• Journal of Astronomy and Space Sciences
• /
• 제18권2호
• /
• pp.137-144
• /
• 2001

1995년에 발사된 무궁화위성 1, 2호기 REA 추력기에 대한 성능을 지상국에서 측정된 추적데이터를 이용하여 추정하였다 추정에 사용된 추적데이터는 1999년 말에서 2000년 초에 측정된 값들을 사용하였다. 추정을 위해 사용된 기법은 일반적으로 널리 알려진 최소자승추정 법(Least Square Estimation)방법이며 궤도추정과 병행해서 추력기의 작동에 의해 발생하는 기동속도변화를 추정하도록 구성하였다 추력기 성능 추정 결과 무궁화위성 1호기 REA의 경우에 계획치 대 획득속도변화의 비율이 온펄스 모드의 경우 64%로서 상당히 많은 성능감소가 있었음을 알 수 있었으며 무궁화위성 2호의 경우는 5년 이상의 임무를 수행했음에도 불구하고 100%에 이르는 상당히 양호한 성능을 유지하고 있음을 밝힐 수 있었다

• 한국초전도학회:학술대회논문집
• /
• 한국초전도학회 1999년도 High Temperature Superconductivity Vol.IX
• /
• pp.222-222
• /
• 1999

From extensive measurements of the resistance and the dynamic resistance as functions of magnetic field and temperature, we find that the transport in the insulating state beyond the superconductor-insulator (S-I) transition is dominated by bosons(Cooper pairs and/or vortices) and cannot be described by the theory of the fermionic insulating phase. The maximum of the magnetoresistance at B = B$_m$ and the following negative slope in R(B) with increasing field can be explained by the crossover from the "Bose-glass" to the "Fermi-glass" phase as suggested by Paalanen, Hebard, and Ruel. The zero bias peak in dv/dl for biases below the characteristic voltage V$_c$ (or current $I_c$), gives a clue for the assumption of the "dirty boson" model which states that the insulating state above the critical magnetic field is the phase where Cooper pairs are localized due to the Coulomb blockade with a nonvanishing order parameter. The shift to a lower value of the critical magnetic field by overlaying thin Au layer, which is known as a strong spin-orbit scatterer, also supports the bosonic nature of the S-I transition.

• 한국항공우주학회지
• /
• 제36권11호
• /
• pp.1072-1078
• /
• 2008

본 논문에서는 일반적인 타원 궤도상에서의 두 위성체간의 랑데부와 도킹을 수행하기 위한 적응 제어기법을 개발하였다. 직교좌표계를 이용해서 나타낸 두 비행체간의 상대운동방정식을 일반적인 해밀토니안 운동방정식의 형태로 변환한 후, 불확실한 시스템 파라미터를 가진 동적시스템을 위해 개발된 적응제어기법을 적용하여 제어 알고리즘을 유도하였다. 시스템 파라미터를 추정하는데 투사기법을 적용하여 파라미터 추정값의 변화에 의한 특이점을 회피할 수 있도록 하였으며, 수치해석을 통하여 추적비행체의 질량이 불확실한 경우에 대하여 제어 알고리즘의 성능을 검증하였다.

• Journal of Astronomy and Space Sciences
• /
• 제32권3호
• /
• pp.257-268
• /
• 2015

Characteristics of delta-V requirements for deploying an impactor from a mother-ship at different orbital altitudes are analyzed in order to prepare for a future lunar CubeSat impactor mission. A mother-ship is assumed to be orbiting the moon with a circular orbit at a 90 deg inclination and having 50, 100, 150, 200 km altitudes. Critical design parameters that are directly related to the success of the impactor mission are also analyzed including deploy directions, CubeSat flight time, impact velocity, and associated impact angles. Based on derived delta-V requirements, required thruster burn time and fuel mass are analyzed by adapting four different miniaturized commercial onboard thrusters currently developed for CubeSat applications. As a result, CubeSat impact trajectories as well as thruster burn characteristics deployed at different orbital altitudes are found to satisfy the mission objectives. It is concluded that thrust burn time should considered as the more critical design parameter than the required fuel mass when deducing the onboard propulsion system requirements. Results provided through this work will be helpful in further detailed system definition and design activities for future lunar missions with a CubeSat-based payload.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2002년도 춘계학술대회논문집
• /
• pp.214-219
• /
• 2002

As the tangential flow inside the clearance of tribe elements such as bearings and seals is increased as the shaft speed increases, the system stability will be decreased due to the increment of the instability parameter. To reduce the tangential flow inside the clearance of the balance sleeve, anti-swirl injection mechanism is applied. The balance sleeve is used in resisting the axial force induced by impeller in high pressure multi-stage pump. In this paper, total three cases are experimentally investigated; original balance steeve, anti-swirl injection balance steeve with 0 axial degree and anti-swirl injection balance sleeve with 30 axial degree. Experiments are focused in the comparison of vibration level and leakage flow rate. The results clearly shows that the anti-swirl injection balance sleeve with 0 axial degree improves the vibration characteristics. However, the anti-swirl injection balance sleeve with 30 degree aggravates the vibration characteristics. In the standpoint of leakage performance, both anti-swirl injection balance sleeves show the better result than the original balance sleeve.

• International Journal of Aeronautical and Space Sciences
• /
• 제17권2호
• /
• pp.184-194
• /
• 2016

In existing identification methods for on-orbit spacecraft, such as eigensystem realization algorithm (ERA) and subspace method identification (SMI), singular value decomposition (SVD) is used frequently to estimate the modal parameters. However, these identification methods are often used to process the linear time-invariant system, and there is a lower computation efficiency using the SVD when the system order of spacecraft is high. In this study, to improve the computational efficiency in identifying time-varying modal parameters of large spacecraft, a faster recursive algorithm called fast approximated power iteration (FAPI) is employed. This approach avoids the SVD and can be provided as an alternative spacecraft identification method, and the latest modal parameters obtained can be applied for updating the controller parameters timely (e.g. the self-adaptive control problem). In numerical simulations, two large flexible spacecraft models, the Engineering Test Satellite-VIII (ETS-VIII) and Soil Moisture Active/Passive (SMAP) satellite, are established. The identification results show that this recursive algorithm can obtain the time-varying modal parameters, and the computation time is reduced significantly.

• 한국소음진동공학회논문집
• /
• 제12권8호
• /
• pp.632-638
• /
• 2002

As the tangential flow inside the clearance of tribo elements such as bearings and seals is increased as the shaft speed increases, the system stability will be decreased due to the increment of the instability parameter. To reduce the tangential flow inside the clearance of the balance sleeve, anti-swirl injection mechanism is applied. The balance sleeve is used in resisting the axial force induced by impeller in high pressure multi-stage pump. In this paper, total three cases are experimentally investigated; original balance sleeve, anti-swirl injection balance sleeve with 0 axial degree and anti-swirl injection balance sleeve with 30 axial degree. Experiments are focused in the comparison of vibration level and leakage flow rate. The results clearly shows that the anti-swirl injection balance sleeve with 0 axial degree improves the vibration characteristics. However, the anti-swirl injection balance sleeve with 30 degree aggravates the vibration characteristics. In the standpoint of leakage performance, both anti-swirl injection balance sleeves show the better result than the original balance sleeve.

• 천문학논총
• /
• 제30권2호
• /
• pp.295-296
• /
• 2015

This study deals with the generalization of the Elliptic Restricted Three-Body Problem (ER3BP) by considering the effects of radiation and oblate spheroid primaries. This may illustrate a gas giant exoplanet orbiting its host star with eccentric orbit. In the three dimensional case, this generalization may possess two additional equilibrium points ($L_{6,7}$, out-of-plane). We determine the existence of $L_{6,7}$ in ER3BP under the effects of radiation (bigger primary) and oblateness (small primary). We analytically derive the locations of $L_{6,7}$ and assume initial approximations of (${\mu}-1$, ${\pm}\sqrt{3A_2}$), where ${\mu}$ and $A_2$ are the mass parameter and oblateness factor, respectively. The fixed locations are then determined. Our results show that the locations of $L_{6,7}$ are periodic and affected by $A_2$ and the radiation factor ($q_1$).

• Journal of Astronomy and Space Sciences
• /
• 제30권4호
• /
• pp.321-326
• /
• 2013

The modulation transfer function (MTF) is a widely used indicator in assessments of remote-sensing image quality. This MTF method is also used to restore information to a standard value to compensate for image degradation caused by atmospheric or satellite jitter effects. In this study, we evaluated MTF values as an image quality indicator for the Geostationary Ocean Color Imager (GOCI). GOCI was launched in 2010 to monitor the ocean and coastal areas of the Korean peninsula. We evaluated in-orbit MTF value based on the GOCI image having a 500-m spatial resolution in the first time. The pulse method was selected to estimate a point spread function (PSF) with an optimal natural target such as a Seamangeum Seawall. Finally, image restoration was performed with a Wiener filter (WF) to calculate the PSF value required for the optimal regularization parameter. After application of the WF to the target image, MTF value is improved 35.06%, and the compensated image shows more sharpness comparing with the original image.

• 한국인터넷방송통신학회논문지
• /
• 제19권5호
• /
• pp.169-173
• /
• 2019

본 논문에서는 SAR 탑재체의 운용모드 설계방안 및 설계결과 그리고 주요성능에 대한 분석 결과를 제시하였다. SAR 시스템 설계는 요구사항을 만족하는 주요변수의 설계값 도출로 진행된다. 저궤도에서 운용하는 100kg 미만의 초소형위성을 가정하고 고해상의 영상을 위하여 X-대역의 주파수를 선정하였다. 주어진 설계 요구사항을 반영하여 주파수 대역폭, 관측영역 설계, 안테나 설계를 진행하고, 설계결과를 반영하여 목표 영상품질인 NESZ 만족여부를 확인하였다. 또한 설계값을 반영하여 관측영역별로 최적의 PRF를 설계하였다. 또한 소형, 경량화를 위한 안테나 형태를 제안하였다. 또한 설계된 변수를 적용하여 체계성능을 확인하였다.