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Numerical research on slamming characteristics of aircraft landing on water

Journal of Hydrodynamics 2023年第1期35卷 171-184页

作者： Dao-sheng Ning Ya-jun Shi Gui-yong Zhang Heng Wang Huan Hu Zhi-fan Zhang State Key Laboratory of Structural Analysis for Industrial Equipment School of Naval Architecture EngineeringDalian University of TechnologyDalian116024China China Ship Scientific Research Center Wuxi200136China Collaborative Innovation Center for Advanced Ship and Deep-Sea Exploration Shanghai200240China State Key Laboratory of Explosion Science and Technology Beijing Institute of TechnologyBeijing100081China

In order to investigate the impact characteristic of an aircraft landing on water,a computational fluid dynamics(CFD)simulation is conducted to explore the slamming characteristics of the NACA TN 2929 A *** flow around the model is solved by using Reynolds-averaged Navier-Stokes equations with the shear stress transport(SST)k—ωturbulence model,based on finite volume method(FVM).The free surface is captured by using the volume of fluid(VOF)method,and the aircraft impact process is realized with help of overset mesh ***,the effects of horizontal and vertical velocities and initial pitch angle on the slamming load,attitude change,impact pressure and flow field evolution are *** results reveal that the horizontal velocity has a considerable influence on whether the aircraft’s horizontal tail hits the water,and further affects the maximum vertical load as well as the maximum pitch angle throughout the impact *** vertical velocity determines the slamming load before the horizontal tail strikes the water,while the horizontal velocity has a significant effect on the load after the horizontal tail hits the water.A smaller initial pitch angle results in not only a heavier slamming load but also a more dramatic change of the posture after the aircraft impacts the *** impact pressure of the aircraft is maximized at the junction of the approaching surface of the fuselage and the free *** some cases,the pressure is also concentrated on the undersurface of the horizontal tail.

关键词： Computational fluid dynamics(CFD) aircraft landing water entry slamming load motion attitude change

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An aircraft brake control algorithm with torque compensation based on RBF neural network

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Chinese Journal of Aeronautics 2024年第1期37卷 438-450页

作者： Ning BAI Xiaochao LIU Juefei LI Zhuangzhuang WANG Pengyuan QI Yaoxing SHANG Zongxia JIAO School of Automation Science and Electrical Engineering Beihang UniversityBeijing 100191China Science and Technology on aircraft Control Laboratory Beihang UniversityBeijing 100191China Key Laboratory of Advanced aircraft Systems(Beihang University) Ministry of Industry and Information TechnologyBeijing 100091China Research Institute for Frontier Science Beihang UniversityBeijing 100191China Ningbo Institute of Technology of Beihang University Ningbo 315800China Tianmushan Laboratory Xixi Octagon CityYuhang DistrictHangzhou 310023China

The wheel brake system of an aircraft is the key to ensure its safe landing and rejected takeoff.A wheel’s slip state is determined by the brake torque and ground adhesion torque,both of which have a large degree of *** is this nature that brings upon the challenge of obtaining high deceleration rate for aircraft brake *** overcome the disturbances caused by the above uncertainties,a braking control law is designed,which consists of two parts:runway surface recognition and wheel’s slip state *** runway surface recognition,the identification rules balancing safety and braking efficiency are defined,and the actual identification process is realized through recursive least square method with forgetting *** slip state tracking,the LuGre model with parameter adaptation and a brake torque compensation method based on RBF neural network are proposed,and their convergence are *** effectiveness of our control law is verified through simulation and ground *** in the experiments on the ground inertial test bench,compared to the improved pressure-biased-modulation(PBM)anti-skid algorithm,fewer wheel slips occur,and the average deceleration rate is increased by 5.78%,which makes it a control strategy with potential for engineering applications.

关键词： aircraft landing Brakes Disturbance observer Neural networks Runway identification

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A Finite element model to evaluate airport flexible pavements response under impact

A Finite element model to evaluate airport flexible pavement...

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The 2nd International Conference on Applied Mechanics and Mechanical Engineering(ICAMME 2011)

作者： Michele Buonsanti Giovanni Leonardi MECMAT Department University of Reggio Calabria DIMET Department University of Reggio Calabria

This paper using finite elements（FE） an approach to determine the contact stresses in a flexible pavement under landing aircraft loads is presentedThe proposed 3-Dimensional model simulates the behaviour of flexible runway pavements during the landing phaseA study on the impact of a rubber solid on the free surface of a granular plate is presented, simulating an aircraft gear system landing on with a flexible surfaceThis study is performed considering two tires on the structural pavement, with the real loads applied directly on the two wheels of the gear systemThe application takes in account the frictional phenomena developed between rubber solid and the surface of the pavement during the lockwire.

关键词： Pavement Airport Impact Finite element analysis aircraft landing

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Active Fault-Tolerant LPV Control for Elevator Failure of Civil aircraft Autolanding Based on Two-Stage Kalman Filter

Active Fault-Tolerant LPV Control for Elevator Failure of Ci...

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作者： Xudong Wang Shiqian Liu Yuanjun Sang Guangrui Zhou School of Aeronautics and Astronautics Shanghai Jiaotong University

This paper presents an active fault-tolerant linear parameter varying（LPV） autolanding controller for a civil aircraft subject to elevator failure during landing maneuver. Firstly, an LPV autolanding controller is designed to assure the acceptable tracking performance and stability of the civil aircraft’s autoland. The scheduling parameter is chosen as the estimation of the elevator failure factor. Secondly, a two-stage Kalman filter estimator is designed to estimate the failure factor. Then, the LPV controller and the estimator are integrated to achieve the active fault-tolerant performance. Finally, simulations of the autolanding control system show that a superior fault-tolerance can be achieved.

关键词： aircraft landing Linear parameter varying Two-stage Kalman filter Fault tolerant control

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