• Proceedings of the Korean Society of Tribologists and Lubrication Engineers Conference
• /
• 1996.04b
• /
• pp.68-72
• /
• 1996

본 연구에서는 에어오일 윤활하의 고속용 앵귤러 콘택트 볼베어링에 있어서, 여러 축방향의 하중과 윤활량의 변화에 대하여 회전속도에 따른 베어링의 마찰 토오크를 변화를 측정하고, 또한 회전속도, 하중 및 윤활량의 변화가 베어링 접촉부에서의 유막형성에 어떠한 영향을 미치는가를 알아보고자 한다.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.34 no.2
• /
• pp.167-174
• /
• 2010

In this study, the optimal position for the backrest pivot of an office chair was investigated by evaluating its performance in terms of the lumbar support and sliding distance of the back from the backrest during tilting motions. The simulation was performed using a mathematical model, which included a human body and a chair. Forty-two backrest pivot points were selected on the sagittal plane around the hip joint of a sitting model. A motion analysis study was also performed using a prototype of an office chair (A-type) with a backrest pivot located on the hip joint of a normal Korean model and a typical office chair (B-type) with its pivot located under the seat. The simulation results showed that both the lordosis angle and the slide distance of the back were minimized when the backrest pivot was positioned close to the hip joint. The experimental results showed that the slide distance and gap between the sitter's lumbar and the backrest was smaller with the A-type than the B-type. Based on the simulation and experimental results, it can be concluded that the backrest can support the sitter's lumbar area more effectively as the pivot position for reclining approaches closer to the hip joint. In this position, the sitter can maintain a comfortable and healthy sitting posture. This paper presents the methods and guidelines for designing an office chair with ergonomic considerations.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.12 no.4
• /
• pp.42-47
• /
• 2008

The power control system of Smart UAV is similar to the propeller pitch governing concept of turboprop aircraft. The pilot adjusts the engine power directly and the pitch governor controls the propeller pitch to maintain the propeller rotational speed. The electronic engine controller(EEC) of PW206C engine developed for helicopter is not fit for the power control concept of Smart UAV, and therefore the manual back-up system of PW206C engine is used for the engine power control of Smart UAV. Engine performance estimation program is used to predict the control range of power lever angle(PLA) according to the variation of engine output shaft speed, flight altitude and flight speed. These data provide a guide for the PLA control in manual mode operation.

• Journal of Radiation Protection and Research
• /
• v.33 no.2
• /
• pp.47-51
• /
• 2008

Objective: This study analyzed errors due to rotation or tilt of the magnetic resonance (MR) imaging indicator during image acquisition for a stereotactic radiosurgery. The error correction procedure of a commercially available stereotactic neurosurgery treatment planning program has been verified. Materials and Methods: Software virtual phantoms were built with stereotactic images generated by a commercial programming language, Interactive Data Language (version 5.5). The thickness of an image slice was 0.5 mm, pixel size was $0.5{\times}0.5mm$, field of view was 256 mm, and image resolution was $512{\times}512$. The images were generated under the DICOM 3.0 standard in order to be used with Leksell GammaPlan$^{(R)}$. For the verification of the rotation error correction function of Leksell GammaPlan$^{(R)}$, 45 measurement points were arranged in five axial planes. On each axial plane, there were nine measurement points along a square of length 100 mm. The center of the square was located on the z-axis and a measurement point was on the z-axis, too. Five axial planes were placed at z=-50.0, -30.0, 0.0, 30.0, 50.0 mm, respectively. The virtual phantom was rotated by $3^{\circ}$ around one of x, y, and z-axis. It was also rotated by $3^{\circ}$ around two axes of x, y, and z-axis, and rotated by $3^{\circ}$ along all three axes. The errors in the position of rotated measurement points were measured with Leksell GammaPlan$^{(R)}$ and the correction function was verified. Results: The image registration errors of the virtual phantom images was $0.1{\pm}0.1mm$ and it was within the requirement of stereotactic images. The maximum theoretical errors in position of measurement points were 2.6 mm for a rotation around one axis, 3.7 mm for a rotation around two axes, and 4.5 mm for a rotation around three axes. The measured errors in position was $0.1{\pm}0.1mm$ for a rotation around single axis, $0.2{\pm}0.2mm$ for double and triple axes. These small errors verified that the rotation error correction function of Leksell GammaPlan$^{(R)}$ is working fine. Conclusion: A virtual phantom was built to verify software functions of stereotactic neurosurgery treatment planning program. The error correction function of a commercial treatment planning program worked within nominal error range. The virtual phantom of this study can be applied in many other fields to verify various functions of treatment planning programs.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 1995.04a
• /
• pp.354-359
• /
• 1995

회전익의 소재로 복합재료를 선택하게 됨에 따라 헬리콥터의 유지, 보수 및 성능에서 유리하게 되었지만 허브 형태의 간소화로 인하여 해석상의 어려움은 확대 되었다고 할 수 있을 것이다. 따라서 회전익의 단면특성은 더욱 중요한 의미를 갖게 되었다. 회전익의 단면특성을 결정하기 위해서 우선적으로 각 방향운동의 연성항을 소거하는 것이 계산상 유리하고 따라서 관성주축방향을 결정하는 것이 중요하다. 그러나 회전익의 익형이 대칭형이 아니고 복합한 재료로 구성되어 있을 뿐 아니라 효율의 극대화를 위하여 축방향을 따라 비틀림을 부여하고 있기 때문에 관성주축의 방향을 결정하는데 많은 어려움이 존재한다. 따라서 본 연구에서는 실제 회전익을 그 연구 대상으로 회전익 단면의 등가강성행렬을 추출하고 외팔보의 공학이론과 회전행렬을 이용하는 방법으로 관성주축방향을 결정하는 방법을 제시하였다. 해석방법의 타당성을 확보하기 위하여 엄밀해를 알고 있는 간단해 단면을 갖는 외팔보를 이용하여 검증하였다. 이러한 방법은 관성주축방향을 결정하는 새로운 프로그램의 개발이라는 부담을 최소화 하였을 뿐 아니라, 해석방법 자체가 가지는 간편성으로 인하여 많은 시간과 노력을 줄일수 있을 것으로 기대된다.

• Journal of the Korean Chemical Society
• /
• v.28 no.1
• /
• pp.34-40
• /
• 1984

The reorientational motion of $C_6F_6$ in neat liquid is investigated in the temperature range 293∼333K by analyzing ${\nu}_2$ and ${\nu}_16$ bands of its Raman spectrum. Diffusion constants for the tumbling ($D_{\bo}$) and spinning ($D_{\parallel}$) motions are determined. The reorientation of the molecule seems to be distinctly anisotropic. Based on the hydrodynamic model, the tumbling motion of the figure axis of $C_6F_6$ is largely diffusional. On the other hand, the spinning motion of the same axis looks mostly inertial.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.3 no.3
• /
• pp.47-52
• /
• 1999

Fatigue test is an essential procedure in the dynamic structure design. It is performed to confirm that the structure should safety the required life. In this study, fatigue life for 750㎾ class horizontal axis wind turbine composite blade was investigated. Required fatigue stress was calculated by fan Bond's empirical equation and S-N linear damage method. Fatigue load for FEM analysis was calculated using load spectrum through experiments and Spera's method. Service fatigue stress was obtained by FEM with the calculated fatigue load. From comparison of the fatigue stresses, fatigue life over 20 years was confirmed.

• Journal of the Institute of Convergence Signal Processing
• /
• v.4 no.3
• /
• pp.55-60
• /
• 2003

In the controller design of position or velocity control system, the flexibility of the mechanical system is always the limiting factor to the higher performance. Most mechanical systems coupled with rotary shaft are 2-Inertia systems which are consist of motor and load inertia. These inertias make a torsion In rotary shaft and cause torsional vibration. To suppress vibration, various control strategies have been proposed mainly for controlling 2-inertia system. In this paper, a speed controller design for a 2-inertia system composed of voltage controlled DC motor and load inertia is made by using CDM(coefficient diagram method). First, the 2-inertia system model is derived. Then the CDM is used to design the proper controller. A validity of this approach is confirmed by simulation and experimental results.

• Journal of Advanced Navigation Technology
• /
• v.27 no.1
• /
• pp.50-56
• /
• 2023

INS(Inertial Navigation System) calculates navigation information using a vehicle's acceleration and angular velocity without the outside information. However, when navigation is performed for a long time, navigation error gradually diverges and the performance decreases. To enhance INS's performance, the rotation of inertial measurement unit is developed to compensate error sources of inertial sensors, which is called RINS(Rotational Inertial Navigation System). This paper analyzes the influence of several errors for dual-axis RINS and the shows the results using simulation.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
• /
• 1998.04a
• /
• pp.194-199
• /
• 1998

축어긋남이 있는 회전체-볼베어링계에 대한 동적모델을 이용하여, 각축어긋남에 의한 2x 축진동현상을 조사하였다. 이때 유효베어링강성계수를 정의하여 축어긋남과 불균형량에 의해 발생되는 강성계수의 평균과 동기 변화성분을 운동방정식에 도입하였다. 수치해석과 실험결과는 각축어긋남에 의한 바나나 형태의 선회궤적이 회전체계 임계속도의 1/2이 도는 속도영역에서 뚜렷이 나타나는 것을 보여주었다.