• 한국소음진동공학회논문집
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• 제22권11호
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• pp.1042-1048
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• 2012

A 2-axis gimbal system is one of main disturbance sources affecting image jitter response of a satellite. The gimbal system comprises azimuth stage and elevation stage, and these pointing mechanism can be rotated by stepping motors about its azimuth and elevation axes simultaneously. Because of the complex and coupled dynamic motion of the gimbal system, its moment of inertia and structural modes can be changed according to the system configuration, and thus the gimbal system generates complicated and non-linear disturbance characteristics. In order to improve the jitter response of a spacecraft, it is an indispensable process to reduce the micro-vibration disturbance level of the antenna system. In the present research, a 2-axis gimbal system was manufactured and then its micro-vibration test was performed in terms of two types of stepping motors(2-phase and 5-phase). The test results show that the disturbance level of the gimbal system can be reduced by replacing the 2-phase stepping motor with the 5-phase one, and the average disturbance attenuation ratio is 56 % in peak level and 48 % in standard deviation level. The experimental results confirm that it is an efficient jitter reduction method to adopt a high-phase stepping motor.

• 한국정보통신학회:학술대회논문집
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• 한국정보통신학회 2013년도 추계학술대회
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• pp.641-642
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• 2013

이 연구는 대형 고해상도 타일드 디스플레이를 활용한 천리안 해양관측위성 영상 가시화 시스템을 구현하였다. 이 시스템은 타일드 디스플레이에서 멀티 터치와 키넥트 모션 제스쳐 인식 인터랙션을 제공하여 한반도 중심의 해양환경 위성 영상을 효과적으로 관측 및 분석 할 수 있도록 도와준다. 방대한 메모리양의 고화질 천리안 해양 관측 위성 영상은 멀티스케일 이미지 로드 기법을 사용하여 다양한 조작에서도 타일드 디스플레이 화면에 매끄럽게 출력되도록 하였다. 이 가시화 시스템은 기본적으로 특정 날짜에 해당하는 시간 단위의 해양관측 위성 영상을 동적으로 화면에 출력되며, 사용자는 멀티 터치나 키넥트 인터랙션을 통하여 영상을 자유롭게 확대 축소하고 상하좌우로 이동하며 다양한 기능 버튼을 누르는 등의 인터랙션을 할 수 있도록 하였다.

• 제어로봇시스템학회논문지
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• 제13권10호
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• pp.962-969
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• 2007

In this paper, an approach is developed for relative state estimation of satellite formation flying. To estimate relative states of two satellites, the Extended Kalman Filter Algorithm is adopted with the relative distance and speed between two satellites and attitude of satellite for measurements. Numerical simulations are conducted under two circumstances. The first one presents both chief and deputy satellites are orbiting a circular reference orbit around a perfectly spherical Earth model with no disturbing acceleration, in which the elementary relative orbital motion is taken into account. In reality, however, the Earth is not a perfect sphere, but rather an oblate spheroid, and both satellites are under the effect of $J_2$ geopotential disturbance, which causes the relative distance between two satellites to be on the gradual increase. A near-Earth orbit decays as a result of atmospheric drag. In order to remove the modeling error, the second scenario incorporates the effect of the $J_2$ geopotential force, and the atmospheric drag, and the eccentricity in satellite orbit are also considered.

• 한국항공우주학회지
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• 제47권11호
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• pp.795-802
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• 2019

본 논문에서는 인공위성의 근접운용에서 발생할 수 있는 위치-자세 결합운동을 정의하고, 이를 듀얼 쿼터니언 기반의 운동방정식을 통해 접근한다. 인공위성의 위치-자세 결합운동은 두 위성의 상대운동에서 목표 지점이 무게 중심이 아닌 위성체 위의 임의의 점에 위치할 때 발생하며, 특히 근거리 운용에서 명확히 보여진다. 듀얼 쿼터니언 기반의 운동방정식은 각속도 상태를 직접 반영하여, 자세의 변화가 위치에 영향을 미치는 위치-자세 결합운동을 간결하게 정의할 수 있다. 여기에서는 위치-자세 결합운동의 해결을 위해 기존의 접근방법과 함께 듀얼 쿼터니언 기반의 운동방정식을 새롭게 제시한다. 수치 시뮬레이션에서는 두 위성의 상대운동에서 위치-자세 결합운동으로 목표 지점에 대한 위치 오차가 발생함을 보이고, 듀얼 쿼터니언 기반의 운동방정식이 이를 해결할 수 있음을 검증한다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
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• pp.91-94
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• 2005

A numerical formula that presents relationship between a point of a satellite image and its ground position is called a sensor model. For precise geolocation of satellite images, we need an error-free sensor model. However, the sensor model based on GOES ephemeris data has some error, in particular after Image Motion Compensation (IMC) mechanism has been turned off. To solve this problem, we investigate three sensor models: Collinearity model, Direct Linear Transform (DLT) model and Orbit-based model. We apply matching between GOES images and global coastline database and use successful results as control points. With control points we improve the initial image geolocation accuracy using the three models. We compare results from three sensor models that are applied to GOES-9 images. As a result, a suitable sensor model for precise geolocation of GOES-9 images is proposed.

• 한국정밀공학회지
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• 제33권10호
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• pp.789-796
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• 2016

The weight of an antenna system pointing satellite on the mobile platform is restricted by the weight limit of the mobile platform. The maximum power of the actuator driving the antenna system is thus limited because a high power actuator needs a heavier weight. Thus, a drive system is designed to have a low torque requirement by reducing the gravitational torque depending on gravity or acceleration of the mobile platform, including vibration, shock, and accelerated motion. To reduce the gravitational torque, the mathematical model of the gravitational torque is preferentially obtained. However, the method to directly estimate the mathematical model in an antenna system has not previously been reported. In this paper, a method is proposed to estimate the gravitational torque as a mathematical model in the antenna system. Additionally, a method is also proposed to calculate the optimal weight of the balancing weight to compensate for the gravitational torque.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 추계학술대회논문집
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• pp.737-742
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• 2002

This reaserch is concern with dynamic modeling of satellite with deployable solar arrays equipped with strain energy hinges(SEH). It is found from experiments that the SEH has the nonlinear dynamic characteristics and complex buckling behavior which is difficult to explain theoretically. In this paper, we use an equivalent one dimensional nonlinear torsional spring for the SEH. Lagrangian equations of motion are used for the derivations.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2003년도 한국우주과학회보 제12권2호
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• pp.42-42
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• 2003

Satellite formation flying is the placing of multiple satellites into nearby orbits to form 'clusters' of satellites. These clusters of satellites usually work together to accomplish a mission. There are many benefits to using multiple satellite as opposed to one large satellites such as increasing productivity. reducing mission and launch cost. Hill's equations are useful to describe the relative motion of two satellites in formation flying, however. the disturbance forces acting on satellites is not considered in that equations. In this paper, a method for maintaining the relative distance between satellites is presented, which used mean orbital elements considering J2 perturbation. Control design process is also presented for minimizing total fuel consumption.

• Journal of Astronomy and Space Sciences
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• 제16권2호
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• pp.159-166
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• 1999

As the spatial resolution of remote sensing satellites becomes higher, very accurate determination of the position of a LEO (Low Earth Orbit) satellite is demanding more than ever. Non-symmetric Earth gravity is the major perturbation force to LEO satellites. Since the orbit propagation is performed in the celestial frame while Earth gravity is defined in the terrestrial frame, it is required to convert the coordinates of the satellite from one to the other accurately. Unless the coordinate conversion between the two frames is performed accurately the orbit propagation calculates incorrect Earth gravitational force at a specific time instant, and hence, causes errors in orbit prediction. The coordinate conversion between the two frames involves precession, nutation, Earth rotation and polar motion. Among these factors, unpredictability and uncertainty of Earth rotation, called UTI-UTC, is the largest error source. In this paper, the effect of UTI-UTC on the accuracy of the LEO propagation is introduced, tested and analzed. Considering the maximum unpredictability of UTI-UTC, 0.9 seconds, the meaningful order of non-spherical Earth harmonic functions is derived.

• 한국위성정보통신학회논문지
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• 제8권4호
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• pp.26-29
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• 2013

군중의 혼잡한 정도를 추정하기 위해서는 텍스처 기반의 방법을 이용하거나 움직임을 검출하여 혼잡한 정도를 추정한다. 본 논문에서는 이 두 가지를 혼합한 방법을 제안한다. 또한 ROI 영역을 설정하여 영역내의 혼잡한 정도의 기준을 명확히 하였으며, 특징 정규화를 통하여 카메라 각도 변화의 오차를 줄이고자 하였다. 이 시스템을 DSP에 탑재하여 임베디드 기반의 실시간 시스템을 구축하였다.