• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.10
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• pp.973-978
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• 2010

In this paper, we studied the shimmy phenomena of an aircraft nose landing gear considering free-play. Shimmy is a self-excited vibration in lateral and torsional directions of a landing gear during either the take-off or landing. This phenomena is caused by a couple of conditions such as low torsional stiffness of the strut, friction and free-play in the gear, wheel imbalance, or worn parts, and it may make an aircraft unstable. Free-play non-linearity is linearized by the described function for a stability analysis in a frequency domain, and time marching is performed using the fourth-order Runge-Kutta method. We performed the numerical simulation of the nose landing gear shimmy and investigated its linear and nonlinear characteristics. From the numerical results, we found limit-cycle-oscillations at the speed under linear shimmy speed for the case considering free-play and it can be concluded that the shimmy stability can be decreased by free-play.

• Composites Research
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• v.20 no.1
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• pp.8-14
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• 2007

Nonlinear aeroelastic analyses of composite wing with flap are performed considering free-play and dynamic stiffness of actuator. Doublet-Hybrid method is used for the calculation of subsonic unsteady aerodynamic forces. Free-play is modeled as a bilinear spring and is linearized by using the describing function method. Dynamic stiffness is obtained from governing equation of gear system and the aeroelastic analyses were performed according to ply-angle of laminate and material. The linear and nonlinear flutter analysis results show that the flutter characteristics are significantly dependent on the free-play and dynamic stiffness. from the nonlinear flutter analysis, various types of limit cycle oscillations are observed in a range of air speeds below or above the linear divergent flutter boundary.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.4
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• pp.295-301
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• 2007

The aeroelastic characteristics of a wing with control surface freeplay are investigated. The transonic small disturbance equation is used for unsteady aerodynamic forces in subsonic/transonic region. The fictitious mass method is introduced to apply a modal approach to nonlinear structural models. Nonlinear aeroelastic time responses are calculated by the coupled time integration method. Using these methods, an efficient aeroelastic analysis is achieved for aerodynamic and structural nonlinearities simultaneously. The effects of the aerodynamic nonlinearity, initial flap amplitude, and freeplay magnitude in aeroelastic characteristics are investigated in this study.

• Proceedings of the Korean Society of Disaster Information Conference
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• 2017.11a
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• pp.347-348
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• 2017

헬리컬파일은 한 개 이상의 나선형 원판이 고강도 강관 파이프에 부착된 말뚝이다. 기존의 헬리컬파일은 커플러 형태의 연결방식을 사용하였으나, 볼트 구멍과 볼트사이의 유격 및 연결소켓과 강관 사이의 유격등으로 인한 높은 지지력 기대가 힘들었다. 본 연구는 헬리컬파일 연결방식 개선을 위해 기존 커플러형식에서 플랜지 형식을 적용하였고, 정재하시험을 통해 지지력을 비교 분석 하였다. 정재하시험결과 플랜지 형태의 연결방식이 커플러 형태의 연결방식보다 높은 지지력이 발휘되었고 플랜지형태 적용시 상향식그라우팅이 가능하여 품질이 향상되었다. 또한 연결부 유격을 방지 할 수 있었다.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.14 no.1
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• pp.39-44
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• 2013

Seat is the part relevant to comfortableness and safety among automotive parts directly. It also should have sufficient stiffness and strength to satisfy these conditions and ensure the safety of passenger. Automotive seat is modelled with 3D and is simulated with structural analyses about three kinds of experiments by before and after gap, side gap, before and after moment strength. As analysis result, deformation angles of $0.038^{\circ}$ and $0.04^{\circ}$ are respectively shown at before and after gap test, side gap test. Through before and after the moment strength test, maximum total deformations of 0.18946mm and 3.2482mm are respectively shown at front and rear loads. By the study result of no excessive deformation and no fracture at automotive seat frame, the sufficient rigidity and strength to guarantee the safety of passenger can be verified.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.35 no.9
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• pp.1077-1082
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• 2011

Ball joint is a rotating and swiveling element that is typically the interface between two parts. In an automobile, the ball joint is the component that connects the control arms to the steering knuckles by playing a role of bearing. The ball joint can also be installed in linkage systems for motion control applications. This paper describes the simulation strategy for a ball joint analysis, considering manufacturing process. Its manufacturing process can be divided into plugging and spinning. Then, the interested response is selected as the stress distribution generated between its ball and bearing. In this paper, a commercial code of NX DAFUL 2.0 using an implicit integration method is introduced to calculate the response. In addition, the gap analysis is performed to investigate the fitness. Also, the optimum design is suggested through case studies.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.4
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• pp.341-348
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• 2015

This paper addresses Monte-Carlo simulation analyses for the stage separation of the general launch vehicle. The stage separation event of the launch vehicle occurs during a very short time and is related with many dynamic parameters. The stage separation is a critical event in that the launch fails if there is a collision during the stage separation. The stage separation analyses was conducted for the general launch vehicle to confirm the separation without collision within the designed clearance in case of the random input parameters. This paper presents the stochastic results of the stage separation of the launch vehicle using the Monte-Carlo simulation.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 2010.05a
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• pp.859-860
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• 2010

• Proceedings of the Korean Nuclear Society Conference
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• 1998.10a
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• pp.373-373
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• 1998

• 한국지구과학회:학술대회논문집
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• 2006.02a
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• pp.236-236
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• 2006