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检索条件"机构=Aviation Key Laboratory of Science and Technology on Aero Utility System Integration"

共 250 条记录，以下是51-60 订阅

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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...

引用

CSAA/IET International Conference on Aircraft utility systems (AUS 2024)

作者： Cui Zongtai Shen Xun Gu JingXian Yang Yang Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing 211106 People's Republic of China

ISBN: (数字)9781837242108

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.

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Design of Litz Wire for a Slotless High-speed Permanent Magnet Motor with Gramme-ring Windings

Design of Litz Wire for a Slotless High-speed Permanent Magn...

引用

2022 Joint Magnetism and Magnetic Materials - Intermag Conference, INTERMAG 2022

作者： Zhu, Lingfeng Wan, Yuan Jia, Yuqi Guo, Jian Li, Qiang Jiang, Xuefeng Nanjing University of Science and Technology Nanjing210094 China Avic Nanjing Engineering Institute of Aircraft System/Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211102 China

ISBN: (纸本)9781665483346

The heating problem is a major concern for the design of high-speed permanent magnet motor (HSPMM). This paper first analyzed the copper loss of the litz wires of a slotless gramme-ring-winding HSPMM with gramme-ring windings, combining the analytical and finite-element methods. Then the computational fluid dynamics model was established for thermal analysis. Through the calculation of the loss and temperature field, the strand number and cross-section shapes were finally optimized for litz wires to pursue the minimum temperature rise of the motor, with the methods of DOE and second-order response surface. The proposed optimization process of the design of litz wires is also useful in other electric motors. © 2022 IEEE.

关键词： Winding

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Optimization of Design Method for Thermal Shrinkable Backup Ring in Aircraft Hydraulic Components 5th

Optimization of Design Method for Thermal Shrinkable Backup ...

引用

5th China aviation science and technology Conference, 2021

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

ISBN: (纸本)9789811674228

For the leakage failure caused by the damage of the rubber seal, the cause of the rubber ring damage is analyzed. Through the torsion and rapture of the rubber ring, the problem of thermal shrinkable poly tetrafluoroethylene (PTFE) backup ring heating over shrinkage is found. Finally, this failure is solved by optimizing the design method of the backup ring, including the reserved shrinkage, thickness compensation, etc. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Rubber

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Analysis and Improvement on Asymmetrical Wear in Aircraft Bootstrap Reservoir 5th

Analysis and Improvement on Asymmetrical Wear in Aircraft Bo...

引用

5th China aviation science and technology Conference, 2021

作者： Xu, Xiangrong Zhang, Pengfei Zhou, Qinghe Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China AVIC Jincheng Nanjing Engineering Institute of Aircraft System Nanjing211106 China

ISBN: (纸本)9789811674228

Aiming at the leakage failure and asymmetrical abrasion of a certain type bootstrap reservoir of aircraft, the analysis is carried out from the sealing type and supporting structure of the reservoir. Through comparison, it is known that under the same sealing type and sealing parameters, other similar components did not leak, so the failure is not caused by the sealing type and sealing parameters. From the perspective of the internal support, the bootstrap reservoir is a multi-nested structure, which requires high coaxiality of each component, and even over-constraint. The components is prone to generate additional load during operation and aggravate the wear of the sliding pair, including seals, high-pressure pistons, piston rods, etc. By enlarging the mating clearance, over-constraints of the internal matches are removed, the sliding pair wear in the high pressure cylinder is avoided, and the leakage failure of the bootstrap reservoir is eliminated. Considering that removing a constraint will influence the stiffness of the whole structure, vibration and impact tests have been carried out, and the new bootstrap reservoir has passed the tests. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Wear of materials

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STUDY ON THE APPLICATION OF DUAL-MODE VAPOUR COMPRESSION CYCLE system IN HELICOPTER CABIN THERMAL MANAGEMENT

STUDY ON THE APPLICATION OF DUAL-MODE VAPOUR COMPRESSION CYC...

引用

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

作者： Luo, Pinggen Sun, Zhichuan Yuan, Jiaqi Xia, Wenqing China Helicopter Research and Development Institute No.6-8 Hangkong Road Jingdezhen China AVIC Nanjing Engineering Institute of Aircraft Systems No.33 Shuige Road Nanjing China Aviation Key Laboratory of Science and Technology on Aero Utility System Integration No.33 Shuige Road Nanjing China Nanjing University of Aeronautics and Astronautics Nanjing China

With the increasingly widespread application of modern helicopters, the demand for high-quality thermal management in helicopter crew cabins and electronic equipment cabins has become increasingly prominent. To construct the thermal management system architecture for a helicopter's dual-cabin environmental control, the technical paradigm of a dual-mode vapour compression cycle has been referenced, and a new design concept of recycling lubricating oil heat for auxiliary cabin heating has been proposed. Through the method of system simulation modelling and analysis, a dynamic simulation analysis of the system’s cooling/heating performance under extreme weather conditions was conducted. The study explored the dynamic fluctuation characteristics of both active control parameters (expansion valve opening and compressor speed) and passive control parameters (air temperature, cooling capacity, and heating capacity) within the cabin. The simulation results indicate that overshooting the system’s cooling capacity towards a higher level can help rapidly reduce the air temperature within the cabin. Additionally, there are significant differences in the response characteristics of parameters between dual-cabin and single-cabin operational scenarios. Verified by the simulation results, the proposed helicopter dual-cabin environmental control thermal management system exhibits the feasibility for engineering applications. © The Institution of Engineering & technology 2024.

关键词： Signal receivers

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A FUEL TANK INERT AIR PREPARATION system FOR UAV

A FUEL TANK INERT AIR PREPARATION SYSTEM FOR UAV

引用

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

作者： Liu, Chengyan Qiao, Sijia Gou, Ruirui Lu, Yueliang AVIC Nanjing Engineering Institute of Aircraft Systems Nanjing211106 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China The Third Military Representative Office of Air Force Equipment Department in Nanjing Nanjing211106 China

The fuel tank inert air preparation system (APS) for unmanned aerial vehicles (UAVs) is a relatively novel field. APS is essentially an air refrigeration cycle. APS can cool engine bleed air to a suitable temperature before being used by the on board inert gas generation system (OBIGGS). According to the characteristics of UAVs, an inert APS for fuel tank without ram air and pre-cooling system is proposed in this paper. The matching calculation process of APS is introduced in detail in this paper. Based on AMESim software, the performance simulation model of APS is built. The simulation results show that the APS can meet the performance demand of cooling air under the full flight envelope. The research results of this paper have certain guiding significance for the design work of the tank inert APS applicable to UAVs. © The Institution of Engineering & technology 2024.

关键词： Flight envelopes

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A Method for Reconstructing The Shape of Wing Panels Based on Fiber Optic Sensors and Tomographic Imaging Principles 15

A Method for Reconstructing The Shape of Wing Panels Based o...

引用

15th IEEE Global Reliability and Prognostics and Health Management Conference, PHM-Beijing 2024

作者： Zhan, Jun Zeng, Jie Xiang, Chao Cui, Jinpeng Zeng, Cheng Zhu, Linfeng Lu, Mingyu State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics No. 29 Yudao Street Nanjing210016 China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing Engineering Institute of Aircraft System Jincheng AVIC Nanjing China COMAC Beijing Aircraft Technology Research Institute Changping District Xiaotangshan Future Science and Technology City Beijing102211 China

ISBN: (纸本)9798350354010

The aircraft wing structure shape reconstruction method based on discrete strain information not only provides data support for the digital collaborative health monitoring and prediction technology of wing structure but also helps to improve the aerodynamic shape and flight quality of the aircraft, achieve structural stealth, and enhance the pointing accuracy of the on-board conformal antenna. As result, a wing skin panel shape reconstruction method based on the principle of tomographic imaging and strain information perception is proposed. According to the idea of tomographic imaging, a "non-intrusive" layout form that only requires sensors to be arranged on the periphery of the monitoring area is designed, breaking through the limitation that sensors can not be arranged in the monitoring area under special working conditions. A method for constructing the deflection shape function of the wing skin panel based on the concept of synthetic curvature is proposed, solving the problem of error accumulation and elimination of deformation inversion at non-monitoring points of the measured structure caused by the uncertainty of the limited discrete layout of sensors and the choice of interpolation fitting method. On this basis, a model deformation monitoring and inversion system for wing skin panel based on fiber optic grating sensors is constructed. The experimental results show that under the single-end fixed bending and torsion working condition, the average relative error of the panel model shape reconstruction is 4.17%. Under the double-end fixed double-concentrated load working condition, the average relative error of the shape reconstruction is 8.07%. The wing deformation distribution information reconstructed by the method proposed in this paper can be mapped onto the virtual twin model of the wing, providing technical support for the safety assessment, early warning, and on-condition maintenance of the entire service life of key structures of the aircraft. © 2024

关键词： Fixed wings

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A Numerical Solution of a Hose-And-Drogue Aerial Refueling system: Multi-body Dynamic Model with Varying Constraints 5th

A Numerical Solution of a Hose-And-Drogue Aerial Refueling S...

引用

5th China aviation science and technology Conference, 2021

作者： Fan, Boqian Ji, Kang Wang, Jian Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing211106 China Aviation Key Laboratory of Science and Technology On Aero Electromechanical System Integration Nanjing211106 China

ISBN: (纸本)9789811674228

Probe-and-drogue aerial refueling is a widely used military technique for transferring fuel between aircrafts. A dynamic model for the study of the hose-and-drogue system requires three essential elements, which are the dynamics of the bodies, the external loads and the constraints on the bodies. However, in the most advanced models, either the reel behavior is absent or the interactions between the reel and the hose are ignored. In this paper a model is presented that fully reflects the dynamic behaviors of the hose-drogue system in a multi-body dynamic approach. In the model, the hose is represented by a series of discrete links, while the reel and drogue are represented by mass points connected to the hose. The interaction between the reel and the discrete links of the hose are treated as variable constraints to accurately reflect the hose-drogue system before and during the hose-probe contact. A numerical method based on Newton-Raphson iteration is proposed to solve the multi-body dynamic system with variable constraints. A demonstrative simulation reveals the performance of the method. In the simulation result, the take-up behavior of the hose is observed, which validates the model. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Hose

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Research on the Recognition of Aircraft Fuel Pump Parts Based on Deep Learning

Research on the Recognition of Aircraft Fuel Pump Parts Base...

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

作者： Cui, Zongtai Tian, Qilong Yang, Yang Yang, Chen Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing211106 China Nanjing Engineering Institute of Aircraft Systems AVIC Nanjing211106 China

ISBN: (数字)9781839537769

ISBN: (纸本)9781839537769

As it enables production lines to identify parts independently in their tasks, the application of machine vision has become the trend of flexible manufacturing development. In recent years, deep learning has achieved great success in the field of machine vision. It can recognize patterns with higher accuracy and better generalization, and can satisfy the demands of flexible manufacturing in a better way. In this paper, aiming at the recognition in the assembly line of aircraft fuel pumps, a parts recognition method based on depth learning is studied, an algorithm model for parts recognition based on Inception-v3 is obtained by the application of transfer learning method. The results show that by this way the accuracy of parts recognition could be above 90%, which can meet the demand of recognition accuracy in actual equipment production. © 2022 IET Conference Proceedings. All rights reserved.

关键词： Convolutional neural networks

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A High-Frequency GaN-Based Motor Drive for Aircraft Electro-Mechanical Actuators 18

A High-Frequency GaN-Based Motor Drive for Aircraft Electro-...

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18th IEEE Conference on Industrial Electronics and Applications, ICIEA 2023

作者： Luo, Bin An, Zezhou Shen, Hongming Li, Sihai Guan, Wenqing Zhou, Kai Luo, Guagnzhao Xiao, Xi Zeng, Youhua Northwestern Polytechnical University School of Automation Xi'an China Northwestern Polytechnical University Gansu Key Laboratory of Aeronautical Electro-Mechanical Actuator Lanzhou China Aviation Key Laboratory of Science and Technology on Aero Electromechanical System Integration Nanjing China Avic Beijing ShuGuang Aviation Electric Co.Ltd Beijing China

ISBN: (纸本)9798350312201

Cascade GaN devices extremely attractive for aircraft EMAs application because it has the high switching frequency, low loss and high temperature operating capability. However, owing to complex device structure and high dv/dt and di/dt characteristics, GaN-based motor drive are more prone to current or voltage overshoots and oscillations, even device breakdown. In this paper, a prototype of 5-kW GaN-based motor drive is demonstrated with 100 kHz switching frequency. The mathematical model of turn-ON dv/dt effect and the turn-OFF di/dt effect of cascode GaN based inverter was established to reveal the occurrence mechanism of false trigger and oscillation. Then a systematic design methodology to design the gate driver and snubber parameters is proposed. Finally, experimental are carried out to validate the proposed design methods. © 2023 IEEE.

关键词： Electromechanical actuators

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