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Chinese Journal of Aeronautics 2017年第1期30卷 47-65页

作者： fu Jian Jean-Charles Maré fu yongling School of Mechanical Engineering and Automation Beihang University Beijing 100083 China Institut Clement Ader (CNRS UMR 5312) INSA-Toulouse Toulouse 31077 France

In the aerospace field, electromechanical actuators are increasingly being implemented in place of conventional hydraulic actuators. For safety-critical embedded actuation applications like flight controls, the use of electromechanical actuators introduces specific issues related to thermal balance, reflected inertia, parasitic motion due to compliance and response to failure. Unfortunately, the physical effects governing the actuator behaviour are multidisciplinary, coupled and nonlinear. Although numerous multi-domain and system-level simulation packages are now available on the market, these effects are rarely addressed as a whole because of a lack of scientific approaches for model architecting, multi-purpose incremental modelling and judicious model implementation. In this publication, virtual prototyping of electromechanical actuators is addressed using the Bond-Graph formalism. New approaches are proposed to enable incremental modelling,thermal balance analysis, response to free-run or jamming faults, impact of compliance on parasitic motion, and influence of temperature. A special focus is placed on friction and compliance of the mechanical transmission with fault injection and temperature dependence. Aileron actuation is used to highlight the proposals for control design, energy consumption and thermal analysis, power network pollution analysis and fault response.

关键词： Bond Graph Electro-hydrostatic actuator Electromechanical actuator More electric aircraft Modelling Power-by-wire Power loss Simulation

Multi-level virtual prototyping of electromechanical actuation system for more electric aircraft

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Chinese Journal of Aeronautics 2018年第5期31卷 892-913页

作者： Jian fu Jean-Charles MARE Liming YU yongling fu School of Mechanical Engineering and Automation Beihang University Institut Clement Ader (CNRS UMR 5312) INSA-Toulouse Flying College Beihang University

Electromechanical actuators（EMAs） are becoming increasingly attractive in the field of more electric aircraft because of their outstanding benefits, which include reduced fuel burn and maintenance cost, enhanced system flexibility, and improved management of fault detection and isolation. However, electromechanical actuation raises specific issues when being used for safetycritical aerospace applications like flight controls： huge reflected inertia to load, jamming-type failure, and increase of backlash with service due to wear and local dissipation of heat losses for thermal balance. This study proposes an incremental approach for virtual prototyping of EMAs. It is driven by a model-based system engineering process in order to enable simulation-aided *** practices supported by Bond graph formalism are suggested to develop a model＇s structure efficiently and to make the model ready for use（or extension） by addressing the above mentioned issues. Physical effects are progressively introduced, and the realism of lumped-parameter models is increased step-by-step. In particular, multi-level component models are architected to ensure continuity between engineering activities. The models are implemented in the AMESim simulation environment, and simulation responses are given to illustrate how they can be used for preliminary sizing, control design, thermal balance verification, and faults to failure analysis. The proposed best practices intend to provide engineers with fast, reusable, and efficient means to assess performance virtually and enhance maturity, performance, and robustness.

关键词： Bond graph Electromechanical actuator Flight control Model-based system engi-neering More electric aircraft Power-by-wire

Variants of Secondary Control with Power Recovery for Loading Hydraulic Driving Device

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Chinese Journal of Mechanical Engineering 2015年第3期28卷 618-633页

作者： LI Wanguo fu yongling CHEN Juan QI Xiaoye School of Mechanical Engineering and Automation Beihang University

Current high power load simulators are generally incapable of obtaining both high loading performance and high energy efficiency. Simulators with high energy efficiency are used to simulate static-state load, and those with high dynamic performance typically have low energy efficiency. In this paper, the variants of secondary control（VSC） with power recovery are developed to solve this problem for loading hydraulic driving devices that operate under variable pressure, unlike classical secondary control（CSC） that operates in constant pressure network. Hydrostatic secondary control units are used as the loading components, by which the absorbed mechanical power from the tested device is converted into hydraulic power and then fed back into the tested system through 4 types of feedback passages（FPs）. The loading subsystem can operate in constant pressure network, controlled variable pressure network, or the same variable pressure network as that of the tested device by using different FPs. The 4 types of systems are defined, and their key techniques are analyzed, including work principle, simulating the work state of original tested device, static operation points, loading performance, energy efficiency, and control strategy, etc. The important technical merits of the 4 schemes are compared, and 3 of the schemes are selected, designed, simulated using AMESim and evaluated. The researching results show that the investigated systems can simulate the given loads effectively, realize the work conditions of the tested device, and furthermore attain a high power recovery efficiency that ranges from 0.54 to 0.85, even though the 3 schemes have different loading performances and energy efficiencies. This paper proposes several loading schemes that can achieve both high dynamic performance and high power recovery efficiency.

关键词： load simulator variants of secondary control power recovery efficiency energy regeneration hydraulic driving device simulation A

Flow characteristics of integrated motor-pump assembly with phosphate ester medium for aerospace electro-hydrostatic actuators

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Chinese Journal of Aeronautics 2023年第9期36卷 392-407页

作者： Jiangao ZHAO Jian fu Yuchen LI Haitao QI Yan WANG yongling fu The Laboratory of Aerospace Servo Actuation and Transmission Beijing 100191China Research Institute for Frontier Science Beihang UniversityBeijing 100191China School of Mechanical Engineering and Automation Beihang UniversityBeijing 100191China

Motor-pump assembly is the core component of the Aerospace Electro-hydrostatic Actuator(EHA).Thus,the design of the motor pump can be very challenging under conditions of high speed and wide pressure range,especially in particular working *** ultimate goal is to pursue better flow characteristics under a wide range of working *** this paper,we built a sub-model of the main friction interfaces and a model of single-shaft coaxial motor-pump assembly adopting the method of hierarchical *** experimental investigation of the output characteristics was mainly carried out in a phosphate ester medium ***,the flow characteristics were compared and analyzed with the simulation *** indicated that the flow characteristics of the motor-pump assembly could be accurately simulated by the model and quite severe in a low speed and high-pressure environment.

关键词： EHA Friction interfaces More electric aircraft Motor-pump Multidisciplinary modeling

Performance optimization of grooved slippers for aero hydraulic pumps

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Chinese Journal of Aeronautics 2016年第3期29卷 814-823页

作者： Chen Juan Ma Jiming Li Jia fu yongling Department of Mechanical Engineering and Automation Beihang UniversityBeijing 100191China Sino-French Engineer School Beihang UniversityBeijing 100191China AVIC Xi'an Flight Automatic Control Research Institute.Xi'an 710065 China

A computational fluid dynamics （CFD） simulation method based on 3-D Navier Stokes equation and Arbitrary Lagrangian Eulerian （ALE） method is presented to analyze the grooved slip- per performance of piston pump. The moving domain of grooved slipper is transformed into a fixed reference domain by the ALE method, which makes it convenient to take the effects of rotate speed, body force, temperature, and oil viscosity into account. A geometric model to express the complex structure, which covers the orifice of piston and slipper, vented groove and the oil film, is constructed. Corresponding to different oil film thicknesses calculated in light of hydrostatic equilibrium theory and boundary conditions, a set of simulations is conducted in COMSOL to analyze the pump characteristics and effects of geometry （groove width and radius, orifice size） on these characteristics. furthermore, the mechanics and hydraulics analyses are employed to validate the CFD model, and there is an excellent agreement between simulation and analytical results. The simulation results show that the sealing land radius, orifice size and groove width all dramatically affect the slipper behavior, and an optimum tradeoff among these factors is conducive to optimizing the pump design.

关键词： Arbitrary LagrangianEulerian (ALE) Computational fluid dynam-ics (CFD) Grooved slipper Hydraulic pump Navier-Stokes equation Performance analysis

Review of cylinder block/valve plate interface in axial piston pumps: Theoretical models,experimental investigations, and optimal design

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Chinese Journal of Aeronautics 2021年第1期34卷 111-134页

作者： Jiang'ao ZHAO yongling fu Jiming MA Jian fu Qun CHAO Yan WANG School of Mechanical Engineering and Automation Beihang UniversityBeijing 100191China Laboratory of Aerospace Servo Actuation and Transmission Beihang UniversityBeijing 100191China State Key Laboratory of Mechanical System and Vibration Shanghai Jiao Tong UniversityShanghai 200240China

Axial piston pumps have been widely used in aircraft hydraulic systems to supply the system with pressurized fluid. The continuous improvement of the aircraft performance has put forward the demand on aviation piston pumps for high power density, safety, and reliability. The lubricating interfaces in axial piston machines are the key design issue that greatly determines the pump performance and service life. The cylinder block/valve plate interface is one of these critical lubricating interfaces and has received considerable attention from many researchers in the last half century. This study aims to review the state-of-the-art literature on the cylinder block/valve plate interface comprehensively and systematically. First, we introduce various theoretical models developed to investigate the lubrication behaviors of the interface and compare them in terms of their assumptions and limitations. Second, the experimental studies on the cylinder block/valve plate interface are presented comprehensively, where the involved test rigs are divided into three types according to their fidelity levels and measurement functionality. Third, we summarize some typical approaches of structure optimization, surface shaping, and surface strengthening, which help improve the load-carrying and anti-wear capacities of the interface under severe operating conditions. Finally, the challenges and future trends of the cylinder block/valve plate interface research are discussed briefly.

关键词： Axial piston pump Cylinder block/valve plate interface Theoretical model Test rig Optimization methods

Digital fixed-frequency hysteresis current control of a BLDC motor applied for aerospace electrically powered actuators

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Chinese Journal of Aeronautics 2018年第6期31卷 1287-1297页

作者： Jian fu yongling fu Liming YU Jianwen GUO Rongrong YANG Mingkang WANG School of Mechanical Engineering and Automation Beihang University Flying College Beihang University

In the conventional cascade control structure of aerospace electrically powered actuators, the current（or electromagnetic torque） loop plays a critical role in realizing a rapid response for a digitally controlled Brush Less Direct Current（BLDC） motor. Hysteresis Current Control（HCC） is an effective method in improving the performance of current control for a BLDC ***, the varying modulating frequency in the traditional HCC causes severe problems on the safety of power devices and the electromagnetic compatibility design. A triangular carrier-based fixed-frequency HCC strategy is expanded by relaxing the constraints on the rising and descending rates of the winding current to advance the capability of HCC to realize fixed-frequency modulation in the steady state. Based on that, a new flexible-bound-size quasi-fixed-frequency HCC is proposed, and the range feasible to realize fixed-frequency modulation control can cover the entire running process in the steady state. Meanwhile, a corresponding digital control strategy is designed,and four digitalization rules are proposed to extend the capacity to achieve fixed-frequency modulation control to the unsteady working state, that is, a novel fixed-frequency modulation is *** and experimental results prove the effectiveness of this improved fixed-frequency HCC strategy.

关键词： BLDC motor Current control Fixed-frequency modulation Flexible bound size Hysteresis current control PWM Triangular carrier

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

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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

Investigations on MBSE modelling and dynamic performance assessment of an electrical trimmable horizontal stabilizer actuator

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Chinese Journal of Aeronautics 2023年第11期36卷 417-433页

作者： Wensen ZHANG Jian fu Jean-Charles MARÉ Haolin MA Tianxiang XIA yongling fu Jiangao ZHAO School of Mechanical Engineering and Automation Beihang UniversityBeijing 100191China INSA–Institut Clément Ader(CNRS UMR 5312) Toulouse 31400France Nanjing Engineer Institute of Aircraft System Jincheng AVICNanjing 211100China

With the development of power-by-wire technology for more electric aircraft,the electromechanical actuator(EMA)has the advantages to replace the conventional hydraulic servo actuator in some aerospace flight *** hydraulically powered trimmable horizontal stabilizer actuation(THSA)system is nowadays developed to be electrically *** their safety-criticality,no-back mechanism and redundant load paths are utilized to meet the flight control ***,rare literatures have introduced these functions and addressed the virtual prototyping activities from system-level point of *** paper proposed such a model of a THSA system with dual electric power sources and fault-tolerant mechanical load *** nonlinear effects of components are considered with realism,and system-level simulation test is conducted to support the model-based system engineering(MBSE)*** models are developed with a power view instead of a pure signal *** on the friction effect and compliance effect with backlash or preload,some improved and novel approaches are adopted for these crucial components and validated via experimental ***,the implemented systemlevel model enables injection of crucial ***,the simulation of the proposed model shows that it is an efficient resource to investigate the actuator’s dynamic performance,to virtually prove that the actuator meets the fail/safe constraint,and to demonstrate the soundness of the fault monitoring functions.

关键词： Electro-mechanical actuator Flight control Mechanical load path Modelling No-back mechanism

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