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CSAA/IET International Conference on Aircraft utility systems, AUS 2018

作者： Hu, Yaohua Nanjing Engineering Institute of Aircraft Systems Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (纸本)9781785617911

The constant power speed range (CPSR) of the multi-layered interior permanent magnet (IPM) machines are investigated for the traction applications. The constant power speed range of the initial design is weak because the characteristic current is too large. Then, the structure of initial model is optimized to other two structures. Not only the constant power speed range of two optimized structures are improved by reduce the magnet volume and increase the rib width, but also can reduce the manufacturing complexity and magnet cost. The widest constant power speed range is obtained when the characteristic current equals to the rated current. Finally, a multi-layered IPM machine is manufactured to verify the FE analysis. © 2018 IET Conference Publications. All rights reserved.

关键词： Permanent magnets

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Study on Outer Rotor FSCW Permanent Magnet Machines for Unmanned Aerial Vehicle Electric Green Taxiing systems

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IOP Conference Series: Materials science and Engineering 2020年第1期887卷

作者： Hua Xu Yaohua Hu Jinpeng Yang Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing 211106 China

This paper considers the possibility of adopting an outer rotor fractional slot concentrated winding (FSCW) permanent magnet synchronous machine (PMSM) for Unmanned Aerial Vehicle Electric Green Taxiing (EGT) application. The electromagnet performance such as no-load air-gap flux density, flux linkage distribution, electromotive force (EMF), average torque, torque ripple, and iron losses are studied by finite-element analysis (FEA). The results show the iron loss is mainly effected by the machine frequency. The unmanned aerial vehicle EGT structure are introduced, which includes the outer rotor FSCW PM machine, the reducer, the clutch, and the tire.

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Study on Lumped Magnetic Circuit in Interior PM Machines for Aircraft Electric Green Taxiing systems

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IOP Conference Series: Materials science and Engineering 2020年第1期751卷

作者： Pengfei Zhang Yaohua Hu Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing 211106 China

This paper considers the possibility of adopting a V-shaped interior permanent magnet (IPM) machine for Electric Green Taxiing (EGT) application. This rotor topology of the IPM machine has been optimized to reduce the torque ripple and iron loss. An analytical lumped magnetic circuit model was adopted to minimize the total harmonic distortion (THD) of air-gap flux density for the V-shaped IPM machine. The results of analytical lumped magnetic circuit model were compared with finite-element analysis (FEA). With the optimized rotor structure parameters, the torque ripple at the maximum torque per ampere and iron loss at the flux-weakening control were investigated.

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Study on Magnet Eddy Current Losses in Interior Permanent Magnet Machines for Aircraft Electric Green Taxiing systems

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IOP Conference Series: Materials science and Engineering 2020年第1期751卷

作者： Yaohua Hu Pengfei Zhang Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing 211106 China

The magnet eddy current of multi-layered interior permanent magnet (IPM) machines is studied in the paper for the aircraft electric green taxiing systems. The armature reaction flux density distribution, eddy current density and harmonic spectrum at the end of permanent magnet are analysed. A method to reduce the magnet eddy current of multi-layered IPM machines is presented. That is to increase the distance between outer permanent magnet and rotor surface and the distance between two layers of permanent magnet so as to provide a larger core path for armature reactive flux. This method can effectively reduce the magnet eddy-current loss of the multi-layered IPM machines and improve the operation efficiency.

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Numerical investigation of influence of structure and operating parameters on performance of vortex oil filter

Numerical investigation of influence of structure and operat...

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CSAA/IET International Conference on Aircraft utility systems, AUS 2018

作者： Wang, Ning Chen, Weijian Ning, Guoli Hui, Ma Key Laboratory of Aircraft Environment Control and Life Support MIIT Nanjing University of Aeronautics and Astronautics Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (纸本)9781785617911

In this paper, the three-dimensional numerical simulation of solid-liquid two-phase flow in a vortex oil filter is performed by means of numerical simulation. The Reynolds stress turbulence model is used in the simulation flow field, and the DPM model is used for solid particle tracking. The influence of key structural parameters and operating parameters on the filtering effect was mainly studied, such as the inlet width, the size of the overflow pipe, the wall thickness and the insertion depth, the size of the cone angle and the length of the cone end. The results provide the basis for the rational design of the vortex oil filter. © 2018 IET Conference Publications. All rights reserved.

关键词： Vortex flow

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All-Electric Aircraft Nose Wheel Steering system with Two Worm Gears

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Transactions of Nanjing University of aeronautics and Astronautics 2018年第1期35卷 170-180页

作者： Zhang Ming Li Chuang Wu Xin Zhu Yin Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics&AstronauticsNanjing 210016P.R.China Shanghai Aircraft Design and Research Institute Shanghai 201210P.R.China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing 211106P.R.China

As all-electric aircraft has many advantages,an aircraft nose wheel steering system would be developed to the all-electric *** the control demand of the nose wheel steering system,based on the basic principles of nose wheel steering system and the design technique of mechanotronics,an all-electric aircraft nose wheel steering system,composed of a nose wheel steering mechanism of two worm gear and a control servo system of fly-by-wire with both steering and anti-shimmy functions is designed to meet the demand for operation control in the nose wheel steering ***,based on the LMS-AMESim software,the simulation model of the system is established to simulate the dynamics for the verification of its steering *** simulation results indicate that the nose wheel steering system is reasonable,and can meet the requirements of the general ***,the prototypes of the steering mechanism and control system are studied to validate the design,and the steering test bench is prepared to test the designed *** test results,such as steer angle,rotate speed of motor are analyzed in details and compared with the theoretical *** analysis and comparison results show that the design is reasonable and the property of the prototype can achieve the design objectives.

关键词： mechanotronics design nose wheel steering system all-electric aircraft design landing gear

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Research on improved control method of electromechanical actuation

Research on improved control method of electromechanical act...

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作者： Xiao, Xi Xiong, Si Wu, Xia Liu, Dan Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Jiangsu211106 China Beijing Aeronautical Science and Technology Research Institute of COMAC Beijing102211 China

This study presents a kind of feedback between smooth and discontinuous feedback control method for electromechanical servo system. First, the construction and working principle of electromechanical servo systems was introduced on the basis of their structure characteristic. Then with the building of the electromechanical servo system structure, some research on the control strategy of permanent-magnet synchronous motors has been developed control in the light of their control characteristics. Combined with the theory of the field oriented control and the structure features and performance metrics of the mechanical and electrical servo system, a simulation model for the mechanical and electrical servo system was built. The simulation result shows the reliability of this method. © 2018 Institution of Engineering and technology. All rights reserved.

关键词： Servomechanisms

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The study and optimization of noise in a fuel pump

The study and optimization of noise in a fuel pump

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CSAA/IET International Conference on Aircraft utility systems, AUS 2018

作者： Li, Shiqiu Zhang, Xiaobo Wei, Zhicong Aviation Key Laboratory of Sicience and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing China China Agricultural University Beijing China

ISBN: (纸本)9781785617911

With the continuous advancement of industry technology, fuel pumps are increasingly subject to vibration and noise problems in addition to high speed, high pressurization value, etc. In this paper, the noise of a fuel pump was tested and a design optimization to suppress the noise was proposed. The sound pressure level(SPL) was found exceeding requirements firstly. The numerical analysis model of the pump showed that the main reason of the noise is caused by pressure pulsation between the impeller and the vane. An optimized design of impeller and vane of the pump was proposed. The numerical results show that the pressure pulsation at the blade passing frequency(BPF) is significantly reduced. Finally, the optimized impeller and guide vane were machined and tested. Test result shows that the SPL of the fuel pump drops significantly, meeting the noise requirements. The research findings can serve as a reference for the design optimization of other aviation fuel pumps. © 2018 IET Conference Publications. All rights reserved.

关键词： Fuels

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Reduction of Iron Loss in a V-Shaped IPM Machine for Traction Applications

Reduction of Iron Loss in a V-Shaped IPM Machine for Tractio...

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International Conference on Electrical Machines and systems (ICEMS)

作者： Ma Zhiyong Yaohua Hu Chen Can The Fourth Representative Office of the Navy in Nanjing Navy Military Representative Office in Nanjing Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems Nanjing China

ISBN: (纸本)9781728133997

This paper has proposed a novelty method to reduce the iron loss of a V-shaped interior permanent magnet (IPM) machine for traction applications. By optimizing the pole-arc to pole-pitch ratios of magnets and shaping the rotor iron, the total iron losses of initial model is extremely reduced, due to the harmonics of rotor magnetomotive force are reduced. The waveforms and harmonics of air gap flux density and flux density of stator core are studied. The core loss and core loss density of three IPM motors are analyzed and compared. The efficiency of the optimized V-shaped IPM machine can be improved under high speed condition by the reduction of iron loss.

关键词： Iron loss Interior permanent magnet (IPM) machine Rotor magnetomotive force harmonics Shaping the rotor iron Core loss air-gap flux density Integrated Pest Management harmonics reduction Stator cores MAGNETS machine waveforms

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The analysis of multi-cylinder synchronization in the load simulation system for reciprocating seals

The analysis of multi-cylinder synchronization in the load s...

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CSAA/IET International Conference on Aircraft utility systems, AUS 2018

作者： Guo, Shengrong Zhang, Pengfei Zhou, Qinghe Sun, Dechen Ku, Houtao Peng, Chao Ouyang, Xiaoping Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft System Shuige Road 33 Nanjing211106 China State Key Laboratory of Fluid Power and Mechatronic Systems Zhejiang University Zheda Road 38 Hangzhou310027 China

ISBN: (纸本)9781785617911

The load simulation system is a subsystem of the reciprocating sealing test system, to evaluate the working life of the aircraft actuator's sealing components. In this paper, a synchronization controller based on bias coupling is developed to study the control characteristics of the multi-cylinder synchronization under the control of one servo valve. The dynamic model of the load is established and verified by simulations and experiments. The influences of friction, load, and etc. on the synchronization are also analyzed. And the results indicated that synchronization error can be effectively reduced using the controller, besides great cost savings. © 2018 IET Conference Publications. All rights reserved.

关键词： Synchronization

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