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2024 3rd International Conference on Applied Mechanics and advanced Materials, ICAMAM 2024

作者： Li, Chongyuan Yao, Weixing Key Lab. of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and Astronautics Nanjing210016 China

This article introduces a method to determine the Detail Fatigue Rating (DFR) of lugs through constant amplitude fatigue testing. Fatigue tests of titanium alloy lugs were designed, and the DFR of lugs was calculated based on the test results. A comparative analysis was conducted from two aspects: the relative width (d/b) and the loading direction (?) of straight lugs, and the effect of lug parameters on the DFR was discussed. The results indicate that the DFR of lugs is positively correlated with the relative width (d/b) and negatively correlated with the loading direction (?). © Published under licence by IOP Publishing Ltd.

关键词： Titanium alloys

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Improving aircraft nose wheel steering stability based on control continuation method

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science China(Technological sciences) 2025年第3期68卷 258-277页

作者： Qiaozhi YIN Dexu KONG Jiawei WANG Hong NIE Xiaohui WEI National Key Laboratory of Helicopter Aeromechanics Nanjing210016China State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing210016China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing210016China AVIC Nanjing Engineering Institute of Aircraft Systems Nanjing211106China

Aircraft steering instability during the taxiing process sometimes occurs resulting from the unstable bifurcation phenomena of the nonlinear steering dynamic system,which may lead to severe *** this study,the control parameter design of an aircraft nose wheel steering control system based on the control continuation method is proposed to reduce the number of unstable bifurcation points and enlarge the system stable region area in a certain parameter ***,the aircraft turning performance can be improved ***,a nonlinear aircraft rollout dynamic model is constructed,and the aircraft ground steering bifurcation characteristics are obtained under the open-loop steering control ***,the bifurcation performances under three closed-loop nose wheel steering controllers based on the feedback control method are compared,and the control parameter of the quadratic nonlinear controller with a better bifurcation control effect is selected as a second bifurcation parameter to analyze the directional system stability via two-parameter bifurcation ***,the influence of a crosswind on the aircraft ground steering bifurcation performance is studied for various control parameter ***,the control effects of a traditional proportional-integral-derivative(PID)nose wheel steering control law and the designed feedback controller are compared and ***,a semi-physical experiment of the aircraft nose wheel steering system is carried out,and different control parameter values are selected for test verification,which can further verify the control effect of the designed nonlinear feedback *** results indicate that the feedback control method is unable to vary the system bifurcation types,but appropriate control parameter design can effectively shrink the system instability region and even eliminate the unstable Hopf bifurcation points under some specific working conditions,improving the aircraft ground turning stability re

关键词： aircraft taxiing dynamics and stability nose wheel steering control system control continuation steering bifurcation characteristics quadratic feedback control

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An architecture decomposition method of pneumatic catapult system based on OPM and DSM

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Chinese Journal of Aeronautics 2023年第8期36卷 168-181页

作者： Lu GAN Gang YANG Xianhui LI Enze ZHU Hu CHEN Xiaohui WEI State Key Laboratory of Mechanics and Control of Aerospace Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and AstronauticsNanjing 210016China College of General Aviation and Flight Nanjing University of Aeronautics and AstronauticsNanjing 210016China

The architecture strategy of the Unmanned Aerial vehicle(UAV)pneumatic launch system should continue to evolve to adapt to complex and variable operating *** representation,decomposition perspective,and cluster analysis play a vital role in the early phase of system architecture *** order for the system to emerge anticipated and desirable intrinsic functional properties,an architecture decomposition method based on the ObjectProcess Methodology(OPM)and design Structure Matrix(DSM)is put forward in this *** OPM is proposed to model the UAV launch process formally,and the matrix representation of the architecture of the pneumatic launch system is *** the extension of the definition and operations of DSM,with the Idicula-Gutierrez-Thebeau Algorithm plus(IGTA+)clustering algorithm,the transformation of the pneumatic launch system architecture from process decomposition to function decomposition is demonstrated in this *** analysis shows that the architecture decomposition of the pneumatic launch system meets the functional requirements of stakeholders.

关键词： Architecture decomposition Cluster analysis design structure matrix Object-process methodology Pneumatic catapult system

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Reliability analysis of arresting hook engaging arresting cable for carrier-based aircraft influenced by multifactors

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Chinese Journal of Aeronautics 2023年第1期36卷 311-323页

作者： Yiming PENG Yin YIN Pengpeng XIE Xiaohui WEI Hong NIE State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and AstronauticsNanjing 210016China Shanghai Institute of Spacecraft Equipment Shanghai 200240China

The carrier-based aircraft landing and arrest process is complex and nonlinear,and includes the coupling effect between the aircraft and arresting *** has many uncertain factors,which lead to difficulty in the reliability *** make the reliability analysis more accurate and effective,this paper presents some *** a certain type of carrier-based aircraft as the research object,a dynamic model of the landing and arrest cable was established,and the accuracy of the model was verified using lab.ratory test *** on the model,this paper shows how the key parameters,including the sinking velocity,pitch angle and horizontal velocity,affect the collision rebound performance of the arresting *** that,a limit state equation of the arresting hook system’s reliability was *** the implicit limit state equation,a surrogate model of the reliability of the arresting hook was established using the Support Vector Machine(SVM)method,and then reliability analysis was carried out using the Monte Carlo ***,it was explained in detail how the key parameters affect the reliability of the hook engaging the arresting cable,and some meaningful conclusions were *** analysis method and its results can provide a reference for the top-level parameter design of carrier-based aircraft and reliability research on the arresting systems.

关键词： Arresting cable Arresting devices Dynamics Reliability Support Vector Machines

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Bifurcation analysis of dual-sidestay landing gear locking performance considering joint clearance

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Chinese Journal of Aeronautics 2022年第7期35卷 209-226页

作者： Kui XU Yin YIN Yixin YANG Hong NIE Xiaohui WEI State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and AstronauticsNanjing 210016China

Sidestay lock mechanism is an important part of landing gear system,and the locking performance can be analyzed based on changes in its ***,during numerical continuation analysis of fully-rigid dual-sidestay landing gear without clearance,it has been found that the appearance of bifurcation points does not necessarily imply that both sidestay links can be locked *** problem reveals the limitations of fully-rigid model with ideally-articulated in solving dual-sidestay mechanisms with extremely high motion ***,this study proposes a bifurcation analysis method for synchronous locking of dual-sidestay landing gears,which takes into consideration the joint *** in-depth analysis of this problem,we initially build kinematic and mechanical models of a landing gear mechanism that consider joint ***,the models are solved based on *** fundamental causes of synchronous locking are discussed in detail,and the number of bifurcation points is found to be closely related to whether the landing gear is completely ***,the effects of structural parameters on the synchronous locking are analyzed,and the feasible region of parameters satisfying synchronous locking condition is given,which agrees well with the test results.

关键词： Bifurcation Clearance Dual-sidestay landing gear Numerical continuation Synchronous locking

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Optimization design containing dimension and buffer parameters of landing legs for reusable landing vehicle

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Chinese Journal of Aeronautics 2022年第3期35卷 234-249页

作者： Bo LEI Ming ZHANG Hanyu LIN Hong NIE Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and AstronauticsNanjing 210016China State Key Laboratory of Mechanics and Control of Mechanical Structure Nanjing University of Aeronautics and AstronauticsNanjing 210016China

For the landing legs with single air chamber in the buffer structure of the reusable landing vehicle,the geometric topological models and the dynamic model associated with the hard points of the landing legs are *** geometric constraint relationship in the design of the landing legs is also *** whole vehicle dropping test is conducted,and the test results agree well with that of the simulation model,which validates the dynamic *** on the verified model,the effect of hard point positions on the performance of the landing system is *** multidisciplinary collab.rative optimization algorithm and archive-based micro genetic algorithm(CO-AMGA)are used to optimize the design parameters that contain the hard points and the *** with artificial iteration,the maximum landing impact acceleration response of the vehicle and the buffer struct maximum force are reduced by 30.70%and 14.51%respectively,and the maximum length of retractable pillar decreases by 8.54%while the design margin increases by 69.11%.The proposed optimization method is efficient and can greatly facilitate the design of landing legs.

关键词： Dynamics Impact test Landing system Optimization design Reusable landing vehicle

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Motion Reliability Analysis of Retractation Mechanism Based on Co-simulation 6th

Motion Reliability Analysis of Retractation Mechanism Based ...

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6th China Aeronautical science and technology Conference, CASTC 2023

作者： Zhou, Jiyuan Yan, Yumeng Yin, Yin Nie, Hong Wei, Xiaohui State Key Laboratory of Mechanics and Control for Aerospace Structures Nanjing University of Aeronautics and Astronautics Nanjing210016 China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and Astronautics Nanjing210016 China

ISBN: (纸本)9789819988631

The motion reliability of the landing gear retraction mechanism is influenced by multiple random factors during the aircraft’s service life, resulting in poorer motion reliability and undesirable motion characteristics. This paper proposes a method to analyze the motion reliability of the retraction mechanism that considers the influence of multi-source random factors, and the proposed method is applied to the rotatable tire-type landing gear retraction mechanism of a hypersonic vehicle. Then the sources of random factors that affect the performance of the retraction mechanism are thoroughly studied, and the probability method is used to determine the randomness of joint clearances, installation deviations, and aerodynamic load. Additionally, to address the issue of the retraction mechanism failure mode being an implicit function, an estimation model of the motion reliability of the retraction mechanism under multi-source random factors is established. The model is based on the Monte Carlo method and neural network, using a verified co-simulation model of the retraction mechanism. Finally, the impact of the mean and standard deviation of joint clearances, installation deviations, and aerodynamic load on motion reliability is evaluated. key inspection guidelines are also provided for the operation and maintenance of the retraction mechanism. © 2024, Chinese Society of Aeronautics and Astronautics.

关键词： Aerodynamic loads

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Parameter effects on high-speed UAV ground directional stability using bifurcation analysis

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Chinese Journal of Aeronautics 2021年第11期34卷 1-14页

作者： Qiaozhi YIN Xiaohui WEI Hong NIE Jian DENG State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and AstronauticsNanjing 210016China MIIT Key Laboratory of Multifunctional Lightweight Materials and Structures Nanjing University of Aeronautics and AstronauticsNanjing 210016China

A loss of ground directional stability can trigger a high-speed Unmanned Aerial vehicle(UAV)to veer off the *** order to investigate the combined effects of the key structural and operational parameters on the UAV ground directional stability from a global perspective,a fully parameterized mathematical high-speed UAV ground nonlinear dynamic model is developed considering several nonlinear *** bifurcation analysis procedure of a UAV ground steering system is introduced,following which the simulation efficiency is greatly improved comparing with the time-domain simulation *** the numerical continuation method is employed to investigate the influence of the nose wheel steering angle and the global stability region is *** bifurcation parameter plane is divided into several parts with different stability properties by the saddle nodes and the Hopf bifurcation *** find that the UAV motion states will never cross the bifurcation curve in the nonlinear ***,the dual-parameter bifurcation analyses are presented to give a complete description of the possible steering *** is also found that BT bifurcation appears when the UAV initial rectilinear velocity and the tire frictional coefficient *** addition,results indicate that the influence of tire frictional coefficient has an opposite trend to the influence of initial rectilinear ***,using bifurcation analysis method to identify the parameter regions of a UAV nonlinear ground dynamic system helps to improve the development efficiency and quality during UAV designing phase.

关键词： Bifurcation analysis Ground directional stability High-speed UAV Nonlinear system Numerical continuation

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advanced Finite Element Modeling Methods for Tensile and Bending Analysis of Arresting Gear Cables

SSRN

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SSRN 2024年

作者： Li, Long Peng, Yiming Wang, Yifeng Wei, Xiaohui Nie, Hong State Key Laboratory of Mechanics and Control of Mechanical Structures Nanjing University of Aeronautics and Astronautics Jiangsu Nanjing China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and Astronautics Jiangsu Nanjing China

This study addresses the gap in understanding the dynamic bending behavior of multi-layer twisted steel cable, pivotal in various industrial applications such as naval aircraft arresting systems. Utilizing advanced finite element modeling, the research explores the mechanical responses of these cables under macroscopic bending scenarios. By integrating beam elements and connectors within the finite element framework, the study simulates complex inter-strand interactions under various loading conditions. Results indicate that this method significantly enhances the prediction accuracy of the cables’ mechanical properties, thus offering substantial improvements in design and performance analysis of arresting gear systems. This study's value lies in its potential to refine mechanical modeling of complex cable systems, thereby optimizing operational efficiency and safety in engineering applications. © 2024, The Authors. All rights reserved.

关键词： Finite element method

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Research on Turning Characteristics of Helicopter Ground Motion

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Transactions of Nanjing University of Aeronautics and Astronautics 2022年第5期39卷 593-605页

作者： LI Jin ZHANG Ming* HUANG Jianxin CHEN Xiang WEI Xiyang China Helicopter Research and Development Institute Jingdezhen 333001P.R.China Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle Nanjing University of Aeronautics and AstronauticsNanjing 210016P.R.China

In the passive turning state,the helicopter turns through the tail rotor force and the friction of the ground to the *** practice,it is found that the helicopter will turn difficultly under low aircraft ground speed or static *** paper takes a certain type of helicopter as the research object,and establishes the dynamic model of helicopter ground turning motion based on the basic theory of *** model takes into account the six-degree-of-freedom motion model of the helicopter body,the motion model of the landing gear buffer,the tire mechanics model and the friction characteristics of the strut friction *** dynamic simulation of the helicopter right angle turn and static turn is carried out,and the influence of parameters such as tail rotor pull,taxi speed,tail wheel stability distance on the dynamic response of the turn is *** results show that under the same ground taxing speed,the tail wheel angle increases with the increase of tail rotor *** the tail rotor force is the same,the tail wheel angle increases with the increase of ground taxing *** the helicopter is completely static,it is the most difficult to turn,which requires much bigger force of the tail rotor to *** addition,the change of the stability distance of the tail wheel has an obvious influence on the *** the stability distance is doubled,the tail rotor force will be reduced by 30%to the same angle of the tail wheel.

关键词： helicopter ground motion dynamics analysis passive turning landing gear

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