces as inputs. Next, NDI is applied to the control of the slow states using the outputs of the fast loop as inputs. Simulation results for the nonlinear flight control system are given to illustrate the effectiveness of the technique. The validation of the designed flight system controller is demonstrated through real flight test.
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