• 한국기계가공학회지
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• 제18권12호
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• pp.104-110
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• 2019

A nanosatellite designed by the Korea Microgravity Science Laboratory (KMSL) is currently under development. The KMSL nanosatellite is designed to perform two different scientific missions in space. To successfully complete missions, a variety of tests must be conducted to verify the performance of the designed satellite before launch. As part of the qualification test campaign, the KMSL nanosatellite underwent high level vibrational tests (to comply with Falcon 9 qualification level) to demonstrate the integrity of the system. The purpose of this study is to demonstrate that the primary structure and all electronic and mechanical components can withstand the vibrations and the loads experienced during the launch period. To this end, the KMSL nanosatellite was exposed to static and dynamic loads and various types of vibrations that are inevitably produced during the space vehicle launch period. The vibration test results clearly demonstrated that all avionics and mechanical components can withstand the vibrations and the loads applied to the KMSL nanosatellite's body through a Pico-satellite Orbital Deployer (POD).

• Journal of Astronomy and Space Sciences
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• 제41권1호
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• pp.43-60
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• 2024

Korea Pathfinder Lunar Orbiter (KPLO) is South Korea's first space exploration mission, developed by the Korea Aerospace Research Institute. It aims to develop technologies for lunar exploration, explore lunar science, and test new technologies. KPLO was launched on August 5, 2022, by a Falcon-9 launch vehicle from cape canaveral space force station (CCSFS) in the United States and placed on a ballistic lunar transfer (BLT) trajectory. A total of four trajectory correction maneuvers were performed during the approximately 4.5-month trans-lunar cruise phase to reach the Moon. Starting with the first lunar orbit insertion (LOI) maneuver on December 16, the spacecraft performed a total of three maneuvers before arriving at the lunar mission orbit, at an altitude of 100 kilometers, on December 27, 2022. After entering lunar orbit, the commissioning phase validated the operation of the mission mode, in which the payload is oriented toward the center of the Moon. After completing about one month of commissioning, normal mission operations began, and each payload successfully performed its planned mission. All of the spacecraft operations that KPLO performs from launch to normal operations were designed through the system operations design process. This includes operations that are automatically initiated post-separation from the launch vehicle, as well as those in lunar transfer orbit and lunar mission orbit. Key operational procedures such as the spacecraft's initial checkout, trajectory correction maneuvers, LOI, and commissioning were developed during the early operation preparation phase. These procedures were executed effectively during both the early and normal operation phases. The successful execution of these operations confirms the robust verification of the system operation.

• 한국정보통신학회논문지
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• 제20권5호
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• pp.1031-1039
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• 2016

QZSS(Quasi-Zenith Satellite System)는 일본의 위성항법시스템으로 도심지역에서 GPS 시스템의 가시성 향상을 위해 계획되었다. 첫 번째 위성(Michibiki)이 2010년 발사되었으며 이후 정상적으로 항법신호를 방송하고 있다. 따라서 본 논문은 GPS와 QZSS를 이용한 통합위성항법시스템의 성능을 분석하는데 목적이 있다. 특히 한반도 주변에서의 통합위성항법 시스템 사용 관점에서 연구가 진행되었으며, QZSS 시스템의 특성 분석, 실험 장비를 이용한 실측 및 통계적 분석 등을 통해 체계적인 연구를 하여 GPS와 QZSS 위성항법 시스템이 가시성측면에서 장애를 받는 경우 뿐 아니라 평상의 위치 측정에도 더욱 신뢰성이 높음을 확인하였다. 또한 한반도 영역에서 다양한 항법파라미터 향상에 GPS와 QZSS 통합위성항법시스템이 매우 유용할 것으로 전망된다.

• 항공우주시스템공학회지
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• 제12권3호
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• pp.9-17
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• 2018

지구 관측용 소형 위성카메라의 경우, 중대형 위성에 비해 상대적으로 약한 구조 안정성으로 인해 열악한 발사환경 및 우주환경에서 광부품의 정렬오차가 발생하기 쉽다. 발생한 정렬오차는 위성카메라의 광학 성능 저하를 유발시킨다. 본 연구에서는 소형 위성 카메라의 정렬오차를 보상하기 위하여 3축 포커스 메커니즘을 제안하였다. 이 메커니즘은 3개의 압전 작동기로 구성되어 x-축, y-축 틸트 및 디스페이스(De-space) 보정을 수행할 수 있다. 포커스 메커니즘의 설계 요구조건은 슈미트-카세그레인(Schmidt-Cassegrain) 타입의 목표 광학계 설계에서 도출되었다. 부경 정렬오차 보상을 위하여 부 반사경의 뒤에 포커스 메커니즘을 부착하여 부경의 3축 운동을 제어하였다. 이 때 파면오차로 인한 광학 성능 저하를 최소화하기 위한 플렉셔를 Box-Behnken 실험계획법을 통하여 설계하였으며, ANSYS를 이용하여 파면오차 해석을 수행하였다. 제작된 포커스 메커니즘은 작동기의 수학적 모델링, PID 제어기 설계, 서보 제어실험을 통해 서보성능을 검증하였다.

• 항공우주시스템공학회지
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• 제13권4호
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• pp.26-36
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• 2019

고해상도 지구 관측위성에서는 광학 부품간 정밀한 위치 정렬도가 요구된다. 그러나, 가혹한 위성 발사환경 및 우주환경 같은 외부 요인에 의해 광부품의 정렬오차가 발생한다. 이러한 정렬오차에 의해 저하된 영상품질을 보상하기 위해 포커스 메커니즘이 적용된 위성광학계의 설계가 필요하다. 본 논문에서는 위성카메라 정렬오차 보상이 가능한 목표광학계의 제작 및 성능 실험에 대한 연구를 수행하였다. 먼저 설계된 목표광학계를 제작/조립/정렬하였으며, 이 완료된 목표 광학계를 사용하여 영상 촬영 실험을 수행하였다. 영상 촬영 실험은 포커스 메커니즘에 의한 상의 변화를 이미지로 확인하는 실험과 오토콜리메이터를 이용하여 USAF 타깃을 촬영해 MTF를 분석하는 실험을 수행하였다. 실험 결과를 통해 포커스 메커니즘을 통하여 정렬오차를 충분히 보상할 수 있음을 확인하였으며, 궤도상에서 정렬오차를 보상할 수 있는 리포커싱의 기초자료를 확보하였다.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2005년도 춘계학술대회논문집
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• pp.949-952
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• 2005

According to the national space program in Korea, is satellites will be launch into space up to 2015. Especially, KARI is going to develope of its own a high resolution camera of less than 1m to be mounted on next Multipurpose Satellite. When performing testing of large spacecraft or hardware that will be launched into orbit, it is necessary to conduct a testing with space-simulated environment. To achieve this requirement, thermal vacuum chamber is generally used. KARI has been developed a very Large Thermal Vacuum Chamber(LTVC) from 2003 to accomodate future space program, such as KOMPSAT, COMS, and Launch vehicles. This new facility will be used to qualify the first self developed High Resolution Camera, which will be loaded on KOMPSAT-3. To perform an optical test for space camera, it is necessary to provide vibration free environment. Thus the vibration responses on the optical table due to external vibration should be minimized by using a special isolation system. In this paper, we propose the concept design of vibration isolation system for the development of the high resolution camera.

• 한국방재학회:학술대회논문집
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• 한국방재학회 2011년도 정기 학술발표대회
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• pp.12-19
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• 2011

Drawing on its extensive experience with natural disasters, Japan has been dispatching Japan Disaster Relief (JDR) team to disaster-stricken countries to provide specialist assistance in rescue and medical operations. The JDR team has assisted in the wake of disasters including the 2004 Indian Ocean Earthquake and the 2008 Sichuan Earthquake in China. Information about the affected area is essential for a rapid disaster response. However, it can be difficult to gather information on damages in the immediate post-disaster period. To help overcome this problem, we have built on an Earthquake Damage Estimation System. This system makes it possible to produce distributions of the earthquake's seismic intensity and structural damage based on pre-calculated data such as landform and site amplification factors for Peak Ground Velocity, which are estimated from a Digital Elevation Model, as well as population distribution. The estimation result can be shared with the JDR team and with other international organizations through communications satellite or the Internet, enabling more effective rapid relief operations.

• 한국항행학회논문지
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• 제19권1호
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• pp.1-6
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• 2015

전 세계적으로 급속하게 증가하는 항공교통량으로 인해 ICAO는 기존의 항행장비를 위성항법 기반으로 대체해 나가고 있으며, 이의 일환으로 기존의 ILS를 이용한 이착륙 서비스를 GBAS 로 대체할 계획을 수립 하였다. GBAS는 활주로까지 항공기를 유도하는 정밀 접근 서비스와 공항 주위의 정밀위치정보 서비스를 제공하는 위성항법 보강시스템을 이용하여 ILS와 달리 한 개의 시스템으로 활주로의 수에 관계없이 요구 성능을 제공할 수 있으며 curved approach가 가능하다는 장점을 보유하고 있다. 본 논문에서는 태안비행장 비행시험을 통한 ILS접근 절차와 GBAS curved approach절차를 비교하여 비행시간 단축 및 연료 감소효과를 분석하였으며 실제 비행시험을 통하여 이를 측정 확인 하였다.

• 한국전산유체공학회지
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• 제10권2호
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• pp.48-53
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• 2005

This work discusses the numerical analysis, the design and experimental test of the SMA actuator along with its capabilities and limitations. Convective heating and cooling using water actuate the SMA(Shape memory alloy) element of the actuator. The fuel such as propane, having a high energy density, is used as the energy source for the SMA actuator in order to increase power and energy density of the system, and thus in order to obviate the need for electrical power supplies such as batteries. The system is composed of a pump, valves, bellows, a heater(burner), control unit and a displacement amplification device. The experimental test of the SMA actuator system results in 150 MPa stress(force : 1560 N) with $3\%$ strain and 0.5 Hz. actuation frequency. The actuation frequency is compared with the prediction obtained from numerical analysis. For the designed SMA actuator system, the results of numerical analysis were utilized in determining design parameters and operating conditions.

• 대한원격탐사학회지
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• 제37권4호
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• pp.777-788
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• 2021

Since aerosol has a relatively short duration and significant spatial variation, satellite observations become more important for the spatially and temporally continuous quantification of aerosol. However, optical remote sensing has the disadvantage that it cannot detect AOD (Aerosol Optical Depth) for the regions covered by clouds or the regions with extremely high concentrations. Such missing values can increase the data uncertainty in the analyses of the Earth's environment. This paper presents a spatial gap-filling framework using a univariate statistical method such as DCT-PLS (Discrete Cosine Transform-based Penalized Least Square Regression) and FMM (Fast Matching Method) inpainting. We conducted a feasibility test for the hourly AOD product from AHI (Advanced Himawari Imager) between January 1 and December 31, 2019, and compared the accuracy statistics of the two spatial gap-filling methods. When the null-pixel area is not very large (null-pixel ratio < 0.6), the validation statistics of DCT-PLS and FMM techniques showed high accuracy of CC=0.988 (MAE=0.020) and CC=0.980 (MAE=0.028), respectively. Together with the AI-based gap-filling method using extra explanatory variables, the DCT-PLS and FMM techniques can be tested for the low-resolution images from the AMI (Advanced Meteorological Imager) of GK2A (Geostationary Korea Multi-purpose Satellite 2A), GEMS (Geostationary Environment Monitoring Spectrometer) and GOCI2 (Geostationary Ocean Color Imager) of GK2B (Geostationary Korea Multi-purpose Satellite 2B) and the high-resolution images from the CAS500 (Compact Advanced Satellite) series soon.