• Aerospace Engineering and Technology
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• v.7 no.2
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• pp.76-81
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• 2008

The vibration test system of satellite environment test dept. has been used successfully for the vibration tests of a majority of korean space programs. To meet the recent needs of large size test facility available for the vibrational tests of the huge launch vehicles and satellites, KARI have developed the large size multi-electromagnetic shaking system with $3{\times}3m$ head expander system. The new system will consist of three electromagnetic shakers which has 160 kN thrust force individually, and be able to sustain up to 8 tons test load and 300 kNm overturing moment. This paper describes the design components in the development process of multi-excitation shaker system.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.35 no.8B
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• pp.1188-1196
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• 2010

In this paper, worldwide standards and regulations on in-band/out-of-band emission characteristics of DMB broadcasting equipments are reviewed, and emission mask requirements of terrestrial low power DMB repeater under 10mW/MHz are analyzed. Out-of-band emission mask drafts suitable for single/multiple block low power repeaters are proposed. Validity and usefulness of the proposed drafts is evaluated and verified in the several experiments. Using the proposed standard, small-sized and cost-effective DMB repeater can be easily implemented to broaden DMB broadcasting coverage by reducing weak signal areas.

• Proceedings of the Korea Water Resources Association Conference
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• 2015.05a
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• pp.597-597
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• 2015

기후변화에 따른 홍수 위험도 증가와 태풍 및 집중호우의 증가는 도시지역의 홍수로 인한 피해가 커지고 있다. 실제로 최근 10년간 홍수로 인한 재산피해 및 인명피해는 해마다 늘고 있다. 이러한 홍수피해를 최소화 할 수 있는 도시지역 초단기 강우 예보 시스템 개발은 필수적이다. 그동안 기상레이더를 이용한 강우예측 모형은 국내외적으로 많이 개발이 되어 있지만, 위성을 이용한 단기간 강우예보모형은 많이 부족한 실정이다. 최근 국내 최초 기상위성의 발사로 위성을 이용한 강수관측 및 초단기 예보가 가능하게 되었다. 이러한 초단기 강우 예보 시스템의 기본예측모형인 구름이동벡터를 개발하기 위해서 본 연구에서 COMS 위성자료를 이용하였다. COMS 위성은 2011년 4월에 발사되어 현재 운영 중에 있다. COMS 위성 자료는 현재 일본 정지궤도 위성 MTSAT 위성자료와 달리 한반도 영역을 대상으로 적외채널 자료들을 8-15분 간격으로 수집 가능하여 집중호우 예보에 매우 유리하다. COMS 위성의 연속되는 위성 구름의 교차상관을 통해서 이동벡터를 산출하여 예측 모형을 산출하였다. 교차상관 기법은 연속되는 구름 자료에 대해서 두 윈도우 사의 상관계수의 최대치를 찾아냄으로써 구름의 이동방향과 이동속도를 산출하는 방법이다. 기 개발된 예측모형을 이용하여 한반도 지역의 이동벡터를 산출하였으며, 본 연구에서 산출된 구름이동벡터는 도시지역의 갑자기 발생하는 집중호우나 태풍의 초단기 예측의 기본 모형으로 탑재될 것이다.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.55-63
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• 2007

STSAT-2 (Science & Technology SATellite-2) is a Korea micro-satellite which will be launched at NARO Space center in Koheung, Korea. Launch vehicle for STSAT-2 is KSLV-1 (Korea Space Launch Vehicle-1) which is the first development in Korea space launch vehicle program. Starting development in 2002 EM(Engineering Model), PFM(Proto-Flight Model), and FM(Flight Model) were developed completely. Electrical functional test, space environmental test, and launch vehicle environmental test on system level are performed for testing those development models. In this paper we report the results of STSAT-2 PFM space environmental test and launch vehicle environmental test which is successfully completed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.10
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• pp.912-918
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• 2011

The purpose of this research is to determine the dynamic roll-damping data of a spinning projectile in wind-tunnel testing. In the present work, the high-speed wind-tunnel tests for the roll-damping measurements were conducted on a spin-stabilized projectile model in the Agency for Defense Development's Tri-Sonic Wind Tunnel at spin rates about 12,000 rpm. The test Mach numbers ranged from 0.7 to 1.05, and the angles of attack ranged from -4 to +10 deg. The validity of the wind-tunnel measurement techniques was evaluated by comparing them with the previous test results on the same configuration.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.47 no.8
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• pp.574-581
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• 2019

This paper investigates the effects of thrust misalignments and offsets of the lateral center of gravity of a space launch vehicle on its guidance performance. Sensitivity analysis and Monte Carlo simulations are applied to analyze their effects by computing changes in orbit injection errors when including the error sources. To compensate their effects, the attitude controller including an integrator additionally and the Steering Misalignment Correction (SMC) routine of the Saturn V are considered, and then Monte Carlo simulations are performed to evaluate their performances.

• Journal of the Korean Society of Propulsion Engineers
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• v.10 no.4
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• pp.26-33
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• 2006

The use of high-density propellants can provide performance advantages in space launch vehicles by allowing an improved structural ratio due to smaller propellants tanks. The Jet A-1 fuel is currently used in Korean space launch vehicle development and it has lower density than other advanced hydrocarbon fuels such as RP-1 or RG-1. In this paper, the results of hydraulic and combustion tests conducted for the two newly developed densified hydrocarbon fuels are presented and they are compared with the results of Jet A-1. Conclusively, the two densified hydrocarbon fuels presented equivalent or even higher combustion performance compared to the Jet A-1 and the performance difference was found to be more obvious in the injector of external mixing.

• Aerospace Industry
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• s.88
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• pp.50-51
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• 2005

국내 첫 초음속기 T-50 양산 1호기 출고/국산 전술통제기 1호기 KO-1출고/대한항공,대파된 미 공군 HH-60G 탐색구조헬기조기 수리 납품 달성/대한항공, B717 기수동체 최종호기 납품/국산 스텔스 무인전투기 개발/토종 기상위성 첫 수출/국내 첫 우주발사체 추적소 제주에 건설

• Journal of Space Technology and Applications
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• v.1 no.3
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• pp.319-336
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• 2021

This paper discusses the results of launch environment tests for the engineering qualification model (EQM) of nanosatellite Scale magNetospheric and Ionospheric Plasma Experiment (SNIPE) for scientific missions and lessons learned for the design of nanosatellites. SNIPE is a group of four formation-flying 6U nanosatellites with a range of payloads for missions including space weather measurement. We developed the EQM to verify the preliminary design prior to fabricating the flight model. Launch environment test of EQM was conducted for the first time in 2019, and all failures were corrected and verified at the second test conducted in 2021. A notable point of the two tests is that the nanosatellite deployer used in the first test is different from that of the second test. The second deployer has the capability to fix the internal satellite whereas the first deployer just contains and deploys the satellite. Thus actual mechanical loads the satellite receives is reduced for the second test compared to the first test. This work compares the mechanical responses of two tests and proposes general guidelines for structural design of nanosatellites.

• Journal of Aerospace System Engineering
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• v.18 no.4
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• pp.81-88
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• 2024

The payload BioCabinet of CAS500-3 is designed for 3D stem cell differentiation, culture, and analysis utilizing bio 3D printing techniques in space. The 3D printing technique was initially developed for orbital use; however, it lacks separate validation for extreme launch vibration environments, necessitating a design that mitigates the launch load on the payload. This paper proposes a passive vibration isolator with a low-stiffness elastic support structure and high damping characteristics to reduce the launch loads affecting the BioCabinet. We explore the high-damping characteristics through the superelastic effects of SMA (Shape Memory Alloys) and a multi-layered structure incorporating viscoelastic tape. The effectiveness of the proposed vibration isolation system was confirmed via launch vibration tests on a qualification model.