• 대한기계학회:학술대회논문집
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• 대한기계학회 2002년도 학술대회지
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• pp.263-266
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• 2002

The KSR-III developed by KARI is the first rocket vehicle which is adopting the liquid propellant rocket engine system in Korea. Not only the engine itself, but also the propellant feeding system is one of the most important component in liquid rocket vehicle. In this paper, the authors are intended to introduce the multi-purpose test facility(PTA-II Test Facility) which is constructed for the variety of tests on KSR-III feeding system(single component tests, verification tests, cold flow tests and combustion tests). With the results of these tests, we can identify the characteristics of rocket feeding system and decide the optimum setting values of feeding system for the successful flight.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2003년도 제20회 춘계학술대회 논문집
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• pp.193-196
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• 2003

The KSR-III developed by KARI is the first rocket vehicle which is adopting the liquid propellant rocket engine system in Korea and its flight test was successfully done last year. KSR-III is a sounding rocket class launch vehicle, but there is a sense to accomplish design, manufacture, performance test and finally its flight test by domestic technology. In this paper, the authors are intended to introduce the multi-purpose test facility(PTA-II Test Facility) which is constructed for the variety of tests on KSR-III feeding system(single component tests, verification tests, cold flow tests and combustion tests) and its test results.

• International Journal of Aeronautical and Space Sciences
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• 제16권4호
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• pp.529-536
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• 2015

Various R&D programs for rocket-based combined cycle (RBCC) engines have progressed worldwide for the space development and the defense applications. As a way toward indigenous domestic RBCC program, a preliminary design of flight test conditions was studied in this study for a sub-scale RBCC engine using a sounding rocket. Launch and flight profiles were calculated for several booster options and compared with that of HyShot II program. The result shows that the Korea Sounding Rocket-II (KSR-II) is a proper candidate to perform the flight test available in Korea. The recommend flight test conditions with KSR-II are Mach 6.0 with a test vehicle of 230 kg and Mach 7.4 with 50 kg. Present study will soon be followed by a design of sub-scale RBCC for a flight test using a sounding rocket.

• 한국연소학회:학술대회논문집
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• 한국연소학회 제26회 KOSCO SYMPOSIUM 논문집
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• pp.41-50
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• 2003

Numerical analysis was carried out to investigate performance and combustion characteristics of KSR-III liquid rocket engine with several types of baffle. To evaluate the change of performance and combustion characteristics with several types of baffle, the first numerical calculations were performed about baffle tab, radial blade baffle, and hub-and-spoke baffle. Then radial blade and hub-and-spoke baffle were determined to design two types of the KSR-III engine with baffles. Also to investigate the effect of injector arrangements and baffle positions, two types of radial blade baffle were calculated then numerical calculations were carried out with changing axial length of radial blade I, II and hub-and-spoke baffle. While axial length of baffle effected to performance very small, injector arrangement effected to performance largely through calculations of radial blade I, II. From the viewpoint of combustion instability, hub-and-spoke baffle controlled combustion instability effectively and there was the performance of hub-and-spoke baffle between radial blade I and II.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2001년도 춘계학술대회논문집
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• pp.546-551
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• 2001

Space Test Department at KARI(Korea Aerospace Research Institute) plans to carry out the GVT(Ground Vibration Test) for the KSR(Korea Sounding Rocket)-III FM(Flight Model) which is being developed by Space Technology R＆D Division. KSR-III will be an intermediate to the launch vehicle capable of carrying satellites to their orbits. GVT offers very important information to predict the behavior of KSR in its operation, and to develop the flight control and aerodynamic analysis. For development of test facilities, testing and analysis methods which can be used for the future test, Space Test Department has performed the GVT with KSR-II PFM(Proto-Flight Model) at Satellite Integration ＆ Test Center of KARl This paper discusses the procedures, techniques and the results of it. In this test, to simulate free-free condition, test object hung in the air by 4 bungee cords specially devised. The GVT was carried out using pure random excitation technique with MIMO(Multi-Input-Multi-Output) method with three electromagnetic shakers, and poly-reference parameter estimation was used to identify the modal parameters. As the result of the test, 11 mode shapes and modal parameters below 200㎐ were identified and compared with analytical results.

• 한국철도학회:학술대회논문집
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• 한국철도학회 2006년도 춘계학술대회 논문집
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• pp.364-369
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• 2006

• 한국추진공학회지
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• 제7권3호
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• pp.22-29
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• 2003

KSR-III 추진기관 공급계는 각종 배관류, 밸브류 및 이를 제어하는 제어기로 구성되어 있으며, 엔진으로 유입되는 추진제의 제어를 담당하고 있다. 이러한 공급계 시스템의 특성을 검증하고, 구성부품의 성능을 확인하기 위하여 PTA-I 수류시험을 실시하였다. PTA-I 시험설비는 엔진과 헬륨가압탱크를 제외한 공급계 전체와 지원설비로 이루어져 있다. PTA-I에서는 밸브, 제어기와 같은 단품에 대한 시스템 시험, 배관특성시험, 추진제 유량조절 시험, 배관부 압력 변동폭 및 주파수 특성 시험, 레귤레이터 성능 시험등을 수행하였다. PTA-I 시험을 통하여 구성단품에 대한 문제점을 발견하고 이를 수정보완 하였으며, 공급계 시스템의 설계 데이터와 시험데이터 비교를 통한 설계 검증을 완료하였다. PTA-I 시험의 결과는 PTA-II 및 연소시험을 수행하기 위한 시스템 구성에 적용하였다.

• Journal of Astronomy and Space Sciences
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• 제17권2호
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• pp.277-284
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• 2000

KARI(Korea Aerospace Research Institute) has measured the ozone density profiles over the Korean Peninsular since the launch of the Korean Sounding Rocket-I (KSR-I) in 1993. The purpose of ozone measurements is to obtain the stratospheric and mesospheric vertical ozone density profiles over the Korean Peninsular with solar UV radiometers. With the visible channel of the radiometer, the attitude variation of the rocket was corrected and compensated. Developed system is based on ozone detector designs onboard the KSR-I and KSR-II. We discuss the development of ozone detector which will be onboard the KSR-III and its circuit and vibration test results for EM model.

• 한국군사과학기술학회지
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• 제7권2호
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• pp.126-135
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• 2004

The KSR-III rocket developed by KARI is the first rocket vehicle which is adopting the liquid propellant rocket engine system in Korea and its flight test was successfully done last year, KSR-III is a sounding rocket class launch vehicle, but there is a sense to accomplish design, manufacture, performance test and finally its flight test by domestic technology. In this paper, the authors are intended to introduce the multi-purpose test facility(PTA-II Test Facility) which is constructed for the variety of tests on KSR-III feeding system(single component tests, verification tests, cold flow tests and combustion tests) and its firing test results.

• Journal of Astronomy and Space Sciences
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• 제18권3호
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• pp.249-256
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• 2001

한국항공우주연구원에서는 지난 1998년 KSR-2 촤학로켓에 이온층 전자환경 측정기를 탑재하여 한반도 상공의 전자 밀도, 전자 온도, 부동 전위등을 측정하는데 성공하였다. 이온층 전자환경 측정기는 한반도 상공 이온층의 전자 온도와 밀도를 측정하는데 목적이 있다. 이번 연구에서는 2002년 상반기 발사 예정인 KSR-3 과학로켓에 탑재될 전자환경 측정기를 개발하였고 일본에서 우주 환경 모사 실험을 수행하여 측정기의 성능을 확인하였다. 전자환경 측정기는 랑뮈어 프로브(Langmuir Probe)와 전자 온도 프로브(Electron Temperature Probe)로 구성되어 있으며 이 센서들의 측정 결과로부터 이온층의 전자 밀도와 온도에 대한 정보를 얻을 수 있다. 이렇게 개발된 전자환경 측정기로부터 신뢰성 있는 자료를 얻는다면 IRI(International Reference Ionosphere) 모델이나 PIM(Parameterized Ionospheric Model)과 비교하여 한반도 상공의 이온층 전자 환경에 대한 이해를 돕는데 기여할 수 있을 것으로 기대된다.