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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
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Journal DOI :
The Korean Society of Propulsion Engineers
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Volume & Issues
Volume 19, Issue 6 - Dec 2015
Volume 19, Issue 5 - Oct 2015
Volume 19, Issue 4 - Aug 2015
Volume 19, Issue 3 - Jun 2015
Volume 19, Issue 2 - Apr 2015
Volume 19, Issue 1 - Feb 2015
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Zero-Dimensional Modeling of Plasma Generator in Electrothermal Gun
Kim, Kyoungjin ; Park, Joong-Youn ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 1~9
DOI : 10.6108/KSPE.2015.19.6.001
This paper introduces a zero-dimensional modeling on the plasma generation in electrothermal gun operation. The plasma generator consists of alumina bore and aluminum electrodes which is electrically powered by outer pulse forming network and, traditionally, its numerical simulations have employed time-dependent one-dimensional governing equations. However, by assuming isothermal approximation along the bore and choked bore exit condition, present analysis simplifies the mass and energy equations into zero-dimensional approximation of plasma conditions coupled with mass ablation model and plasma property evaluation. The numerical results show good agreement with the corresponding one-dimensional computations and thus verify the present modeling approach.
Performance Requirement Analysis and Weight Estimation of Reusable Launch Vehicle using Rocket based Air-breathing Engine
Lee, Kyung-Jae ; Yang, Inyoung ; Lee, Yang-Ji ; Kim, Chun-Taek ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 10~18
DOI : 10.6108/KSPE.2015.19.6.010
Performance requirement analysis and weight estimation of a reusable launch vehicle with a rocket-based air-breathing engine(RBCC : Rocket Based Combined Cycle) were performed. Performance model for an RBCC engine was developed and integrated with flight trajectory model. The integrated engine-trajectory model was validated by comparing the results with those from previous research reference. Based on the new engine-trajectory model and previous research results, engine performance requirements were derived for an reusable launching vehicle with gross take-off weight of 15 tones. Dependence of the propellant amount requirement on the mode transition Mach number of the engine was also analyzed.
Study on Flow Analysis of Hot Gas Valve with Pintle
Lee, Kyungwook ; Heo, Seonuk ; Kwon, Sejin ; Lee, Jongkwang ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 19~25
DOI : 10.6108/KSPE.2015.19.6.019
Numerical simulations of the hot gas valve with a pintle have been conducted in order to investigate the effect of numerical methods and computational domains. The grid sensitivity is checked by varying the grid number from 100,000 to 1,700,000. The existence of ambient region doesn`t make the significant differences of the flow-field and the temperature distribution. Three turbulence models are adopted to figure out its influence on the thrust and temperature distribution: Spallart-Allmaras, RNG
SST. The thrusts of the hot gas valve are almost same in all cases of the simulation, however, there are about 5% difference in the temperature distribution. With the ambient region, the difference are observed in the temperature distribution with respect to the number of grids.
Evaluation of Crack Resistance Properties on Particulate Reinforced Composite Propellant using Digital Image Correlation
Na, Seonghyeon ; Choi, Hoonseok ; Oh, Kwangkeun ; Kim, Jaehoon ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 26~32
DOI : 10.6108/KSPE.2015.19.6.026
In this study, it is evaluated for fracture toughness to analyze crack resistance properties of particulate reinforced composite propellant. Fracture toughness test using WST specimen is conducted by temperature conditions from
. Evaluation method for fracture toughness calculated using an equation suggested by ASTM E399 with linear elastic fracture mechanics. From these result, splitting loads and stress intensity factors of propellant increase according to decrease of test temperature. Also, the strain fields of specimen surface using digital image correlation increase as temperature decreased from
, but it sharply decreases at
because of brittle behavior.
Design Study of a Dual-Mode Ramjet Engine with Large Backward-Facing Step
Yang, Inyoung ; Lee, Yang-Ji ; Lee, Kyung-Jae ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 33~41
DOI : 10.6108/KSPE.2015.19.6.033
Scaled model of a dual-mode ramjet engine with large backward-facing step, as a component of the rocket-based combined cycle engine, was designed. Design parameters were derived for this engine with the consideration of application for the rocket-based combined cycle engine. Design methodology was established for these design parameters. The design was partially verified through numerical study. Flow characteristics of the dual-mode ramjet engine with large backward-facing step was investigated experimentally. The design methodology for relevant design parameters established in this study was verified as feasible.
Prediction of the Mechanical Erosion Rate Decrement for Carbon-Composite Nozzle by using the Nano-Size Additive Aluminum Particle
Tarey, Prashant ; Kim, Jaiho ; Levitas, Valeny I. ; Ha, Dongsung ; Park, Jae Hyun ; Yang, Heesung ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 42~53
DOI : 10.6108/KSPE.2015.19.6.042
In this study, the influence of Al particle size, as an additive for solid propellant, on the mechanical erosion of the carbon-composite nozzle was evaluated. A new model which can predict the size and distribution of the agglomerated reaction product(
) was established, and the size of agglomerate were calculated according to the various initial size of Al in the solid propellant. With predicted results of the model, subsequently, the characteristics of mechanical erosion on the carbon-composite nozzle was estimated using a commercial CFD software, STAR CCM+. The result shows that the smaller the initial Al particles are, in the solid propellant, the lower is the mechanical erosion rate of the composite nozzle wall, especially for the nano-size Al particle.
Molecular Level Understanding of Chemical Erosion on Graphite Surface using Molecular Dynamics Simulations
Murugesan, Ramki ; Park, Gyoung Lark ; Levitas, Valery I. ; Yang, Heesung ; Park, Jae Hyun ; Ha, Dongsung ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 54~63
DOI : 10.6108/KSPE.2015.19.6.054
We present a microscopic understanding of the chemical erosion due to combustion product on the nozzle throat using molecular dynamics simulations. The present erosion process consists of molecule-addition step and equilibrium step. First, either
are introduced into the system with high velocity to provoke the collision with graphite surface. Then, the equilibrium simulation is followed. The collision-included dissociation and its influence on the erosion is emphasized and the present molecular observations are compared with the macroscopic chemical reaction model.
Developing Trends of Spinning Process for Manufacturing Thrust Chamber of Launch Vehicle
Lee, Keumoh ; Ryu, Chulsung ; Choi, Hwanseok ; Heo, Seongchan ; Kwak, Junyoung ; Choi, Younho ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 64~71
DOI : 10.6108/KSPE.2015.19.6.064
Spinning process is generally used for manufacturing axisymmetrical, thin-walled thickness and hollow circular cross-section parts. Traditional spinning technology is classified to conventional spinning and power spinning(shear spinning and flow forming). Literature surveys of spinning application for regenerative cooling chamber and divergent nozzle of liquid propellent rocket thrust chamber have been conducted. Most spinning technology has been used mandel for manufacturing chamber and nozzle. Recently, hot spinning has been used much compared to traditional cold spinning.
A Study of the Boron Combustion for the Purpose of the Application for the Ramjet Fuel
Lee, Tae Ho ; Lee, Chang-Hoan ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 72~80
DOI : 10.6108/KSPE.2015.19.6.072
Recently air breathing propulsion system is much interested in relatively comparing to the conventional chemical propulsion, and the R&D of this area is performed much more including the basic research of the solid ramjet in our country. The boron is applied to the solid fuel because of its high heating value, but it has a complicated combustion characteristics. therefore many researches have been studied in this area. In this paper the combustion characteristics of the boron have been investigated through the published papers for the purpose of the ramjet fuel application.
A Study on the Hypersonic Air-breathing Engine Ground Test Facility Composition and Characteristics
Lee, Yang-Ji ; Kang, Sang-Hun ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 81~90
DOI : 10.6108/KSPE.2015.19.6.081
In order to know the characteristics of the hypersonic air-breahting engine, high altitude and Mach number ground test is necessary. Therefore, high pressure and high temperature condition should be simulated to do ground test of the hypersonic air-breathing engine. In this paper, the hypersonic air-breathing engine ground test facility of the Korea Aerospace Research Institute was introduced and the composition and characteristics were described.
A Study on the Mechanical Properties Optimization of Solid Propellant
Choi, Yongkyu ; Ryu, Taeha ; Kim, Nakhyun ; Kim, Jeongeun ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 91~97
DOI : 10.6108/KSPE.2015.19.6.091
The limit values of mechanical properties(MPs) of HTPB/AP/Al Solid Propellant was reviewed according to the rocket motor development procedures and the in-process values of MPs were analyzed by the tool of Process Capability Index. Based on finding the dependency among MPs, the optimization is proposed for reducing the properties defects and for improving the rocket grain safeties.
Thrust Estimation Acting on Rotor of LOX Pump for Liquid Rocket Engine
Kim, Dae-Jin ; Choi, Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 6, 2015, Pages 98~104
DOI : 10.6108/KSPE.2015.19.6.098
Excessive thrust acting on the rotor of pump can cause the damage of pump or the decrease of pump lifetime. Therefore, for ensuring the safety of LOX pump of a liquid rocket engine, the thrust of pump rotor is estimated by similarity tests. Axial thrust is indirectly measured by an axial thrust measurement unit positioned outside pump. Radial thrust is calculated based on pressure distribution of volute scroll. As a result, axial and radial thrust are increased when the flowrate of pump decreases. However, both thrusts do not affect the stability of pump rotor since their values are not large.