• 한국우주과학회:학술대회논문집(한국우주과학회보)
• /
• 한국우주과학회 2003년도 한국우주과학회보 제12권2호
• /
• pp.41-41
• /
• 2003

Satellite formation flying is currently an active area of research in the aerospace engineering. There are many categories for this research such as the determination of initial conditions, formation keeping, configuration and reconfiguration. In this study, a tracking controller using sliding mode techniques is designed to control a satellite for the satellite formation flying. In general, Hill's equations are used to describe the relative motion of the follower satellite with respect to the leader satellite. But, the modified Hill's equations considering J2 perturbation were used for the design of sliding mode controller. Sliding mode control law causes the chattering phenomenon because it is a discontinuous control. Dead-zone was used to avoid the chattering. The Extended Kalman filter was applied to estimate the state vector based on the measurements of relative distance and velocity between two satellites.

• 대기
• /
• 제22권1호
• /
• pp.1-12
• /
• 2012

The Atmospheric motion vectors (AMVs) derived using infrared (IR) channel imagery of geostationary satellites have been utilized widely for real-time weather analysis and data assimilation into global numerical prediction model. As the horizontal resolution of sensors on-board satellites gets higher, it becomes possible to identify atmospheric motions induced by convective clouds ($meso-{\beta}$ and $meso-{\gamma}$ scales). The National Institute of Meteorological Research (NIMR) developed the high resolution visible (HRV) AMV algorithm to detect mesoscale atmospheric motions including ageostrophic flows. To retrieve atmospheric motions smaller than $meso-{\beta}$ scale effectively, the target size is reduced and the visible channel imagery of geostationary satellite with 1 km resolution is used. For the accurate AMVs, optimal conditions are decided by investigating sensitivity of algorithm to target selection and correction method of height assignment. The results show that the optimal conditions are target size of 32 km ${\times}$ 32 km, the grid interval as same as target size, and the optimal target selection method. The HRV AMVs derived with these conditions depict more effectively tropical cyclone OMAIS than IR AMVs and the mean speed of HRV AMVs in OMAIS is slightly faster than that of IR AMVs. Optimized mesoscale AMVs are derived for 6 months (Feb. 2010-Jun. 2010) and validated with radiosonde observations, which indicates NIMR's HRV AMV algorithm can retrieve successfully mesoscale atmospheric motions.

• Journal of Power Electronics
• /
• 제6권1호
• /
• pp.18-28
• /
• 2006

The Electric Power Subsystem (EPS) is one of the most critical systems on any satellite because nearly every subsystem requires power. This makes the choice of power systems the most important task facing satellite designers. The main purpose of the Satellite EPS is to provide continuous, regulated and conditioned power to all the satellite subsystems. It has to withstand radiation, thermal cycling and vacuums in hostile space environments, as well as subsystem degradation over time. The EPS power characteristics are determined by both the parameters of the system itself and by the satellite orbit. After satellite separation from the launch vehicle (LV) to its orbit, in almost all situations, the satellite subsystems (attitude determination and control, communication and onboard computer and data handling (OBC&DH)), take their needed power from a storage battery (SB) and solar arrays (SA) besides the consumed power in the EPS management device. At this point (separation point, detumbling mode), the satellite's angular motion is high and the orientation of the solar arrays, with respect to the Sun, will change in a non-uniform way, so the amount of power generated by the solar arrays will be affected. The objective of this research is to select satellite EPS component types, to estimate solar array illumination parameters and to determine the efficiency of solar arrays during both detumbling and normal operation modes.

• 제어로봇시스템학회:학술대회논문집
• /
• 제어로봇시스템학회 2004년도 ICCAS
• /
• pp.413-416
• /
• 2004

The tracking antenna system must be always pointed to a satellite for data link among moving vehicles. Especially, for an antenna mounted on a moving vehicle, it needs the stabilized the antenna system. So, software and hardware, signal processing of motion detection sensors, real-time processing of vehicle dynamics, trajectory estimation of satellite, antenna servo mechanism, and tracking algorithm, are unified in the antenna system. The purpose of this paper is to design the embedded tracking antenna control system for satellite communication. The embedded OS(Operating System) based stabilization and tracking algorithm was implemented. The performance of the designed embedded control system was verified by the real satellite communication test.

• 한국영어학회지:영어학
• /
• 제3권3호
• /
• pp.341-373
• /
• 2003

A cross-linguistic examination of motion constructions reveals that the nature of the special property of English motion verbs that Tenny (1995) discussed-namely, why English can freely append locational delimiters to manner-of-motion verbs, as in Bill swam/rowed/canoed to the end of the lake -resides not in the verbs but in the semantic structure of the prepositions that denote transition from motion to end location. It is further argued that the differentiation of bounded paths from non-bounded Ones provides a clear-cut basis on which to distinguish motion constructions from resultative constructions. This proposal provides an alternative to the analyses of resultative constructions by Wechsler (1997) and Rappaport Hovav and Levin (2001).

• 대한원격탐사학회:학술대회논문집
• /
• 대한원격탐사학회 2003년도 Proceedings of ACRS 2003 ISRS
• /
• pp.825-827
• /
• 2003

Multi-Spectral Camera(MSC) is a payload on the KOMPSAT-2 satellite to perform the earth remote sensing. The instrument images the earth using a push-broom motion with a swath width of 15 km and a ground sample distance (GSD) of 1 m over the entire field of view (FOV) at altitude 685 Km. The instrument is designed to have an on-orbit operation duty cycle of 20% over the mission lifetime of 3 years with the functions of programmable gain/ offset and on-board image data compression/storage. The MSC instrument has one(1) channel for panchromatic imaging and four(4) channel for multi-spectral imaging covering the spectral range from 450nm to 900nm using TDI CCD Focal Plane Array (FPA). In this paper, the architecture and function of MSC hardware including electrical interface and the operation concept which have been established based on the mission requirements are described. And the design and the preparation of MSC system operation are analyzed and discussed.

• Journal of Astronomy and Space Sciences
• /
• 제24권4호
• /
• pp.315-326
• /
• 2007

최근에 제안된, 이웃하는 타원 궤도의 상대운동에 대한 몇 가지 양함수형 해를 분석하였다. 이 해를 이용한 상대운동 결과를 일반 선형화 운동 방정식의 해석적 해와 비교했다. 수치계산 결과를 위한 초기 조건은 Hill-Clohessy-Wiltshire(HCW) 운동방정식에 의한 해의 역함수로 구했다. 기준 궤도의 차이에도 불구하고 상대적으로 작은 이심률의 궤도 일 경우에는 타원 상대운동 궤도와 원 상대운동 궤도의 결과는 근접했다. 주위성의 궤도가 상대적으로 큰 이심률을 가질 경우에는, 기본 궤도로 원 궤도를 이용하는 HCW 운동방정식은 다른 타원 상대운동 궤도 방정식의 해보다 상대적으로 큰 오차를 갖는다.

• 전자통신동향분석
• /
• 제34권3호
• /
• pp.65-74
• /
• 2019

The Earth Stations in Motion (ESIM) system is one of the most modern satellite systems, providing high-speed and high-capacity communication with mobility. To facilitate ESIM in the Ka band, operational, technical, and regulatory studies have been conducted in the International Telecommunication Union Radiocommunication Sector (ITU-R) since 2016. In this paper, we introduce the ESIM and discuss its system characteristics and frequency sharing issues with respect to existing services in the same frequency bands. Taking into account current standardization activity in the ITU-R, we provide the latest study results of ESIM operation based on the Conference Preparatory Meeting Report for the World Radiocommunication Conference-19.

• 항공우주시스템공학회지
• /
• 제1권3호
• /
• pp.32-36
• /
• 2007

When the reaction wheel rotates, the disturbance occurs mainly due to the mass imbalance. It is necessary to predict the effect of disturbance on the attitude stability of the satellite. The disturbance forces and torques are identified and the attitude jitter of the satellite is analyzed depending on the configuration of the wheels. On the analysis the equation of the satellite motion is combined with the translational and rotational dynamics of the wheels. The accuracy of analysis is verified by simulation of STSAT-3 satellite.

• Journal of Astronomy and Space Sciences
• /
• 제6권2호
• /
• pp.91-100
• /
• 1989

정지 위성 궤도의 평균 궤도 요소를 비 특이점 궤도 요소 항으로 연구하였다. 실제 위성의 위치는 평균 궤도로부터 단주기 섭동 만큼 위성 위치가 진동하는데, 그 진동의 진폭은 1800m 이하이다. $e_c$ 와 $e_s$의 평균값도 얻었다.