• 대한기계학회논문집A
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• 제24권1호
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• pp.232-239
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• 2000

The paper describes the parametric instability of free-free beams subjected to a controlled pulsating follower force. The beam has a tip rigid body not a mass point, and the direction of pulsating follower force is controlled by the direction control sensor. Equations of motion are derived by Hamilton's principle and the instability regions are obtained by finite element formulation. The effects of magnitude, rotary inertia, the distance between free end of the beam and the center of gravity of the rigid body on the instability types and regions are investigated by the change of the constant and periodic part of the follower force.

• 대한기계학회논문집
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• 제17권10호
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• pp.2467-2474
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• 1993

This paper deals with the cantilever subjected to a follower force which is generated by real rocket motor which has linearly decreasing thrust. The cantilever is assumed to be uniform and elastic one, In the theoretical analysis, the tip mass of rocket motor is considered as a rigid body and effects of its dynamic parameters are shown and compared with the experimental results. Particularly, the variation of the 2nd natural frequency due to the decreasing thrust is measured in the experiments and compared with the theoretical estimations. Approximate method is adopted in the theoretical analysis using Galerkin method by introducing 3-element modified operator and modified variable which represent eqation of motion and natural boundary conditions. In general, structural damping effects can be neglected and all the rigid body parameters must be taken into account in case of the short action time of the follower force and the relatively big tip mass like the system of this paper according to the experiment. Good agreement was obtained between the theoretical estimations and the experimental results by neglecting structural damping and considering all the rigid bidy parameters of the tip mass.

• 대한기계학회논문집A
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• 제22권3호
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• pp.680-683
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• 1998

In case of the infinite body containing a rigid inclusion with line crack shape, stress intensity factor is determined and the relation between stress intensity factor and stress distribution near a crack tip is developed. Also, the relation between stress intensity factor and Kolosoff stress function is developed. Finally, these results are compared with those that the crack surface is under no traction.

• 한국정밀공학회지
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• 제15권7호
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• pp.91-97
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• 1998

The analysis model is the infinite body consisted of power law creep material containing a rigid inclusion with line crack shape subjected to the arbitrarily directional stress on an infinite boundary. The crack analysis is performed using the complex pseudo-stress function. The strain rate intensity factor is determined in the closed form as new fracture mechanics parmeter which represents the magnitudes of stress and strain rate near the tip in power law creep material.

• Advances in aircraft and spacecraft science
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• 제9권3호
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• pp.263-278
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• 2022

The time-varying structural reliability of an aeroelastic launch vehicle subjected to stochastic parameters is investigated. The launch vehicle structure is under the combined action of several stochastic loads that include aerodynamics, thrust as well as internal combustion pressure. The launch vehicle's main body structural flexibility is modeled via the normal mode shapes of a free-free Euler beam, where the aerodynamic loadings on the vehicle are due to force on each incremental section of the vehicle. The rigid and elastic coupled nonlinear equations of motion are derived following the Lagrangian approach that results in a complete aeroelastic simulation for the prediction of the instantaneous launch vehicle rigid-body motion as well as the body elastic deformations. Reliability analysis has been performed based on two distinct limit state functions, defined as the maximum launch vehicle tip elastic deformation and also the maximum allowable stress occurring along the launch vehicle total length. In this fashion, the time-dependent reliability problem can be converted into an equivalent time-invariant reliability problem. Subsequently, the first-order reliability method, as well as the Monte Carlo simulation schemes, are employed to determine and verify the aeroelastic launch vehicle dynamic failure probability for a given flight time.

• 대한기계학회논문집A
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• 제21권2호
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• pp.245-251
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• 1997

The dynamic behavior of elastic columns under the action of the subtangential force is studied in this paper. The subtangential force is the combination of the tip mass dead load and pure follower thrust. In this study, the tip mass is assumed to be a rigid body rather than a point mass. The equations of motion are derived based on the extended Hamilton's principle and the finite element method. Then the equations of motion are trasformed into a dimensionless form, and several parameters are identified. It is found that the critical subtangential force can be changed subtangentially by considering the parameters related to tip mass. It is also shown that the nonconservativeness of the applied force has a significant effect on the type of instability. The influence of the self-weight of the column on the variation of the critical force is also investigated.

• 소음진동
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• 제5권3호
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• pp.385-394
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• 1995

Recently, since robot manipulator becomes faster and lighter, its link is no longer regarded as rigid body, and robot controller which only controls robot position cannot reduce vibration of the flexible link. Therefore vibration control is needed in robot manipulator control in addition to position control. In the case that tip mass changes when robot manipulator in working, it is clear that the efficiency of the vibration/position controller designed for the fixed system goes down. In this paper, the system with time varying parameters, adaptive control theory is adopted which estimates parameters changed by the variation of the tip mass and re-calculates the gain of the controller. Validify of the proposed adaptive controller and capability of the estimator are evaluated by computer simulations and experiments. Comparison results of the optimal controller for the fixed system and proposed adaptive controller and carried out.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 1996년도 춘계학술대회 논문집
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• pp.313-318
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• 1996

This paper deals with the dynamic behavior of elastic columns under the action of subtangential forces. The above subtangential force can be-realized by the combination force between the dead load of thetip mass and the pure follower thrust. The tip mass is assumed to be a rigid body not a mass point as it has been assumed so for. The equations of motion are formulated based on extended Hamilton's principle and the finite element method. It is shown that nonconservativeness of the applied force has greatly effect on the instability type. It is found that the critical subtangential force can also be changed by consideration of the tip mass parameters taking into account of its magnitude, rotary inertia and size. The influence of the self-weight of the column on the change of the critical force is also investigated.

• 대한조선학회논문집
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• 제28권1호
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• pp.60-68
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• 1991

비압축성 유체유동에 대한 Navier-Stokes 방정식과 충돌 접촉면 조건으로 특징지어지는 강체-유체 충돌문제를 Lagrangian 유한요소법에 의해 해석하였으며, 계산의 편의상, 속도장을 점성및 중력항과 압력항으로 나누어 수행하는 소위 fractional step method를 도입하였다. 유체영역은 4절점의 4각형 요소로 분할하였으며, 충분히 작은 시간간격의 도입을 전제로 하여 explicit time marching법으로 수치해석하였다. 매 시간 step의 초기에 우선 운동량-충격량 법칙으로 강체의 수면충돌후 속도를 구했으며, 그 속도로 표현되는 충돌 접촉면의 경계조건과 완전한 형태의 자유표면조건 그리고 운동방정식 및 연속 방정식을 모두 만족하는 속도장을 구하였다. 본 논문에서 제시하는 수치해석법에 의하면, 유체충격문제에 있어 매우 중요하다고 알려져 있는 tip splash를 포함하는 자유표면의 형상을 쉽게 추적해 갈 수 있다. Lagrangian 유한요소법의 적용의 타당성을 확인하기 위하여 대칭형 2차원 쐐기 모양의 강체가 수면충돌하는 경우를 예로하여 시간의 경과에 따른 충격수압의 분포 및 충격외력 등을 추정한 결과, 본 방법의 적용의 유효성과 아울러 몇가지 유용한 결론을 유도할 수 있었다.

• 대한기계학회논문집
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• 제17권11호
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• pp.2762-2772
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• 1993

The paper deals with the flutter of a cantilevered beam subjected to a rocket thrust generated by a solid rocket motor. It is saaumed that the rocket thrust is to be a constant follower thrust, and produced by the installation of a solid rocket motor to the tip end of the cantilevered beam. The rocket motor is considered to be a rigid body having finite sizes, but not a mass point as it has been assumed so far. Governing equations are derived through the extended Hamilton's principle, and finite element method is applied to obtain the theoretical prediction for critical follower thrust. The maximum follower thrust is also calculated through the change of shear deformation parameter of the beam in the numerical simulation. The theoretical prediction for flutter or stability is verified by experiment. The experimental results show that critical follower thrust in theory agrees well with the experimental value taking account of the magnitude, rotary inertia of the rocket motor and the distance from the tip end of the beam to the center of gravity of the rocket motor.