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检索条件"机构=Aviation Key Laboratory of Science and Technology On Aero-Electromechanical System Integration"

共 252 条记录，以下是11-20 订阅

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DESIGN OF THE MAGNETIC CIRCUIT COMPENSATION TYPE OF LARGE ANGLE MEASUREMENT OF RVDT

DESIGN OF THE MAGNETIC CIRCUIT COMPENSATION TYPE OF LARGE AN...

引用

2024 CSAA/IET International Conference on Aircraft Utility systems, AUS 2024

作者： Wang, Hongchao Jiang, Hongyan Mao, Shijie Wang, Yin Han, Chao Zhao, Yuqing Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft Systems AVIC Jincheng Jiangsu Nanjing211106 China

In order to meet the need of large angle measurement of actuating system, the miniaturization and dexterity is taken as the design idea. By redesigning the structure of rotor core and stator coil, the measuring angle is expanded without increasing the number of components, the volume and weight of RVDT. In addition, in order to improve the linearity of induced voltage of RVDT, the method of magnetic circuit compensation is adopted. When making the rotor core, tilting its side, the total magnetic flux of RVDT is stable when the rotor core rotates at any angle. By using theoretical analysis, simulation experiment and prototype test, the design of magnetic circuit compensation type of large angle measurement of RVDT is verified. © The Institution of Engineering & technology 2024.

关键词： Angle measurement

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Trade-Off of the Clearance at the Control Plunger Section of a Solenoid Valve 6th

Trade-Off of the Clearance at the Control Plunger Section of...

引用

6th China aeronautical science and technology Conference, CASTC 2023

作者： Li, Changming Cui, Pengbo Xu, Xiangrong AVIC Jincheng Nanjing Engineering Institute of Aircraft System Nanjing211106 China Aviation Key Laboratory of Science and Technology On Aero Electromechanical System Integration Nanjing211106 China

ISBN: (纸本)9789819988662

Aiming at block failure of a type of solenoid valve, the clearance at the control plunger section was trade-off, and the purpose is to solve the block while not causing over leakage of the whole valve. According to the analysis of the internal leakage channel of the solenoid valve, it is known that there is no leakage in the clearance at the control plunger section under the power-off condition, and the leakage through the clearance is far less than the allowable value when the power is turned on, that is, the clearance can be increased to eliminate the jam. Within the allowable range of leakage, calculated according to the annular gap flow formula, when the eccentricity of the control plunger in the sleeve takes the extreme values 0 and 1, the unilateral maximum allowable values of the clearance are 6.3 μm and 4.6 μm respectively. According to the estimation of the leakage test results, the eccentricity of the control plunger in the sleeve is 0.42, and the unilateral maximum allowable value of the clearance is 5.8 μm. By increasing the clearance of the control plunger section, the block failure of the solenoid valve is eliminated, and no over-leakage occurs. © 2024, Chinese Society of aeronautics and Astronautics.

关键词： Blockage Clearance Leakage Solenoid valve Trade-off

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INFLUENCE OF CONTROL COMPONENTS ON THE OPEN-LOOP CHARACTERISTICS OF AIRBORNE EVAPORATIVE CYCLE system

INFLUENCE OF CONTROL COMPONENTS ON THE OPEN-LOOP CHARACTERIS...

引用

2024 CSAA/IET International Conference on Aircraft Utility systems, AUS 2024

作者： Wang, Ruiqi Zhan, Hongbo Ouyang, Jingpeng Gao, Zanjun Yang, Hua Hu, Wenchao Nanjing Engineering Institute of Aircraft Systems AVIC Jincheng Nanjing China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

In this paper, an airborne evaporative cycle system is built, and R1234ze is used as the working medium. To explore the open-loop behavior of an airborne evaporative cycle system, we examined how adjusting the compressor speed and electronic expansion valve opening affects the compressor inlet superheat, heat source outlet temperature, and refrigeration capacity. The test results indicate that, in the specified testing conditions, the impact of compressor speed and electronic expansion valve opening on system performance is evident. As compressor speed increases, there is a significant rise in compressor inlet superheat, a notable decrease in heat source outlet temperature, and a substantial increase in refrigeration capacity. Conversely, an increase in electronic expansion valve opening leads to a significant reduction in compressor inlet superheat. © The Institution of Engineering & technology 2024.

关键词： Compressors

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Research on the cabin pressure control system based on the gray wolf fuzzy PID algorithm 2

Research on the cabin pressure control system based on the g...

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2023 2nd International Conference on aerospace and Control Engineering, ICoACE 2023

作者： Wang, Shun Meng, Fanxing Yang, Yonghui Yang, Changbao Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China Nanjing Engineering Institute of Aircraft Systems Nanjing211106 China

The cabin pressure control system is typically nonaffine-nonlinear time-varying system. In this paper, the fuzzy PID control method optimized by gray wolf algorithm is proposed to solve the problems of large overshoot and long adjustment times in traditional control methods. Simulation results show that the fuzzy PID control method optimized by gray wolf algorithm proposed in this paper improves the dynamic characteristics of the system, reduces cabin pressure error and adjustment time, stabilizes the control process, and improves the comfortableness of passengers. © Published under licence by IOP Publishing Ltd.

关键词： Three term control systems

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Exploration of the design method of fuel pump parts structure optimization

Exploration of the design method of fuel pump parts structur...

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2024 CSAA/IET International Conference on Aircraft Utility systems, AUS 2024

作者： Zongtai, Cui Xun, Shen Xian, GuJing Yang, Yang Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing211106 China

With the continuous improvement of performance requirements for aircraft combat, transportation, and power, the weight requirements for aircraft are becoming increasingly stringent, and the demand for lightweight design of aircraft accessories is becoming increasingly urgent. The aviation fuel pump is the core component of the aircraft fuel system. It is of great significance to reduce the mass of redundant structures and improve the power to weight ratio of pumps while ensuring structural strength. Traditional fuel pump design mainly relies on the designer's experience in selecting structural forms and determining parameters. With the development of technology, especially finite element technology, important methods and means have been provided for strength analysis in the design process of fuel pump structures. However, in terms of design methods, pump design has not yet broken through the limitations of traditional empirical design, such as the determination of structural topology, selection of shape, and optimization of structural size parameters. This article explores the commonly used methods of structural optimization design, with a focus on introducing topology optimization theory and its applications. It takes the structural optimization design of a certain type of fuel pump component as the research object, in order to provide some theoretical reference for future fuel pump structural design optimization. © The Institution of Engineering & technology 2024.

关键词： Fuel pump Shape optimization Structural design Topology optimization Abstract

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RESEARCH ON AUTO-TUNING OF CONTROL PARAMETERS FOR aviation ELECTROHYDROSTATIC ACTUATOR BASED ON INTELLIGENT ALGORITHM OPTIMIZATION

RESEARCH ON AUTO-TUNING OF CONTROL PARAMETERS FOR AVIATION E...

引用

2024 CSAA/IET International Conference on Aircraft Utility systems, AUS 2024

作者： Chen, Yuxi Chen, Lijun Yao, Yeming Wang, Xiaoping Chang, Cheng Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China Nanjing Engineering Institute of Aircraft Systems Jincheng Corporation AVIC Nanjing China

This paper takes the aviation Electro-hydrostatic Actuator (EHA) as the research object, analyses its working principle and structural characteristics, establishes mathematical models for the drive motor, pump and cylinder, and builds a simulation model based on MATLAB/Simulink. Addressing the issues of strong nonlinearity, cumbersome manual tuning of PI parameters under strong disturbances, and poor control effects in the EHA systems, this paper proposes an auto-tuning method for PI control parameters based on improved Bayesian optimization. A comparative analysis is conducted with traditional manual tuning methods and RF methods. According to simulation comparison results, the proposed method outperforms traditional tuning methods in terms of robustness and rapidity. © The Institution of Engineering & technology 2024.

关键词： MATLAB

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Optimization Design of Electrical Axial Fan Based on NSGA - II Algorithm 6th

Optimization Design of Electrical Axial Fan Based on NSGA - ...

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6th China aeronautical science and technology Conference, CASTC 2023

作者： Zhao, Yu-Shu AVIC Nanjing Engineering Institute of Aircraft Systems Nanjing211106 China Aviation Key Laboratory of Science and Technology On Aero Electromechanical System Integration Nanjing211106 China

ISBN: (纸本)9789819988631

A fast sequencing genetic algorithm, NSGA-II is applied to the performance optimization of axial flow electric fans on multi eletric aircraft to improve the effectiveness of environmental control systems (ECS) and reduce fuel penalty. The degree of sweep and curve of blades is set as the optimization parameters, while low power and large flow rate is set as the optimization objectives to optimize the initial design. NSGA-II algorithm is used to control the optimization parameters, and an automated simulation analysis process is established to achieve automatic iteration and optimization. The power of the optimized fan model is reduced by 8.8% compared to the prototype. The results show that the method used in this paper has good effects in dealing with multi-objective and multi-parameter performance optimization problems of axial flow fans. The method has also certain reference value for the optimization design of other turbomachine. © 2024, Chinese Society of aeronautics and Astronautics.

关键词： Multiobjective optimization

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STUDY ON THE RELATIONSHIP BETWEEN THE FRICTION PAIRS WEAR AND THE PLUNGER FRACTURE

STUDY ON THE RELATIONSHIP BETWEEN THE FRICTION PAIRS WEAR AN...

引用

2024 CSAA/IET International Conference on Aircraft Utility systems, AUS 2024

作者： Zou, Pengjian Zhang, Haoran Gu, Manning Xia, Tianxiang Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China Nanjing Engineering Institute of Aircraft System Jincheng Corporation AVIC Nanjing211106 China

The plunger pump is one of the most complicated hydraulic components, the fault reason is hidden, the traditional analysis method such as theoretical formula is difficult to study its fault principle and correlation. In some cases of plunger pump failure, the fracture of the plunger is usually accompanied by serious wear of plunger and sliding shoe. In order to study the correlation between kinematic pairs wear and plunger fracture, a flexible-solid coupling dynamic digital prototype of plunger pump is built, which takes into account the action of hydraulic pressure and rotating load in a rotating cycle. The friction force of the friction pair is considered by modifying the contact method of the friction surface of kinematic pair. The simulation results show that the plunger pair wear leads to the increase of supporting force of sliding shoes, the wear of plunger and sliding shoe leads to the sharp increase of stress of plunger neck, the wear of kinematic pair is related to the plunger fracture. © The Institution of Engineering & technology 2024.

关键词： Friction

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The Research of A Plate Fin Cold Plate Characters Based on Numerical Simulation

The Research of A Plate Fin Cold Plate Characters Based on N...

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2022 CSAA/IET International Conference on Aircraft Utility systems, AUS 2022

作者： He, Pengcheng Zhao, Pengtao Hu, Liang Wang, Ruiqi Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

The cold plate which constructs by plate fins through 36% aqueous solutions of ethylene glycol to control the heated bottom face to below 28°C, was simulated by Fluent software. The properties such as density and specific heat and thermal conductivity and viscosity of 36% aqueous solutions of ethylene glycol were derived from the doctor thesis of R Wang by neural network method. The low Re k-Ε model was used with shell wall type. The inlet boundaries from 1000Pa to 2500Pa were analysed, the two passes of cold plate flow detail patterns were given, non-uniform velocity field has shown, all parts of the cold plate are coupling. The distributions have shown that pressure and velocity fields nearly with 2D characters, while the temperature field own 3D characters, Performance of cold plate needs to improve the heat sink utilization. The full model shall be considered formore exact results. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Ethylene glycol

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Functional simulation of the cabin pressure control system based on stateflow 3

Functional simulation of the cabin pressure control system b...

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2024 3rd International Conference on aerospace and Control Engineering, ICoACE 2024

作者： Wang, Yehao Meng, Fanxin Yang, Yonghui Wang, Shun Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Jiangsu Nanjing211106 China AVIC Nanjing Engineering Institute of Aircraft Systems Jiangsu Nanjing211106 China

The cabin pressure control system(CPCS) is an important part of the aircraft environmental control system. In the actual flight process, it needs to achieve different functions according to the working scene. In this paper, the architecture and working principle of the CPCS system are summarized, and the functions of the system are analyzed;the control logic of each function is designed and simulated by the Stateflow platform. The results show that the control logic and its transition constraints designed in this paper can meet the functional requirements of the system, and the dynamic response is rapid, which can be used for the cabin pressure control system of civil aircraft system function design and verification to provide a reference. © 2025 Institute of Physics Publishing. All rights reserved.

关键词： Aircraft control

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