• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.8
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• pp.695-701
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• 2016

Spacecraft propulsion system is a kind of rocket engine that has been developed from the end of 1950s for attitude control and orbit maintenance of satellite. Since the spacecraft propulsion system has to be used for a relatively long time, therefore, stability of propellant and life of thruster could be very important factor for propulsion system design. Recently, green propellant propulsion and all electrical propulsion system have became very important issue, and we also need a development according to well organized plan. In this paper, we will introduce the development status, key technologies and development prospect of spacecraft propulsion system.

• Journal of Advanced Navigation Technology
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• v.21 no.6
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• pp.579-584
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• 2017

SBAS is a satellite based navigation correction system that provides correction information and integrity information of GNSS signal through geostationary satellite based on analysis of GNSS signal in ground station. KASS, a Korean SBAS, is aiming at the APV-1 class SoL service in 2022. Sufficient ground and flight tests must be performed in advance to provide SoL services. However, since KASS, the Korean SBAS, has not yet been added in Korea, specific detailed evaluation items are not presented. EGNOS, which is expected to be the most compatible with KASS and is being serviced after its development, has already been evaluated. In this paper, we analyze the regulations applied to EGNOS construction and analyze the criteria of ground and flight test evaluation items required for flight testing, which is expected to be referenced to the flight inspection process in the future.

• Journal of Astronomy and Space Sciences
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• v.18 no.2
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• pp.163-173
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• 2001

In this paper, space radiation environment and single event effect(SEE) have been analyzed for the KOMPSAT-2 operational orbit. As spacecraft external and internal space environment, trapped proton, SEP(solar energetic particle) and GCR(galactic cosmic ray) high energy Protons and heavy ions spectrums are analyzed. Finally, SEU and SEL rate prediction has been performed for the Intel 80386 microprocessor CPU that is planned to be used in the KOMPSAT-2. As the estimation results, under nominal operational condition, it is predicted that trapped proton and high energetic proton induced SBU effect will not occur. But, it is predicted that heavy ion induced SEU can occur several times during KOMPSAT-2 3-year mission operation. KOMPSAT-2 has been implementing system level design to mitigate SEU occurrence using processor CPU error detection function of the on-board flight software.

• 한국지형공간정보학회:학술대회논문집
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• 2002.03a
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• pp.145-149
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• 2002

CORONA는 미국이 1960년에서 1972년까지 냉전시대 관심지역에 대한 첩보영상을 취득하기 위하여 운영한 영상취득시스템으로 1995년 일반에 자료가 공개됨에 따라 과거의 고해상도 영상자료를 이용할 수 있는 길이 열리게 되었다. 그러나 현재까지 CORONA 영상처리를 위한 모듈을 제공하는 원격탐측 소프트웨어가 개발되어 있지 않기 때문에 CORONA 영상을 이용하여 수치표고모형이나 정사영상을 제작하기 위해서는 적절한 모델링 방법이 필요하다. CORONA 영상은 파노라마 영상으로 필름 가장자리로 갈수록 왜곡이 많이 생기며 사진기 지표가 없고 위성의 궤도와 위치, 자세, 속도, IMC(Image Motion Compensation)에 대한 자세한 자료를 제공하지 않는 문제점이 있다. 따라서 본 논문에서는 지형복원을 위하여 지상기준점을 이용하는 2가지 모델링 방법을 이용하였다. 첫 번째는 파노라마 왜곡과 촬영 비행체 이동에 의한 왜곡, IMC에 의한 왜곡을 보정하는 모형식을 구성하여 이용하였으며, 두 번째는 위성과 센서에 대한 정보를 필요로 하지 않는 다항식비례모형(RFM; Rational Function Model)을 이용하였다. 대상지역은 서울지역의 입체영상으로 대략 $33km{\times}26km$ 지역이다. 영상은 지상해상도 약 2.7m로 스캐닝하였고 1:1000 수치지도를 통해 20개의 기준점과 36개의 검사점을 관측하였다. 검사점의 위치정확도를 평가해 본 결과 첫 번째 방법은 수평방향으로 평균 3.9m(X), 2.8m(Y)의 오차를 보였으며 표고의 경우 4.2m의 오차를 보여주었다. 두 번째 방법은 수평방향으로 평균 3.2m(X), 2.8m(Y)의 오차를 보였으며 표고의 경우 5.5m의 오차를 보여주었다. 지형복원 정확도를 검증하기 위하여 첫 번째 방법을 이용하여 대상지역 중 일부인 서울 남산지역에 대해 정사영상과 10m간격의 DEM을 제작하였으며 1:1000 수치지도를 통해 제작된 DEM과 비교한 결과 총 43990개 격자점의 표고 차이는 평균 5.98m였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.9
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• pp.799-804
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• 2015

The purpose of this study is to analyse the dynamic disturbances(disturbed forces and disturbed torques) due to attitude control thruster's plume impingement on the solar arrays. To produce database of the dynamic disturbances a sweep analysis was done, in which the two parameters are used; the distance between the thruster and solar arrays and the thruster tilt angle. Based on the database, a third order polynomial approximation is computed to represent the characteristics of the disturbed forces and torques. The final results are the coefficients of the approximation for each solar array angle position. These results as input data are used to optimize the configuration of the attitude control thrusters. This analysis is appled to the two candidate solar arrays for Geo-Kompsat-2 satellite and the results of the disturbed forces and disturbed torques are compared and analysed.

• Journal of Korean Society for Geospatial Information Science
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• v.22 no.1
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• pp.47-54
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• 2014

Precise Point Positioning (PPP) algorithms using GPS code pseudo-range measurements were developed and their accuracy was validated for the purpose of implementing them on a portable device. The group delay, relativistic effect, and satellite-antenna phase center offset models were applied as fundamental corrections for PPP. GPS satellite orbit and clock offsets were taken from the International GNSS Service official products which were interpolated using the best available algorithms. Tropospheric and ionospheric delays were obtained by applying mapping functions to the outputs from scientific GPS data processing software and Global Ionosphere Maps, respectively. When the developed algorithms were tested for four days of data, the horizontal and vertical positioning accuracies were 0.8-1.6 and 1.6-2.2 meters, respectively. This level of performance is comparable to that of Differential GPS, and further improvements and fine-tuning of this suite of PPP algorithms and its implementation at a portable device should be utilized in a variety of surveying and Location-Based Service applications.

• Journal of Korean Society for Geospatial Information Science
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• v.3 no.2 s.6
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• pp.15-28
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• 1995

The GPS positioning involves not only 'natural' errors associated with the satellites position errors, refraction of EM wave in the ionosphere, etc., but also 'artificial' errors associated with the operation of S/A (Selective Availability). In this paper, we present the principles, accuracies and applicabilities of our personal DGPS method, which employs the position-correction method on the GPS positionings data collected at the reference and the remote sites. The essential requirement of our DGPS method is that two GPS receivers should utilize the identical Navstar satellites at the same time. The positioning error (1 drms) of the stand-alone GPS is of an order of a few tens meters, while that of horizontal position by our DGPS method is about 1m and that of vertical position is about 2m We applied out DGPS technique in positioning moving objects, and obtained satisfactory results in tracking the trajectories of a car on the road and the those of drifters in the sea.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.21 no.7
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• pp.842-849
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• 2010

This paper deals with a TT&C circularly polarized turnstile antenna for LEO satellites. The turnstile antenna consists of radiator for radiating power to free-space and power divider for generating circularly polarized wave. we presents a radiator to tolerate in space environments and a power divider to provide flat phase difference at wide bandwidth. The bandwidth of the proposed antenna covers the frequency bands of up- and down-link. The antenna shows wide beamwidth and enhanced axial ratio for unfavorable space environments.

• Journal of the Korea Institute of Information and Communication Engineering
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• v.19 no.7
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• pp.1539-1545
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• 2015

GPS (global positioning system) is a popular system that provides location information by measuring arrival time difference at the receiver between several GPS satellite signals. GPS is widely used in commercial area as well as military systems. Reliable GPS signal reception is more important in the military systems. However, since the carrier frequencies of the GPS signals are well known, the GPS receivers are vulnerable to intentional jamming attacks. To remove jammers but maintain GPS signals at the received signals, a popular technique is an adaptive beam steering method based on array antenna. Among adaptive beam steering techniques, this paper considers MVDR (minimum variance distortionless response) algorithm, and proposes a new adaptive technique that preserves the received signals at desired direction, but removes the jamming signals adaptively. The performance of the proposed method is verified through computer simulation.

• Korean Journal of Remote Sensing
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• v.31 no.6
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• pp.583-598
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• 2015

This paper presents derivation of background temperature from geostationary satellite and its validation based on ground measurements and Geographic Information System (GIS) for future use in weather and surface heat variability. This study only focuses on daily and monthly brightness temperature in 2012. From the analysis of COMS Meteorological Data Processing System (CMDPS) data, we have found an error in cloud distribution of model, which used as a background temperature field, and in examining the spatial homogeneity. Excessive cloudy pixels were reconstructed by statistical reanalysis based on consistency of temperature measurement. The derived Brightness temperature has correlation of 0.95, bias of 0.66 K and RMSE of 4.88 K with ground station measurements. The relation between brightness temperature and both elevation and vegetated land cover were highly anti-correlated during warm season and daytime, but marginally correlated during cold season and nighttime. This result suggests that time varying emissivity data is required to derive land surface temperature.