• Aerospace Engineering and Technology
• /
• v.9 no.2
• /
• pp.204-209
• /
• 2010

The current status of the development of pyrostarters, which play a role as a turbo pump starter in liquid propellant propulsion systems by supplying pressurized gas to power turbines for engine start, has been introduced. Firstly, the development history is briefly summarized, and secondly the current technical status in core parts for the development of pryrostarters such as solid propellants, internal ballistics, rupture discs, and igniters are presented. The current technical achievements could make it feasible to fulfill the development requirements for pyrostarters.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.42 no.7
• /
• pp.544-551
• /
• 2014

A program of launch vehicle performance analysis is composed for the education of the conceptual design of launch vehicles and the requirement analysis for the propulsion system design. The program is applied for the mission analysis of space launch vehicles based on KSLV-II with liquid rocket boosters. The 75-ton class liquid rocket engine is assumed for the boosters by referring the mass ratio of KSLV-II second stage. The launch performance analysis is carried out for KSLV-II with 2, 3 and 4 boosters by targeting the circular orbit of 700 km altitude. The trajectory is assumed as two-dimension considering the variation of the flight environment. Payload of advanced KSLV-II could be increased to maximum 3 tons, though it is limited by the thrust performance of the upper stage.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1205-1211
• /
• 2017

The Propulsion System Test Complex(PSTC) was constructed for the verification test of each stage's propulsion system of KSLV-II. Main Control System(MCS) is the system to operate the onboard equipment and the ground equipment of the PSTC simultaneously. This paper describes the critical design, the development status, and test results of Main Control System. The MCS will be used for the interface connection between ground control systems and onboard equipment. Test sequence and operation process of the Work Manager will be conducted by MCS.

• Defense and Technology
• /
• no.10 s.140
• /
• pp.16-29
• /
• 1990

세계 방위산업계에서 Snecma, Aerospatiale, Matra, SEP, Thomson-CSF, SNPE, Dassault, Sextant Avionique 및 Turbomeca등 굴지의 명성을 자랑삼고 있는 회사들을 거느리고 있는 GIFAS는 고도의 숙련된 기능능력과 저렴한 노동력을 갖고 있는 아시아.태평양 지역의 방산업체들이 공동투자, 면허생산 및 기술이전등을 모색하고 있다는 것을 잘 알고 있다. 새로운 기술의 최선봉에서 개척자로서 면모를 갖춘 GIFAS는 4가지 주요분야(항공기에 대한 기체, 헬기 및 유도탄, 추진기관 및 장비와 우주발사체)에 관련된 약 2백개의 회사를 보유하고 있다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.12 no.1
• /
• pp.37-43
• /
• 2008

In order to verify the performance of upper stage propulsion system designed to operate in the upper atmosphere, test facility which can simulate high altitude is needed. Cylindrical supersonic exhaust diffuser, which utilizes the momentum of exhaust gas, provides a simple means for providing a low pressure around the propulsion system. This paper describes sub-systems and specification of high altitude test facility developed for the test of KSLV-I kick motor. Performance of the facility has been successfully verified through five times of hot firing tests.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2005.11a
• /
• pp.72-78
• /
• 2005

Considerable achievements on scramjet technology have been performed since the end of 1950's when the improvement of performance on ramjet engine was begun. From the viewpoint of rapid and economic efficiency, scramjet propulsion system is presently regarded as the most promising one considered to be applied to the atmospheric hypersonic airplanes and ballistic weapons and even the space launch vehicles. Histories and current trends on scramjet development of USA and Russia are investigated and suggested in this paper.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2005.11a
• /
• pp.79-85
• /
• 2005

Considerable achievements on scramjet technology have been performed since the end of 1950's when the improvement of performance on ramjet engine was begun. From the viewpoint of rapid and economic efficiency, scramjet propulsion system is presently regarded as the most promising one considered to be applied to the atmospheric hypersonic airplanes and ballistic weapons and even the space launch vehicles. Histories and current trends on scramjet development of france, Germany, Japan and Australia are investigated and suggested in this paper.

• Current Industrial and Technological Trends in Aerospace
• /
• v.7 no.1
• /
• pp.43-55
• /
• 2009

Advanced countries in aerospace have been struggle to realize the hypersonic air-breathing system since originating the concept of the hypersonic air-breathing propulsion system during the first half of the twentieth century. At last, NASA's X-43A Hyper-X did successful Mach 10 flight in November 2004. Each countries are running the program to applicate this hypersonic air-breathing propulsion system to SSTO(Single Stage to Orbit) or TSTO(Two Stage to Orbit) vehicle or hypersonic missile system at present. In this paper, we wrote the history and current issues of the hypersonic air-breathing propulsion system and hypersonic flight with the hypersonic air-breathing propulsion system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• v.y2005m4
• /
• pp.16-19
• /
• 2005

The basic research on KM(Kick Motor) for space launch vehicle was carried out. KM whick will be used as 2nd stage solid rocket motor. in Korean Satellite Launch Vehicle(I) has been developing. KM is a solid rocket motor using composite propellant based on HTPB and is composed of composite motor case and submerged nozzle. To develop KM rocket motor satisfing a given set of requirement, firstly the full-scale KM was designed, then sub-scale motor reduced about $50\%$ were manufactured and tested.

• Aerospace Engineering and Technology
• /
• v.11 no.2
• /
• pp.117-121
• /
• 2012

Upper stage propulsion system designed for operation in the upper atmosphere should be tested under nozzle full flow conditions to verify its performance on the ground. KARI has carried out high altitude simulation test of KSLV-I kick motor using cylindrical supersonic exhaust diffuser. Also cold and hot flow test for the sub-scaled diffuser have been conducted to verify the design of real scale diffuser and to study its operating characteristics. This paper deals with the results obtained from these high altitude simulation tests.