• The Bulletin of The Korean Astronomical Society
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• v.36 no.2
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• pp.134.2-134.2
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• 2011

APT(Asian-Pacific Telecommunity)는 아시아-태평양지역 국가의 공동이익을 도모하기 위하여 결성된 아-태지역 전파협의체 조직으로, WRC(세계전파통신회의)회의에서의 아-태지역 주관청의 공동이익을 얻기 위해 APG(APT Conference Preparatory Group for WRC)회의를 연간 1회의 비율로 개최하고 있다. 2012년의 WRC-12회의에 대비하여 아태지역 회원국의 최종 공동의견서를 작성하기 위해, APG-12 5차회의가 2011년 8월 29일-9월 3일 부산에서 개최되었으며, 전파천문업무 보호 및 22 GHz 대역 달탐사, 38 GHz 대역 Space-VLBI운용대역과 관련된 WRC-12 의제 1.6, 1.11, 1.12 등에 대한 회의가 있었다. 따라서 한국천문연구원에서는 달탐사계획과 관련된 22 GHz 대역에서의 전파천문업무 및 우주연구업무의 원활한 운용을 위해, APG-12 5차회의에 참석하여 WRC-12회의에 제출하기 위한 아-태지역 국가의 공동의견서 작성에 주도적인 역할을 담당하였다. 본 발표에서는 국내의 달탐사계획과 관련되어, APG-12 5차 회의에 제안한 우리나라의 기고서 제안 내용 및 동 회의에서의 최종 아태지역 회원국 공동의견서 결과 및 향후 대응책에 대해서도 알아보고자 한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.6
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• pp.34-41
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• 2014

A feasibility study of thrust control of hybrid propulsion system for lunar exploration is presented. The thrust control experiments were performed by controlling the oxidizer mass flow rate where the thrust modulation is carried by using a ball valve and a stepping motor. The gaseous oxygen (GOX) and the HDPE (High Density PolyEthylene) were used for the oxidizer and solid fuel, respectively. It was found that the thrust levels were stable without much fluctuation during the modulation period, and that the thrust was exactly controlled with target thrust modulation ratio of 53% and 32%.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.12
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• pp.1037-1044
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• 2014

In this study, we designed a drop test system considering lunar surface environment and tested landing gear of experimental lunar lander. The lunar lander would be landed at soil place for soft landing. When the lunar lander touches down, the acceleration of the lander is largely affected by mechanical characteristics of the lunar soil. Accordingly, a drop test using lunar soil is needed to verify the performance of the lunar landing gear. Because the lunar soil is not available generally, we developed a lunar simulant KAUMLS(Korea Aerospace University Mechanical Luna Simulant) based on mechanical properties of the lunar soil of NASA's LUNA PROJECT. In addition, drop tests on steel plate and dry sand are performed to evaluate impact characteristics by the surface environment.

• Journal of Space Technology and Applications
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• v.1 no.3
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• pp.375-395
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• 2021

Korea plans to send a pathfinder lunar orbiter to the Moon for the first time in August 2022. And according to the 3rd Basic Plan for Space Development Promotion, the plan is to send a lunar lander to the Moon before 2030. The selection of the lunar landing area can be varied depending on the lunar lander's mission, therefore preliminary research on the lunar landing sites is essential for a successful lunar exploration mission design. This paper analyzed the characteristics of major regions among 14 proposed regions using NASA's MoonTrek based on the data on the candidate areas for the major moon landing proposed sites by the NASA workshop in 2018. And we looked into what kind of future moon landing missions are suitable for these areas. We also looked at the importance of lunar Antarctica area through the recent lunar landing areas of Moon landing countries and Artemis plan.

• Proceedings of the Acoustical Society of Korea Conference
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• 1998.06c
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• pp.483-486
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• 1998

한국해양연구소 온누리호에 장착된 에어건 배열에서 건 간격에 따른 빔 패턴 변화를 확인하였으며 남극해역에서 획득된 탐사자료와 비교하였다. 컴퓨터 모의과정과 배열 이론을 이용하여 신호진폭 및 빔 폭 변화 등을 시간 및 주파수 영역에서 분석하였다. 154 Hz에서 송이배열 (cluster array) 및 폭 배열 (wide array)의 빔 폭 변화는 배열 형태보다는 건 간격에 큰 영향을 받고 있어 배열 형태가 달라도 빔 폭은 서로 유사하게 변한다. 건 간격이 클수록 송이배열이 90$^{\circ}$의 빔 패턴에서 주엽 (mainlobe)이 최대치가 되는 것과는 달리 폭배열은 0$^{\circ}$에서 최대치를 나타내며 부엽 (sidelobe)은 건 간격과 무관하게 나타난다. 두 배열의 선형간섭이 점차 줄어드는 건 간격은 2.43 m이다. 남극해 탐사자료는 건 간격이 증가함에 따라 주신호 진폭은 약하게 기포는 강하게 증가한다. 이러한 결과는 빔 패턴 변화에서도 마찬가지로 나타나는데 건 간격이 클수록 주엽의 빔 폭이 점차 좁아져 강한 빔 패턴을 나타냄으로서 남극 탐사자료와 서로 잘 일치한다.

• Current Industrial and Technological Trends in Aerospace
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• v.5 no.1
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• pp.3-11
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• 2007

1990년대 초부터 2000년대 중반까지 구소련의 붕괴와 예산 투자의 저조로 정체기에 접어들었던 우주개발은 달 및 행성탐사와 같은 새로운 연구개발 움직임과 중국, 인도 등 새로운 우주강자의 부상으로 현재 신성장기를 맞이하고 있는 것으로 보인다. 전 세계 우주프로그램의 정부투자도 2006년 총 50.36 십억 달러로 역사상 최고점을 기록하고 있기도 하다. 주요 우주개발국들은 미국의 우주탐사 계획에 버금가는 탐사계획들을 잇따라 발표했으며, GPS, GLONASS, Galileo 등 위성항법 분야 연구개발에도 높은 우선순위를 부여하고 있다. 정부의 연구개발 투자 확대는 우주산업의 활성화에 직접적으로 영향을 미치는 요인이 된다. 실제로 미국 우주산업 매출의 90%가, 그리고 유럽 우주산업 매출의 60%가 정부고객으로부터 발생하고 있다. 2005년 우주산업 매출은 총 88.8 십억 달러로 전년대비 6% 정도 성장하였으며, 여전히 위성서비스 분야가 전체 매출에서 차지하는 비중이 60%로 가장 높다. 본고에서는 우주분야의 정부 예산 투자 현황과 우주탐사 및 위성항법을 중심으로 한 새로운 연구개발 움직임을 국가별로 살펴보고, 우주산업의 동향과 전망, 그리고 우리나라의 우주산업과 우주개발 관련 주요 정책변화, 현재 진행 중인 국가 우주개발 프로그램에 대해 간략하게 살펴보도록 하겠다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.11
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• pp.984-997
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• 2015

Chang'e-3 consisting of a lunar lander and exploration rover was launched on December 1, 2013 aboard a Long March 3B rocket flying from Xichang space launch center. Chang'e-3 was inserted into the lunar orbit after about a 5-day transit to the Moon and landed on the targeted landing site after orbiting around the Moon for 8 days. The successful landing of the Chang'e-3 gives a lot of help to analyze the future needs of the subsystem technologies and to figure out the trajectory from launch to lunar landing as well as operation sequences in the development of Korean lunar exploration is scheduled. Therefore, the configuration and analysis of overall mission of Chang'e-3 is performed based on the public information from the press and website. As a result, overall mission trajectory is reconstructed by solving boundary condition and then estimating control variable. Visibility status and eclipse status also analyzes so communication and power charge condition is as good as to operate lunar lander. Mass budget of the lander is derived using ${\Delta}V$ according to specific impulse.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.4
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• pp.284-290
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• 2014

To successfully explore the moon by lunar lander, it is essential to guarantee the safe landing of lunar lander. Therefore, efficient shock absorption system of lunar lander should be designed in order to reduce landing impact force. Also, for more practical design of lunar lander, it is important to consider the effect of lunar regolith. In the line of thought, finite element model of lunar lander considering the effect of lunar regolith is developed. To reduce landing impact force, optimization of shock absorption system for lunar lander has been carried out. In optimization, sequential approximate optimization method based on meta-model is used. Through the result of optimization, it is verified that landing impact force on lunar lander can be efficiently reduced by the present optimization procedure.

• Journal of the Korean Geotechnical Society
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• v.38 no.9
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• pp.19-33
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• 2022

Planarity geotechnical exploration missions were actively performed during the 1970s and there was a period of decline from the 1 990s to the 2000s because of budget. However, exploring space resources is essential to prepare for the depletion of Earth's resources in the future and explore resources abundant in space but scarce on Earth, such as rare earth and helium-3. Additionally, the development of space technology has become the driving force of future industry development. The competition among developed countries for exoplanet exploration has recently accelerated for the exploration and utilization of space resources. For these missions and resource exploration/mining, geotechnical exploration is required. There have been several missions to explore exoplanet ground, including the Moon, Mars, and asteroids. There are Apollo, LUNA, and Chang'E missions for exploration of the Moon. The Mars missions included Viking, Spirit/Opportunity, Phoenix, and Perseverance missions, and the asteroid missions included the Hayabusa missions. In this study, space planetary mineral resource exploration technologies are explained, and the future technological tasks of Korea are described.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.9
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• pp.734-745
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• 2017

The navigation system of lunar lander are composed of various navigation sensors which have a complementary characteristics such as inertial measurement unit, star tracker, altimeter, velocimeter, and camera for terrain relative navigation to achieve the precision and autonomous navigation capability. The required performance of sensors has to be determined according to the landing scenario and mission requirement. In this paper, the specifications of navigation sensors are investigated through covariance analysis. The reference error model with 77 state vector and measurement model are derived for covariance analysis. The mission requirement is categorized as precision exploration with 90m($3{\sigma}$ ) landing accuracy and area exploration with 6km($3{\sigma}$ ), and the landing scenario is divided into PDI(Powered descent initiation) and DOI(Deorbit initiation) scenario according to the beginning of autonomous navigation. The required specifications of the navigation sensors are derived by analyzing the performance according to the sensor combination and landing scenario.