W
Won-Ho Shin
Researcher at KAIST
Publications - 18
Citations - 317
Won-Ho Shin is an academic researcher from KAIST. The author has contributed to research in topics: Flutter & Aeroelasticity. The author has an hindex of 9, co-authored 18 publications receiving 285 citations. Previous affiliations of Won-Ho Shin include Samsung Electro-Mechanics.
Papers
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Journal ArticleDOI
Surgical Robot System for Single-Port Surgery With Novel Joint Mechanism
Won-Ho Shin,Dong-Soo Kwon +1 more
TL;DR: A new surgical robot system for single-port surgery that uses a novel joint mechanism suitable for surgical instruments with multiple degrees of freedom (DOF) that can prevent hysteresis of the joint and achieve more accurate motion with a large force is proposed.
Journal ArticleDOI
Aeroelastic characteristics of cylindrical hybrid composite panels with viscoelastic damping treatments
TL;DR: In this paper, the effects of transverse shear deformation on cylindrical composite panels with structural damping treatments have been analyzed using the finite element method based on the zig-zag layerwise shell theory.
Proceedings ArticleDOI
Design of a compact 5-DOF surgical robot of a spherical mechanism: CURES
TL;DR: In this paper, a design methodology for a compact surgical robot is presented, considering workspace and force requirements, a simulation and experiments are conducted to determine the design parameters, and the compact robot CURES of 5DOF spherical mechanism is developed from the analysis and its properties are presented.
Journal ArticleDOI
Nonlinear flutter of aerothermally buckled composite shells with damping treatments
Won-Ho Shin,Il-Kwon Oh,In Lee +2 more
TL;DR: In this paper, the aerothermally buckled cylindrical composite shells with various damping treatments were implemented using the theory of layerwise displacement field, and the arc-length method and iterative nonlinear scheme were taken up to estimate the postbuckling deformation of composite shells due to aerothermal loads.
Journal ArticleDOI
Nonlinear Aeroelastic Analysis of a Deployable Missile Control Fin
TL;DR: In this paper, the authors investigated the nonlinear aeroelastic characteristics of a deployable missile control fin and applied the fictitious mass modal approach to reduce the problem size and the computation time in the linear and nonlinear flutter analyses.