• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.9
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• pp.775-783
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• 2017

In this paper, an impulsive rendezvous problem by using minimum energy of spacecraft in different orbits is addressed. In particular, the orbits considered in this paper are the general orbits including the elliptic orbit, while most of the orbits considered in the literature have been restricted within co-planar or circular orbits. The constraints for solving this optimization problem are the Kepler's equation formulated with the universal variable, and the final position and velocity of two spacecraft. Also, the Lagrange coefficients, sometimes called as f and g solution, are used to describe the orbit transfer. The proposed method technique is demonstrated through numerical simulation by considering the minimum energy, and both the minimum energy and the wait time, respectively. Finally, it is also verified by comparing with the Hohmann transfer known as the minimum energy trajectory. Although a closed-form solution cannot be obtained, it shows that the suggested technique can provide a new insight to solve various orbital transfer problems.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.1
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• pp.17-23
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• 2020

Upper stage of launch vehicle mainly injects a lunar explorer from low earth orbit to the moon at a distance of 380,000 km. In foreign lunar explorer, the upper stage is separated from the explorer after the explorer is injected into the earth-moon transfer trajectory, and the lunar explorer then uses on-board propellant to carry out mid-course correction maneuvers and lunar orbit insertion maneuvers. This study describes a newly presented small liquid upper stage. Using a small liquid upper stage with a wet mass of 2.9 tonnes, the lunar explorer not only can be injected earth-moon transfer trajectory but also can be performed lunar orbit insertion. This study provides acceptable mass range of the lunar explorer and the scope of acceptable mission range also describes based on the launch from Naro Space Center.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.12
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• pp.867-875
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• 2022

The preliminary mission analysis of a lunar lander, which is mounted on the upper stage of a Korean space launch vehicle, is performed when landing on the moon through a trans-lunar injection maneuver after being injected into the earth's low orbit by th launcher in this paper. Both direct landing and orbital landing methods, which have each advantage and disadvantages, are applied and their transfer orbit characteristics are analyzed according to the launch date when launching in lunar October 2030. We also analyzed the launch dates which satisfying eclipse conditions, solar elevation conditions, and tracking time intervals such as the US lunar lander Surveyor-1. The obtained results show that the most appropriate launch date is the 4th day of lunar October in case of direct landing method, and the 3rd day in case of indirect landing method, since the argument of perigee of the trans-lunar injection orbit and eclipse conditions are favorable in the dates.

• Aerospace Engineering and Technology
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• v.10 no.2
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• pp.87-93
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• 2011

FSSA(Fine Sun Sensor Assembly) is the important sensor for satellite attitude control. FSSA measures the direction of the sun's rays and determines whether the satellite is in the eclipse or not. FSSA for GEO Satellite is also used to acquire the attitude error information in the attitude control reference frame and acquire the Sun direction during transfer orbit or mission Process. This paper shows the configuration of Fine Sun Sensor for LEO and GEO Satellite and their principle of operation that angle measurement is obtained by using the transfer function which is the ratio of the difference between output currents of Solar Cell to the sum of all output currents.

• Journal of the Korean Chemical Society
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• v.28 no.4
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• pp.217-230
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• 1984

The MINDO/3 method was used in determination of transition states and activation barriers for various 1,2-, 1,3- and 1,5-sigmatropic hydrogen rearrangements involving systems with central carbon atom. It was found that, besides the consideration of orbital symmetry, steric effect, aromaticity, and orbital interactions were found to dictate the stability of the transition state. For systems with hetero atoms, lone pair orbitals tend to ease orbital distortion required at the transition state by participating in hydrogen transfer process and were found to lower the activation barrier accordingly. Comparison of the relative barrier heights with those obtained by using more sophisticated ab initio MO calculations showed that the MINDO/3 results give qualitatively the same tendency of the relative order of the activation barriers.

• Aerospace Engineering and Technology
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• v.8 no.1
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• pp.108-116
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• 2009

This paper considers the trajectory design problem for a lunar orbiter when launched by KSLV-II. KSLV-II puts its kick motor stage and lunar orbiter into a low earth orbit, and then the kick motor stage performed the translunar injection. To simulate more realistic situations, TLI (Trans-Lunar Injection) and LOI (Lunar Orbit Injection) maneuvers are modeled as finite burns. The feasibility of the lunar mission by KSLV-II are confirmed by the numerical results that show the reasonable required-velocity and propellant usage.

• Defense and Technology
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• no.1 s.131
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• pp.6-13
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• 1990

지상 수백km정도의 고도밖에는 왕복할수 없는 현재의 제한된 우주수송능력은 비교적 가까운 우주공간에서 화물을 운반하고 작업을 하는 궤도기동체(OMV)와 우주공간의 어느 곳, 어떤 궤도에도 왕래하는 우주전이비행체(STV)를 필요로 하고 있다. 이들은 재래식 화학로켓을 개량한 진보형 추진시스템을 1차적으로 활용하는 방향으로 개발이 진행되고 있다. 우주와 지구사이를 비교적 경제적으로 용이하게 왕래하고 우주공간에서 자유로이 기동작동하는 추진시스템이 완성되면, 인류의 우주개척은 본궤도에 오르게 되며, 생활권을 우주로 옮기는 날도 가까워질 것이다

• Journal of Aerospace System Engineering
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• v.10 no.4
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• pp.35-40
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• 2016

Mid-course correction maneuvers (MCCMs) are necessary to correct the launch-vehicle dispersion to go to the Moon. There were 3 or 4 MCCMs needed for a direct transfer trajectory. But the strategy for MCCMs of the phasing-loop trajectory is different, because it has a longer trans-lunar trajectory than direct transfer does. An orbiter using a phasing-loop trajectory has several rotations of the Earth, so the orbiter has several good places, such as perigee and apogee, to correct the launch-vehicle dispersion. Although launch dispersion is relatively high, the launch vehicle is not as accurate as we expected. A good MCCM strategy can overcome the high dispersion by using small-magnitude correction maneuvers. This paper describes the phasing-loops sequence and strategy to correct high launch-vehicle dispersions.

• Bulletin of the Korean Space Science Society
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• 1995.10a
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• pp.39-39
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• 1995

• Proceeding of EDISON Challenge
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• 2014.03a
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• pp.211-224
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• 2014

금속을 포함한 분자에 대한 양자계산은 정확하고 일관된 결과를 얻기가 힘들 뿐만 아니라 상당한 컴퓨터 자원을 소비하며 많은 시간이 소요된다. 본 연구에서는 복잡한 양자계산의 근사를 위한 방법으로 본래 정성적인 구조 예측에 사용되는 닮은 궤도함수분석(Isolobal Analysis)을 정량적인 측면에서 접근해보고, 이를 통해 닮은 궤도(Isolobal) 구조를 가지고 있는 단위들(radical 등)에 대해서 계산을 근사할 수 있는 방법에 대해 논의한다. $CH_3$, $CH_2$와 닮은 궤도 구조를 가진 전형 원소를 중심으로 하는 분자들에 대해 가장 기초적인 근사계산인 Hartree-Fock 양자계산을 수행하였다. $(CUH_5){_2}^{2-}$를 표적으로 결합 구조를 예측하기 위한 경향성을 계산한 결합 성질로부터 파악한다. 분석 결과 동일한 주기에 대해서는 원자반지름(Atomic radii)에 대해 조화 형태의 결합에너지가 얻어졌으며, 동일한 족에 대해서는 좋은 근사가 되지 않았다. 파악된 경향성을 바탕으로 금속의 결합을 근사한 에너지에 대해서는 -1054.1875 kJ/mol로 비교적 큰 오차를 보였으나, 오차 항에 대한 분석이 가능해 추가적인 계들에 대한 계산으로 근사를 교정할 수 있을 것으로 보인다.