• Resources Recycling
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• v.23 no.6
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• pp.30-39
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• 2014

The trajectories of PCB(Printed Circuit Board) particles in the corona discharge electrostatic separation was simulated. The PCB particles are prepared by crushing bare board, which disassembled from electronic components, consist mostly of copper and FR-4(Flame Retardant Level-4) Firstly, a model was established for calculating of detachment points of PCB particles from the rotating electrode in separator. The model of detachment points was derived from equilibrium of force such as gravity force, centrifugal force, electrostatic force. The trajectories of particles after detachment was calculated by acceleration derived from time-integrating method of motion equation. In this simulation, particle size, supplied voltage, rotation speed of rotating roll electrode and angle of induction electrode were adopted as variables. While the trajectories of FR-4 particles were affected by all variables, rotation speed of rotating roll electrode was dominant variables affecting trajectories of copper particles.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.9
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• pp.64-74
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• 2003

This paper proposes a new autonomous stationkeeping system suitable for geostationary satellite and conducts computer simulation to verify the proposed algorithm. The proposed onboard system receives pseudo-range signal from ground equipments located at two different position with long baseline, determines the orbit error in realtime and generates orbit control commands. For minimized onboard stationkeeping logic and better reliability, the orbit controller is designed to generate control signal to have the orbit roughly follow predetermined reference range data which is generated through ground based computer simulation. The reference range data is assumed to be uploaded with time tag. A simple orbit controller is proposed which combines the reference $\Delta$V and feedback control signal. Finally, the performance of the proposed system is verified through the computer simulations.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.10
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• pp.770-778
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• 2013

Solar sail propulsion uses solar radiation pressure to propel spacecraft without propellant, and it is useful for deep-space missions and continuos orbit maneuver missions. After a brief introduction of solar sail dynamics, locally optimal trajectories in Sun-centered and Earth-centered orbits are analyzed. Numerical simulations for the optimal trajectories are performed. Trajectory for the rendezvous with Halley comet is generated, and different planet escape methods are compared.

• Proceedings of the KIEE Conference
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• 2003.11b
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• pp.3-6
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• 2003

뱀형 로봇은 일반적인 바퀴형 이동로봇과 운동 메카니즘이 상이하며 다관절로 이루어져 있기 때문에 장애물 회피에 있어 빠른 정보의 처리와 이를 위한 특별한 정보가 요구된다. 이를 실현하기 위하여 로봇은 자신의 위치를 지속적으로 파악하면서 장애물의 좌표 값과 일정한 거리의 간격을 두고 움직여야 한다. 주행 궤도 및 장애물 회피를 위한 알고리즘을 검증하기 위하여 가상 뱀형 시뮬레이터를 제작하였다. 시뮬레이터는 이동 주행 궤도를 생성하고, 지나온 궤도를 재현할 수 있는 재현기(Back Tracker), 앞으로 이루어질 뱀형 로봇의 위치와 자세를 알아보는 예견기(Predictor)로 구성된다. 시뮬레이터를 통하여 주위의 장애물을 안전하게 통과할 수 있는 일반적인 알고리즘인 포텐셜함수의 특성을 알아보고, 국소 최소점(Local Minima)에 빠지기 쉬운 단점을 극복하기 위한 방안을 제시한다. 본 논문에서는 뱀의 이동 주행 궤적을 알아보고, 주위의 장애물을 안전하게 통과할 수 있도록 하는 알고리즘에 대한 고찰과 제안한 알고리즘을 소프트웨어적인 3D 시뮬레이션을 통하여 걸과를 분석하고 검증한다.

• Proceedings of the KIEE Conference
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• 2006.07b
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• pp.1130-1131
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• 2006

본 논문은 고속선에 사용 중인 UM71-C 궤도회로에 대한 전기적인 특성에 관한 시뮬레이션 실행결과를 나타낸다. 고속선 운행선상의 샘플개소를 선정하여 환경에 따른 선로정수를 구하고 전송라인의 특성임피던스와 전파정수를 반영시켜 레일전압과 전류에 대한 시뮬레이션을 수행하였으며, 차상검측시스템에서 측정되어진 검측데이터 파형과 비교하였다. 이러한 모델링 작업은 궤도회로 구성요소의 기능저하를 사전 예측하여 열차의 안전운행을 확보하기 위한 기초자료로 사용되어 질 수 있으며, 또한 차상검측시스템에서 얻어진 검측데이터와의 비교를 통해 유지보수에 활용 가능한 활용지침 및 분석기준을 작성하기 위해 필요하다.

• Aerospace Engineering and Technology
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• v.13 no.2
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• pp.122-130
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• 2014

GEO-KOMPSAT-2 which is under development by KARI to be launched in 2018 is expected to be injected into its orbit through the standard GTO(Geostationary Transfer Orbit) or SSTO(Supersynchronous Transfer Orbit). While the standard GTO mission has been applied for the most of the geostationary satellites, the SSTO mission is rare case and significantly different from the standard GTO mission in technical point of view. This paper lists the operational constraints to be applied for GEO-KOMPSAT-2 SSTO mission, and introduces a preliminary LAE burn plan for GEO-KOMPSAT-2 mission. In order to evaluate the developed plan, a simulation study has been performed considering ground station visibility.

• Journal of the Korea Society for Simulation
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• v.28 no.3
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• pp.75-82
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• 2019

A Satellite Communication (SATCOM), which is applied to various systems to communicate with other systems at the limited wired communication situation, is required to head at a stable point of the space, because this system uses a geostationary satellite. It is important to know satellite tracking heading angles such as elevation angle and azimuth angle for the immovable antenna's latitude, longitude, and altitude. Moreover, calculation of heading angle is critical for SATCOM antenna on a moving platform. In this study, a antenna heading angle calculation method is applied to compute elevation and azimuth angle for a SATCOM antenna and the heading angle simulation is executed for the Korea peninsula and surrounding areas. To verify this simulation, satellite tracking test is conducted using a SATCOM antenna which uses monopulse signal tracking method. The simulation is confirmed by comparing this test result with the simulation. And we make a suggestion for calculation of polarization angle of this antenna.

• Proceedings of the Korea Society for Simulation Conference
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• 2002.11a
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• pp.59-64
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• 2002

위성의 자세 및 궤도, 추진기 등 상태의 동적 반응과 위성체 내부의 원격 명령 및 원격측정 처리 과정을 시뮬레이션하여 관제시스템의 운용자 교육 및 위성 이상상태 분석을 위한 위성 다목적실용위성 2호 시뮬레이터을 객체지향설계기법을 이용하여 설계한 내용을 기술한다.

• Journal of the Korea Society for Simulation
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• v.19 no.4
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• pp.123-128
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• 2010

The space radiation/total ionizing Dose(TID) and its effects, and the GEO satellite system design considerations in space radiation environment are studied in this paper using Spenvis(Space Environment Information System). The GEO satellite system in space environment is simulated by NASA AP8/AE8, JPL91 and NRL CREME models, repectively for trapped particle, solar proton and cosmic-ray. The total ionizing Dose which is accumulated continuously to spacecraft electronics has been expressed as the function of aluminum thickness. These values can be used as the criteria for the selection of electronic parts and shielding thickness of the Digital Channel Amplifier(DCAMP) structure.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.22 no.12
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• pp.2763-2771
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• 1997

To determine the satellite orbital positions considering interference caused by inter-satellite systems is one of the most improtant issues in terms of optimal usage of satellite network resources. In this paper, considering ITU filing situation, we present the satellite orbital positions determination method to minimize iter-satellite system interference effect in the fixed satellite communication using an optimization method. Through the computer simulatio, it was shown that the proposed method is suitable to determine the satellite orbital positions.