• Current Industrial and Technological Trends in Aerospace
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• v.4 no.2
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• pp.86-97
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• 2006

일본은 1954년 도쿄대학의 이도가와 교수가 로켓연구반을 구성하여 연구와 실험을 시작한 후 1955년 8월에 펜슬로켓을 제작하여 수평비행실험을 시작하였다. 이후 베이비 로켓, 카파 로켓, 람다 로켓으로 이어지는 개발과정에서 1970년 람다로켓인 L-4S-5 로켓으로 인공위성 ‘오수미’를 발사하는데 성공하여 자체 위성발사국의 지위를 얻었다. 그러면서 미국으로부터 발사체 기술을 받아 N-1 로켓을 개발하여 1975년에 성공적으로 발사하였다. 이후 자체적으로 기술개발에 성공한 H-I 로켓에 이어 일본의 기간 발사체가 된 H-II A 로켓에 이르기까지 일본은 우주발사체 개발을 지속적으로 꾸준히 발전시켜왔다. 본 논문에서는 일본의 기간 발사체가 된 H-II A 로켓 및 H-II B(H-II A 능력향상형 로켓)에 이르기까지 일본의 로켓 개발과정을 설명하고 또 H-II A 로켓이 어떻게 일본의 기간 로켓이 되었는지 또 H-II A 능력 향상형 로켓, H-II B 로켓의 향후 에 대하여 논의하고자 한다.

• Aerospace Engineering and Technology
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• v.1 no.1
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• pp.117-127
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• 2002

In this paper, structure design of the payload section of the KSR-III was performed. The payload section of the KSR-III, which corresponds to the second stage, consists of the Scientific Payload Section for the mission of the rocket, the Payload Section (Electronics) for the communication between the rocket and the ground station, and the Payload Section (Attitude Control) for the attitude control of the rocket. In order to accomplish the mission, every payload and component should operate successfully during the mission period and the structure must satisfy the requirements of the payloads. In this research, precise composition of the payload section and payloads arrangement of the KSR-III were performed. And the modification of the structure to meet the requirements were described.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.10a
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• pp.68-76
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• 2004

It is essential to develop a transient engine system analysis model for turbopump fed type liquid rocket engine development, especially for deriving engine system test number and conditions. In this study, we proposed a mathematical model of turbopump fed type liquid rocket engine, and inspected transient mode changes around the nominal thrust level of a rocket engine according to variations of trust control valve's opening ratio. To verify the results, we solved the same problem with AnaSyn software from Russia, and concluded that the transient code showed the similar results within $2\%$ with AnaSyn.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.407-410
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• 2005

Acoustic coupling between combustion chamber and gas-liquid scheme injectors are studied numerically in liquid rocket engine adopting linear acoustic analysis. The injectors can play a role as half-wave resonators. The combustion chamber with numerous injectors shows peculiar acoustic coupling with the injectors. As the injector length approaches a half wavelength or the original tuning length, new injector-coupled acoustic modes show up in the chamber and thereby, the acoustic-damping effect of the tuned injectors is appreciably degraded.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.109-115
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• 2011

Development cases of space launch vehicle upper stage engine were studied. HM-7, Vinci, LE-5, RL10 engines are representative upper stage engines of Europe, Japan, and United States. It was realized that upper stage engines were developed with more than two engine test facilities and the development period was 5 to 8 years accompanied with 10~11 engines.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.3
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• pp.75-86
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• 2004

KSR-III is the first Korean sounding rocket propelled by a liquid propellant propulsion system and it has been developed over 5 years using purely domestic technologies. The propulsion system of KSR-III is a 13-ton class see-level thrust liquid rocket engine(LRE) which utilizes liquid oxygen and kerosene for its propellants and employed pressurized propellant feeding and ablative cooling system. The problem of combustion instabilities which has brought the most difficulty in the development was resolved by implementation of a baffle. Through the development of KSR-III LRE, meaningful achievements have been made in the core technologies of LRE such as design of injectors and combustion chambers and test, evaluation, and control of combustion instabilities. The acquired technologies will be applied to the development of higher performance LREs necessary for future space development programs such as Korean Small Launch Vehicles(KSLV) In this paper, the development of KRE-III LRE system is described including its design, analyses. performance tests and evaluation.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.4
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• pp.67-75
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• 2004

It is essential to develop a transient analysis model for the turbopump-fed type liquid rocket engine development, especially for deriving the number of test and its parameters. In this study we proposed a mathematical model of turbopump-fed type liquid rocket engine, and inspected transient mode changes of a rocket engine according to variations of thrust control valve opening ratio. To verify the results, we solved the same problem with AnaSyn software from Russia, and concluded that the results of transient code we developed deviated within 2% from AnaSyn results. Also, using the transient engine analysis code we showed the possibility to find out the system level design Parameters of the components. For example, we modeled a pressure stabilizer which is used to control the consistency of mixture ratio in the gas generator as forced damping system, and found the stability range of the natural frequency and the damping ratio with the transient engine system analysis code.

• Journal of Astronomy and Space Sciences
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• v.15 no.2
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• pp.373-389
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• 1998

The test result of the X-ray observation system is presented which have been developed at Korea Astronomy Observatory for 3 years(1995 -1997). The instrument, which is composed of detector and signal processing parts, is designed for the future observations of compact X-ray sources. The performance of the instrument was tested by mounting on the two-stage Korean Sounding Rocket, which was launched from Taean rocket flight center on June 11 at 10:00 KST 1998. Telemetry data was received from individual parts of the instrument for 32 and 55.7 sec, respectively, since the launch of the rocket. In this paper, the result of the data analysis based on the received telemetry data and discussion about the performance of the instrument is reported.

• Aerospace Engineering and Technology
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• v.11 no.2
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• pp.182-194
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• 2012

To develop a liquid rocket engine with high reliability and safety under constraints of limited time and budget an optimal diagnosis system for the engine needs to be developed in parallel with the development of the engine. This paper is intended to set a development direction of the diagnosis system for the liquid rocket engine through the literature survey and addresses possible engine defects, characteristics of parameters for diagnosis and diagnostic methods including real-time diagnosis, post-test/post-flight diagnosis, fault detection method, parameter circuit method and test diagnosis. In addition tasks to be performed in the design and operation phases of the engine and foreign application case of engine diagnosis are presented.

• Journal of Space Technology and Applications
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• v.4 no.2
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• pp.153-168
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• 2024

Sounding rockets are cost-effective and rapidly deployable tools for directly exploring the ionosphere and microgravity environments. These rockets achieve their target altitudes quickly and are equipped with various scientific instruments to collect real-time data. Perigee Aerospace plans its inaugural test launch in the first half of 2024, followed by a second performance test launch in January 2025. The second launch, scheduled off the coast of Jeju Island, aims to reach an altitude of approximately 150 km with a payload of 30 kg, conducting various experiments in the suborbital region. Particularly in mid-latitude regions, the ionosphere sporadically exhibits increased electron densities in the sporadic E layers and magnetic fluctuations caused by the equatorial electrojet. To measure these phenomena, the sounding rocket version of ionospheric anomaly monitoring by magnetometer and plasma-probe (IAMMAP), currently under development at the KAIST Satellite Research Center, will be onboard. This study focuses on enhancing our understanding of the mid-latitude ionosphere and designing observable missions for the forthcoming performance tests.