• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.437-444
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• 2010

This paper deals with the attitude control of an underactuated spacecraft that has one single-gimbal variable-speed CMG. An underactuated spacecraft may not converge to arbitrary attitudes if its total angular momentum is not zero. To stabilize a spacecraft, the CMG has to align with the angular momentum in the inertial frame. Four different install configurations for the CMG have been considered and controllable angular momentums have been analyzed. Also, based on the backstepping method, stabilizing control laws have been presented and their properties have been compared.

• Journal of Satellite, Information and Communications
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• v.12 no.4
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• pp.50-55
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• 2017

In this paper, the design of the RF system monitoring and control system of KUS (KASS: KASS Uplink Station) which constitutes KASS (Korea Augmentation Satellite System) is described. The Korean satellite calibration system is named KASS and aims to develop the SBAS system of the APV-1 level SoL service level and the CAT-1 test operation technology. Software and hardware development environment, function and algorithm of supervisory control device, structure of supervisory control device, and user interface were designed to implement KUS / RFS monitoring control device. We have secured the stability and reliability of the system by using the monitoring and control system design of the COMS (Communication Ocean & Meteorological Satellite) and the Korea Satellite 5A / 7 control system, which has already been used for the design of the surveillance control system. In addition, we have made it possible to provide the user interface according to the actual operator's request more conveniently.

• ICROS
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• v.3 no.2
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• pp.26-33
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• 1997

본 논문에서는 위성발사체의 유조제어시스템에 대하여 일본의 발사체를 중심으로 개략적으로 살펴보았으며, 특히 최근 발사에 성공한 NASDA의 H-II 발사체의 SRB와 ISAS의 M-3SII의 상단의 조합으로 구성된 J-I 발사체의 유도제어시스템에 대하여 간략히 소개하였다. 또한, 발사체의 유도를 위한 여러 가지 유도법 가운데 일본의 과학위성 발사체 M-3H-3을 모델로 하여 최적제어이론을 이용한 발사체 유도법칙을 유도하였으며, 이 때 유도법칙의 해는 Newton-Raphson 수치해법 알고리즘을 사용하여 구하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.4
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• pp.40-46
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• 2006

It is required to develop a highly reliable attitude & orbit control system of satellite that is less expensive as the technology of satellite design & integration is recently matured dramatically. To accomodate this kind of needs, the two axis attitude control method for wheel-based momentum-biased satellite system whose momentum bias vector points to a certain direction(sun direction), is developed using simple but reliable sensors and actuator: three axis magnetometer and coarse sun sensor are used as sensors, and magnetic torque bars are used as actuator. Classical PD type controller design methodologies are applied on a satellite system for the two axis control with the proper assumptions. Nonlinear simulation results are included to demonstrate the long term stability and the performance of closed-loop system design results.

• Journal of Astronomy and Space Sciences
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• v.15 no.1
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• pp.245-250
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• 1998

Attitude determination and control of satellite is important component which determines the accomplish satellite missions. In this study, attitude control using reaction wheels and momentum dumping of wheels are considered. Attitude control law is designed by Sliding control and LQR. Attitude maneuver control law is obtained by Shooting method. Wheels momentum dumping control law is designed by Bang-Bang control. Four reaction wheels are configurated for minimized the electric power consumption. Wheels control torque and magnetic moment of magnetic torquer are limited.

• Bulletin of the Korean Space Science Society
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• 2011.04a
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• pp.26.1-26.1
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• 2011

위성 편대비행 시스템에서 궤도 및 자세의 결정과 제어를 동시에 시뮬레이션 할 수 있는 통합 시스템을 설계하고 개발하였다. 실제 위성에서는 궤도 제어가 수행되는 동안 자세는 계속 변한다. 그러므로 임무수행을 위해 편대위성들의 자세를 동기화하기 위해서는 편대위성들의 자세 결정과 제어가 필요하다. 이와 같이 실제와 같은 시뮬레이션을 위해서, 궤도 및 자세의 결정과 제어를 동시에 수행할 수 있는 통합된 시뮬레이터 시스템이 필요하다. 통합 시뮬레이터 시스템의 개발은 기존에 연세대학교에서 개발한 GPS 시뮬레이터를 이용한 편대비행 테스트베드와 하드웨어 자세 시뮬레이터를 각각 보완한 후 통합하는 방법으로 수행하였다. 이 두 시스템은 서로 독립적으로 개발되었기 때문에 통합을 위하여 하드웨어 인터페이스와 소프트웨어 인터페이스 부분으로 나누어 설계와 개발을 수행하고, 최종적으로 결합하는 절차로 통합을 완료하였다. 마지막으로 개발된 통합 시뮬레이터 시스템과 통합 시나리오를 사용하여 궤도와 자세를 동시에 시뮬레이션 하고, 이를 통해 개발된 통합 시스템을 검증하였다. 이 연구를 통해 개발된 궤도와 자세가 통합된 하드웨어 시뮬레이터 시스템은 실제 위성에 가까운 시뮬레이션을 수행할 수 있을 뿐만 아니라 하드웨어와 소프트웨어 인터페이스에 대한 검증이 가능하고 실제의 하드웨어 특성으로부터 생기는 에러를 고려하여 알고리즘의 실제 성능을 평가할 수 있다.

• Proceedings of the KIEE Conference
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• 2008.07a
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• pp.1944-1946
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• 2008

본 논문에서는 통신해양기상위성의 추력기 구동장치에 대하여 기술하였다. 위성에서는 위성체 전력공급을 위한 태양전지판, 위성의 자세제어를 위한 모멘텀 휠과 추진계, 온도제어 등을 담당하는 다양한 추력기 (actuator)가 존재한다. 위성의 안정적인 동작을 위해 각각의 추력기를 제어하기 위한 전기 및 기계 접속 요구사항을 수용하는 인터페이스 기능을 담당하는 추력기 구동장치 (Acutator Drive Electronics, ADE)가 필요하다. 통신해양기상위성의 추력기 구동장치는 안정적인 동작을 위해서 1개의 ADE5 구조체 안에 ADE5 A와 ADE5 B가 중복되어서 구현되었다. ADE5는 ADE5 A와 B가 수동적 중복구조를 갖지만, 추력기와 ADE5 A, B가 상호연결되어 있어서 위성의 상태에 따라서 2개의 ADE5 A, B가 혼합적으로 사용될 수 있다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.5
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• pp.423-429
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• 2014

Passive attitude stabilization methods using the permanent magnet combined with hysteresis damper and the gravity gradient boom have been widely used for the attitude determination and control of cube satellite, due to its advantage of system simplicity. In this paper, on-orbit thermal characteristics of the cube satellite considering the attitude profiles obtained from the above passive attitude stabilization methods have been investigated through on-orbit thermal analysis. In addition, the effectiveness of the various thermal coatings on the panel for the communication antenna installation has been verified.

• Journal of Satellite, Information and Communications
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• v.2 no.1
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• pp.48-55
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• 2007

The system requirement definition, system configuration, major parameters for GNSS ground station development are presented in this paper. GNSS ground station system consists of the GNSS sensor station, up link station and monitoring & control system. The GNSS sensor station consists of navigation receiver subsystem which process the GPS and Galileo navigation signal, automic clock subsystem, meteorological data receiving subsystem and navigation data processing subsystem. To communicate the error correction of navigation fate, GNSS sensor station interface with GNSS Control Center.

• Journal of the Institute of Electronics Engineers of Korea SC
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• v.37 no.1
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• pp.19-29
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• 2000

Because the previous simulation tool for attitude control of satellite was designed for the modeling of rigid body and PD controller, the attitude error can be made more than the limitation value for keeping for communication link, and then the communication link can be lost at moving of satellite. So, for rapid attitude restoration and design of stable and modernized controller, the modelling of rigid body and flexible body structure for moving GEO and LEO satellites were performed. Also the minimum time controller is designed for the rapid restoration of attitude error at communication broken and to minimize the disconnection period from ground communication system during the satellite stationkeeping. The linear regulator is designed using the space state vector that is better than accuracy and stability of PD controller. Firstly the simulation was performed for comparison of the rigid and stability of PD controller. Firstly the simulation was performed for comparison of the rigid and flexible models using PD controller and the case of the pitch angle changing by ground command, and the case of the periodic north-south stationkeeping are performed for the analysis of response characteristics of each controller when the attitude is changed. As a result, the flexible body model represents more sililar results of real situation than the rigid body model. The minimum time controller can restore 7 times rapidly than PD controller for its lost attitude. The linear regulator has several merits for capability of adaptation against the external disturbance, stability and response time. In future, we can check the estimated results using this satellite model and controller for real operation. Futhermore the development of new controller and training can be supported.