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11th International Forum on Electrical Engineering and Automation, IFEEA 2024

作者： Zhang, Yirui Yang, Shibin Xi, Xulong College of Safety Science and Engineering Civil Aviation University of China CAUC Tian Jin China Aircraft Strength Research Institute of China National Key Laboratory of Strength and Structural Integrity Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics Xi'an China

ISBN: (纸本)9798331516611

Active disturbance rejection control (ADRC) is an advanced control technology, which does not depend on the precise model of the controlled object and can deal with external disturbance effectively. Therefore, in order to solve the errors of glide path and flight path caused by wind disturbance during the automatic landing of civil aircraft, ADRC can be applied to the system. The second-order cascade LADRC systems of longitudinal and lateral directions are designed respectively, in which the attitude angle control is designed for inner loop and the position control is designed for out loop. The simulation shows that both cascaded LADRC and PID controllers have a certain inhibitory effect on wind disturbance. While the LADRC controller has smaller overshoot, stronger robustness, stronger course keeping ability and anti-interference ability. And the parameters of LADRC controller need to be adjusted are not too many, which meets the actual engineering requirements. © 2024 IEEE.

关键词： Disturbance rejection

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Study on Evolution of Surface Morphology and Temperature of Carbon Fiber Composites Irradiated by Millisecond Pulsed Laser 2

Study on Evolution of Surface Morphology and Temperature of ...

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2nd International Conference on Advanced Optics and Photonics Research in Engineering, AOPR 2022

作者： Gong, Lei Zhang, Yu Zhang, Yizhuo Wang, Hongrui Zhang, Chi AVIC Manufacturing Technology Institute Beijing100024 China Aviation Key Laboratory of Science and Technology on Structural Impact Dynamics Aircraft Strength Research Institute of China Xi'an710065 China

The study of the interaction between laser and composite materials has attracted the attention of many researchers. In this paper, the surface morphology and temperature evolution of T300 carbon fiber composites irradiated by millisecond pulse laser were studied and analyzed experimentally. The transient morphology change process of the front surface of the material was observed by a camera. With the injection of pulsed laser energy, the material began to change its characteristics from the center, leading to a decrease in reflectivity of it, and this area expanded with the accumulation of laser energy. The temperature change on the back of the material was observed by a thermal imager. Within a certain range and the same laser irradiation time, the greater the injected energy per unit area, the faster the temperature of the back center rises. However, under the same circumstances as above, the highest center temperature of the back of the composites is only related to the total energy injected, and has nothing to do with the spot size. © Published under licence by IOP Publishing Ltd.

关键词： Pulsed lasers

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Fracture toughness of fibre failure modes in laminated composites under dynamic loading 4

Fracture toughness of fibre failure modes in laminated compo...

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4th International Conference on Defence technology, ICDT 2024

作者： He, Rui Cheng, Longfei Gao, Yidi Cui, Hao Li, Yulong Liu, Jianhu TaiHu Laboratory of Deepsea Technological Science Wuxi China National Key Laboratory of Ship Structural Safety China Ship Scientific Research Center Wuxi China Shaanxi Key Laboratory of Impact Dynamics and Its Engineering Applications Northwestern Polytechnical University Xi'an China School of Civil Aviation Northwestern Polytechnical University Suzhou China

The fracture toughness regarding fibre tensile failure and fibre compression kinking was measured using compact tension and compact compression specimens on a uniaxial bi-directional electromagnetic Hopkinson bar system. During the dynamic tests, the strain/displacement fields were monitored using the digital image correlation technique with a high-speed camera. Digital and scanning electron microscopy were used to investigate the fracture faces of the tested specimens. The initial fracture toughness for fibre tensile failure under quasi-static and dynamic loading was 166 kJ/m2 and 113 kJ/m2, respectively. For fibre compression kinking, the initial fracture toughness was approximately 120 kJ/m2 for both loading conditions. Less fibre pull-out may be responsible for the decrease in fracture toughness for fibre tensile failure under dynamic loading. Whereas for fibre compression kinking failure, there was no significant difference in the fracture faces of the damaged specimens at different loading rates. © 2024 Institute of Physics Publishing. All rights reserved.

关键词： High speed cameras

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STUDY ON THE INFLUENCE OF TYPICAL RUNWAY ENVIRONMENT ON THE CRASHWORTHINESS OF FUSELAGE SECTION 3

STUDY ON THE INFLUENCE OF TYPICAL RUNWAY ENVIRONMENT ON THE ...

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3rd International Conference on Mechanical, Aerospace and Automotive Engineering, CMAAE 2023

作者： Zhou, Yukun Zhu, Shuhua Xi, Xulong College of Aerospace Engineering Nanjing University of Aeronautics and Astronautics Nanjing210016 China Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics Aircraft Strength Research Institute of China Xi’an710065 China

ISBN: (纸本)9781839539954

In order to study the crashworthiness of civil aircraft fuselage section in typical runway crash environments, this paper takes the metal fuselage structure of a typical civil aircraft as the research object. The environment models of the multi-layer structural runway, the off-runway soil and the rigid ground, and the structural model of the middle fuselage section of a certain type of civil aircraft were established. Furthermore, based on the simulation model, the effects of different ground environments on the fuselage section structural crashworthiness under the action of the vertical impact speed of 7m/s were studied by means of the finite element simulation method. The simulation results show that the mesh size of the ground environment has a significant effect on the calculation time;For asphalt concrete runway modeled based on the elastic layer theory, the thickness of the soil base is the key to the overall model dimensions;the multi-layer structural runway environment has a certain buffering effect on the structural collision process compared with the rigid surface environment;the surface icing runway environment has a smaller effect on the dynamic response of the fuselage section structure under vertical impact;while the off-runway soil environment has a stronger buffering effect, but it will change the way of energy absorption of the structure. © The Institution of Engineering & technology 2023.

关键词： Asphalt concrete

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Study on Automatic Landing of Civil Aircraft Based on LADRC

Study on Automatic Landing of Civil Aircraft Based on LADRC

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Electrical Engineering and Automation (IFEEA), International Forum on

作者： Yirui Zhang Shibin Yang Xulong Xi College of Safety Science and Engineering Civil Aviation University of China CAUC Tian Jin China National Key Laboratory of Strength and Structural Integrity Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics Aircraft Strength Research Institute of China Xi'an China

ISBN: (数字)9798331516611

ISBN: (纸本)9798331516628

关键词： Robust control Electrical engineering PI control Automation Attitude control Position control Robustness PD control Aircraft Aircraft propulsion

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An Updating Method of Aero Tyre Model by Shimmy Test 6th

An Updating Method of Aero Tyre Model by Shimmy Test

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6th China Aeronautical science and technology Conference, CASTC 2023

作者： Liu, Chongchong Liu, Xiaochuan Xu, Yong Du, Xiaolei Yang, Zhengquan Liu, Shengli National Key Laboratory of Strength and Structural Integrity Aircraft Strength Research Institute of China Shanxi Xi’an710065 China Aviation Key Laboratory of Technology and Science on Structure Impact Dynamics Aircraft Strength Research Institute of China Shanxi Xi’an710065 China School of Mechanics Civil Engineering and Architecture Northwestern Polytechnical University Xi’an710072 China School of Mathematics and Statistics Northwestern Polytechnical University Xi’an710072 China

ISBN: (纸本)9789819988600

Speed and oscillation frequency are two key factors that effect tyre lateral dynamic characteristics. Tyre models for previous landing gear shimmy analysis use stationary shape functions for the lateral tyre deformation which eliminate the effects of tyre speed and oscillation frequency. The lateral dynamic characteristics of tyre are studied by test on the dynamometer facility. The variation trend of amplitudes of the tyre self-aligning moment and lateral force with different speeds and oscillation frequencies is observed and fitted based on test results. The tyre model for landing gear shimmy analysis is updated by fitted coefficients. Nonlinear shimmy bifurcation analysis shows the shimmy unstable region enlarges when the tyre speed and frequency effects are considered. The method of updating tyre shimmy model based on test results could be used in landing gear shimmy analysis to improve the analysis accuracy. © 2024, Chinese Society of Aeronautics and Astronautics.

关键词： Dynamometers

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A Rapid and Integrated Modeling Method of Aircraft Vulnerability Based on CATIA Analysis Simulation Module 5th

A Rapid and Integrated Modeling Method of Aircraft Vulnerabi...

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5th China aviation science and technology Conference, 2021

作者： Pei, Yang Shi, Likuan Ge, Yuxue Li, Mingsuo Bai, Chunyu Zhang, Yu School of Aeronautics Northwestern Polytechnical University Xi’an710072 China Science and Technology on Electro-Optic Control Laboratory Luoyang471009 China Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics Aircraft Strength Research Institute of China Xi’an710065 China

ISBN: (纸本)9789811674228

Aircraft vulnerability modeling is the basis and prerequisite for vulnerability analysis. At present, vulnerability modeling methods include combinatorial geometry, triangular patch, and tetragonal patch. However, these methods have disadvantages such as low modeling accuracy, complex modeling process, and finite element software. Under the problems of the above methods, a vulnerability modeling method is proposed based on the CATIA Analysis Simulation module, in which the secondary development of the aircraft shape and the tetragonal mesh, materials, and attribute of the components data file are completed. In this method, the geometrical modeling and meshing are synchronized and integrated into the CATIA platform which shortens the vulnerability pre-modeling process. Taking the US "Scan Eagle" UAV as an example, the input model file for vulnerability analysis is generated. The effect of this method and the traditional finite element modeling method is compared in C and K kill levels, which verifies the validity and usability of the proposed method. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Aircraft

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A Slider-Type Trim Strategy to Deal with Wing Perforation Damage Based on CFD 5th

A Slider-Type Trim Strategy to Deal with Wing Perforation Da...

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5th China aviation science and technology Conference, 2021

作者： Peng, Qiancheng Pei, Yang Li, Mingsuo Bai, Chunyu Zhang, Yu School of Aeronautics Northwestern Polytechnical University Xi’an710072 China Science and Technology on Electro-Optic Control Laboratory Luoyang471009 China Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics Aircraft Strength Research Institute of China Xi’an710065 China

ISBN: (纸本)9789811674228

In this paper, a numerical simulation study is carried out on the aerodynamic characteristics of the aircraft wing surface after damage. The damage form is the wing perforation. To study the aerodynamic characteristics of the UAV under the condition of varying degrees of damage to the wings of the small airplane model, establish the geometric model of the airplane model in the CATIA 3D modeling software, and establish the geometric model in ANSYS ICEM and divide the calculation domain flow field grid. Perform aerodynamic calculations in ANSYS FLUENT. Firstly, the aerodynamic characteristics of the undamaged aircraft are calculated and analyzed, and then the aerodynamic characteristics of each damage situation are compared according to the different damage positions, and a response strategy using the slider as an auxiliary trim method is proposed. The research results have certain reference value for aircraft design of this type of layout. © 2022, The Author(s), under exclusive license to Springer Nature Singapore Pte Ltd.

关键词： Wings

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Ultra-Long Tensional Stress Wave Loading for Polymer Under Intermediate High Strain Rates

SSRN

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SSRN 2024年

作者： Yin, Jianping Miao, Yinggang Wu, Zhibo He, He Zhang, Chenxu Sun, Ruoheng Liu, Jie Li, Yulong Shaanxi Key Laboratory of Impact Dynamics and its Engineering Application School of Aeronautics Northwestern Polytechnical University Shaanxi Xi’an710072 China School of Civil Aviation Northwestern Polytechnical University Xi’an710072 China School of Aeronautics Northwestern Polytechnical University Xi’an710072 China Joint International Research Laboratory of Impact Dynamics and its Engineering Applications School of Aeronautics Northwestern Polytechnical University Shaanxi Xi’an710072 China School of Materials Science and Engineering Hubei University Wuhan430062 China National Key Laboratory of Strength and Structural Integrity Shaanxi Xi’an710072 China

The Hopkinson bar technique frequently encounters challenges when dealing with large strain requirements, particularly under intermediate strain rate tensile loading. This work presents a methodology to generate ultra-long tensional stress waves using a specifically designed tube that impacts incident bar, and subsequently derived reflected wave is elaborately designed to follow its previous incident wave, forming a continuous and ultra-long tensional stress wave. It is then integrated into a split Hopkinson tension bar for performing dynamic tension tests under intermediate strain rate and large strain loading. Meanwhile, a short transmission bar is developed and analyzed to accurately capture the ultra-long transmitted wave for interpreting specimen stress. The validity of this approach is confirmed through theoretical deductions and finite element simulations. To experimentally verify the apparatus for intermediate strain rate tensile loading, tensile tests were conducted on a rubber specimen at an average strain rate of approximately 64 s-1. The system demonstrated the capability to achieve wave durations of up to 200 ms and strains of up to 1200%. High frame rate camera images were used to demonstrate the reliability and effectiveness of the apparatus. Finally, the study discusses the potential extensions and limitations of this experimental setup, for a broader range of strain rates and materials tested using the developed Hopkinson tension bar. © 2024, The Authors. All rights reserved.

关键词： Strain rate

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Image-Driven Prediction of Fatigue Crack Growth in Metal Materials Via Spatiotemporal Neural Network

SSRN

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SSRN 2024年

作者： Liang, Jiaming Yu, Yin Hu, Yile Wan, Chunhua Feng, Xiaozhe Lab of Civil Aircraft Structures Testing School of Aeronautics and Astronautics Shanghai Jiao Tong University Shanghai200240 China Aerospace Structure Research Center School of Aeronautics and Astronautics Shanghai Jiao Tong University Shanghai200240 China National Key Laboratory of Strength and Structural Integrity Aircraft Strength Research Institute of China Xi’an710065 China Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics Aircraft Strength Research Institute of China Xi’an710065 China

This study proposes an image-driven model based on SimVP spatiotemporal neural network (STNN) to predict the fatigue crack growth (FCG) in aluminum alloys. This methodology marks a pioneering usage of STNN for FCG analysis. It avoids the need for repetitive modeling, extensive computations, and conventional mechanical assumptions. The datasets are gathered from the fatigue experiments with different crack positions, angles, and load levels, amounting to a total of 17,925 frames of images obtained from DIC. Subsequently, the displacement fields are interpolated onto uniform grids and then augmented to be fitted into STNN. The proposed method is validated with edge- and central-cracked specimens under 15.0% and 20.0% load levels. The generalization performance of the proposed method is studied by predicting FCG under the load levels and crack angles which are absent in the training set. In addition, the predictive capability of FCG is investigated with short and long step-sizes by collecting image data with varying intervals. The over-all structural similarity index measures (SSIM) are above 0.968 and the root mean square error (RMSE) can be suppressed under 0.025 mm. The predicted displacement field, crack length, and crack growth rate have every good agreement with experimental measurements. © 2024, The Authors. All rights reserved.

关键词： Fatigue crack propagation

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