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| 1 | Recent advance in nonlinear aeroelastic analysis and control of the aircraft显示文摘A review on the recent advance in nonlinear aeroelasticity of the aircraft is presented in this paper. The nonlinear aeroelastic problems are divided into three types based on different research objects,namely the two dimensional airfoil,the wing,and the full aircraft. Different nonlinearities encountered in aeroelastic systems are discussed firstly,where the emphases is placed on new nonlinear model to describe tested nonlinear relationship. Research techniques,especially new theoretical methods and aeroelastic flutter control methods are investigated in detail. The route to chaos and the cause of chaotic motion of two-dimensional aeroelastic system are summarized. Various structural modeling methods for the high-aspect-ratio wing with geometric nonlinearity are discussed. Accordingly,aerodynamic modeling approaches have been developed for the aeroelastic modeling of nonlinear high-aspect-ratio wings. Nonlinear aeroelasticity about high-altitude longendurance(HALE) and fight aircrafts are studied separately. Finally,conclusions and the challenges of the development in nonlinear aeroelasticity are concluded. Nonlinear aeroelastic problems of morphing wing,energy harvesting,and flapping aircrafts are proposed as new directions in the future. | Xiang Jinwu Yan Yongju Li Daochun | 2014 | Chinese Journal of Aeronautics2014，27，1： | 14 |
| 2 | Aeroservoelastic modeling and analysis of a canard-configured air-breathing hypersonic vehicles显示文摘Air-breathing hypersonic vehicles (HSVs) are typically characterized by interactions of elasticity, propulsion and rigid-body flight dynamics, which may result in intractable aeroservoelastic problem. When canard is added, this problem would be even intensified by the introduction of low-frequency canard pivot mode. This paper concerns how the aeroservoelastic stability of a canard-configured HSV is affected by the pivot stiffnesses of all-moveable horizontal tail (HT) and canard. A wing/pivot system model is developed by considering the pivot torsional flexibility, fuselage vibration, and control input. The governing equations of the aeroservoelastic system are established by combining the equations of rigid-body motion, elastic fuselage model, wing/pivot system models and actuator dynamics. An unsteady aerodynamic model is developed by steady Shock-Expansion theory with an unsteady correction using local piston theory. A baseline controller is given to provide approximate inflight characteristics of rigid-body modes. The vehicle is trimmed for equilibrium state, around which the linearized equations are derived for stability analysis. A comparative study of damping ratios, closed-loop poles and responses are conducted with varying controller gains and pivot stiffnesses. Available bandwidth for control design is discussed and feasible region for pivot stiffnesses of HT and canard is given. | Zeng Kaichun Xiang Jinwu Li Daochun | 2013 | Chinese Journal of Aeronautics2013，26，4： | 7 |
| 3 | Aerodynamic Performance of the Locust Wing in Gliding Mode at Low Reynolds Number显示文摘 | Jinwu Xiang Jianxun Du Daochun Li Kai Liu | 2016 | Journal of Bionic Engineering2016，13，2： | 6 |
| 4 | Design and experimental study of a new flapping wing rotor micro aerial vehicle显示文摘A three-wing Flapping Wing Rotor Micro Aerial Vehicle(FWR-MAV)which can perform controlled flight is introduced and an experimental study on this vehicle is presented.A mechanically driven flapping rotary mechanism is designed to drive the three flapping wings and generate lift,and control mechanisms are designed to control the pose of the FWR-MAV.A flight control board for attitude control with robust onboard attitude estimation and a control algorithm is also developed to perform stable hovering flight and forward flight.A series of flight tests was conducted,with hovering flight and forward flight tests performed to optimize the control parameters and assess the performance of the FWR-MAV.The hovering flight test shows the ability of the FWR-MAV to counteract the moment generated by rotary motion and maintain the attitude of the FWR-MAV in space;the experiment of forward flight shows that the FWR-MAV can track the desired attitude. | Xin DONG Daochun LI Jinwu XIANG Ziyu WANG | 2020 | Chinese Journal of Aeronautics2020，33，12： | 3 |
| 5 | Mechanism of chromosomal DNA replication initiation and replication fork stabilization in eukaryotes显示文摘Chromosomal DNA replication is one of the central biological events occurring inside cells.Due to its large size,the replication of genomic DNA in eukaryotes initiates at hundreds to tens of thousands of sites called DNA origins so that the replication could be completed in a limited time.Further,eukaryotic DNA replication is sophisticatedly regulated,and this regulation guarantees that each origin fires once per S phase and each segment of DNA gets duplication also once per cell cycle.The first step of replication initiation is the assembly of pre-replication complex(pre-RC).Since 1973,four proteins,Cdc6/Cdc18,MCM,ORC and Cdt1,have been extensively studied and proved to be pre-RC components.Recently,a novel pre-RC component called Sap1/Girdin was identified.Sap1/Girdin is required for loading Cdc18/Cdc6 to origins for pre-RC assembly in the fission yeast and human cells,respectively.At the transition of G1 to S phase,pre-RC is activated by the two kinases,cyclin-dependent kinase(CDK)and Dbf4-dependent kinase(DDK),and subsequently,RPA,primase-polα,PCNA,topoisomerase,Cdc45,polδ,and polεare recruited to DNA origins for creating two bi-directional replication forks and initiating DNA replication.As replication forks move along chromatin DNA,they frequently stall due to the presence of a great number of replication barriers on chromatin DNA,such as secondary DNA structures,protein/DNA complexes,DNA lesions,gene transcription.Stalled forks must require checkpoint regulation for their stabilization.Otherwise,stalled forks will collapse,which results in incomplete DNA replication and genomic instability.This short review gives a concise introduction regarding the current understanding of replication initiation and replication fork stabilization. | WU LiHong LIU Yang KONG DaoChun | 2014 | Science China(Life Sciences)2014，57，5： | 3 |
| 6 | A modified airfoil-based piezoaeroelastic energy harvester with double plunge degrees of freedom显示文摘In this letter,a piezoaeroelastic energy harvester based on an airfoil with double plunge degrees of freedom is proposed to additionally take advantage of the vibrational energy of the airfoil pitch motion.An analytical model of the proposed energy harvesting system is built and compared with an equivalent model using the well-explored pitch-plunge configuration.The dynamic response and average power output of the harvester are numerically studied as the flow velocity exceeds the cut-in speed(flutter speed).It is found that the harvester with double-plunge configuration generates 4%–10% more power with varying flow velocities while reducing 6% of the cut-in speed than its counterpart. | Yining Wu Daochun Li Jinwu Xiang Andrea Da Ronch | 2016 | Theoretical & Applied Mechanics Letters2016，6，5： | 2 |
| 7 | DNA replication origins, ORC/DNA interaction, and assembly of pre-replication complex in eukaryotes显示文摘在真核细胞的房间的 Chromosomal DNA 复制高度复杂、复杂地调整。由于它的大尺寸,一个典型真核细胞的染色体包含地点把 DNA 合成发生的 DNA 复制起源称为的几千开始中的百~十个。因为仅仅 DNA 的某个数量能在一有限时间从单个起源被复制,多重开始地点移开一种染色体尺寸的限制。这些多重起源的激活必须被协调以便 chromosomal DNA 的每个片断精确每房间周期被复制仅仅一次。尽管 DNA 复制是为房间生长的一个重要过程,它的机制高度被保存,最近的研究也沿着进化的线在起源结构,复制前建筑群(pre-RC ) 的集会和复制开始的规定揭示重要差异。在分裂酵母 Schizosaccharomyces pombe 的 DNA 复制起源被发现包含由除必要起源识别以外的 Sap1 蛋白质是固定的第二个必要元素复杂绑定的地点。Sap1 最近被表明是在装载开始蛋白质 Cdc18 到起源起一个必要作用并且直接因此参予 pre-RC 形成的新奇复制开始蛋白质。在这评论,我们在理解 DNA 复制起源怎么被组织, pre-RC 怎么并且怎么被装配总结最近的进展 DNA 复制在酵母和 metazoans 被开始并且调整。 | Jingya Sun Daochun Kong | 2010 | Acta Biochimica et Biophysica Sinica2010，42，7： | 2 |
| 8 | Quasirational dynamic system显示文摘Using the iterations of quasirational mappings, the theorems on dynamic system are generalized to the quasirational dynamic system. Some different results are also obtained. | SUN Daochun & YANG Lo1. Department of Mathematics, South China Normal University, Guangzhou 510631, China 2. Institute of Mathematics, Academy of Mathematics and System Sciences, Chinese Academy of Sciences, Beijing 100080, China | 2000 | Chinese Science Bulletin2000，45，14： | 2 |
| 9 | On the distribution of values of random Dirichlet series显示文摘 | Yu Jiarong | 1990 | Chin Ann of Math1990，11，： | 1 |
| 10 | Aerodynamic characteristics of morphing wing withflexible leading-edge显示文摘The morphing wing can improve the flight performance during different phases.However,research has been subject to limitations in aerodynamic characteristics of the morphing wing with a flexible leading-edge.The computational fluid dynamic method and dynamic mesh were used to simulate the continuous morphing of the flexible leading-edge.After comparing the steady aerodynamic characteristics of morphing and conventional wings,this study examined the unsteady aerodynamic characteristics of morphing wings with upward and downward deflections of the leading-edge at different frequencies.The numerical results show that for the steady aerodynamic,the leading-edge deflection mainly affects the stall characteristic.The downward deflection of the leading-edge increases the stall angle of attack and nose-down pitching moment.The results are opposite for the upward deflection.For the unsteady aerodynamic,at a small angle of attack,the transient lift coefficient of the upward deflection,growing with the increase of deflection frequency,is larger than that of the static case.The transient lift coefficient of the downward deflection,decreasing with the increase of deflection frequency,is smaller than that of the static case.However,at a large angle of attack,an opposite effect of deflection frequency on the transient lift coefficient was demonstrated.The transient lift coefficient is larger than that of the static case when the leading edge is in the nose-up stage,and lower than that of the static one in the nose-down stage. | Zi KAN Daochun LI Tong SHEN Jinwu XIANG Lu ZHANG | 2020 | Chinese Journal of Aeronautics2020，33，10： | 1 |
| 11 | Design,Modeling and Analysis of a Sharp-edge Hypersonic Stealthy Re-entry Vehicle显示文摘 | Liu Guofu Li Daochun Xiang Jinwu | 2015 | Procedia Engineering2015，99，： | 1 |
| 12 | Common Borel points of a meromorphic function and its derivatives in the unit circle显示文摘 | Sun Daochun | 1984 | Acta Mathematica Scientic1984，，2： | 1 |
| 13 | Angular distribution of solu- tions of higher order linear differential equations 显示文摘 | Wu Zhaojun Sun Daochun | 2007 | J Korean Math Soc2007，44，6： | 1 |
| 14 | Ultra high voltage transmission in China: developments, current status and future prospects显示文摘 | Huang Daochun Shu Yinbiao Ruan Jiangjun | 2009 | Proceedings of the IEEE2009，97，3： | 1 |
| 15 | On the distribution of random Dirichlet series(ii)显示文摘 | SUN Daochun YU Jiarong | 1990 | Chin Ann of Math1990，11，1： | 1 |
| 16 | Ultra high voltage transmission in China: developments, current status and future prospeets显示文摘 | Huang Daochun Shu Yinbiao Ruan Jiangjun | 2009 | Proceedings of the IEEE2009，97，3： | 1 |
| 17 | Ultra High Voltage Transmission in China Developments,Current Status and Future Prospects显示文摘 | HUANG Daochun SHU Yinbiao RUAN Hiangjun | | 0，，03： | 1 |
| 18 | On an fundamental inequality of quasiconformal mappings and its application显示文摘 | Gao Zongsheng Sun Daochun | 1996 | Journal of Mathematics1996，16，04： | 1 |
| 19 | Aeroelasticdynamic response and control of an airfoil section withcontrol surface nonlinearities显示文摘 | Li Daochun Guo Shijun Xiang Jinwu | 2010 | Journal of Sound andVibration2010，329，： | 1 |
| 20 | Flashover prevention on high-altitude HVAC transmission line insulator strings显示文摘 | Huang Daochun Ruan Jiangjun Cai Wei | 2009 | IEEE Trans on Dielectrics and Electrical Insulation2009，16，1： | 1 |
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