• 산업경영시스템학회지
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• 제30권3호
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• pp.165-173
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• 2007

A space launch vehicle system represents a typical example of large-scale multi-disciplinary systems, consisting of subsystems such as mechanical structure, electronics, control, telecommunication, propulsion, material engineering etc. A lot of cost is required to develop the launch vehicle system. A precise planning of R&D cost is very essential to make a success of the launch vehicle development program. Especially in the early development phase of a new space launch vehicle system, cost estimation techniques and analogy from past similar development data are very useful methods to estimate a development cost of the launch vehicle system. Now Korea Aerospace Research Institute is in charge of the KSLV-I (Korea Space Launch Vehicle-I) Program that is a part of Korea National Space program. KSLV-I Program is a national undertaking to develop launch capabilities to deliver science satellites of a 100kg-class into a low earth orbit. It is hereafter, going to plan to develop a new korean space launch vehicle. In this paper, first the development costs of well-known launch vehicles in the world are presented to provide a reference to make a development plan of a new launch vehicle. Second this paper introduces the present status of cost estimation applications at NASA. Finally this paper presents the results from application of a TRANSCOST, a parametric cost model, to derive a cost estimate of a new launch vehicle development, as an example.

• 대한공간정보학회지
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• 제22권1호
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• pp.47-54
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• 2014

휴대용 단말에 간편하게 구현 가능하도록 GPS의 코드의사거리 관측치 기반의 정밀단독측위(PPP; Precise Point Positioning) 알고리즘을 개발하고 그 성능을 검증하였다. PPP에 필요한 기본 모델로 그룹 딜레이, 상대성 효과, 위성안테나 위상중심오프셋 보정모델을 적용하였다. 위성 궤도와 시계오차는 IGS(International GNSS Service) 공식 산출물에 최적의 알고리즘을 통해 보간하고, 대류권과 전리층 오차는 각각 과학기술용 GPS 자료처리 소프트웨어로 산출한 참값과 GIM(Global Ionosphere Model)을 사상함수를 적용해 시선방향 오차로 변환해 적용하였다. 개발된 알고리즘을 4일간 테스트한 결과 수평오차는 0.8~1.6m, 수직오차는 1.6~2.2m 수준으로 나타났다. 이는 DGPS 측위결과와 유사한 성능으로 향후 PPP 알고리즘의 추가개선이 이루어질 경우 다양한 측량 및 위치기반서비스 분야에 활용 가능할 것으로 기대된다.

• 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.

• 천문학회보
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• 제41권1호
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• pp.47.3-48
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• 2016

The zodiacal light (ZL), combination of the sunlight scattered by and the infrared light emitted by the interplanetary dust (IPD) particles, changes with time due to the asymmetric distribution of the particles with respect to the Earth's orbit. Especially, the variation of the ZL brightness toward the ecliptic poles are useful to probe the properties of the global distribution of the IPD because we can evade the effect of the small scale structures, such as the asteroidal dust bands. The ecliptic poles are frequently visited by the infrared (IR) space telescopes owing to their sun-synchronous orbits or for specific purposes. We collect and analyze the observations toward the ecliptic poles by COBE/DIRBE, AKARI, and MIRIS, covering the wavelengths from about 1 to $25{\mu}m$. The observed seasonal variations of the ZL are modeled with a simple IPD cloud model to derive cloud parameters. The parameters are compared with those of the empirical cloud models by Kelsall et al. (1998) and Kondo et al. (2016), and the discrepancies are discussed.

• 천문학회보
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• 제41권1호
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• pp.41.2-41.2
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• 2016

The follow-up BVRI photometric observations of NSVS 1461538, which was discovered as an $Algol/{\beta}$ Lyr eclipsing variable by Hoffman, Harrison & McNamara (2009), were performed for three years from 2011 to 2013 by using the 61-cm telescope and CCD cameras of Sobaeksan Optical Astronomy Observatory (SOAO). New light curves have deep depths both of the primary and secondary eclipses, rounded shapes outside eclipses and a strong O'Connell effect, indicating that NSVS 1461538 is a typical W UMa close binary system rather than an $Algol/{\beta}$ Lyr type binary star. A period study with all the timings shows that the orbital period may vary in a sinusoidal way with a period of about 5.6 yr and a small semi-amplitude of about 0.008 d. The cyclical period variation was interpreted as a light-time effect due to a tertiary body with a minimum mass of $0.66M{\odot}$. The first photometric solution with the Wilson-Devinney binary model shows that the system is a W-subtype contact binary with the mass ratio ($q=m_c/m_h$) of 3.46, orbit inclination of 85.6 deg and fill-out factor of 30%. From the existing empirical relationship between parameters, the absolute dimension was estimated. The masses and radii of the component stars are $0.28M{\odot}$ and $0.71R{\odot}$ for the less massive but hotter primary star, respectively, and $0.96M{\odot}$ and $1.21R{\odot}$ for the more massive secondary, respectively. Possible evolution of the system is discussed in the mass-radius and the mass-luminosity planes.

• Journal of Power Electronics
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• 제11권6호
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• pp.870-879
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• 2011

Regulated peak power tracking (RPPT) systems such as the series structure and the series-parallel structures are commonly used in satellite space power systems. However, these structures process the solar array power or the battery power to the load through two cascaded regulators during one orbit cycle, which reduces the energy transfer efficiency. Also the battery charging time is increased due to placement of converter between the battery and the solar array. In this paper a parallel structure has been proposed which can improve the energy transfer efficiency and the battery charging time for satellite space power RPPT systems. An analogue controller is used to control all of the required functions, such as load voltage regulation and solar array stabilization with maximum power point tracking (MPPT). In order to compare the system efficiency and the battery charging efficiency of the proposed structure with those of a series (conventional) structure and a simplified series-parallel structure, simulations are performed and the results are analyzed using a loss analysis model. The proposed structure charges the battery more quickly when compared to the other two structures. Also the efficiency of the proposed structure has been improved under different modes of solar array operation when compared with the other two structures. To verify the system, experiments are carried out under different modes of solar array operation, including PPT charge, battery discharge, and eclipse and trickle charge.

• 천문학회보
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• 제37권2호
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• pp.107.1-107.1
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• 2012

We present the results of far-ultraviolet (FUV) observations of comet C/2001 Q4 (NEAT) obtained with Far-ultraviolet Imaging Spectrograph (FIMS) on board the Korean microsatellite STSAT-1, which operated at an altitude of 700 km in a sun-synchronous orbit. FIMS is a dual-channel imaging spectrograph (S channel 900-1150 ${\AA}$, L channel 1350-1750 ${\AA}$, ${\lambda}/{\Delta}{\lambda}$ ~ 550) with large image fields of view (S: $4^{\circ}.0{\times}4^{\prime}.6$, L: $7^{\circ}.5{\times}4^{\prime}.3$, angular resolution 5'-10') optimized for the observation of diffuse emission of astrophysical radiation. Comet C/2001 Q4 (NEAT) was observed with a scanning survey mode when it was located around the perihelion between 8 and 15 May 2004. Several important emission lines were detected including S I (1425, 1474 ${\AA}$), C I (1561, 1657 ${\AA}$) and several emission lines of CO $A^1{\Pi}-X^1{\Sigma}^+$ system in the L channel. Production rates of the notable molecules, such as C I, S I and CO, were estimated from the photon fluxes of these spectral lines and compared with previous observations. We compare the flux and the production rates in the radius of $3{\times}10^5$ km with $20{\times}10^5$ km from the central coma. We obtained L-channel image which have map size $5^{\circ}{\times}5^{\circ}$ The image was constructed for the wavelength band of L-channel (1350 - 1710 ${\AA}$. We also present the radial profiles of S I, C I, CO obtained from the spectral images of the central coma. The radial profiles of $2{\times}10^6$ km region are compared with the Haser model.

• 항공우주산업기술동향
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• 제9권1호
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• pp.119-129
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• 2011

달착륙선이 주어진 임무를 수행하기 위해서는 달궤도 진입 후 성공적인 착륙이 보장되어야 한다. 착륙환경에서 발생되는 높은 충격하중 하에서 착륙선 본체 및 탑재체의 파손을 막기 위해서는 높은 충격흡수율 및 자세 안정성이 요구된다. 따라서 착륙 시 발생하는 충격을 효과적으로 흡수하면서 기체의 전복 및 쓰러짐을 막을 수 있는 착륙장치는 달착륙선의 핵심 구성요소이다. 본 논문에서는 현재까지 달착륙에 성공한 달착륙선과 현재 개발단계에 있는 달착륙선을 대상으로 다양한 착륙장치 설계안들을 검토 및 비교하였으며, 현재 진행되고 있는 한국형 달탐사선 예비설계요구조건에 부합하는 착륙장치의 요구조건 및 이를 충족시킬 수 있는 착륙장치 설계에 대한 예를 제시하고자 한다.

• 항공우주기술
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• 제12권1호
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• pp.213-220
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• 2013

국가우주개발계획에 따라 2020년 이후 한국형 달탐사선이 발사될 예정이다. 달탐사선은 무인 경량화모델로 달궤도선과 달착륙선 2종을 개발할 계획이다. 달탐사선의 구조체는 발사 및 궤도하중, 착륙하중을 견딜 수 있는 구조적 안정성과 탑재장비의 장착공간을 제공할 뿐만 아니라 발사체의 탑재능력을 고려하여 가볍게 설계되어야 한다. 이를 위해 달탐사선 구조체의 개발과 관련된 핵심기술의 선행개발이 요구된다. 특히, 달착륙선의 경우 착륙선이 달 지면에 안전하게 착륙할 수 있게 해주는 착륙장치의 개발기술이 필수적이다. 본 논문에서는 달착륙선 지상시험모델 구조체의 설계, 제작, 시험을 포함한 개발내용을 다룬다.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2009년도 춘계학술대회 논문집
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• pp.167-171
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• 2009

정지궤도에서는 세계 최초의 해양관측위성으로 개발된 정지궤도 해양위성(GOCI, Geostationary Ocean Color Imager)은 통신해양기상위성(COMS, Communication, Ocean and Meterological Satellite)의 탑재체로서 2009년말 발사 예정이다. 정지궤도 해양위성의 복사보정은 센서의 전기적 특성에 의한 잡음을 제거하기 위한 암흑전류 교정(Dark Current Correction)을 먼저 수행한 다음, 주운영지상국인 해양위성센터(KOSC, Korea Ocean Satellite Center)에서 수신된 위성의 원시자료의 Digital Number(DN)를 실제 해양원격탐사에서 이용하는 물리량인 복사휘도(Radiance, $W/m^2/{\mu}m/sr$)로 변환하는 복사보정을 수행한다. 정확도 높은 복사보정을 수행하기 위해서는 기준광원의 복사휘도와 센서의 물리적 특성을 정확하게 알아야 한다. 정지궤도 해양위성 궤도상 복사보정(on-orbit radiometric calibration)에서는 태양이 기준광원이기 때문에, 기준 태양복사모델(Thuillier 2004 Solar Irradiance Model)에서 지구-태양간 거리 변화(1년 주기)를 보정한 태양의 방사도 (Irradiance)를 이용하고, 태양입사각에 대한 태양광 확산기의 감쇄 특성 변화를 고려하여 센서에 입력되는 복사휘도를 계산한다. 센서의 물리적 특성으로 인한 복사보정의 오차를 줄이기 위해 우주방사선 및 우주먼지(space debris)로 인해 위성 운용기간 중 그 특성이 저하되는 태양광 확산기(solar Diffuser)의 특성변화를 모니터링하기 위한 DAMD(Diffuser Aging Monitoring Device)를 이용한다. 정지궤도 해양위성 주관운영기관인 한국해양연구원의 해양위성센터에서는 정지궤도 해양위성 복사보정을 수행하기 위한 S/W를 통신해양기상위성 자료처리시스템 개발사업의 일환으로 개발하였으며, 관련 성능 시험을 수행하고 있다.