• 한국의학물리학회지:의학물리
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• 제26권2호
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• pp.87-92
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• 2015

호흡연동 래피드아크 치료는 무건운 하중의 선형가속기 갠트리의 회전과 정지의 반복과정에서 갠트리 회전 재시작점의 오차와 다엽조리개의 정확한 움직임 및 갠트리 속도와 같은 래피드아크의 선량정확도를 결정하는 요소들의 오차 가능성으로 인한 선량 오류가 발생할 수 있다. 본 연구에서는 이러한 갠트리의 회전과 정지의 반복적인 동작이 호흡연동 래피드아크 치료의 정확도에 어떠한 영향을 끼치는 지 치료 시 총 회전과 정지 동작 수를 결정하는 빔조사 구간 길이의 변화를 통해 분석하였다. 총 10명의 간암 환자를 대상으로 래피드아크 치료계획을 수립하였고, RPM 호흡연동 장치와 정확한 빔조사 구간 길이를 설정하기 위해 동적 팬텀을 사용하였다. 각 래피드아크 치료계획 당 EPID를 사용한 portal dosimetry delivery quality assurance (DQA) 계획과 이차원 다이오드 검출기배열장치인 MapCHECK2를 사용한 DQA 계획을 수립하여 호흡연동 방사선 치료과정에서 누적된 선량분포의 정확도를 분석하였다. 모든 환자의 호흡주기는 4초로 설정하였고, 수립한 DQA 계획들을 호흡연동 없이 연속적으로 조사하는 것과, 1초의 빔조사 구간과 2초의 빔조사 구간, 총 3가지의 경우에 대해 실제 방사선량 측정과 감마평가를 통해 선량의 정확도를 분석하였다. Portal dosimetry DQA 경우 평균 감마평가의 합격률은 호흡연동 없이 연속적일 때 $98.72{\pm}0.82%$ 였고, 1초의 빔조사 구간의 경우 $94.91{\pm}1.64%$, 2초의 빔조사 구간의 경우 $98.23{\pm}0.97%$이었다. MapCHECK2 DQA경우 평균 감마평가의 합격률은 호흡연동 없이 연속적일 때 $97.80{\pm}0.91%$였고, 1초의 빔조사 구간의 경우 $95.38{\pm}1.31%$, 2초의 빔조사 구간의 경우 $97.50{\pm}0.96%$였다. 본 연구 결과를 통해 빔조사 구간의 길이가 증가하여 갠트리 정지 동작 수가 감소할수록 호흡연동 래피드아크의 선량 정확도가 증가함을 확인할 수 있었으며, 이러한 특성을 호흡연동 방사선치료 대상 환자의 선정 및 호흡방식에 대한 교육과정에 고려되어야 할 것으로 판단되었다.

• 대한방사선치료학회지
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• 제26권2호
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• pp.247-256
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• 2014

목 적 : 췌장 환자 방사선 치료 중 기점(Fiducial) 대상 내부 및 외부 종양 움직임의 오차를 정량화 하고자 한다. 또한 cone beam computed tomography (CBCT) 를 기반으로 호흡 시 췌장의 움직임 분석하고자 한다. 대상 및 방법 : 용적 세기변조 회전조사 (V-MAT)를 적용, 정위적 방사선 치료를 국소 진행성 췌장암 환자 11명을 대상으로 하였다. CBCT 및 직교 투시이미지를 적용하여 기점(Fiducial Marker)의 Inter, intra-fraction 움직임 변화를 치료 전, 치료 진행 시 분석하였다. 결 과 : 치료 후 프로토콜을 오프라인 교정 프로토콜을 사용하여, CBCT 와 직교투시 간의 평균 오차(범위)는 0.0(-1.7~4.0), 0.3(-0.5~3.0) and 0.0(-4.1~6.6)mm 측방 (LR), 세로 (AP) 및 종 방향 (SI) 이였다. 무작위 Inter-fraction Setup 오차 결과는 -0.1, -2.3 and -1.1 mm: 95% Fiducial포함 마진은 각 9.9, 7.8, 12.5mm로 수식되었다. 결 론 : 위 분석으로 뼈 일치 정렬 후 잔류 불확실성이 있으며, SI 방향에 큰 임의의 움직임은 적합한 여백이 필요하다. 주변 내부 장기를 보호, 내부 장기 문제점을 최소화, 호흡편차를 고려, 치료 시 정기적으로 측정하여야 한다.

• Journal of the Optical Society of Korea
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• 제8권3호
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• pp.137-146
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• 2004

A new method of obtaining the eigenmode of an anisotropic planar waveguide is studied. The planar waveguide can be composed of an arbitrary number of isotropic or uniaxially anisotropic layers, provided all the optical axes arc lying in the incidence plane. Since the equation of motion for the TE mode is not different from that for the TE mode in an isotropic planar waveguide, only the equation of motion for the TM mode is of any concern. For this kind of device structure, the Maxwell's equations can be solved for one component of the electric field and one component of the magnetic field. The resulting coupled set of equations is linear in the propagation constant and the eigenmode can be easily obtained using canned numerical routines.

• 제어로봇시스템학회논문지
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• 제8권10호
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• pp.881-889
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• 2002

Mobility analysis for various mobile mechanisms including mechanisms with lack of geometric generality is performed. Joint screws are employed to find the sire of feasible joint motion space or each of independent loops of mobile mechanisms. Particularly, the concept of "representative screws" is introduced to represent the feasible motion spaces for subsets of joints belonging to either a loop or a sub-system consisting of several closed loops. Firstly. simplified joint model for each of low different typical wheels popularly employed in mobile robots is described. Then. mobility analysis fir various types of planar mobile robots and the Mars Rover mobile robot for navigation on the rocky road on Mars arc performed. It is confirmed that the obtained results in this study coincide with the previous ones which were obtained by suing imaginary Joints approach(1)pproach(1)

• Advances in aircraft and spacecraft science
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• 제4권4호
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• pp.371-399
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• 2017

The motion of propeller driven airplanes, flying at constant speed on ascending or descending helical trajectories is analyzed. The dynamical abilities of the airplane are shown to result in restrictions on the ranges of the geometrical parameters of the helical path. The physical quantities taken into account are the variation of air density with altitude, the airplane mass change due to fuel consumption, its load factor, its lift coefficient, and the thrust its engine can produce. Formulas are provided for determining all the airplane dynamical parameters on the trajectory. A procedure is proposed for the construction of tables from which the flyability of trajectories at a given angle of inclination and radius can be read, with the corresponding minimum and maximum speeds allowed, the final altitude reached and the amount of fuel burned. Sample calculations are shown for the Cessna 182, a Silver Fox like unmanned aerial vehicle, and the C-130 Hercules.

• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2004년도 학술대회지
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• pp.212-219
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• 2004

The effect of frequency and amplitude of the OWC (Oscillating Water Column) motion on the nonlinear reaction forces in an air duct arc studied experimentally. Experimental OWC model is idealized as a simple circular cylinder with an orifice type air duct located at the middle of the top rid. Reaction forces due to forced heave oscillation are measured and analyzed. By subtracting the effect of inertia forces and restoring forces, pneumatic damping force and added spring force are deduced. The effects of the frequency and amplitude of the heave motion are discussed. Also, the effects of solidity of the duct on the reaction forces are discussed.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 1997년도 추계학술대회 논문집
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• pp.446-449
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• 1997

Yard cranes are very useful equipments for handling of heavy containers. But rope-driven yard cranes must have a little of sway and skew motion because ropes arc passive mechanical device. So many researches have been concentrated on anti-sway algorithm controlling trolley speed. But control algorithm of trolley speed is not practical in windy weather. In this paper, we are going to propose a new structure for anti-sway. This structure uses aux. :opes. The control strategy with auxiliary rope is very useful to sway control of yard crane because rope length is shorter than quay-sidc container cranes. In this paper, we derive cquatlons of motion of trolley system which have anti-sway controller to use auxiliary rope. And we propose the control strategy and analyse the behavior of the proposed system.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 Proceedings of the Korea Automatic Control Conference, 11th (KACC); Pohang, Korea; 24-26 Oct. 1996
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• pp.77-82
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• 1996

This paper is concerned with how to utilize kinematic redundancy to reconstruct the inverse kinematic solution which is not attainable due to hardware limitations. By analyzing the error due to hardware limitations, we are to show that the recoverability of limitation reduces to the solvability of a reconstruction equation under the feasibility condition. It will be next shown that the reconstruction equation is solvable if the configuration is not a joint-limit singularity. The reconstruction method will be proposed based on the geometrical analysis of recoverability of hardware limitations. The method has the feature that no task motion error is induced by the hardware limitations while minimizing a possible null motion error, under the recoverability assumed.

• Advances in aircraft and spacecraft science
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• 제3권4호
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• pp.399-425
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• 2016

The dynamical requirements are obtained for airplanes to travel on inclined circular trajectories. Formulas are provided for determining the load factor, the bank angle, the lift coefficient and the thrust or power required for the motion. The dynamical properties of the airplane are taken into account, for both, airplanes with internal combustion engines and propellers, and airplanes with jet engines. A procedure is presented for the construction of tables from which the flyability of trajectories at a given angle of inclination can be read, together with the corresponding minimum and maximum radii allowed. Sample calculations are shown for the Cessna 182, a Silver Fox like unmanned aerial vehicle, and a F-16 jet airplane.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.201-201
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• 2000

Recently in the design of fuel tanks(launch vehicle, ship, automobile) which transport a large amount of liquid in the cargo holds, the structural damage due to liquid-sloshing becomes an important problem. The impact pressure from sloshing is most violent when the liquid motion of a partially filled tank is in resonance with the motion of a system. In this paper, the sloshing natural periods in liquid tanks are estimated for partially filled tanks with various geometries. In addition to, controlled for a launch vehicle with liquid sloshing effect by PD controller and sloshing filter The PD gain and sloshing filter parameter arc determined by optimal algorithm.