• 한국항공우주학회지
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• 제40권6호
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• pp.506-514
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• 2012

본 논문에서는 비행체의 운동 역학을 고려한 경로 추종을 위한 시선각 유도 법칙의 유도 게인 설계 기법에 대해 기술하였다. 비례-미분 게인과 접근 거리의 설계 변수로 구성된 시선각 기반 유도 법칙은 유도 게인 결정시 대부분 경험적 또는 실험적인 방법으로 설계하는 것이 일반적인데 이러한 경우 정밀하고 일관적인 경로 추종 성능 보장이 어렵고 비행체 기동 한계 및 운용 속도 등에 따라 설계 변수를 재설계해야하는 단점이 있다. 이러한 단점을 보완하기 위해 본 연구에서는 비행체의 속도에 따른 운동 역학을 고려하여 설계 변수의 개수를 최소화하고 비행 속도에 따라 유도 법칙 게인이 변화되어 정밀한 경로 추종이 가능할 뿐만 아니라 안정적이고 일관된 성능을 갖는 유도 법칙의 게인 설정 기법을 제안하였다. 제안된 기법은 비행체의 자세에 대한 1차 응답 속도를 고려한 비선형 시뮬레이션을 수행하여 추종 성능을 평가하였으며 선형 경로와 원형 경로에 대한 비행 시험 을 통해 추종 성능 및 알고리듬의 타당성을 실험적으로 확인하였다.

• Journal of Positioning, Navigation, and Timing
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• 제11권2호
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• pp.71-81
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• 2022

In order for electro-optical tracking system (EOTS) to have accurate target coordinate, accurate navigation results are required. If an integrated navigation system is configured using an inertial measurement unit (IMU) of EOTS and the vehicle's navigation results, navigation results with high rate can be obtained. Due to the time-delay of the navigation results of the vehicle in the EOTS and scale factor errors of the EOTS IMU in high-speed and high dynamic operation of the vehicle, it is much more difficult to have accurate navigation results. In this paper, an integrated navigation system of EOTS which compensates time-delay and scale factor error is proposed. The proposed integrated navigation system consists of vehicle's navigation system which provides time-delayed navigation results, an EOTS IMU, an inertial navigation system (INS), an augmented Kalman filter and integration Kalman filter. The augmented Kalman filter outputs navigation results, in which the time-delay of the vehicle's navigation results is compensated. The integration Kalman filter estimates position, velocity, attitude error of the EOTS INS and accelerometer bias, accelerometer scale factor error, gyro bias and gyro scale factor error from the difference between the output of the augmented Kalman filter and the navigation result of the EOTS INS. In order to check performance of the proposed integrated navigation system, simulations for output data of a measurement generator and land vehicle experiments were performed. The performance evaluation results show that the proposed integrated navigation system provides more accurate navigation results.

• 한국위성정보통신학회논문지
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• 제1권2호
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• pp.76-82
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• 2006

한국전자통신연구원이 개발하여 항공우주연구원의 관제소에 설치한 아리랑2호 위성 관제시스템은 지난 7월 28일 발사된 아리랑2호 위성의 운용에 사용되고 있다. 아리랑2호 관제시스템의 대표적인 기능으로는 원격측정데이터 수신 및 처리, 원격명령 생성 및 송신, 위성 추적 및 거리측정, 궤도 예측 및 결정, 위성자세 조정계획, 그리고 위성 시뮬레이션 등이 있다. 아리랑2호 위성은 아리랑1호 위성의 임무를 이어받아 수행하며, MSC (Multi Spectral Camera) 및 정밀궤도결정, 정밀자세결정 등을 통해 아리랑1호에 비해 훨씬 향상된 해상도의 사진을 제공하는 성능을 가지고 있다.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2003년도 한국우주과학회보 제12권2호
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• pp.46-46
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• 2003

Since its launching on 21 December 1999, the KOrea Multi-Purpose SATellite-Ⅰ (KOMPSAT-Ⅰ) has been successfully operated by the Mission Control Element (MCE), which was developed by the Electronics and Telecommunications Research Institute (ETRI). Most of the major functions of the MCE have been successfully demonstrated and verified during the three years of the mission life of the satellite. The Mission Analysis and Planning Subsystem (MAPS), which is one of the four subsystems in the MCE, played a key role in the Launch and Early Orbit Phase (LEOP) operations as well as the on-orbit mission operations. This paper presents the operational performances of the various functions in MAPS. We show the performance and analysis of orbit determinations using ground-based tracking data and GPS navigation solutions. We present four instances of the orbit maneuvers that guided the spacecraft from injection orbit into the nominal on-orbit. We include the ground-based attitude determination using telemetry data and the attitude maneuvers for imaging mission. The event prediction, mission scheduling, and command planning functions in MAPS subsequently generate the spacecraft mission operations and command plan. The fuel accounting and the realtime ground track display also support the spacecraft mission operations. We also present the orbital evolutions during the three years of the mission life of the KOMPSAT-Ⅰ.

• 한국정밀공학회지
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• 제21권1호
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• pp.101-108
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• 2004

An electro-hydraulic manipulator using hydraulic actuators has many nonlinear elements, and its parameter fluctuations are greater than those of an electrically driven manipulator. So it is relatively difficult to obtain stable control performance. In this report, we applied disturbance estimation and compensation type robust control to all axes in a 3-link electro-hydraulic manipulator. From the results of experiment, it was confirmed that the performance of trajectory tracking and attitude regulating is greatly improved by the disturbance observer, which model is the same for each axis. On the other hand, for the autonomous assembly tasks, it is said that compliance control is one of the most available methods. Therefore we proposed compliance control which is based on the position control by disturbance observer for our manipulator system. To realize more stable contact work, the states in the compliance loop are feedback, where not only displacement but also velocity and acceleration are considered. And we applied this compliance control to Peg-in-Hole insertion task and analyzed mechanical relation between peg and hole. Also we proposed new method of shifting the position of end-effector periodically for the purpose of smooth insertion. As a result of using this method, it is experimentally confirmed that Peg-in-Hole insertion task with a clearance of 0.05［mm］can be achieved.

• 한국항공우주학회지
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• 제32권4호
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• pp.24-33
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• 2004

본 논문에서는 광범위한 비선형 함수 근사 성질을 갖고 있는 온라인 적응 신경회로망을 이용하여 헬리콥터 비행 제어 시스템을 설계하였다. 기존의 시스템 모델링 오차를 보상하는 방식과는 달리, 시스템의 입출력 정보를 통해 피드백 선형화 기법에서 필요한 두 개의 비선형 함수를 신경회로망을 이용하여 대체하는 방법을 적용하였다. 두 개의 비선형 함수를 신경회로망으로 대체하여 구성된 폐회로 시스템의 추적 성능과 내부 안정성을 보장하기 위하여 신경회로망의 가중치 학습 방법을 리야프노프 함수를 이용하여 유도하였다. 그리고 헬리콥터 저속 비행 모드에 대한 수치 시뮬레이션 결과를 통해 신경회로망을 적용한 제어 시스템의 성능을 검증하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.49-53
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• 1994

Advanced Real-Time Satellite Simulator(ARTSS) has been developed to support the telemetry, tracking and command operations of the ETRI satellite control system and to provide satellite engineers a more powerful and informative satellite simulations tool on the desktop. To provide extensive simulation functions for a communication satellite system in the pre-operational and operational missions, ARTSS uses a geosynchronous orbit(GEO) satellite model consisting of the attitude and orbit control subsystem, the power subsystem, the thermal subsystem, the telemetry, command and ranging subsystem, and the communications payload subsystem. In this paper, the system features and functions are presented and the satellite subsystem models are explained in detail.

• 제어로봇시스템학회논문지
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• 제10권1호
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• pp.47-53
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• 2004

An electro-hydraulic manipulator using hydraulic actuators has many nonlinear elements, and its parameter fluctuations are greater than those of an electrically driven manipulator. So it is quite difficult to obtain stable control performance. We have applied a disturbance estimation and compensation type robust control to all the axes in a 6-link electro-hydraulic manipulator. It was confirmed that the performance of trajectory tracking and attitude regulating was greatly improved by the disturbance observer. For autonomous assembly tasks, it is said that compliance control is one of the most popular methods in contact task. We have proposed a compliance control based on the position control by a disturbance observer for our manipulator system. To realize more stable contact work, the states in the compliance loop are feedbacked, where not only displacement but also the velocity and acceleration are considered. We have also applied this compliance control to the Peg-in-Hole insertion task and proposed new methods of (1)rotating of the end-effector periodically in order to reduce the friction force, (2)random searching for the center of a hole and (3)trajectory modification to reduce the impact force. As a result of these new methods, it could be experimentally confirmed that the Peg-in-Hole insertion task with a clearance of 0.007 [mm] could be achieved.

• Child Health Nursing Research
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• 제11권1호
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• pp.63-71
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• 2005

Purpose: This study was done to examine the effects of a smoking prevention program on primary school students. Method: The design for this study was a nonequivalent quasi-experimental control group pretest-posttest. The smoking prevention program was provided to grade 5 and 6 students selected from two schools in Jecheon. The experimental group consisted of 72 students and the control group, 73 students. A smoking prevention program composed of smoking prevention education (once a week for 40 minutes over a period of 8 weeks) and supportive environment for smoking prevention was developed by modifying several smoking prevention programs. The research was conducted from May 15 to October 10, 2003. Result: 1) After completion of the smoking prevention program, the mean scores for knowledge about smoking, attitude to smoking, and intention toward non-smoking were not significantly different between the experimental group and the control group. Conclusions: To affectively achieve the aims of a smoking prevention program, the effectiveness of the program should not be measured over the short term only. Long-term tracking of students educated in the program, to identify the rate of those who later become smokers needs to be done.

• 한국항공우주학회지
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• 제43권1호
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• pp.40-48
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• 2015

본 논문에서는 RF탐색기 측정치인 산란점 모델링 기법에 대해 제안한다. 우선 상대자세 각 따라 변화하는 ISAR 영상(Inverse Synthetic Aperture Radar Image)로부터 기준 산란점을 생성하였다. 다음으로 RF탐색기 측정치의 주요 불확실성 요소인 잡음세기(noise strength), 깜박임(blink), boresight 오차를 기준 산란점에 부가한다. 본 연구에서 제안된 RF탐색기 모델은 다양한 표적추적 필터 알고리듬 개발에 사용할 수 있다.