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Numerical simulation of aerodynamic interaction for a tilt rotor aircraft in helicopter mode

Chinese Journal of Aeronautics 2016年第4期29卷 843-854页

作者： Ye Liang Zhang Ying Yang Shuo Zhu Xinglin Dong Jun Aviation Key Laboratory of Science and Technology on Aerodynamics of High Speed and High Reynolds Number AVIC Aerodynamics Research Institute

A rotor CFD solver is developed for simulating the aerodynamic interaction phenomenon among rotor, wing and fuselage of a tilt rotor aircraft in its helicopter mode. The unsteady Navier-Stokes equations are discretized in inertial frame and embedded grid system is adopted for describing the relative motion among blades and nacelle/wing/fuselage. A combination of multi-layer embedded grid and 'extended hole fringe' technique is complemented in original grid system to tackle grid assembly difficulties arising from the narrow space among different aerodynamic components, and to improve the interpolation precision by decreasing the cell volume discrepancy among different grid blocks. An overall donor cell searching and automatic hole cutting technique is used for grid assembly, and the solution processes are speeded up by introduction of OpenMP parallel method. Based on this solver, flow fields and aerodynamics of a tilt rotor aircraft in hover are simulated with several rotor collective angles, and the corresponding states of an isolated rotor and rotor/wing/fuselage model are also computed to obtain reference solution. Aerodynamic interference influences among the rotor and wing/fuselage/nacelle are analyzed, and some meaningful conclusions are drawn. (C) 2016 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd.

关键词： Aerodynamic interaction Extended hole fringe Multi-layer embedded grid Navier-Stokes equations tilt rotor

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Extended State Observer Based Sliding Mode Control for a tilt rotor UAV

Extended State Observer Based Sliding Mode Control for a Til...

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第36届中国控制会议

作者： Huangxing Lin Rong Fu Jianping Zeng Department of Automation Xiamen University

ISBN: (纸本)9781538629185

This paper focuses on the transition flight control for a small tilt rotor unmanned aerial vehicle(UAV).Aiming at the longitudinal model of a tilt rotor UAV,a novel sliding mode control(SMC) method is proposed to guarantee that the states converge to the desired sliding surfaces in finite ***,extended state observers(ESOs) are provided to enhance the system’s robustness to the *** show the effectiveness of the proposed approach.

关键词： tilt rotor sliding mode control extended state observer

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Mode Transition Control of Dual tilt rotor Unmanned Aerial Vehicle Based on Dynamic Analysis

Mode Transition Control of Dual Tilt Rotor Unmanned Aerial V...

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第32届中国控制与决策会议

作者： Ruijian Zheng Yuqing He Zhong Liu Liying Yang Feng Gu College of Information Scicnce and Engineering Northcastern University State Key Laboratory of Robotics Shenyang Institute of AutomationChinese Academy of Sciences Institutes for Robotics and Intelligent Manufacturing Chinese Academy of Sciences University of Chinese Academy of Sciences

To achieve the mode transition of a dual tilt rotor unmanned aerial vehicle（dual-TRUAV） from helicopter mode to airplane mode,this study focuses on its transition control method based on necessary dynamic *** dynamic characteristics of the dual-TRUAV especially the longitudinal dynamics are simplified and analyzed mainly,where the influence of the rotor tilt angle on dual-TRUAV dynamics is *** the above dynamic analysis,the transition control strategy based on the rotor tilt angle is *** stability analysis of the system with the designed control method is carried out via passive theory,and some simulation results are displayed to validate the control effectiveness.

关键词： tilt rotor Unmanned Aerial Vehicle Dynamic Analysis Model Transition Control Passivity

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