• 한국전산구조공학회논문집
• /
• 제19권1호
• /
• pp.85-92
• /
• 2006

이 논문은 일단고정 타단스프링으로 지지된 변단면 Beck 기둥의 임계하중에 관한 연구이다. 기둥의 변단면을 중실 직사각형 단면을 갖는 선형 변단면으로 채택하고, Bernoulli-Euler보 이론을 이용하여 경사종동력이 작용하는 소위 Beck 기둥의 자유진동을 지배하는 상미분방정식과 경계조건을 유도하였다. 이 미분방정식을 수치해석하여 하중-고유진동수 곡선을 얻고 이로부터 발산임계하중 및 동요임계하중을 산출하였다. 수치해석의 결과로부터 변단면 형태, 경사변수 및 스프링 강성이 임계하중에 미치는 영향을 고찰하였다

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

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2006년도 춘계학술대회논문집
• /
• pp.254-257
• /
• 2006

In this paper a dynamic behavior(natural frequency) of a cracked cantilever and simply supported pipe conveying fluid is presented. In addition, an analysis of the flutter and buckling instability of a cracked pipe conveying fluid subjected to a follower compressive load is presented. Based on the Euler-Bernouli beam theory, the equation of motion can be constructed by using the Lagrange's equation. The crack section is represented by a local flexibility matrix connecting two undamaged beam segments. The crack is assumed to be in the first mode of fracture and to be always opened during the vibrations.

• International Journal of Aeronautical and Space Sciences
• /
• 제7권1호
• /
• pp.84-90
• /
• 2006

The formation flying of satellites has been identified as an enabling technology for many future space missions. The application of conventional thrusters for formation flying usually results in high cost, limited life-time, and a large weight penalty. Various methods including the use of coulomb forces have been considered as an alternative to the conventional thrusters. In the present investigation, we investigate the feasibility of achieving the desired formation using Coulomb forces. This method has several advantages including low cost, light weight and no contamination. A simple controller based on the relative position and velocity errors between the leader and follower satellites is developed. The proposed controller is applied to circular formations considering the effects of disturbances in initial formation conditions as well as system nonlinearity. Results of the numerical simulation state that the proposed controller is successful in establishing circular formations of leader and follower satellites, for a formation size below 100 m.

• Structural Engineering and Mechanics
• /
• 제58권1호
• /
• pp.59-91
• /
• 2016

Laminated composite shells are commonly used in various engineering applications including aerospace and marine structures. In this paper, using semi-analytical finite strip method, the buckling behavior of laminated composite deep as well as thick shells of revolution under follower forces which remain normal to the shell is investigated. The stiffness caused by pressure is calculated for the follower forces subjected to external fibers in thick shells. The shell is divided into several closed strips with alignment of their nodal lines in the circumferential direction. The governing equations are derived based on first-order shear deformation theory which accounts for through thickness-shear flexibility. Displacements and rotations in the middle surface of shell are approximated by combining polynomial functions in the meridional direction as well as truncated Fourier series with an appropriate number of harmonic terms in the circumferential direction. The load stiffness matrix which accounts for variation of loads direction will be derived for each strip of the shell. Assembling of these matrices results in global load stiffness matrix which may be un-symmetric. Upon forming linear elastic stiffness matrix called constitutive stiffness matrix, geometric stiffness matrix and load stiffness matrix, the required elements for the second step analysis which is an eigenvalue problem are provided. In this study, different parameter effects are investigated including shell geometry, material properties, and different boundary conditions. Afterwards, the outcomes are compared with other researches. By considering the results of this article, it can be concluded that the deformation-dependent pressure assumption can entail to decrease the calculated buckling load in shells. This characteristic is studied for different examples.

• 한국전산구조공학회:학술대회논문집
• /
• 한국전산구조공학회 2006년도 정기 학술대회 논문집
• /
• pp.985-991
• /
• 2006

For a shear-deformable beam-column element subjected to non-conservative forces. equations of motion and a finite element formulation are presented applying extended Hamilton's principle. The influence of non-conservative force's direction parameter. internal and external damping forces, and shear deformation and rotary inertia effects on divergence and flutter loads of Beck's columns are intensively investigated based on element stiffness. damping and mass matrixes derived for the non-conservative system.

• 대한기계학회논문집
• /
• 제9권5호
• /
• pp.606-612
• /
• 1985

본 논문에서는 전보의 연속으로서 말단질량이 부착된 기둥의 자유단에 압축 종동력이 작용하는 비보존적 탄성계의 불완전 고정단에 나타나는 스프링 특성의 영향 을 연구하였다. 고정단은 병진스프링과 회전스프링으로 구속되었고, 이들 스프링 상 수의 여러 값이 말단질량과 연성(coupling)되어 기둥의 안정성에 미치는 영향을 연구 하였다. 기둥의 전단변형과 회전관성의 영향을 고려하였으며, Hamilton's principle 로서 계의 운동방정식과 경계조건의 식을 유도하여 수치해석하였다.

• 대한기계학회논문집A
• /
• 제34권3호
• /
• pp.361-367
• /
• 2010

3 차원 캠의 하나인 배럴캠은 자동화 생산 기계에서 인덱스 드라이브 유닛의 부품으로 많이 사용된다. 캠의 회전축과 종동절의 회전축이 90 도의 위상으로 직교한다. 인덱스 드라이브는 일정한 속도로 회전하는 캠의 입력에 대해 회전하고 정지한다. 터렛이 배럴캠의 회전에 의해 작동하는 동안 종이컵이 매우 빠르고 정확하게 성형된다. 그러나, 배럴캠과 종동절사이의 지속적인 미끄럼 접촉에 의해 점착마모가 발생하며 이러한 마모는 시스템의 성능에 영향을 준다. 결과적으로 제품의 불량율을 증가시킨다. 본 연구에서는 종이컵 성형기에 사용되는 배럴캠의 마모에 영향을 주는 인자가 접촉력임을 확인한다. 배럴캠과 롤러 사이의 접촉력은 다물체 동역학 모델을 이용해 계산한다. 그리고 해석 결과와 실제 시스템의 마모부와 비교를 통해 중요 마모 인자가 접촉력임을 검증한다.

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

• 한국전산구조공학회:학술대회논문집
• /
• 한국전산구조공학회 1994년도 봄 학술발표회 논문집
• /
• pp.57-64
• /
• 1994

The purpose of this paper is to find minimum surface shape of pneumatic structure using the finite element method. The pneumatic membrane structure is a kind of large deformation problem and very flexible composite material, which mean geomatric nonlinearity. It is not to resist for compression and resultant moment. As the displacement due to internal pressure is getting bigger, it should be considered the direction of forces. It becomes non-linear problem with the non-conservative force. The follower-force depends on the deformation and the direction of force is normal to each element. The solution process is obtained the new stiffness matrix (load correction matrix) depending on deformation through each iterated step. However, the stiffness matrix have not the symmetry and influence on the time of covergence. So in this paper Newton-Rhapson method for solving non-linear problem and for using symmetic matrix, the load direction is changed in each iterated step using the transformation matrix.