• Title/Summary/Keyword: 착륙선

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Development of Korean Lunar Highland Soil Simulant (KIGAM-L1) (한국형 달 고원 모사토(KIGAM-L1) 개발)

  • Tae-Yun Kang;Eojin Kim;Kyeong Ja Kim
    • Journal of Space Technology and Applications
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    • v.4 no.2
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    • pp.121-136
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    • 2024
  • Korea Pathfinder Lunar Orbiter (KPLO), launched in August 2022, is successfully carrying out its mission. Korea's lunar lander and rover programs are expected to proceed in the future. To successfully carry out the mission after the lunar lander has landed on the surface, the performance of the equipment to be mounted should be checked in a laboratory environment similar to the Moon. Scientists and engineers of several countries, including the United States and China, use lunar soil simulant which is developed to resemble lunar soil for simulating the surface of the lunar landing site. Several lunar probe landing sites are being discussed in Korea, and lunar soil simulants such as Korea Hanyang Lunar Simulant-1 (KOHLS-1), Korea Aerospace University Mechanical Lunar Simulants (KAUMLS), and Korea Lunar Simulant-1 (KLS-1), which are similar to the characteristics of lunar mare soil, have been developed. However, those simulants are not useful if the landing site is chosen as a highland area. In this study, we introduce the process of developing KIGAM-L1, a lunar highland soil simulant similar to the chemical composition of the Apollo 16 lunar soil sample and the particle size distribution of lunar soil sample 60500-1, in case the lunar lander lands at highland area.

달착륙선의 전력시스템 개념설계와 지상시험모델용 추력기 밸브구동 전원장치 개발

  • Jang, Seong-Su;Ju, Gwang-Hyeok
    • The Bulletin of The Korean Astronomical Society
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    • v.37 no.2
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    • pp.196.2-196.2
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    • 2012
  • 본 논문은 달착륙선의 개념설계를 위하여 고려한 전력시스템의 설계와 달착륙선의 지상시험모델용 추력기 밸브구동 전원장치 개발에 대해 기술하였다. 달착륙선의 임무특성을 고려하여 전력시스템의 구조를 검토하고, 극한의 온도환경에서 달착륙선의 임무수행을 위하여 필요한 전력에너지를 충분히 공급할 수 있도록 태양전지 배열기와 배터리의 용량, 그리고 전장품의 용량을 설계하였다. 특히 경량의 달착륙선 개발을 위하여 고효율의 태양전지를 이용한 태양전지 배열기와 리튬-이온 배터리를 검토하였다. 극한의 우주환경에서 태양전지배열기의 동작특성을 검토하고 생성될 수 있는 최대 전력을 분석하여 최적의 태양전지 배열기의 면적을 분석하고, 장시간의 월식을 고려하여 배터리의 방전특성에 따른 배터리의 전압특성을 검토하였다. 그리고 달착륙선의 전력시스템 개념설계의 타당성 검토를 위하여 유럽에서 개념설계 중인 달착륙선의 전력시스템 사양과 용량에 대해 비교검토를 수행하였다. 현재 개발중인 지상검증모델용 달착륙선의 전력시스템 설계와 추력기 밸브구동 전원장치의 개발에 관해 기술하였다. 지상검증용 전력시스템은 태양전지배열기의 장착 없이 배터리의 전력만을 사용하여 지상검증모델용 달착륙선의 부하에 전력을 공급할 수 있도록 설계되었다. 달착륙선 지상시험모델의 비행시간과 임무에 따른 부하특성을 고려하여 상용 리튬-이온 배터리의 용량을 선정하였으며, 부하의 전력을 고려하여 간단한 보호회로를 설계하였다. 그리고 지상검증용 전원시스템은 추력기의 밸브구동을 위한 추력기 밸브구동 전원장치, DC/DC 컨버터 전원 모듈, 모니터링 모듈, 그리고 위급상황에서 전원을 차단하기 위한 "Emergency STOP" 모듈로 구성되어 있다.

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Preliminary design of lunar lander ground test model (달착륙선 지상 시험 모델을 위한 추진시스템 기본 설계)

  • Kim, Su-Kyum;Yu, Myoung-Jong;Choi, Ji-Yong;Lee, Jae-Won
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.27-30
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    • 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.

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Introduction to Chang'e-3 and Analysis of Estimated Mission Trajectory (창어 3호 개요 및 임무궤적 추정결과 분석)

  • Choi, Su-Jin;Lee, Donghun;Bae, Jonghee;Rew, Dong-Young;Ju, Gwanghyeok;Sim, Eun-Sup
    • 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.

Descent Dataset Generation and Landmark Extraction for Terrain Relative Navigation on Mars (화성 지형상대항법을 위한 하강 데이터셋 생성과 랜드마크 추출 방법)

  • Kim, Jae-In
    • Korean Journal of Remote Sensing
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    • v.38 no.6_1
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    • pp.1015-1023
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    • 2022
  • The Entry-Descent-Landing process of a lander involves many environmental and technical challenges. To solve these problems, recently, terrestrial relative navigation (TRN) technology has been essential for landers. TRN is a technology for estimating the position and attitude of a lander by comparing Inertial Measurement Unit (IMU) data and image data collected from a descending lander with pre-built reference data. In this paper, we present a method for generating descent dataset and extracting landmarks, which are key elements for developing TRN technologies to be used on Mars. The proposed method generates IMU data of a descending lander using a simulated Mars landing trajectory and generates descent images from high-resolution ortho-map and digital elevation map through a ray tracing technique. Landmark extraction is performed by an area-based extraction method due to the low-textured surfaces on Mars. In addition, search area reduction is carried out to improve matching accuracy and speed. The performance evaluation result for the descent dataset generation method showed that the proposed method can generate images that satisfy the imaging geometry. The performance evaluation result for the landmark extraction method showed that the proposed method ensures several meters of positioning accuracy while ensuring processing speed as fast as the feature-based methods.

Virtual Flight Test for Conceptual Lunar Lander Demonstrator (달 착륙선 개념설계형상 검증모델 가상비행시험)

  • Lee, Won-Beom;Rew, Dong-Young
    • Aerospace Engineering and Technology
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    • v.12 no.1
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    • pp.87-93
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    • 2013
  • The conceptual design lunar lander demonstrator has been developed to use as a test bed for advanced spacecraft technologies and to test a prototype planetary lander capable of vertical takeoff and landing. Size of the lunar lander demonstrator is the same as that of lunar lander conceptually designed, however, the weight of lunar lander demonstrator is designed in 1/6 scale in consideration of gravity difference between moon and earth. The thruster clustering and virtual flight test were performed in the demonstrator fixed on the ground. The demonstrator ground test has been conducted for two months in the test site for the solid motor combustion of the Goheung Flight Center. The purposes of ground test of demonstrator are to demonstrate and verify essential electronics, propulsion system, control algorithm, embedded software, structure and system operation technologies before developing the flight model lander. This paper is described about the virtual flight test including test configuration, test aims and test facilities

Performance Analysis of Landing Point Designation Technique Based on Relative Distance to Hazard for Lunar Lander (달 착륙선의 위험 상대거리 기반 착륙지 선정기법 성능 분석)

  • Lee, Choong-Min;Park, Young-Bum;Park, Chan-Gook
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.44 no.1
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    • pp.12-22
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    • 2016
  • Lidar-based hazard avoidance landing system for lunar lander calculates hazard cost with respect to the desired local landing area in order to identify hazard and designate safe landing point where the cost is minimum basically using slope and roughness of the landing area. In this case, if the parameters are only considered, chosen landing target can be designated near hazard threatening the lander. In order to solve this problem and select optimal safe landing point, hazard cost based on relative distance to hazard should not be considered as well as cost based on terrain parameters. In this paper, the effect of hazard cost based on relative distance to hazard on safe landing performance was analyzed and it was confirmed that landing site designation with two relative distances to hazard results in the best safe landing performance by an experiment using three-dimensional depth camera.

Integrated Simulation of Descent Phase using the RCS jet for a Lunar Lander (RCS jet을 고려한 달착륙선의 Descent phase 통합 시뮬레이션)

  • Min, Chan-Oh;Jeong, Seun-Woo;Lee, Dae-Woo;Cho, Keum-Rae
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.41 no.6
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    • pp.473-480
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    • 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.

Automatic Landing Flight Test of TR-60 Tilt Rotor UAV based on RTK GPS (RTK GPS 기반 TR-60 틸트로터무인기 자동착륙 비행시험)

  • Yu, Chang-Seon;Jang, Eun-Yeong;Song, Bok-Seop;Jo, Am;Park, Beom-Jin;Kim, Yu-Sin;Gang, Yeong-Sin;Choe, Seong-Uk;Gu, Sam-Ok
    • 한국항공운항학회:학술대회논문집
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    • 2016.05a
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    • pp.30-34
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    • 2016
  • TR-60 틸트로터 무인기는 전장 3m, 최대이륙중량 200kg로서 2013년 2월 자동천이비행에 성공한 비행체로서 현재 해상운용을 위한 함상이착륙기술을 개발 중에 있다. 무인기 해상운용은 육상보다 심한 염무와 바람과 선박의 운동에 의한 착륙대의 이동 등의 열악한 환경에서 이루어져야 한다. 이동이 있는 착륙대와 착륙장 주변의 장애물을 고려하면 정확한 착륙을 위한 정밀한 항법유도가 요구된다. TR-60의 정밀항법유도를 위해서 수cm 단위의 정확도를 갖는 RTK GPS 기반의 정밀상대항법과 이동 착륙장 대한 자동착륙유도를 설계하고 구현함으로 함상자동 이착륙 기술을 개발하였다. 본 논문에서는 RTK GPS 기반의 정밀상대항법과 자동착륙유도에 대한 연구와 함상접근착륙절차에 따른 자동착륙정확도 측정 비행시험 결과를 기술하였다.

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