Go to the main menu
Skip to content
Go to bottom
REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
Editor in Chief :
Volume & Issues
Volume 10, Issue 4 - Dec 2006
Volume 10, Issue 3 - Sep 2006
Volume 10, Issue 2 - Jun 2006
Volume 10, Issue 1 - Mar 2006
Selecting the target year
Determination of The Cryogenic Propellant Parameters at Pressurization of The Propulsion System Tank by Bubbling
Bershadskiy Vitaly A. ; Jung, Young-Suk ; Lim, Seok-Hee ; Cho, Gyu-Sik ; Cho, Kie-Joo ; Kang, Sun-Il ; Oh, Seung-Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 1~10
In this paper, a calculation method of the thermodynamic parameters of cryogenic propellant is proposed when a cryogenic propellant tank is pressurized by gaseous helium(GHe) bubbling. Temperature of cryogenic propellant and mass of dissolved GHe into propellant were analyzed at the various operation of pressurization of tile liquid oxygen(LOX) and hydrogen(
) tank using helium bubbling. It was evaluated how the GHe bubbling influences to the thermodynamic parameters of LOX and
with results of the analysis. With the proposed calculation method, It will be able to confirm the feasibility of GHe bubbling as a pressurization system of cryogenic propellant tank and to optimize the pressurization system using GHe bubbling.
Analysis on Two Parallel Flows in Convergent Channel
Kwon, Jin-Kyung ; Kim, Tae-Wook ; Kim, Jin-Hyun ; Kim, Jae-Yeol ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 11~18
Compound flow by confluence of two parallel flows through a convergent channel and its choking phenomenon are calculated by one-dimensional isentropic model and completely mixing model. Optical observations and pressure measurements for subsonic/subsonic compound flows are carried out and compared with the results of one-dimensional calculations. As a result, it is found that inlet conditions of one flow influence the behavior of the other flow as well as the choking condition and present experimental data agree well with the results of one-dimensional calculations.
Thermal Transient Characteristics of Initiator with STS 304 Bridgewire
Yoon, Ki-Eun ; Ryu, Byung-Tae ; Choi, Chang-Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 19~25
Thermal transient tests were performed on the electric initiator with STS 304 bridgewire(diameter 2.3 mil) and
primary charge. Analysing the test data using fitted Wire Model shows that the thermal characteristic parameter related to primary charge is changed sharply around
. It is determined that this phenomenon is due to endothermic reaction from phase transition of
, which is a component of the primary charge.
Spray and Combustion Characteristics of High Density Hydrocarbon Fuel
Lim, Byoung-Jik ; Moon, Il-Yoon ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 26~33
The use of high-density propellants can provide performance advantages in space launch vehicles by allowing an improved structural ratio due to smaller propellants tanks. The Jet A-1 fuel is currently used in Korean space launch vehicle development and it has lower density than other advanced hydrocarbon fuels such as RP-1 or RG-1. In this paper, the results of hydraulic and combustion tests conducted for the two newly developed densified hydrocarbon fuels are presented and they are compared with the results of Jet A-1. Conclusively, the two densified hydrocarbon fuels presented equivalent or even higher combustion performance compared to the Jet A-1 and the performance difference was found to be more obvious in the injector of external mixing.
Comparison of Forming force on forward and Backward Flow Forming for Combustion Chamber
Nam, Kyoun-Go ; Cho, Cheon-Hwey ; Hong, Sung-In ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 34~39
The flow forming has been used to produce long thin walled tube parts, with reduced forming force and enhanced mechanical for a good finished part, compared with other method formed parts. Especially, the flow forming is suitable for making high precision thin walled cylinders, such as rocket motor cases, combustion chamber, hydraulic cylinders and high-pressure vessels and so on. In this paper, finite element analysis of three-roller forward and backward flow forming for combustion chamber is carried out to study effects of forming depth and feed rate on forming force. The axial and radial forming forces of forward flow forming on several forming depth and feed rate conditions are compared with those of backward flow forming.
Combustion Experiments of a High Pressure Liquid Propellant Thrust Chamber
Seo, Seong-Hyeon ; Han, Yeoung-Min ; Moon, Il-Yoon ; Lee, Kwang-Jin ; Kim, Jong-Kyu ; Lim, Byung-Jik ; Ahn, Kyu-Bok ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 40~46
A 30-tonf-class fullscale thrust chamber for the application to a Low-Earth-Orbit Space Launch Vehicle has been combustion tested over the wide ranges of a mixture ratio and a chamber pressure. The thrust chamber designed for a pump-fed open cycle engine was tested with an ablative chamber instead of a regenerative one for the initial evaluation of its performance and function. The test results revealed stable combustion characteristics. The hardware survived the harsh environment and showed very sound functional characteristics. The measured combustion efficiency turned out to be 95% and a specific impulse at sea level was estimated as 254sec, which are comparable to or above the predetermined design values.
3-D finite Element Analysis for Thermo-Mechanical Behavior of Laminated Carbon-Phenolic Composite Ring for Rocket Nozzle Insulator
Lee, Sun-Pyo ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 47~53
In this paper, the thermal insulator structure of a real rocket which is fabricated in a way that laminated composite rings are connected in series is analyzed using 3-dimensional axisymmetric finite element models. Simulation of cowl zone using a real operating conditions provides that the stress distribution in the laminated composite ring is largely influenced by ply-angles, axial dimensions, and boundary conditions. Notably the plylift that is the precursor to the wedge-out occurs in the ring-to-ring bonding region. It is hypothesized that after the plylift the wedge is dropped out due to the shear stresses in the ply-angle direction and axial compressive stresses.
A Study on Compressor Map Generation of a Gas Turbine Engine Using Hybrid Intelligent Method
Kong, Chang-Duk ; Kho, Seong-Hee ; Ki, Ja-Young ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 54~60
A method for generating the compressor map from some performance measuring data using the hybrid intelligent technique was newly proposed. In order to improve accuracy of the traditional scaling method, a method to generate the compressor map using the GAs(Genetic Algorithms) was previously proposed, but the method has a drawback that it can not find correctly surge and choke points of the compressor map. However, the proposed hybrid intelligent method can determine obviously those points as well as improve the accuracy of the compressor map through complementarily using the GAs and the scaling method.
The Principle and a Prototype System for Burning Rate Measurement of Solid Propellants Using Ultrasound
Song, Sung-Jin ; Jeon, Jin-Hong ; Kim, Hak-Joon ; Oh, Hyun-Taek ; Kim, In-Chul ; Yoo, Ji-Chang ; Jung, Jung-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 61~68
To measure burning rate of solid propellants using ultrasound, a special closed bomb and an ultrasonic and pressure measurement system are fabricated. During pressurization tests and homing tests on propellants, ultrasonic and pressure signal are acquired in real time fashion by this system. Based on acquired signals, analysis programs using two different algorithm which can measure burning rates corresponding to pressures are compared. One algorithm is to correct sound velocity variation of propellants and solid couplant, another one is only to correct sound velocity variation of propellants. And accuracies of homing rates measured through these algorithms are calculated through comparison with the burning rates measured using strand burner method.
Structural Analysis of Liquid Rocket Thrust Chamber Regenerative Cooling Channel using Bodner-Partom Viscoplastic Model
Ryu, Chul-Sung ; Baek, Un-Bong ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 69~76
Elastic-viscoplastic structural analysis has been performed for regenerative cooling chamber of liquid rocket thrust chamber using Bodner-Partom visco-plastic model. Strain rate test was conducted for a copper alloy at various temperatures in order to get material constants of visco-plastic model used in the structural analysis. Material constants of visco-plastic model were obtained from strain rate test results and visco-plastic model was incorporated into finite element program, Marc, by means of a user subroutine. The structural analysis results indicated that the deformation of cooling channel is mostly caused by thermal loading rather than pressure loading and confirmed structural stability of the cooling channel under the operating condition.
Design, Fabrication and Testing of Planar Type of Micro Solid Propellant Thruster
Lee, Jong-Kwang ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 77~84
With the development of micro/nano spacecraft, concepts of micro propulsion are introduced for orbit transfer and drag compensation as well as attitude control. Micro solid propellant thruster has been attention as one of possible solution for micro thruster. In this paper, micro solid propellant thruster is introduced and research on basic components of a micro solid propellant thruster is reported. Micro Pt igniter was fabricated through negative patterning and quantitative effect of geometry was estimated. The characteristic of HTPB/AP solid propellant was investigated to measure the homing velocity. A combustion chamber was fabricated by means of anisotropic etching of photosensitive glass. Finally, micro solid propellant thrusters having various geometries were fabricated and tested.
A Thermal Analysis of Liquid Rocket Combustors using a Modelling of Film Cooling Performance
Kim, Hong-Jip ; Cho, Won-Kook ; Moon, Yoon-Wan ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 85~92
A design program has been developed to predict film cooling performance of a liquid rocket engine. A thermal protecting effect of low mixture ratio gas layer has been analysed by CFD. A one-dimensional film cooling model based on the CFD results has been implemented to the previously developed design program of regenerative cooling. Satisfactory agreement has been achieved by comparing the predicted maximum heat flux at the throat of a subscale chamber and the average measured value, and the predicted nozzle average heat flux and the measured value for a full scale chamber with film cooling. It is ascertained that the film cooling is effective to reduce the throat heat flux in rocket engine chamber.
Film cooling Effects on Wall Heat Flux of a Subscale Calorimetric Combustion Chamber
Kim, Jong-Gyu ; Lim, Byoung-Jik ; Seo, Seong-Hyeon ; Han, Yeoung-Min ; Kim, Hong-Jip ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 93~99
The effects of the changes of a film cooling mass flow rate and operating conditions on wall heat flux characteristics of a subscale calorimetric combustion chamber were investigated by experiment and numerical analysis. At the nominal operating condition, with the film cooling mass flow rate being 10.5 percent of a main fuel mass flow rate, maximum heat flux at the nozzle throat was measured to be 30 percent lower than that without the film cooling. For the relatively higher mixture ratio and chamber pressure condition, maximum heat flux at the nozzle throat was increased by 31 percent compared to that of the nominal condition test without film cooling.
Study on Installed Performance Simulation of Aircraft Gas-Turbine Engine Considering Inlet and Exhaust Losses
Kong, Chang-Duk ; Owino, George.Omollo. ;
Journal of the Korean Society of Propulsion Engineers, volume 10, issue 4, 2006, Pages 100~108
Experimental study has been a general way to evaluate inlet and exhaust duct performances, but this is not only costly but also time consuming. Computational simulation is hence replacing experimental study and consequently time and cost saving. This paper therefore aims to investigate typical component performance of the intake and exhaust ducts using 3D representation. In this study a specific inlet and exhaust was modeled and analyzed to estimate its losses and flow field using computational fluid dynamic program with flow visualization capabilities. A process that requires geometry data to be modeled. That allowed for possibility of design trade off in designing phase. Installed performance of a specific turbo shaft engine was finally evaluated with the estimated inlet, exhaust and other accessories losses.