Search

Your search keyword '"Xiao, Zhongyun"' showing total 16 results
Start Over Author "Xiao, Zhongyun"
16 results on '"Xiao, Zhongyun"'

3. Rigid-Flexible Dynamics Analysis of a Large Deformation Flexible Beam Based on Finite Volume Beams

Author

Han, Wei, Qi, Long, Xiao, Zhongyun, Angrisani, Leopoldo, Series Editor, Arteaga, Marco, Series Editor, Panigrahi, Bijaya Ketan, Series Editor, Chakraborty, Samarjit, Series Editor, Chen, Jiming, Series Editor, Chen, Shanben, Series Editor, Chen, Tan Kay, Series Editor, Dillmann, Rüdiger, Series Editor, Duan, Haibin, Series Editor, Ferrari, Gianluigi, Series Editor, Ferre, Manuel, Series Editor, Hirche, Sandra, Series Editor, Jabbari, Faryar, Series Editor, Jia, Limin, Series Editor, Kacprzyk, Janusz, Series Editor, Khamis, Alaa, Series Editor, Kroeger, Torsten, Series Editor, Liang, Qilian, Series Editor, Martin, Ferran, Series Editor, Ming, Tan Cher, Series Editor, Minker, Wolfgang, Series Editor, Misra, Pradeep, Series Editor, Möller, Sebastian, Series Editor, Mukhopadhyay, Subhas, Series Editor, Ning, Cun-Zheng, Series Editor, Nishida, Toyoaki, Series Editor, Pascucci, Federica, Series Editor, Qin, Yong, Series Editor, Seng, Gan Woon, Series Editor, Speidel, Joachim, Series Editor, Veiga, Germano, Series Editor, Wu, Haitao, Series Editor, Zhang, Junjie James, Series Editor, Jia, Yingmin, editor, Du, Junping, editor, and Zhang, Weicun, editor

Published
2020
Full Text
View/download PDF

4. Numerical Investigation on a Porous Wall Model for the Transonic Wall Interference

Author

MOU Bin, WANG Jiantao, HUANG Yong, XIAO Zhongyun, and LIU Dawei

Subjects
wide-body aircraft, wall interference, numerical simulation, wind tunnel test, Motor vehicles. Aeronautics. Astronautics, TL1-4050
Abstract

Flows passing a wide-body aircraft at cruising, drag divergence or diving status are transonic. When the aircraft model is tested in a transonic wind tunnel, strong shock waves may be induced due to the tunnel wall and the model, and incur complex interference as a strong nonlinear coupling phenomenon. In order to investigate the wall interference to the standard model of a wide-body aircraft mounted in the FL-26 wind tunnel, a numerical simulation method based on a porous wall model is developed. Based on this wall model method, the coupling effect of wall interference at Mach numbers ranging from 0.8 to 0.92 is studied. Comparing with the wall pressure information method, results with the porous wall model indicate positive effect of the porous wall flow on the lift coefficient of wide-body aircraft, as well as more modification to drag coefficient.

Published
2021
Full Text
View/download PDF

12. Development of a Modularized Virtual Flight Simulator based on Multiple Discipline Coupled Method

Author

Ziwei Wang, Sheng Zhang, Fan Liu, and Xiao Zhongyun

Subjects
History, Development (topology), Computer science, ComputerApplications_COMPUTERSINOTHERSYSTEMS, Flight simulator, Simulation, Computer Science Applications, Education
Abstract

The problem of aircraft control involves multiple subjects and has always been extremely complicated in mechanics modelling. Virtual flight simulation was put forward in order to reduce the cost of full-scale airplane flying test and wind tunnel experiment. A typical virtual flight simulator includes a computational fluid dynamics (CFD) solver, a structure dynamics (FD) function, and a flight controller. However, existed virtual flight solver usually ignores the universal modelling of dynamics for complex aircraft configuration and the modularization of CFD, FD and flight controller module, which makes it very inconvenient for many in-house virtual flight codes for engineering application and commercial software development. A new framework of virtual flight simulation platform is established with a parallel Reynolds Averaged Navier-Stokes (RANS) solver, a structured moving overlapping grid function, a generic multiple body dynamics (MBD) solver, and a plug-in type flight controller platform. A universal data exchange interface between MBD and flight controller is presented. An X-wing missile flying forward and pitching-up maneuvering validation case is conducted with the current virtual flight simulator, the result is compared with Matlab Simulink solver based on steady aerodynamic database and good agreement is obtained.

Published
2021

13. Numerical Investigation of Aeroelastic Deformation Effect on the NASA Common Research Model

Author

Lu Zhang, Xiao Zhongyun, Fan Liu, and Shuai Ma

Subjects
History, business.industry, Computer science, Structural engineering, business, Aeroelasticity, Deformation effect, Computer Science Applications, Education, Research model
Abstract

The risk of the aeroelastic deformation of the wings to the flight safety has become increasingly prominent for commercial transport aircraft due to the requirements for lightweight structure. In this work, Reynolds averaged Navier-Stokes (RANS) method coupled with transfinite interpolation were employed to investigate the influence of static elastic deformation of wing on aerodynamic characteristics of NASA CRM. Both bend and twist distributions were scaled in numerical simulations based on dynamic pressure, which was shown to be reasonable by the compassions between the calculations and measurements. The numerical results show premature flow separation in the middle and outboard of the wing for original configuration. Furthermore, the flow separation was supressed by the upward bending of the wing and negative twist in the leading edge, and the aerodynamic characteristics of the aircraft were improved by the aeroelastic deformation.

Published
2021

16. Numerical simulation of missile air-launching process under rail slideway constraints.

Author

Liu Gang, Xiao Zhongyun, Wang Jiantao, and Liu Fan

Abstract

Computational fluid dynamics and rigid body dynamics models are solved in a loosely coupled way to simulate a missile launched from an aircraft by rail, the motions consist of three phases, which correspond to two or multi- hanger phase, single hanger phase and free motion phase. In order to simulate the motion of missiles subjected to single hanger constraint, the constrained dynamics equations are derivated from six degree of freedom motion equations, the model is verified by simulating free rotation of rigid body (Euler gyro) and procession of rotational rigid body( Lagrange gyro), which shows good agreement with the theoretical solutions. After that, the launching process of a missile from an aircraft is numerically simulated, in which constrained and non-constrained rigid-body dynamics models are switched corresponding to hanger's position. By numerical simulation, trajectories and attitudes profile of the missile are obtained. The results show that the missile is impacted by lateral wash flows at moderate angles of attack, resulting in large lateral force and yawing moment, causing the missile to roll rapidly and produce missile-frame interference further. In the phase of single hanger constraint, the missile tends to pitch due to normal aerodynamic force, gravity, normal overload and soon, which may lead to interference with rail launcher on harsh conditions. [ABSTRACT FROM AUTHOR]

Published
2015
Full Text
View/download PDF

Catalog

Books, media, physical & digital resources
See catalog results