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Design and performance analysis of position-based impedance control for an electrohydrostatic actuation system

Chinese Journal of Aeronautics 2018年第3期31卷 584-596页

作者： Yongling FU Xu HAN Nariman SEPEHRI Guozhe ZHOU Jian FU Liming YU Rongrong YANG School of Mechanical Engineering and Automation Beihang University Beijing 100083 China Department of Mechanical Engineering University of Manitoba Manitoba R3T 2N2 Canada China Academy of Launch Vehicle Technology Beijing 100076 China Flying College Beihang University Beijing 100083 China

Electrohydrostatic actuator（EHA） is a type of power-by-wire actuator that is widely implemented in the aerospace industry for flight control, landing gears, thrust reversers, thrust vector control, and space robots. This paper presents the development and evaluation of positionbased impedance control（PBIC） for an EHA. Impedance control provides the actuator with compliance and facilitates the interaction with the environment. Most impedance control applications utilize electrical or valve-controlled hydraulic actuators, whereas this work realizes impedance control via a compact and efficient EHA. The structures of the EHA and PBIC are firstly introduced. A mathematical model of the actuation system is established, and values of its coefficients are identified by particle swarm optimization. This model facilitates the development of a position controller and the selection of target impedance parameters. A nonlinear proportional-integral position controller is developed for the EHA to achieve the accurate positioning requirement of PBIC. The controller compensates for the adverse effect of stiction, and a position accuracy of 0.08 mm is *** experimental results are presented to verify the applicability of PBIC to the EHA. The compliance of the actuator is demonstrated in an impact test.

关键词： actuation system Aerospace Electrohydrostatic actuator Force control Nonlinear dynamics Particle swarm optimization Position control

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Modeling and Experiment of a Morphing Wing Integrated with a Trailing Edge Control actuation system

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Chinese Journal of Mechanical Engineering 2012年第2期25卷 248-254页

作者： HE Yuanyuan GUO Shijun School of Aerospace Engineering Beijing Institute of TechnologyBeijing10081China Department of Aerospace Engineering School of EngineeringCranfield UniversityMK430ALUK

Morphing wing has attracted many research attention and effort in aircraft technology development because of its advantage in lift to draft ratio and flight *** wing technology combines the lift and control surfaces into a seamless wing and integrates the primary structure together with the internal control *** makes use of the wing aeroelastic deformation induced by the control surface to gain direct force control through desirable redistribution of aerodynamic *** some unknown mechanical parameters of the control system and complexity of the integrated structure become a main challenge for dynamic modeling of morphing *** solve the problem,a method of test data based modal sensitivity analysis is presented to improve the morphing wing FE model by evaluating the unknown parameters and identifying the modeling boundary *** innovative seamless morphing wing with the structure integrated with a flexible trailing edge control system is presented for the *** experimental model of actuation system driven by a servo motor for the morphing wing is designed and *** performing a vibration test and the proposed modal sensitivity analysis,the unknown torsional stiffness of the servo motor and the boundary condition of the actuation mechanism model is identified and *** with the test data,the average error of the first four modal frequency of the improved FE model is reduced significantly to less than 4%.To further investigate the morphing wing modeling,a wing box and then a whole morphing wing model including the skin and integrated with the trailing edge actuation system are established and *** using the proposed method,the FE model is improved by relaxing the constraint between the skin and actuation *** results show that the average error of the first three modal frequency of the improved FE model is reduced to less than 6%.The research results demonstrate that the presen

关键词： morphing wing seamless trailing edge control surface actuation system modeling and vibration test

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An energy-based coupling degradation propagation model and its application to aviation actuation system

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Chinese Journal of Aeronautics 2020年第4期33卷 1288-1298页

作者： Tongyang LI Shaoping WANG Jian SHI Enrico ZIO Xiaoyu CUI School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100083China Energy Department Politecnico di MilanoVia La Masa 34Milano 20156Italy MINES ParisTech PSL Research UniversityCRCSophia Antipolis06410France Department of Nuclear Engineering College of EngineeringKyung Hee UniversityGyeonggi-do 12001South Korea

The degradation of components in complex mechatronic systems involves multiple physical processes which will cause coupling interactions among nodes in the *** interaction of nodes may be carried out not only by physical connections but also by the environment which cannot be described by single network using the traditional *** order to give out a unified model to quantitatively describe the coupling degradation spreading by both physical connections and environment,a novel Energy-Flow-Field Network(EFFN)and a coupling degradation model based on EFFN are proposed in this *** EFFN is driven by energy flow and the state transition of spatially related nodes is triggered by the dissipation *** application is conducted on aviation actuation system in which the degradation spreading by fluid-thermal-solid interaction is *** degradation path and the most probable fault reason can be obtained by combining the state transition and energy output of nodes,which is consistent with the given scenario.

关键词： actuation system Cascading failure Complex system Failure propagation Mechatronic system

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Stability Analysis of a Force-Aided Lever actuation system for Dry Clutches with Negative Stiffness Element

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Journal of Shanghai Jiaotong university(Science) 2018年第2期23卷 218-226页

作者： LIU Fengyu a b c CHEN Li a a.State Key Laboratory of Ocean Engineerin b. Collaborative Innovation Center for Advanced Ship and Deep-Sea Exploratio c. National Laboratory of Automotive Electronics and Control Shanghai Jiao Tong University Shanghai 200240 China

A force-aided lever with a preload spring is not only force-saving but also energy-saving. Therefore, it has great potential to be applied to dry clutch actuations. However, the negative stiffness of the clutch diaphragm spring introduces unstable dynamics which becomes more intensive due to the preload spring. In order to explore the intensified unstability, this paper builds dynamic models for the rotating lever coupling a negative stiffness diaphragm spring and a preload spring. The stability analysis using the Routh-Huiwitz criterion shows that the open-loop system can never be stable due to the negative stiffness. Even if the diaphragm spring stiffness is positive, the system is still unstable when the preload of the spring exceeds an upper limit. A proportionalintegral-derivative(PID) closed-loop scheme addressing this problem is designed to stabilize the system. The stability analysis for the closed-loop system shows that stable region emerges in spite of the negative stiffness; the more the negative stiffness is, the less the allowed preload is. Further, the influences of the dimensions and PID parameters on the stability condition are investigated. Finally, the transient dynamic responses of the system subjected to disturbance are compared between the unstable open-loop and stabilized closed-loop systems.

关键词： negative stiffness preload spring stability dry clutch actuation system force-aided lever

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Architecture Optimization of More Electric Aircraft actuation system

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Chinese Journal of Aeronautics 2011年第4期24卷 506-513页

作者： QI Haitao FU Yongling QI Xiaoye LANG Yan School of Mechanical Engineering and Automation Beihang University Beijing 100191 China Beijing Institute of Control Engineering Beij'ing 100190 China

The optional types of power source and actuator in the aircraft are more and more diverse due to fast development in more electric technology, which makes the combinations of different power sources and actuators become extremely complex in the architecture optimization process of airborne actuation system. The traditional ＂trial and error＂ method cannot satisfy the design demands. In this paper, firstly, the composition of more electric aircraft （MEA） flight control actuation system （FCAS） is introduced, and the possible architecture quantity is calculated. Secondly, the evaluation criteria of FCAS architecture with respect to safe reliability, weight and efficiency are proposed, and the evaluation criteria values are calculated in the case that each control surface adopts the same actuator configuration. Finally, the optimization results of MEA FCAS architecture are obtained by applying genetic algorithm （GA）. Compared to the traditional actuation system architecture, which only adopts servo valve controlled hydraulic actuators, the weight of the optimized more electric actuation system architecture can be reduced by 6%, and the efficiency can be improved by 30% based on the safe reliability requirements.

关键词： more electric aircraft power-by-wire actuation system architecture multiobjective optimization genetic algorithms

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