• 항공우주시스템공학회지
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• 제2권1호
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• pp.37-45
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• 2008

KARI has jointly developed COMS bipropellant propulsion system with EADS Astrium, UK. It is well known at the moment about American or even German efforts for space development and space propulsion activities. On the contrary UK's capability for space development hasn't been recognised well in Korea. The major space activities relevant to the development of chemical and electric propulsion systems in UK, in reference to our space propulsion programme are addressed in detail. In addition the collaboration in prospect between two countries is proposed.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.407-412
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• 2008

"KAGUYA"(SELENE) is a Japanese Lunar Explorer launched by H-IIA rocket from Tanegashima Space Center on 14 September 2007. The dual-mode bipropellant propulsion subsystem of KAGUYA includes two fuel tanks, an oxidizer tank, propellant and pressurant control components, twelve monopropellant 20N thrusters, eight monopropellant 1N thrusters, and a bipropellant 500N Orbit Maneuver Engine(OME). Once the KAGUYA separated from the rocket, it circled the Earth twice and traveled to the Moon, where it entered lunar orbit. All maneuvers were performed through multiple 500N OME/20N thruster firings. This paper describes the in-space performance of KAGUYA Lunar Explorer bipropellant propulsion subsystem.

• 한국추진공학회지
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• 제26권6호
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• pp.86-100
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• 2022

핵추진 시스템의 개념 및 특징들을 소개하고 해외 핵동력 우주추진 기술개발 동향을 정리하였다. 핵추진 원료로 사용되는 우라늄은 비에너지가 매우 높아 기존 화학추진방식 대비 우수한 비추력 성능을 내고, 탑재되는 연료의 양을 줄일 수 있어 장거리 탐사 시 매우 유리한 이점을 가지고 있다. 이러한 이유로, 최근 우주개발 선도국에서 핵추진 기술 연구에 박차를 가하고 있는바, 우주개발 경쟁에서의 우위를 점하기 위해서도 핵동력을 이용한 추진기관의 개발이 반드시 필요하다고 판단된다.

• International Journal of Aeronautical and Space Sciences
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• 제13권4호
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• pp.421-427
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• 2012

Solar Sail propulsion has been validated in space (IKAROS, 2010) and soon several more solar-sail propelled spacecraft will be flown. Using sunlight for spacecraft propulsion is not a new idea. First proposed by Frederick Tsander and Konstantin Tsiolkovsky in the 1920's, NASA's Echo 1 balloon, launched in 1960, was the first spacecraft for which the effects of solar photon pressure were measured. Solar sails reflect sunlight to achieve thrust, thus eliminating the need for costly and often very-heavy fuel. Such "propellantless" propulsion will enable whole new classes of space science and exploration missions previously not considered possible due to the propulsive-intense maneuvers and operations required.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2004년도 한국우주과학회보 제13권2호
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• pp.341-343
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• 2004

In executing the large scale national project, such as development of space launch vehicle, it is most important to guarantee the technological reliability. However the reliability analysis of launch vehicle is different from other mass product goods because of the limitation of budget and number of tests. In this study, the reliability analysis technique of the propulsion system, which is one of the major sub-systems of launch vehicle is illustrated and applied to the liquid rocket engine of KSR-III.

• International Journal of Aeronautical and Space Sciences
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• 제18권4호
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• pp.651-661
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• 2017

A truss-braced wing (TBW) aircraft has recently received increasing attention due to higher aerodynamic efficiency compared to conventional cantilever wing aircraft. For conceptual TBW aircraft design, we developed a propulsion-and-airframe integrated design environment by replacing a semi-empirical turbofan engine model with a thermodynamic cycle-based one built upon the numerical propulsion system simulation (NPSS). The constructed NPSS model benefitted TBW aircraft design study, as it could handle engine installation effects influencing engine fuel efficiency. The NPSS model also contributed to broadening TBW aircraft design space, for it provided turbofan engine design variables involving a technology factor reflecting progress in propulsion technology. To effectively consolidate the NPSS propulsion model with the TBW airframe model, we devised a rapid, approximate substitute of the NPSS model by reduced-order modeling (ROM) to resolve difficulties in model integration. In addition, we formed an artificial neural network (ANN) that associates engine component attributes evaluated by object-oriented weight analysis of turbine engine (WATE++) with engine design variables to determine engine weight and size, both of which bring together the propulsion and airframe system models. Through propulsion-andairframe design space exploration, we optimized TBW aircraft design for fuel saving and revealed that a simple engine model neglecting engine installation effects may overestimate TBW aircraft performance.

• 한국우주과학회:학술대회논문집(한국우주과학회보)
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• 한국우주과학회 2006년도 한국우주과학회보 제15권2호
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• pp.151-151
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• 2006

• International Journal of Aeronautical and Space Sciences
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• 제6권1호
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• pp.61-70
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• 2005

The currently developed propulsion system(PS) is composed of propellant tank, valves, thrusters, interconnecting line assembly and thermal hardwares to prevent propellant freezing in the space environment. Comprehensive engineering analyses in the structure, thermal, flow and plume fields are performed to evaluate main design parameters and to verify their suitabilities concurrently at the design phase. The integrated PS has undergone a series of acceptance tests to verify workmanship, performance, and functionality prior to spacecraft level integration. After all the processes of assembly, integration and test are completed, the PS is integrated with the satellite bus system successfully. At present, the severe environmental tests have been carried out to evaluate functionality performances of satellite bus system. This paper summarizes an overall development process of monopropellant propulsion system for the attitude and orbit control of LEO(Low Earth Orbit) observation satellite from the design engineering up to the integration and test.

• 항공우주산업기술동향
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• 제8권2호
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• pp.24-30
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• 2010

우주태양광 비행은 별이나 레이저에서 나오는 빛의 복사 압력을 이용하여 아주 얇은 물질을 매우 빠른 속도가 되도록 하는 위성체 추진을 위한 방법 중 하나이다. 이에 관한 연구는 미국, 일본, E.U. 그리고 러시아 등에서 기초 연구를 비롯한 우주 비행 시험을 수행하고 있다. 2010년 5월 일본의 JAXA는 세계 최초로 태양광 돛을 가진 행성간 위성체인 "IKAROS"를 금성까지 발사하는데 성공한 바 있다. 현재 태양광 추진 방법으로 태양계를 포함한 은하계에 많은 무인 우주 비행 임무를 수행하고자하는 목표를 가지고 있다. 본 논문에서는 우주 탐사 및 여행을 위한 새로운 추진 방법으로 우주 선진국들의 우주태양광 비행선의 기술 동향에 대해 기술하였다.

• Advances in aircraft and spacecraft science
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• 제6권5호
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• pp.427-442
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• 2019

Small satellites represent an emerging opportunity to realize a wide range of space missions at lower cost and faster delivery, compared to traditional spacecraft. However, small platforms, such as CubeSats, shall increase their actual capabilities. Miniaturized electric propulsion systems can provide the satellite with the key capability of moving in space. The level of readiness of miniaturized electric propulsion systems is low although many concepts have been developed. The present research intends to build a flexible test platform for the assessment of selected small propulsion systems in relevant environment at laboratory level. Main goal of the research is to analyze the mechanical, electrical, magnetic, and chemical interactions of propulsion systems with the modern CubeSat-technology and to assess the performance of the integrated platform. The test platform is a 6U CubeSat hosting electric propulsion systems, providing mechanical, electrical and data interfaces, able to handle a variety of electric propulsion systems, thanks to the ability to regulate and distribute electric power, to exchange data according to several protocols, and to provide different mechanical layouts. The test platform is ready to start the first verification campaign. The paper describes the detailed design of the platform and the main results of the AIV activities.