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

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.04a
• /
• pp.27-30
• /
• 2011

For the successful development of korean lunar lander, the ground test is required in order to verify performance of propulsion system, attitude control system, performance of landing device and etc. In order to develop the lunar lander ground test model, development of large size thruster and pressure regulated propulsion system is now in progress. In this paper, the results of 200N class monopropellant thruster development and propulsion system design will be presented.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.41 no.6
• /
• pp.473-480
• /
• 2013

Researches for various lunar landing technologies are in progress for the lunar exploration program planned for early 2020s in Korea. This paper shows the integrated simulation for safe lunar landing guidance/control system in powered descent phase. Generally, the lunar lander uses on/off(bang-bang) controller to control the RCS jet thrusters instead of proportional controller. In this paper, the on/off controller using phase-plane switching function, and thruster selection algorithm to control sixteen thrusters are applied. Also additional guidance commands are calculated by a proposed fuzzy logic guidance algorithm. The simulation results show that lunar lander can follow a reference trajectory which is generated by optimization method, then land on the surface safely.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.231.2-231.2
• /
• 2012

원격탐사를 위한 지구관측용 전자광학 카메라는 높은 해상도, 넓은 관측 폭 및 높은 선명도를 제공하기 위하여 부피가 크고 무거우며, 큰 전력을 소모하여, 위성본체의 대부분을 차지하도록 개발된다. 그러나, 달 탐사를 위해 달 궤도선이나 달 착륙선에 장착되는 전자광학 카메라는, 고해상도의 고성능을 가지도록 개발되기 보다는, 다기능의 집적도 높은 소형카메라로 개발되는 것이 일반적이다. 이에 따라, 달 탐사용 다기능 전자광학 카메라 개발을 위한 기술검증을 위하여 지상모델이 개발되었다. 본 카메라는 CMOS 센서를 사용하여 컴팩트하게 설계하였고, 스테레오 영상생성을 위해 두 개의 카메라가 동시에 운영되며, 줌 기능을 구현하여 다양한 조건에서도 영상획득이 가능하도록 설계 되었다. 또한 달 궤도선과 착륙선에서 1D 관측 및 2D 관측이 선택적으로 가능하도록 설계되었다. 개발된 지상모델은 실험실에서 수행하는 통상적인 기능 및 성능시험을 수행하였고, 스테레오 영상의 생성기능 등의 검증을 위하여 야외에서 카메라를 정속으로 회전하며 push broom 방식의 1D 촬영모드에 대한 시험을 수행한다. 또한, 항공촬영을 통해 1D 및 2D 촬영을 수행하여, 영상데이터의 처리 및 스테레오 영상데이터 생성 등의 검증 단계를 거친다. 본 논문 발표에서는 다기능의 전자광학 카메라를 지상에서 동작시켜 실제영상을 뽑아내고, 생성된 데이터를 처리하여, 설계된 카메라의 여러 가지 기능들에 대해 검증하는 방법들에 대해 정리 및 발표한다. 즉, 달 궤도에 맞게 설계된 카메라의 노출시간 등을 조절하고, push broom 방식을 모사하기 위하여 카메라를 정속으로 회전시켜 영상을 획득하여 다양한 카메라의 기능을 검증하였다.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.193.2-193.2
• /
• 2012

달착륙선 등과 같은 특수 목적을 위해 제작된 우주용 착륙선에는 착륙 시 전달되는 충격하중이 탑재장비로 전달되지 못하도록 연착륙(soft-landing)을 위한 충격흡수 메커니즘이 구현되어 있어야 한다. 일반적으로 자동차 및 항공기에서는 실린더와 피스톤으로 구성된 유공압식 완충장치를 주로 사용하여, 피스톤 압축으로 실린더 내부 오일 또는 압축공기가 오리피스를 통하여 분출됨에 따라 유체마찰 에너지를 활용한 충격 흡수장치가 일반적이다. 그러나 이와 같은 지상 장비용 유공압식 충격흡수 메커니즘은 진공 및 무중력 우주 환경하에서 오리피스 기능 상실, 유압유 기화 현상 및 극저온/고온 환경에서의 성능저하 등의 문제점으로 인하여 우주용 착륙선 충격완충장치로 적용이 불가능하다. 따라서 기존의 우주용 착륙선의 대부분은 충격에너지를 기계적인 좌굴 소성 변형에너지로 변환하여 충격을 흡수할 수 있도록 알루미늄 허니콤을 주로 많이 사용하여 왔다. 본 연구에서는 진공 및 무중력 우주환경에서 착륙선 충격완충 장치로 적용이 가능하도록 실리콘 포옴과 스프링을 조합하여 구성하였으며, 충격완충 매체로 유압유 및 공압을 대체할 수 있도록 실리콘 포옴을 후방 사출 성형 방식으로 적용하여 오리피스를 통과한 실리콘 포옴의 변형에너지로 충격에너지를 흡수하게 함으로서 착륙 완충효율을 극대화 할 수 있도록 검토하였다.

• The Journal of Korean Institute of Electromagnetic Engineering and Science
• /
• v.25 no.2
• /
• pp.208-216
• /
• 2014

Ground station in lunar mission is responsible to receive telemetry signal including sensor data from lunar orbiter and/or lander. At preliminary stage of developing this ground station, receiving performance such as antenna size and noise temperature should be designed on the basis of link budget analysis. When the antenna of ground station is pointing to the moon to communicate with lunar orbiter and/or lander, noise level is supposed to be increasing due to the lunar flux density. It means that the moon is working as a noise source to degrade receiving performance when antenna is pointing to the moon. Antenna noise temperature contributed by the moon was firstly calculated and secondary validated by using test configuration in this paper. Consequently, it was shown that antenna noise temperature caused by the moon was quietly matched with measured one and G/T degradation of receiving system in lunar mission can be calculated depending on antenna size and frequency.

• Current Industrial and Technological Trends in Aerospace
• /
• v.6 no.1
• /
• pp.27-34
• /
• 2008

One of the purposes of space exploration is to be able to utilize the unlimited natural resources in the universe. For this purpose, plans for lunar and mars bases have been proposed by leading nations. In order to construct bases and search for resources, it is necessary to employ and develop rovers for surface navigation and exploration. With proper knowledge about Lunar surface, technology for lunar rover development can be established without serious obstacles, since robot technology for rover development has been well prepared in Korea. In this paper, lunar rovers and mars rovers developed and planned by other countries as well as the current status of robot technology in Korea have been analyzed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.11a
• /
• pp.581-584
• /
• 2010

Korea Aerospace Research Institute (KARI) started preliminary research about the propulsion system for lunar orbiter and moon lander this year in order to prepare korean moon exploration plan of 2020s. The final goal of this study is to develop a prototype propulsion system for lunar exploration and to perform ground landing test using this propulsion system. In this year, preliminary design of propulsion system and 200N class monopropellant thruster have been conducted. In this paper, the trade-off study result and the design concept of the propulsion system for Korean moon exploration will be introduced and preliminary design of propulsion system will be presented.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.39 no.5
• /
• pp.408-415
• /
• 2011

The moon landing is composed of the de-orbit descent phase, powered descent phase, and the powered descent phase is divide into 3-sub phase of the braking, approach, final landing phase. In this paper, the lunar lander perform landing control using 3-sub phase of optimal trajectory. First, generate the reference trajectory using gauss pseudo-spectral method. Thereafter generate PID controller using altitude and velocity error in each direction. Finally the lunar lander landing system constitute using the Simulink of Matlab, and perform simulation.

• The Science & Technology
• /
• no.5 s.468
• /
• pp.55-57
• /
• 2008