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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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Machine learning for predicting fatigue properties of additively manufactured materials

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Chinese Journal of Aeronautics 2024年第4期37卷 1-22页

作者： Min YI Ming XUE Peihong CONG Yang SONG Haiyang ZHANG Lingfeng WANG Liucheng ZHOU Yinghong LI Wanlin GUO State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Institute for Frontier Science Nanjing University of Aeronautics and AstronauticsNanjing 210016China College of Aerospace Engineering Nanjing University of Aeronautics and AstronauticsNanjing 210016China Shenyang Engine Research Institute Shenyang 110015China Liaoning Key Laboratory of Impact Dynamics on Aero Engine Shenyang 110015China Science and Technology on Plasma Dynamics Laboratory Air Force Engineering UniversityXi’an 710038China

Fatigue properties of materials by Additive Manufacturing(AM) depend on many factors such as AM processing parameter, microstructure, residual stress, surface roughness, porosities, post-treatments, etc. Their evaluation inevitably requires these factors combined as many as possible, thus resulting in low efficiency and high cost. In recent years, their assessment by leveraging the power of Machine Learning(ML) has gained increasing attentions. A comprehensive overview on the state-of-the-art progress of applying ML strategies to predict fatigue properties of AM materials, as well as their dependence on AM processing and post-processing parameters such as laser power, scanning speed, layer height, hatch distance, built direction, post-heat temperature,etc., were presented. A few attempts in employing Feedforward Neural Network(FNN), Convolutional Neural Network(CNN), Adaptive Network-Based Fuzzy Inference System(ANFIS), Support Vector Machine(SVM) and Random Forest(RF) to predict fatigue life and RF to predict fatigue crack growth rate are summarized. The ML models for predicting AM materials' fatigue properties are found intrinsically similar to the commonly used ones, but are modified to involve AM features. Finally, an outlook for challenges(i.e., small dataset, multifarious features,overfitting, low interpretability, and unable extension from AM material data to structure life) and potential solutions for the ML prediction of AM materials' fatigue properties is provided.

关键词： Additive manufacturing Machine learning Fatigue life Fatigue crack growth rate Prediction

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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 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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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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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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Study on the influence of typical runway environment on the crashworthiness of fuselage section

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： Y. Zhou S. Zhu X. Xi College of aerospace engineering Nanjing university of aeronautics and astronautics Nanjing 210016 People's Republic of China Aviation key laboratory of science and technology on structures impact dynamics Aircraft strength research institute of China Xi'an 710065 People's Republic of China

ISBN: (数字)9781837240753

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.

关键词：

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Development and global validation of a 1-week-old piglet head finite element model for impact simulations

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Chinese Journal of Traumatology 2023年第3期26卷 147-154页

作者： Zhong-Qing Su Da-Peng Li Rui Li Guang-Liang Wang Lang Liu Ya-Feng Wang Ya-Zhou Guo Zhi-Gang Li School of Mechanical Electronic and Control EngineeringBeijing Jiaotong UniversityBejing100044China D epartment of NeurosurgeryBejing Children's Hospital CapitalMedical University.National CenterforChildren'sHealthBeijing 100045China Aviation Key Laboratory of Science and Technology on Structures Impact Dynamics China Aircraft Strength Research InstituteXi'an70065China

Purpose:Child head injury under impact scenarios(***,vehicle crashes,etc.)is an important topic in the field of injury *** head of piglet was commonly used as the surrogate to investigate the biomechanical response and mechanisms of pediatric head injuries because of the similar cellular structures and material ***,up to date,piglet head models with accurate geometry and material properties,which have been validated by impact experiments,are *** aim to develop such a model for future ***:In this study,first,the detailed anatomical structures of the piglet head,including the skull,suture,brain,pia mater,dura mater,cerebrospinal fluid,scalp and soft tissue,were constructed based on CT ***,a structured butterfly method was adopted to mesh the complex geometries of the piglet head to generate high-quality elements and each component was assigned corresponding constitutive material ***,the guided drop tower tests were conducted and the force-time histories were ectracted to validate the piglet head finite element ***:Simulations were conducted on the developed finite element model under impact conditions and the simulation results were compared with the experimental data from the guided drop tower tests and the published *** average peak force and duration of the guide drop tower test were similar to that of the simulation,with an error below 10%.The inaccuracy was below 20%.The average peak force and duration reported in the literature were comparable to those of the simulation,with the exception of the duration for an impact energy of 11 *** results showed that the model was capable to capture the response of the pig ***:This study can provide an effective tool for investigating child head injury mechanisms and protection strategies under impact loading conditions.

关键词： Piglet head Finite element model Dynamic response Validation Drop tower tests

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