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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 | 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 |
| 6 | 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 |
| 7 | 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 |
| 8 | 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 |
| 9 | Buckling and post-buckling of a composite C-section with cutout and flange reinforce- ment显示文摘 | Guo Shijun Li Daochun Zhang Xiang | 2014 | Composites Part B : Engineering2014，60，4： | 1 |
| 10 | Robot Pilot:A New Autonomous System toward Flying Manned Aerial Vehicles显示文摘The robot pilot is a new concept of a robot system that pilots a manned aircraft,thereby forming a new type of unmanned aircraft system(UAS)that makes full use of the platform maturity,load capacity,and airworthiness of existing manned aircraft while greatly expanding the operation and application fields of UASs.In this research,the implementation and advantages of the robot pilot concept are discussed in detail,and a helicopter robot pilot is proposed to fly manned helicopters.The robot manipulators are designed according to the handling characteristics of the helicopter-controlling mechanism.Based on a kinematic analysis of the robot manipulators,a direct-driving method is established for the robot flight controller to reduce the time delay and control error of the robot servo process.A supporting ground station is built to realize different flight modes and the functional integration of the robot pilot.Finally,a prototype of the helicopter robot pilot is processed and installed in a helicopter to carry out flight tests.The test results show that the robot pilot can independently fly the helicopter to realize forward flight,backward flight,side flight,and turning flight,which verifies the effectiveness of the helicopter robot pilot. | Zibo Jin Daochun Li Jinwu Xiang | 2023 | Engineering2023，，8： | 0 |
| 11 | Experimental Validation of an Effective Control Mechanism to Enable Flapping Wing Rotor Stable Flight显示文摘Design and implementation of an effective control mechanism is the key to enable the controlledflight of flapping wing rotor micro aerial vehicles(FWR-MAVs).In order to address this open challenge,in this paper,a triple-wing FWR-MAV with its particular control system is proposed.The corresponding experimental study of the vehicle is conducted.As a result,the triple-wing propulsion system demonstrates advantages in both lift generation and flight stability based on the force measurement.The control torques of the proposed FWR-MAV are generated by a particular slipflow rudder mechanism.The effectiveness of such a design combination has been validated experimentally.A series of flight tests are conducted,including sustained hovering and forward-backward maneuvering.To the best of our knowledge,such a design yields the world's first FWR-MAV capable of sustained controlled flight. | Ziyu Wang Xin Dong Jinwu Xiang Daochun Li Zhan Tu | 2022 | Guidance, Navigation and Control2022，2，3： | 0 |
| 12 | Electromagnetic disturbance characteristic of typical high voltage switchgear interruption process in offshore wind farm based on integrated conduction model显示文摘In an offshore wind farm,a high‐voltage switchgear interruption in an offshore substation creates a high‐frequency,high‐amplitude overvoltage that can cause severe electromagnetic interference problems in the intelligent electronic device.To address this issue,mathematical models,vector fitting and finite element method were used to build an integrated electromagnetic disturbance conduction model,whose accuracy was verified by large current interruption tests.Through the simulation of a typical offshore wind farm's single‐phase grounding fault interruption process,the electromagnetic disturbance characteristics and the impact of the ground position are obtained.The results show that during the fault interruption process of phase B grounded,the dominant frequency of disturbance voltage can reach 4.34 MHz,and the amplitude can reach 1.12 kV.The ground grid has a large impact on the interference voltage,which can reach a maximum value of 2.28 kV under specific conditions.The disturbance voltage in the fault process mainly comes through the current transformer,while during the interruption process,it mainly comes through the ground grid.The authors provide a method to establish the integrated electromagnetic disturbance simulation model,which can improve the accuracy of the electromagnetic disturbance conduction process simulation of intelligent components. | Huaqing Wang Daochun Huang Mingjing Shuang Huipeng Li Yiqun Qiu | 2023 | High Voltage2023，8，5： | 0 |
| 13 | IL-33 Downregulates Hepatic Carboxylesterase 1 in Acute Liver Injury via Macrophage-derived Exosomal miR-27b-3p显示文摘Background and Aims:We previously reported that carboxylesterase 1(CES1)expression was suppressed following liver injury.The study aimed to explore the role of interleukin(IL)-33 in liver injury and examine the mechanism by which IL-33 regulates CES1.Methods:IL-33 and CES1 levels were determined in the livers of patients and lipopolysaccharide(LPS)-,acetaminophen(APAP)-treated mice.We constructed IL-33 and ST2 knockout(KO)mice.ST2-enriched immune cells in livers were screened to identify the responsible cells.Macrophage-derived exosome(MDE)activity was tested by adding exosome inhibitors.Micro-RNAs(miRs)were extracted from control and IL-33-stimulated MDEs(IL-33-MDEs)and subjected miR sequencing(miR-Seq).Candidate miR was tested in vitro and in vivo and its binding of a target gene was assessed by luciferase reporter assays.Lentivirus-vector cellular transfection and transcript silencing were used to examine pathways mediating IL-33 suppression of miR-27b-3p.Results:Patient liver IL-33 and CES1 expression levels were inversely correlated.CES1 downregulation in liver injury was rescued in both IL-33–deficient and ST2 KO mice.Macrophages were shown to be responsible for IL-33 effects.IL-33-MDEs reduced CES1 levels in hepatocytes.Exosomal miR-Seq and qRT-PCR demonstrated increased miR-27b-3p levels in IL-33-MDEs;miR-27b-3p was implicated in Nrf2 targeting.IL-33 inhibition of miR-27b-3p was found to be GATA3-dependent.Conclusions:IL-33–ST2–GATA3 pathway signaling increases miR-27b-3p content in MDEs,which upon being internalized by hepatocytes reduce CES1 expression by inhibiting Nrf2.The elucidation of this mechanism in this study contributes to a better understanding of CES1 dysregulation in liver injury. | Ping Gao Min Li Jingli Lu Daochun Xiang Ximin Wang Yanjiao Xu Yue Zu Xinlei Guan Guodong Li Chengliang Zhang | 2023 | Journal of Clinical and Translational Hepatology2023，11，5： | 0 |
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