• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.1
• /
• pp.89-97
• /
• 2018

The test results of a 7-tonf-class engine for the third-stage engine of KSLV-II are presented. Hot-firing tests performed with two engineering model engines are classified into ground tests and high-altitude tests according to the test conditions. The operability verification of the engines were carried out through short and long duration tests. The full duration test performed for the durability verification of the engines revealed a few of items to be improved. Synthetically, encouraging data of adding power to engine development were obtained from the test results. New engines based on these results will be manufactured and consistently verified through hot-firing tests.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.26 no.4
• /
• pp.64-71
• /
• 2022

For the development of an improved upper-stage engine, research on a staged combustion cycle liquid rocket engine is in progress. A cold flow test, ignition test, and combustion test plans were established and performed to develop reignition combustion technology. In order to solve the problem of purge gas flowing into the fuel line, which may cause cavitation in the turbo pump during reignition, the test results of each stage were analyzed. Based on the analysis results, the purge gas inflow problem was solved by reducing the overlapping time between the operation of the bubble removal valve and the opening of the purge valve and the engine fuel valve. Based on this, the reignition combustion test was successfully performed.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.2
• /
• pp.125-130
• /
• 2018

The technology development of a high performance upper stage engine for a GEO(GEostationary Orbit) KSLV(Korea Space Launch Vehicle) is undergoing in Korea Aerospace Research Institute. KSLV is composed of an open cycle engine with gas generator, which is for a low orbit launch vehicle. However the future GEO launch vehicle requires a high performance upper stage engine with a high specific impulse. The staged combustion cycle engine is necessary for this mission. In this paper, current progress and future plan for staged combustion cycle engine development is described.

• Transactions of the Korean Society of Automotive Engineers
• /
• v.10 no.4
• /
• pp.1-6
• /
• 2002

Engine lubrication system is generally affected by vehicle driving conditions, which are composed of acceleration, braking deceleration and accelerating during cornering. The major reason is due to the oil pan system in which oil is directly influenced by inertia farce caused by vehicle driving conditions. Therefore, to confirm safety of engine lubrication system inertia farce effects are also considered in the developing state. For the purpose, we have carried the engine tilting tests using ourselves made test rig. Verifying the test results we also measured the inertia effects on the engine lubrication system using the circular tuning and slalom test with vehicle. Through the comparison study between two kinds of results we obtained that the engine tilting test rig was very useful to confirm the safety evaluation of engine lubrication system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.563-571
• /
• 2017

Test stand for altitude engine test of reciprocating engine was designed, manufactured and validated by preliminary test and simple calculation. These test stand designed to interface with Altitude turbo-shaft engine test facility of Korea Aerospace Research Institute. Many limiting condition for altitude test of reciprocating engine are assumed and test stand was developed to satisfy those limits. Test stand design specially focused on a altitude, Mach number and fuel temperature control for reciprocating engine altitude test with smaller air and fuel flow than turbo-shaft engine.

• Journal of Aerospace System Engineering
• /
• v.1 no.3
• /
• pp.13-20
• /
• 2007

The objective of this study is to investigate endurance test of localization part for T-50 aircraft engine. Major localization parts of the engine (F404-STW-102) was performed using Accelerated Simulated Mission Engine Test. The purpose of this test is to evaluate of quality demonstration capability, to verify design of engine localization parts, and to improvement safety and operation rate of T-50 advanced trainer by finding out operational problems in production phase and fixing it.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.24 no.6
• /
• pp.120-125
• /
• 2020

75 tonf liquid rocket engine combustion test was performed at Naro space center Engine Combustion Test Facility for KSLV-II. A gradual pressure drop was observed during off-design combustion test turbopump inlet condition using cooled kerosene at 271 K. It was found that the water content inside kerosene could cause pressure drop at 40 ㎛ grade filter through the water contests analysis of kerosene, kerosene cooling test and dehydration of kerosene.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.3
• /
• pp.109-118
• /
• 2018

Korea Aerospace Research Institute has developed a staged combustion cycle rocket (SCCR) engine with high specific impulse to send a 3-ton class satellite into geostationary orbit while conducting a Korean Space Launch Vehicle (KSLV) II project. The SCCR engine is different from the KSLV-II engine, which is an open cycle engine using a gas-generator. The SCCR engine with a closed cycle engine is composed of a pre-burner, a turbo pump, and a main combustor. The technology demonstration model (TDM0) was assembled and tested in the 7ton-class engine combustion test facility of Naro Space Center, and the combustion test was successfully conducted.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.18 no.6
• /
• pp.42-49
• /
• 2014

Test device using virtual engine simulator can help reduce the number of engine tests through tests similar to the actual engine tests and repeat the test under the same condition, and thus reduce the engine maintenance and operating costs. Also, as it is possible to easily implement extreme conditions in which it is hard to conduct actual tests, it can prevent engine damages that may happen during the actual engine test under such conditions. In this study, an upgraded small jet engine performance test device was developed that can conduct both real and virtual engine test by applying real-time engine model to the existing micro jet engine performance test device that was previously developed by authors. This newly developed multi-purpose small jet engine performance test device is expected to be used for various educational and research purposes.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.885-891
• /
• 2011

This paper describes the results of preliminary design of rocket engine test facility for the performance evaluation of liquid rocket engine. Design specification and composition of rocket engine test facility are suggested based on the design requirements. The results of the preliminary design of rocket engine test facility will be used as base data for the detail design and construction of rocket engine ground test facility of KSLV-II 75tonf liquid rocket engine.