• 대한토목학회논문집
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• 제29권1D호
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• pp.161-166
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• 2009

고해상도, 고정밀도의 초고차항 전 지구 중력장모델은 현대측지학, 지구물리학, 지구동력학 및 해양학 등 다양한 과학 분야의 발전에 있어서 매우 중요한 의미를 가지고 있다. 본 연구에서는 최근 미국 국가지형정보국(NGA)에서 발표한 초고차항 중력장모델 EGM2008을 소개하고, 초고차항 중력장모델 개발에 있어서의 문제점과 연구현황을 살펴보았으며, 남한지역에서 의 정확도를 분석하였다. 우선 EGM2008을 기존의 전 지구 중력장모델 EGM96 및 한국의 고정밀 합성 지오이드모델인 KGEOID08과 모델 간 정밀도를 비교하였고, 위성측지기준점의 타원체고와 정표고를 이용해 절대 정확도를 평가하였다. 전반적으로 EGM2008은 KGEOID08과 비슷한 높은 정확도를 보였으며, 이는 향후 지역적 지오이드의 개발 또는 전 지구적인 중력장 분석에 큰 도움을 줄 것으로 판단된다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1991년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 22-24 Oct. 1991
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• pp.425-430
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• 1991

For satellite orbit determination, a satellite (K-3H) which is affected by the earth's gravitational field and the earth's atmospheric drag, the sun, and the moon is chosen as a dynamic model. The state vector include orbit parameters, uncertain parameters associated with perturbations and tracking stations. These perturbations include gravitational constant, atmospheric drag, and jonal harmonics due to the earth nonsphericity. Early orbit was obtained with given the predicted orbital parameter of the satellite. And orbit determination, which is applied to Extended Kalman Filter(EKF) for real time implementation , use the observation data which is given by satellite tracking radar system and then orbit estimation is accomplished. As a result, extended sequential estimation algorithm has a fast convergence and also indicate effectiveness for real time operation.

• Steel and Composite Structures
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• 제46권5호
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• pp.669-672
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• 2023

In this research, the researcher has examined the factors affecting the movement of the soccer ball and will show that the effects such as air resistance, altitude above sea level, wind, air pressure, air temperature, air humidity, rotation of the earth, changes in the earth's gravitational acceleration in different areas. It, the geographical length and latitude of the launch point, the change of gravitational acceleration with height, the change of pressure with height, the change of temperature with height and also the initial spin (Magnus effect) affect the movement of projectiles (especially soccer ball). We modelled th ball based on shell element and derive the motion equations by energy method. Finally, using numerical solution, the wave of the ball is studied. The influences of various parameters are investigated on wave propagation of the ball. Therefore, in short, it can be said that the main factors that play a major role in the lateral deviation of the hit ball are the initial spin of the ball and the wind.

• 한국측량학회지
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• 제38권2호
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• pp.153-163
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• 2020

After launching the GOCE (Gravity Field and Steady-State Ocean Circulation Explorer) which obtains high-frequency gravity signal using a gravity gradiometer, many research institutes are concentrating on the development of GGM (Global Geopotential Model) based on GOCE data and evaluating its precision. The precision of some GGMs was also evaluated in Korea. However, some studies dealt with GGMs constructed based on initial GOCE data or others applied a part of GNSS (Global Navigation Satellite System) / Leveling data on UCPs (Unified Control Points) for the precision evaluation. Now, GGMs which have a higher degree than EGM2008 (Earth Gravitational Model 2008) are available and UCPs were fully established at the end of 2019. Thus, EIGEN-6C4 (European Improved Gravity Field of the Earth by New techniques - 6C4), GECO (GOCE and EGM2008 Combined model), XGM2016 (Experimental Gravity Field Model 2016), SGG-UGM-1, XGM2019e_2159 were collected with EGM2008, and their precisions were assessed based on the GNSS/Leveling data on UCPs. Among GGMs, it was found that XGM2019e_2159 showed the minimum difference compared to a total of 5,313 points of GNSS/Leveling data. It is about a 1.5cm and 0.6cm level of improvement compare to EGM2008 and EIGEN-6C4. Especially, the local biases in the northern part of Gyeonggi-do, Jeju island shown in the EGM2008 was removed, so that both mean and standard deviation of the difference of XGM2019e_2159 to the GNSS/Leveling are homogeneous regardless of region (mountainous or plain area). NGA (National Geospatial-Intelligence Agency) is currently in progress in developing EGM2020 and XGM2019e_2159 is the experimentally published model of EGM2020. Therefore, it is expected that the improved GGM will be available shortly so that it is necessary to verify the precision of new GGMs consistently.

• 제어로봇시스템학회논문지
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• 제13권1호
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• pp.72-78
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• 2007

Determination of the local vertical is not trivial for a moving vehicle and in general will require corrections for the Earth geophysical deflection. The vehicle's local vertical can be estimated by INS integration with initial alignment in SDINS(Strap Down INS) system. In general, the INS has drift error and it cause the performance degradation. In order to compensate the drift error, GPS/INS augmented system is widely used. And in the event that GPS is denied or unavailable, celestial navigation using star tracker can be a backup navigation system especially for the military purpose. In this celestial navigation system, the vehicle's position determination can be achieved using more than two star trackers, and the accuracy of position highly depends on accuracy of local vertical direction. Modern tilt sensors or accelerometers are sensitive to the direction of gravity to arc second(or better) precision. The local gravity provides the direction orthogonal to the geoid and, appropriately corrected, toward the center of the Earth. In this paper the relationship between direction of center of the Earth and actual gravity direction caused by geophysical deflection was analyzed by using precision orbit simulation program embedded the JGM-3 geoid model. And the result was verified and evaluated with mathematical gravity vector model derived from gravitational potential of the Earth. And also for application purpose, the performance variation of pure INS navigation system was analyzed by applying precise gravity model.

• International Journal of Aeronautical and Space Sciences
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• 제4권1호
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• pp.99-109
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• 2003

Attitude control law synthesis for the three-axis attitude maneuver of a flexible spacecraft model is presented in this study. The basic idea is motivated by previous works for the extension into a more general case. The new case includes gravitational gradient torque which has significant effect on a wide range of low earth orbit missions. As the first step, the fully nonlinear dynamic equations of motion are derived including gravitational gradient. The control law design based upon the Lyapunov approach is attempted. The Lyapunov function consists of a weighted combination of system kinetic and potential energy. Then, a set of stabilizing control law is derived from the basic Lyapunov stability theory. The new control law is therefore in a general form partially validating the previous work in some sense.

• Journal of Astronomy and Space Sciences
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• 제27권2호
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• pp.97-106
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• 2010

To prepare for a Korean lunar orbiter mission, a precise lunar orbit propagator; Yonsei precise lunar orbit propagator (YSPLOP) is developed. In the propagator, accelerations due to the Moon's non-spherical gravity, the point masses of the Earth, Moon, Sun, Mars, Jupiter and also, solar radiation pressures can be included. The developed propagator's performance is validated and propagation errors between YSPOLP and STK/Astrogator are found to have about maximum 4-m, in along-track direction during 30 days (Earth's time) of propagation. Also, it is found that the lifetime of a lunar polar orbiter is strongly affected by the different degrees and orders of the lunar gravity model, by a third body's gravitational attractions (especially the Earth), and by the different orbital inclinations. The reliable lifetime of circular lunar polar orbiter at about 100 km altitude is estimated to have about 160 days (Earth's time). However, to estimate the reasonable lifetime of circular lunar polar orbiter at about 100 km altitude, it is strongly recommended to consider at least $50\;{\times}\;50$ degrees and orders of the lunar gravity field. The results provided in this paper are expected to make further progress in the design fields of Korea's lunar orbiter missions.

• 한국측량학회지
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• 제27권1호
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• pp.713-722
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• 2009

중력측량은 지구중력장 결정, 지각의 수직운동, 지오이드면의 변화, 해수면변화, 기후변화 등 측지학적, 지구동력학적 연구의 기초이다. 국토지리정보원에서는 최근 들어 FG-5 절대중력계를 도입하여 절대중력 기준망의 구축을 위한 틀을 마련하였고 다차원 다기능 기준점인 통합기준점을 전국에 약 1,200점을 설치하여 상대중력측량을 실시함으로써 한국의 고정밀 지오이드모델의 개발에 큰 기여를 할 것으로 판단된다. 본 연구에서는 상대중력측량의 기본적인 이론 및 방법을 상세하게 설명하였고, 최신 상대중력계 Scintrex CG-5를 이용하여 총 21점에 대한 상대중력측량을 수행하였으며, 자유망조정 및 무게제한 망조정 방법을 이용하여 중력성과를 계산 및 비교 분석하였다. 결과, 두 가지 방법 모두 높은 정밀도의 중력성과 계산이 가능하지만 자유망조정이 무게제한 망조정 방법에 비해 상대적인 우위를 보여주는 것으로 나타났다.

• Journal of Astronomy and Space Sciences
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• 제14권1호
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• pp.136-141
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• 1997

임의의 순간 인공위성의 위치와 속도를 정밀하게 계산하기 위해서는 섭동력을 일으키는 우주공간의 환경을 정확하게 이해하고 분석하여 정량화함으로써 섭동력에 대한 수리적인 모형을 만들어야 한다. 이들 우주환경모델에 의해서 인공위성이 받는 총가속도는 2계 미분방정식으로 표현되며, 이 방정식을 두 번 적분함으로써 원하는 시각에서의 인공위성의 위치와 속도를 얻는 코웰방법을 사용하여 궤도예측 알고리즘을 완성하였다. 정지위성의 궤도에 미치는 주요한 섭동력으로는 지구의 비대칭 중력 포텐셜에 의한 섭동력, 태양과 달의 중력에 의한 섭동력, 태양의 복사압에 의한 섭동력들이 있는데, 그것들의 정밀성을 최대한 높이기 위해 spherical harmonic 계수들을 40 $\times$ 40까지 적용할 수 있도록 했으며, JPL DE 403 ephemeris의 polynomial 내삽을 통해 지구로부터 태양과 달까지의 거리를 정밀하게 계산하였다. 그리고 수치적분 방법으로는 적분간격을 자동으로 조절하는 8계 Runge-Kutta single step 방법을 사용하였다.

• 한국콘텐츠학회논문지
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• 제8권9호
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• pp.274-280
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• 2008

최근 새로운 초 고차 지구중력장 모형(EGM2008)의 개발로 인하여 중력관련 응용분야의 향상이 기대되고 있다. 본 연구는 지구중력장모형(EGM)으로부터 남한지역에 대한 고도이상(height anomalies)를 산정하고 지역별 지오이드고의 특성을 분석하였다. 이를 위하여 7가지 지구중력장모형(EGM2008<2,190>, EGM2008<360>, EGM96, EIGEN-GL04C, EIGEN-CG03C, EIGEN-GL04S1 및 ITG- Grace02S)을 선정하였다. GPS 관측이 수행된 수준점 50개 측점을 점검점으로 선정하여 GPS/Levelling, 국립해양조사원(NORI)의 NORI-05 모형 및 7가지 EGMs에 의한 지오이드 고를 비교 분석하였다. 또한, 남한지역의 경 위도 $1^{\circ}\times1^{\circ}$ 6개 육상부 및 4개 해상부에 대한 30"$\times$30" 격자점을 대상으로 EGM2008 모델에 의한 지오이드고를 NORI-05 모델 및 6가지 EGMs로 부터 구한 결과와 비교하였다. 연구결과, NGA(National Geospatial Intelligence Agency)의 EGM2008(2,190) 모형이 GPS/Levelling 결과에 가장 근접함을 보였다.