• 한국게임학회 논문지
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• 제21권4호
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• pp.73-84
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• 2021

게임분석 방법에 대한 다양한 연구들이 진행되었다. 본 논문에서는 게임의 필수적인 행동의 Core, 게임 문제를 해결하는 행동의 Primary, Core와 Primary를 도와주는 행동의 Secondary로 분류하는 분석 방법을 제안한다. 제안 방법은 게임의 장르적 유사성 및 특징, 콘텐츠의 풍부함, 숙련 난이도를 분석할 수 있다. 사례분석과 사례 조사를 진행하여 분석 사항이 객관적 게임 경험과 일치하는지 확인하였다. 본 연구의 결과는 게임 기획 단계에서 유사 게임과 비교하면서 개발을 진행해나가는데 응용될 수 있을 것이며, 이러한 과정을 통해 게임 기획력 향상 및 경쟁력 있는 게임 개발에 도움될 수 있을 것이라 기대한다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2000년도 제15차 학술회의논문집
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• pp.30-30
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• 2000

In the three axis control of satellite by using reaction wheel and gyro, a Gyro carries out measuring of the attitude angie and the attitude angular velocity. The Gyro is operated by the electronic part and the mechanic actuator. The digital part of the electronic part is consisted of the FPGA (Field Programmable Gate Array), which is one of the methods for designing VLSI (Very Large Scale Integrated Circuit), and the mechanic actuator processes the input/output data by the dynamic model. In the research of the mixed mode of Gyro, the simulation is accomplished by SABER of the mixed mode simulator and the results for the practical implementation of the satellite ACS (Attitude Control System) interfaced with the data processing are proposed.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2005년도 ICCAS
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• pp.1641-1644
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• 2005

Magnetic actuation utilizes the mechanic torque that is the result of interaction of the current in a coil with an external magnetic field. A main obstacle is, however, that torques can only be produced perpendicular to the magnetic field. In addition, there is uncertainty in the Earth magnetic field models due to the complicated dynamic nature of the field. Also, the magnetic hardware and the spacecraft can interact, causing both to behave in undesirable ways. This actuation principle has been a topic of research since earliest satellites were launched. Earlier magnetic control has been applied for nutation damping for gravity gradient stabilized satellites, and for velocity decrease for satellites without appendages. The three axes of a micro-satellite can be stabilized by using an electromagnetic actuator which is rigidly mounted on the structure of the satellite. The actuator consists of three mutually-orthogonal air-cored coils on the skin of the satellite. The coils are excited so that the orbital frame magnetic field and body frame magnetic field coincides i.e. to make the Euler angles to zero. This can be done using a Neural Network controller trained by PD controller data and driven by the difference between the orbital and body frame magnetic fields.