• Journal of Astronomy and Space Sciences
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• 제6권2호
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• pp.101-108
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• 1989

1983년 초 세 부분-COSMOS 1402-A, B, C-으로 분리되어 추락한 소련 위성 COSMOS 1402호의 낙하를 추정하기 위한 알골이즘을 개발하였다. 이 인공위성의 궤도에 영향을 미치는 섭동력으로는 지구의 비대칭 중력포텐셜과 지구의 대기 저항에 의한 섭동력이 고려되었고, 고도에 따른 지구의 대기 밀도를 구하기 위해 표준대기모델을 만들었다. COSMOS 1402호의 낙하시 NASA GSFC가 보내온 궤도요소 자료를 이용하여 COSMOS 1402-A와 C의 낙하시각과 낙하지점을 추정하고, 미국무성의 발표와 비교해 보았다. COSMOS 1402-C의 경우 모두 잘 일치함을 보이나 COSMOS 1402-A 의 경우 낙하시각이 1분, 낙하지점은 경위도 각각 2도씩의 오차를 보였다.

• Journal of Astronomy and Space Sciences
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• 제19권2호
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• pp.89-96
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• 2002

General along-track acceleration was estimated in the KOMPSAT-1 orbit determination process. Several sets of the atmospheric drag and solar radiation pressure coefficients were also derived with the different spacecraft area. State vectors in the orbit determination with the different spacecraft area were compared in the time frame. The orbit prediction using the estimated coefficients was performed and compared with the orbit determination results. The orbit prediction with the different general acceleration values was also carried out for the comparison

• International Journal of Naval Architecture and Ocean Engineering
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• 제12권1호
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• pp.468-478
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• 2020

The wave interaction problem with a vertical slotted breakwater, consisting of impermeable upper, lower parts and a permeable middle part, has been studied theoretically. An analytical model was presented for the estimation of reflection and transmission of monochromatic waves by a slotted breakwater. The far-field solution of the wave scattering involving nonlinear porous boundary condition was obtained using eigenfunction expansion method. The empirical formula for drag coefficient in the near-field, representing energy dissipation across the slotted barrier, was determined by curve fitting of the numerical solutions of 2-D channel flow using CFD code StarCCM+. The theoretical model was validated with laboratory experiments for various configurations of a slotted barrier. It showed that the developed analytical model can correctly predict the energy dissipation caused by turbulent eddies due to sudden contraction and expansion of a slotted barrier. The present paper provides a synergetic approach of the analytical and numerical modelling with minimum CPU time, for better estimation of the hydrodynamic performance of slotted breakwater.

• Journal of Astronomy and Space Sciences
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• 제26권1호
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• pp.31-46
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• 2009

An Unscented Kalman Filter (UKF) for estimation of the attitude and rate of a spacecraft using only magnetometer vector measurement is developed. The attitude dynamics used in the estimation is the nonlinear Euler's rotational equation which is augmented with the quaternion kinematics to construct a process model. The filter is designed for small satellite in low Earth orbit, so the disturbance torques include gravity-gradient torque, magnetic disturbance torque, and aerodynamic drag torque. The magnetometer measurements are simulated based on time-varying position of the spacecraft. The filter has been tested not only in the standby mode but also in the detumbling mode. Two types of actuators have been modeled and applied in the simulation. The PD controller is used for the two types of actuators (reaction wheels and thrusters) to detumble the spacecraft. The estimation error converged to within 5 deg for attitude and 0.1 deg/s for rate respectively when the two types of actuators were used. A joint state parameter estimation has been tested and the effect of the process noise covariance on the parameter estimation has been indicated. Also, Monte-Carlo simulations have been performed to test the capability of the filter to converge with the initial conditions sampled from a uniform distribution. Finally, the UKF performance has been compared to that of the EKF and it demonstrates that UKF slightly outperforms EKF. The developed algorithm can be applied to any type of small satellites that are actuated by magnetic torquers, reaction wheels or thrusters with a capability of magnetometer vector measurements for attitude and rate estimation.

• 한국해양공학회지
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• 제36권2호
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• pp.91-100
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• 2022

In general, the effect of roll motion is not considered in the study on maneuverability in calm water. However, for high-speed twin-screw ships such as the DTMB 5415, the coupling effects of roll and other motions should be considered. Therefore, in this study, the estimation of maneuverability using a 4-degree-of-freedom (DOF; surge, sway, roll, yaw) maneuvering mathematical group (MMG) model was conducted for the DTMB 5415, to improve the estimation accuracy of its maneuverability. Furthermore, a study on the change in turning performance according to the fin angle was conducted. To accurately calculate the lift and drag forces generated by the fins, it is necessary to consider the three-dimensional shape of the wing, submerged depth, and effect of interference with the hull. First, a maneuvering simulation model was developed based on the 4-DOF MMG mathematical model, and the lift force and moment generated by the side fins were considered as external force terms. By employing the CFD model, the lift and drag forces generated from the side fins during ship operation were calculated, and the results were adopted as the external force terms of the 4-DOF MMG mathematical model. A 35° turning simulation was conducted by altering the ship's speed and the angle of the side fins. Accordingly, it was confirmed that the MMG simulation model constructed with the lift force of the fins calculated through CFD can sufficiently estimate maneuverability. It was confirmed that the heel angle changes according to the fin angle during steady turning, and the turning performance changes accordingly. In addition, it was verified that the turning performance could be improved by increasing the heel angle in the outward turning direction using the side fin, and that the sway speed of the ship during turning can affect the turning performance. Hence, it is considered necessary to study the effect of the sway speed on the turning performance of a ship during turning.

• 한국해안·해양공학회논문집
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• 제20권6호
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• pp.532-539
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• 2008

권 등(2008)은 수면보다 높은 사각기둥 저항체를 등간격으로 배치하고 항력계수가 일정한 값을 갖는 흐름조건$(Re>10^4)$에서 수리실험을 수행하여 바닥마찰과 형상저항에 의한 흐름저항을 나타내는 상당저항계수로서의 Manning계수 값을 산정하였다. 그리고 힘의 평형방정식으로부터 유도된 이론식에 실험결과를 사용하여 얻어진 경험적 항력상호작용계수를 도입하여 얻은 상당저항계수 식을 제안하였다. 본 연구에서는 이 수리실험을 3차원 전산유체해석 프로그램인 FLOW-3D를 사용하여 수치모의하고 그 결과를 실험결과 및 상당저항계수 식과 비교하여, 그값들이 매우 잘 일치하는 것을 보였다. 이로부터 이론식에 나타나 있는 것처럼 수면보다 높은 저항체가 존재할때 Manning계수가 수심의 2/3승으로 증가한다는 것과 항력상호작용계수가 이격거리의 지배적 영향을 받고 있음을 확인할 수 있었다.

• 한국해안·해양공학회논문집
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• 제23권5호
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• pp.369-382
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• 2011

본 연구에서는 육상구조물에 작용하는 지진해일파력해석을 위하여 Navier-Stokes slover에 기초한 3차원 혼상류수치해석법을 적용하여 검토하였다. 여기서, 대상구조물을 육상저유탱크와 육상가옥으로 하여 호안과 육상구조물간의 이격거리에 따라 육상구조물에 작용하는 지진해일파력을 검토하였다. 또한 육상구조물에 작용하는 지진해일 파력의 추정을 위하여 항력만을 고려한 방법과 항력 및 관성력을 동시에 고려한 방법을 각각 적용하여 얻은 결과와 수치해석결과 및 설계기준에 의한 결과치를 비교 분석하였다. 이로부터 항력 및 관성력을 동시에 고려하여 추정한 지진해일파력이 항력만을 고려한 경우 보다 수치해석결과에 더 근접하는 것을 확인하였다.

• 한국항행학회논문지
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• 제7권2호
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• pp.135-141
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• 2003

최근에는 비행 데이터를 이용하여 사고발생시, 원인 분석에 이용하는 것뿐만 아니라 여러 종류의 다양한 비행 데이터를 기록할 수 있는 QAR을 이용하여 운항 상황이나 항공기 시스템 상태를 다양하고 폭넓게 예견하여 사전 사고 방지 및 운항 성능 개선에 활용하고 있다. 이에, 본 논문에서는 실제 운항 후 QAR에 기록된 비행 데이터를 이용하여 운항 상황에서 발생된 순시적으로 변화하는 양항비를 추정하였다. 실제 B747-400의 비행 데이터가 기록된 QAR 데이터를 일반적인 항공기 운동방정식에 적용하여 양항비 추정 식을 유도하고 시뮬레이션을 통하여 결과를 검증하였다. 이를 통하여 양항비의 변화를 파악할 수 있으며, 과학적이고 경제적인 조종방법 등 체계적인 운항 성능 향상에 유용할 것으로 판단된다.

• 한국해양공학회지
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• 제17권3호
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• pp.7-12
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• 2003

The Navy has tested the holding capacity of many kinds of anchors in order to propose the design chart for the holding capacity of drag-embedment anchors. The design chart is only applicable up to the cable bottom angle 60 when load is raised to the ultimate weight. However, the anchor experiences a significant uplift force when the angle is above 60 in shallow seas. In this paper, the procedure for the estimation of the holding capacity of anchors in mud is proposed. Drag-embedment anchors do not function well when there is a significant uplift component of load in soft seafloor materials, such as mud. Under these loading and seafloor conditions, gravity anchors seems to be more efficient. However, they are too heavy for their holding capacity. Therefore, suction pile (hollow concrete block) is more beneficial to the foundntion of silt protector in shallow sea with mud seafloor materials.

• 한국군사과학기술학회지
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• 제23권1호
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• pp.18-27
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• 2020

In order to estimate the launch point of a high-speed vehicle, predicting the various characteristics of the vehicle's movement, such as drag and thrust, must be preceded by the estimation. To predict the various parameters regarding the vehicle's characteristics, we build the IMM filter specialized in predicting the parameters of the post-launch phase based on flight dynamics. Then we estimate the launch point of the high-speed vehicle using Inverse Dynamics. In addition, we assume the arbitrary error level of the radar for accuracy of the prediction. We organize multiple-dimensioned IMM structures, and figure out the optimal value of parameters by comparing the various IMM structures. After deriving the optimal value of parameters, we verify the launch point estimation error under certain error level.