• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.32 no.3
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• pp.45-50
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• 2004

The design of reaction wheel control logic is critical to achieve the spacecraft attitude stabilization and performance requirements for the successful mission. Due to various uncertainties on orbit there exist limitation to obtain the model parameters through the ground tests and to design the associated control logic. Thus, the model parameter correction using on-orbit data is essential to the control performance on orbit. This paper performs the system identification using KOMPSAT-1 telemetry data and extracts the model parameters of the reaction wheel. Moreover, the reaction wheel is remodeled and compared with the ground test results.

• Transactions of the Korean Society for Noise and Vibration Engineering
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• v.15 no.4 s.97
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• pp.437-444
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• 2005

This paper presents a robust aeroelastic control methodology of a two dimensional flapped wing system exposed to an incompressible flow field. A robust controller is designed using a linear matrix inequality (LMI) approach for the multiobjective synthesis. The design objectives are to achieve a mix of $H_{\infty}$ performance and H₂ performance satisfying constraints on the closed loop pole locations in the presence of model uncertainties. Numerical examples are presented to demonstrate the effectiveness of LMI approach in damping out the aeroelastic response of 3-DOF flapped wing system.

• Proceedings of the Korea Information Processing Society Conference
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• 2004.05a
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• pp.1533-1536
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• 2004

위성의 비행소프트웨어는 위성이 주어진 임무를 수행할 수 있도록 위성을 제어하는 것으로 지상으로부터의 원격 명령을 받아 처리하고 원격측정 데이터를 지상으로 송신하는 기능과 자세 결정 및 제어, 전력 제어, 열 제어, 탑재체 관리 등의 기능을 수행한다. 본 논문은 다목적실용위성 2호의 비행소프트웨어에서 원격측정 데이터를 저장하고 지상으로 전송하는 기능을 수행하는 MMD (Mass Memory and Downlink Management) 소프트웨어의 설계 및 구현 내용과 시험절차, 방법, 시험결과 등에 대해서 서술하였다.

• Proceedings of the KIEE Conference
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• 2004.07d
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• pp.2634-2636
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• 2004

다목적실용위성2호의 위성 본체시스템에는 지상과 연락을 담당하는 주 컴퓨터인 OBC, 위성의 자세를 제어를 위한 원격구동장치인 RDU 그리고 위성의 전원분배를 제어장치인 ECU인 3개의 동일 프로세서(386)가 탑재되어 각 담당 임무를 수행하는 분산형 구조를 갖고 있다. 각 프로세서는 EEPROM과 SRAM 데이터 메모리를 갖고 있는데 전원 리셋이 일어나면 모든 프로그램은 EEPROM에서 SRAM으로 복사되어 운영 프로그램이 실행하도록 되어 있다. 그러나 SRAM은 우주환경에서 위성체는 방사선에 노출되어 손상을 입을 때 SEU이 발생되어 정보가 왜곡되거나 상실되는 문제를 갖고 있다. 그러므로 본 논문에서는 변형된 해밍코드 기법을 이용하여 데이터를 수신하는 곳에서 에러를 검출 및 수정하는 디지털 회로 설계방법을 기술하고자 한다.

• Proceedings of the Korea Information Processing Society Conference
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• 2005.11a
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• pp.1421-1424
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• 2005

저궤도 위성인 다목적실용위성 2호의 컴퓨터 시스템은 3개 프로세서로 구성된 분산처리 구조이며 프로세서와 프로세서, 프로세서와 주변 장치들과의 통신은 MIL-STD-1553B 버스를 통해 이루어진다. 이들 3개 프로세서들 상에서 실행되는 탑재소프트웨어는 위성의 하드웨어 및 주변 입출력 장치들을 제어 및 관리한다. 그리고 위성의 결함을 관리하는 기능과 비상시에는 지상과의 연결 없이 위성을 자동제어 하는 기능들 또한 탑재소프트웨어에 구현되어져있다. 본 논문에서는 저궤도 위성인 다목적실용위성-2호의 임무를 수행하기 위한 탑재소프트웨어의 구성 및 기능, 개발과정과 개발환경을 소개한다.

• Journal of Drive and Control
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• v.5 no.2
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• pp.32-36
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• 2008

• Journal of the Earthquake Engineering Society of Korea
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• v.9 no.4 s.44
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• pp.55-66
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• 2005

The effectiveness of fuzzy supervisory control technique for the control of seismic responses of smart base isolation system is investigated in this study. To this end, first generation base isolated building benchmark problem is employed for the numerical simulation. The benchmark structure under consideration is an eight-story base isolated building having irregular plan and is equipped with low-damping elastometric bearings and magnetorheological (MR) dampers for seismic protection. Lower level fuzzy logic controllers (FLC) for far-fault or near-fault earthquakes are developed in order to effectively control base isolated building using multi-objective genetic algorithm. Four objectives, i.e. reduction of peak structural acceleration, peak base drift, RMS structural acceleration and RMS base drift, are used in multi-objective optimization process. When earthquakes are applied to benchmark building, each of low level FLCs provides different command voltage and supervisory fuzzy controller combines two command voltages io one based on fuzzy inference system in real time. Results from the numerical simulations demonstrate that base drift as well as superstructure responses can be effectively reduced using the proposed supervisory fuzzy control technique.

• Computational Structural Engineering
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• v.3 no.3
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• pp.141-146
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• 1990

This study is on a seismic analysis of absorber rod in KMRR Reactivity Control Mechanism. The model being studied is two coaxial tubes(control absorber rod and flow tube) immersed in the water and partially coupled(overlap) by water gap. The hydrodynamic mass effects by the water in each surrounding conditions are considered in the model. The natural frequencies, stresses and displacements of the system due to Safe Shutdown Earthquake are computed in the cases of in-phase modes and out-of-phase modes of two coaxial tubes. The results show that maximum stresses are well below the allowable limit but the maximum displacements at the ends of both tubes are so much that the absorber rod contacts with the flow tube(or surrounding wall).

• Aerospace Engineering and Technology
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• v.3 no.2
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• pp.1-6
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• 2004

One of the mechanical system engineer's tasks of satellite design and development is to make the control plan, keep track and estimate the characteristics of system mass properties. As the design phases are going on, mass properties related activities also transit as like a data collection, system mass property estimation and measurement. Fidelity of mass properties database should be confirmed through measurement test. In this paper the control plan and estimation of system mass properties are explained by the actual data and experience of the development of satellite and the fidelity of mass properties database was confirmed through measurement test.

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.3
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• pp.80-89
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• 1998

Propulsion subsystem transfers KOMPSAT into mission orbit and controls its attitude. Design factor consists of structure safety, electrical circuit design, consumable power estimation of thermal hardwares, damping device design of fuel transient pressure, and system configuration design by considering plume effect from thruster firing. System level analysis should be performed for verification of system design under launch vehicle and orbital environment. Electrical functional test of thermal control hardware, proof pressure test, cleanliness verification test, and internal/external leakage test of fuel feeding system should be carried out for performance estimation of propulsion system. Design and assembly process of propulsion subsystem was depicted and reliability of system was verified by test analysis in this paper.