• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.3
• /
• pp.9-15
• /
• 2012

This research simulates the ultrasonic wave propagation in multi-layered media using generalized formular of system response function. We made the artificial defect specimen of a rocket motor and compared with experimental wave forms. The simulation results are coincide with measured waves and we found that the pulse echo method is able to detect unbond defect at liner-propellant interface.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.912-918
• /
• 2011

This research simulates the ultrasonic wave propagation in multi-layered media using generalized formular of system response function. We made the artificial defect specimen of a rocket motor and compared with experimental wave forms. The simulation results are coinciede with mesuared waves and we found that the pulse echo method is able to detect disbond at liner-propellant interface.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2003.10a
• /
• pp.25-28
• /
• 2003

The bearing/sealing test (BST) facility is intended for tests of bearing and seal for turbopump of liquid rocket engine (LRE) in various media (water, liquid nitrogen, liquid oxygen). The bearing test for serviceability is fulfilled with the estimation of the flow rate of cooling medium through the test bearing separator and with the simulation of axial and(or) radial loading. The purpose of seals test is the determination of magnitude of leakages through the seal and a time variation of this magnitude.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.05a
• /
• pp.93-95
• /
• 2009

This is a reviewing paper on the ramjet development programs of the U.S.A. and European countries through the presented papers at the ISABE 2005 and Joint Propulsion Conference 2008. Interestingly, the programs which are developing now are only limited on the ducted rocket, neither liquid nor pure solid fuel ramjet.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2017.05a
• /
• pp.995-999
• /
• 2017

The factors affecting the flow coefficient of a control valve were identified and analyzed. The flow coefficient of a control valve are affected by not only Reynolds Number but also the figure and the roughness of the inlet/outlet pipes. Therefore, the flow coefficient is not a constant value. For the purpose of use in the system such as LRE, requiring the exact flow-coefficient of a control valve, the flow-coefficient should be measured under similar Reynolds Number using the inlet and outlet pipes which have the same figure and roughness with a real system.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.20 no.3
• /
• pp.37-53
• /
• 2016

This paper deals with an optimal output control for Space Shuttle Main Engine (SSME), a liquid propellant rocket engine using a staged-combustion cycle. For this purpose, we modeled simplified mathematical model of SSME using each SSME component divided into 7 major categories and found trim points called Rated Propulsion Level (RPL). For design the closed-loop system of SSME, we designed optimal output feedback Linear Quadratic Regulation (LQR) control system using SSME linearized model under RPL 104% and demonstrated the performance of the controller through numerical simulation.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2006.11a
• /
• pp.191-195
• /
• 2006

It is definitely required to control dispersion of the rocket engine performance in order to accomplish the mission of a launch vehicle successfully. A performance dispersion analysis was conducted for a gas generator cycle liquid rocket engine and the required pressure drops were estimated for engine tunning. As a result, the vacuum thrust dispersion of the engine was from +9.1% to -8.7% and the mixture ratio deviated from +9.7% to -9.6% from the nominal value due to the errors of components and the engine inlet condition of propellants. The required pressure drop in the LOx line to the combustor is higher than in the fuel line for same mixture ratio change.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.6
• /
• pp.73-78
• /
• 2012

The ignition characteristics of liquid rocket engine thrust chambers which have been developed by domestic technology were analyzed through hot-firing tests. Thrust chambers used in hot-firing tests have different characteristics in terms of the injector for ignition, film cooling method and the position of the oxidizer inlet. Also, these thrust chambers used their respective startup sequences. Analysis results showed that according to temperature profiles of the oxidizer manifold, low frequency fluctuation was appeared in ignition area. This low frequency fluctuation didn't give rise to violent malfunction of the thrust chamber, but the continuous observation as a concern parameter in the side of interfaces with engine system and launch vehicle should be demanded.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.451-453
• /
• 2012

Conceptual design and manufacturing scheme of a gas generator for 7 tonf class rocket engine were described. The combustion chamber pressure, O/F ratio, and total flow rate were decided to be 6 MPa, 0.321, and 1 kg/s respectively in consequence of the engine system design. Based on the parameters conceptual design of the gas generator was carried out and its outer dimension was about ${\Phi}100{\times}250mm$. Most parts of the gas generator to be jointed together by brazing or TIG welding and, if possible, the strength and leakproof tests are to be conducted in every step for checking the welding section.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.22 no.6
• /
• pp.104-110
• /
• 2018

Operating mode analysis of a liquid propellant rocket engine(LRE) is a crucial tool through the development of an engine. The operating mode analysis of an engine based on a collection of the acceptance tests of components shows discrepancies when compared to the test results. We propose a correction method for performance parameters to develop an engine analysis model for the gas generator cycle of an LRE. In order to simulate engine behavior, the performance parameters for the analysis model are tuned based on the test results of the 75tf engine of KSLV-II.