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저궤도위성 추력기 기반 궤도제어모드에서 궤도 각속도 변화에 따른 안정화 연구
최홍택(Hong-Taek Choi),오시환(Shi-Hwan Oh),용기력(Ki-Lyuk Yong) 대한기계학회 2010 대한기계학회 춘추학술대회 Vol.2010 No.11
After LEO satellite is launched, it performs the mission on the mission orbit. In general, attitude control subsystem for the LEO satellite consists of ground test mode, safe hole mode, orbit maintenance mode, standby mode and image mode to perform the mission. The satellite performs orbit correction and maintenance and inclination correction and maintenance using thruster after the insertion of the mission orbit. The internal disturbance is caused by thruster which is equipped with incorrectly, change of center of mass, and thrust level, etc. Nutation is also derived during ΔV to change altitude and inclination. Roll and pitch axis rotation is necessary for ΔV. In order to eliminate nutation angle and to stabilize the satellite, ΔV requires correct orbital rate. In this study, we reviewed the orbital rate according to reference frame and compare the attitude date with the requirement of the ΔV.
저궤도 위성 추력기의 교란토크를 고려한 위치 및 방위 설계
최홍택(Hong-taek Choi),김종범(Jong-Bum Kim),공현철(Hyeon-Cheol Gong) 대한기계학회 2006 대한기계학회 춘추학술대회 Vol.2006 No.6
Attitude control subsystem for the LEO satellite consists of contingency mode, maneuver mode and mission mode to perform the mission. The contingency mode is divided into sun acquisition submode, sun pointing submode and gyroless submode, and the maneuver mode is divided into attitude hold submode and △Ⅴ submode, while the mission mode divided into recess submode and image submode. In this paper, I designed thruster location and orientation of which was used for sun acquisition submode and maneuver mode as an actuator considering thruster disturbance torque uncertainty for LEO satellite.
스텝핑 모터 특성에 따른 2축 짐발 안테나 시스템의 미소진동 측정 시험
김대관(Kim Dae-Kwan),최홍택(Choi Hong-Taek),박지용(Park Gee-Yong) 한국소음진동공학회 2012 한국소음진동공학회 학술대회논문집 Vol.2012 No.4
A 2-axis gimbal system is one of main disturbance sources affecting on image jitter response of a satellite. The gimbal system can be rotated on its azimuth and elevation axes, resulting in variation of its moment of inertia and structural modes, so that generates non-linear vibration characteristics. In order to estimate the jitter response, it is an indispensable process to characterize micro-vibration disturbance of the 2-axis gimbal system. In the present research, the vibration characteristics of the 2-axis gimbal system was investigated with respect to the types of stepping motors. The micro-vibration tests were performed for 2-phase and 5-phase stepping motors. The test results show that the disturbance can be reduced with vibration attenuation ratio of 60% by replacing the 2-phase stepping motor with the 5-phase one.