• 한국항공운항학회지
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• 제23권1호
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• pp.49-55
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• 2015

This paper deals with dynamic modeling and controller design of a future Korean lunar module planned to be launched 2020's in Korea. For dynamic modeling of the lunar module, we first assume the lunar module as a rigid body. And we derive equations of motion for the lunar module by considering allocation of main thrusters and reaction thrusters. With the equation of motion, we design the controller based on the quaternion. A Pulse Width Pulse Frequency modulator(PWPFM) is selected for generating on/off signal. Finally, we construct a 2-phase descent mode including initial guidance mode, terminal guidance mode. The MATLAB simulation is performed for evaluating the descent ability and final landing velocity. The dynamic modeling and descent simulation of the lunar module in this paper could be applied for developing the future work of the Korean lunar exploration program.

• 한국지하수토양환경학회:학술대회논문집
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• 한국지하수토양환경학회 2002년도 총회 및 춘계학술발표회
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• pp.315-318
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• 2002

This study was performed to evaluate the effects of air flow rate and aeration mode on the treatment of bioventing for diesel-contaminated soil. Initial concentrations of diesel-contaminated soils were about 2,500 and 9,000mg/kg. Air flow rates were 30, 60, and 100mL/min, and air was injected in the continuous and the intermittent modes. TPH removal efficiency of intermittent aeration mode was higher than that of continuous aeration mode. Greater air flow rate than the value of guidance book was needed for bioventing.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2003년도 ICCAS
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• pp.531-536
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• 2003

In this paper, a redesigned guidance and control system for a lunar lander is presented. In past studies, the authors developed a trajectory and attitude control system which achieves the vertical soft landing on the lunar surface. It is confirmed that the system has a good tracking ability to a predefined profile and good robustness against a thruster failure mode where a partial failure of clustered engines was assumed. However, under the previous control laws, the landing point tends to be shifted, in response to the system parameter values, from a target point. Also, an unbalanced moment due to a thruster failure mode was not considered in the simulation. Therefore, in this study, the downrange control is added to the system to enable the vehicle to land at a pre-assigned target point accurately. Furthermore, inhibiting the effect of the unbalanced moment is attempted thorough redesigning the attitude control system. A numerical simulation was performed to confirm the ability of the proposed system with regard to the above problems. Moreover, in the past simulations, a low initial altitude was assumed as an initial condition: in this study, however, the performance of the proposed system is examined over the whole trajectory from an initial altitude of 10 [km] to the lunar surface.

• 한국정밀공학회지
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• 제28권11호
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• pp.1309-1315
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• 2011

The design process for obtaining the reliable steeraxle casting beam of fork lift truck is studied in this paper, as the casting beam is major component of steeraxle which has a steering function at driving. In this study, the driving mode and damage pattern of casting beam which could be occurred from the customer site were analyzed and it established the design process to predict the fatigue life by FEA(Finite Element Analysis) so that the reliability of steeraxle casting beam could be verified at DVT(Design Validation Test) mode. This paper provides guidance on the process of designing the reliable steeraxle casting beam at the initial design stage and also, provides guidance on the process of solving the problem when the failure is occurred in the field.

• International Journal of Aeronautical and Space Sciences
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• 제17권1호
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• pp.120-131
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• 2016

The full results of troubleshooting process related to the flight control system of a tilt-rotor type UAV in the flight tests are described. Flight tests were conducted in helicopter, conversion, and airplane modes. The vehicle was flown using automatic functions, which include speed-hold, altitude-hold, heading-hold, guidance modes, as well as automatic take-off and landing. Many unexpected problems occurred during the envelope expansion tests which were mostly under those automatic functions. The anomalies in helicopter mode include vortex ring state (VRS), long delay in the automatic take-off, and the initial overshoot in the automatic landing. In contrast, the anomalies in conversion mode are untrimmed AOS oscillation and the calibration errors of the air data sensors. The problems of low damping in rotor speed and roll rate responses are found in airplane mode. Once all of the known problems had been solved, the vehicle in airplane mode gradually reached the maximum design speed of 440km/h at the operation altitude of 3km. This paper also presents a comprehensive detailing of the control systems of the tilt-rotor unmanned air vehicle (UAV).

• 핵의학기술
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• 제15권2호
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• pp.26-29
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• 2011

[F-18]FDG 제조 후 품질관리를 수행하는데 있어서 품질관리 항목 중 잔류용매 시험은 최종 [F-18]FDG 바이알에 잔류하는 유기용매를 측정하기 위한 것이다. 본 연구는 자동합성장치에 따른 최종 [F-18]FDG 바이알에 잔류하는 유기용매의 종류를 파악하고, 잔류량을 측정하고자 하였다. 불꽃이온화 검출기(Flame Ionization Detector)가 장착된 기체크로마토그래프(Agilent Technologies 7890A)를 이용하여 제조 후 일주일 이내의 밀봉 바이알에 보관한 [F-18]FDG를 기체크로마토그래프에 $1.0{\mu}L$ 씩 주입한 후 각 피크영역을 구하였다. FASTlab은 평균이 에탄올 72 ppm, 아세토니트릴 54 ppm, 초산 1030 ppm으로 나타났으며, TRACERlab MX는 평균이 에탄올 439 ppm 및 아세토니트릴 79 ppm이 검출되어 모두 의약품 잔류용매기준의 허용량 이내에 있었다. [F-18]FDG 주사액에 있는 잔류용매는 모두 허용량 이내로 환자검사에 사용하는데 적합하였다. 또한 최종 [F-18]FDG 바이알에 있을 수 있는 초산의 최대 이론량은 1167 ppm으로 따로 검량을 하지 않아도 되는 것으로 나타났다. 이 결과에서는 자동합성장치에 따라 방사성의약품의 잔류용매의 종류 및 양이 다를 수 있음을 보였다.