• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.11a
• /
• pp.55-59
• /
• 2008

It is very difficult to measure an accurate thrust for the performance test of liquid rocket engine. Liquid rocket engine is attached to the propellant feed system, control valve and many other safety systems. Without considering these effects, thrust data measured from the firing test is not reliable and meaningless. In this research, the modified thrust measurement system, which includes both all these side effects is developed for the verification of low thrust liquid rocket engine performance. In addition, reliability appraisal technique is studied to secure the reliability of thrust measurement system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.56-61
• /
• 2011

The deign and lay-out of a combustion chamber test facility(CTF), a turbopump real propellant test facility(TPTF), a rocket engine test facility for 3rd stage engine(SReTF), a rocket engine ground/high altitude test facility(ReTF, HAReTF) and a propulsion system test complex(PSTC) for KSLV-II is briefly described. The development/qualification tests of engine component, 3rd stage engine system and 75ton-class liquid rocket engine system will be performed in CTF, TPTF, SReTF, ReTF and HAReTF and the development test of 1st/2nd/3rd propulsion systems for KSLV-II will be performed in PSTC. These propulsion test facilities will be built in NARO space center considering construction schedule, cost, safety distance and utility factor of propulsion test facilities.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.1112-1114
• /
• 2017

The liquid rocket engine determines the routing of the component placement and layout by adapted the cycle method, the hardware configuration, the gimbal type on the functional implementation, and so on. In this paper, the conceptual routing of major pneumatic lines such as helium (He) supply pneumatic line for driving, many purge pneumatic line and main ignition line based on the main components installed in the liquid rocket engine was performed.

• 한국전산유체공학회:학술대회논문집
• /
• 2005.04a
• /
• pp.96-99
• /
• 2005

The geostationary satellite propulsion system has thermistors which can measure liquid propellant temperature at tanks, pipes and etc. In the satellite propulsion system with several tanks, the propellant in the tanks is moved by temperature change and this temperature pattern is constant. In this paper, the temperature change pattern of KOREASAT 1 propulsion system is compared and the prediction study of pressurant inflow using temperature change of geostationary satellite propulsion system is described.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.6 no.4
• /
• pp.37-45
• /
• 2002

The development process of KSR-III propulsion feeding system is subscripted. The purpose of propulsion feeding system is to feed a certain amount of propellant from propellant tank to engine by the end of combustion. Pressure-fed liquid rocket, KSR-III has the unique characteristics of both pressure regulator and cavitation venturi as a passive flow control device. Main parameters of feeding system are confirmed by both water test and CFD(전산유체) technique. Flow control effect with venturi is confirmed by water test. Initial stabilization characteristic of pressure regulator is confirmed by real propellant test. And, to avoid the effect of resonance between rocket and feeding system, this article deal with POGO(포고) analysis to the feeding system.

• Aerospace Engineering and Technology
• /
• v.4 no.2
• /
• pp.94-100
• /
• 2005

The geostationary satellite propulsion system has thermistors which can measure liquid propellant temperature at tanks, pipes and etc. In the satellite propulsion system with several tanks, the propellant in the tanks is moved by temperature change and this temperature pattern is constant. In this paper, the temperature change pattern of KOREASAT 1 propulsion system is compared and the prediction study of pressurant inflow using temperature change of geostationary satellite propulsion system is described.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.31 no.3
• /
• pp.58-64
• /
• 2003

Pogo is the instability resulting from the interaction between rocket structure and propulsion system of liquid propellant rocket. The coupling of structure and propulsion system can lead to severe problem in rocket. For the analysis of pogo, a time-invariant linearized mathematical model is developed for a selected flight time. Propulsion system is modeled using element representations for each components. Rocket structure is modeled using FEM. Form the results of modal analysis of structure, the behavior of structure can be represented. System equations for coupling structure and propulsion system are composed. The stability in obtained by the eigen solution of system matrix. The optimization of the design variables such as size, place of accumulator for suppressing pogo instability in carried out. This article of study can be used to determine the degree of stability, and guide the design of pogo suppression system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.05a
• /
• pp.181-184
• /
• 2006

We successfully completed the development test for a 10-ton thrust liquid rocket engine using LOX+LNG (Liquefied Natural Gas, or Methane) with a high performance turbopump system. Resulting from the success of the regenerative-cooling capability using LNG, high pressure-generating capability and gas-generating performance, etc, methane engine with the product name CHASE-10 will be commercialized in the near future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2010.05a
• /
• pp.34-37
• /
• 2010

One dimensional transient analysis was studied for turbopump-fed liquid propellant rocket engine(LRE) system in starting using AMESim. The effects of timing of gas generator fuel valve opening and gas generator ignition to start-up stability were researched for open cycle type system using LOX/RP-1 to propellants. Result show that the parameters and sequence on start-up should be considered to design optimized turbopump-fed LRE system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2008.11a
• /
• pp.388-392
• /
• 2008

Research of methods for preventing accidents and minimizing losses during the liquid rocket engine (LRE) test and its exploration is of current importance. In this paper the steps of progress to LRE accidents are defined, and methods for preventing LRE accidents and minimizing losses from accidents are considered. The suggested methods in this paper can be applied to LRE test and exploration for protecting engine system from emergency situation.