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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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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 17, Issue 6 - Dec 2013
Volume 17, Issue 5 - Oct 2013
Volume 17, Issue 4 - Aug 2013
Volume 17, Issue 3 - Jun 2013
Volume 17, Issue 2 - Apr 2013
Volume 17, Issue 1 - Feb 2013
Selecting the target year
Pulse-mode Response Characteristics of a Small LRE for the Precise 3-axes Control of Flight Attitude in SLV
Jung, Hun ; Kim, Jong Hyun ; Kim, Jeong Soo ; Bae, Dae Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 1~8
DOI : 10.6108/KSPE.2013.17.1.001
A liquid-monopropellant hydrazine thruster has several outstanding advantages such as relatively-simple structure, long/stable propellant storability, clean exhaust products, and so on. Therefore hydrazine thruster has such a wide application as orbit and attitude control system (ACS) for space vehicles. A hydrazine thruster with the medium-level thrust to be used in the ACS of space launch vehicles (SLV) has been developed, and its ground firing test result is presented in terms of thrust, impulse bit, temperature, and chamber pressure. It is verified through the performance test that the response and repeatability of thrust are very excellent, and the thrust efficiencies compared to its ideal requirement are larger than 93%.
Analytical Study on the Gas-Solid Suspension Flows through Sonic and Supersonic Nozzles
Sun, JianGuo ; Rajesh, G. ; Kim, Heuydong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 9~17
DOI : 10.6108/KSPE.2013.17.1.009
A considerable deal of work has been carried out to get an insight into the gas-solid suspension flows and to specify the particle motion and its influence on the gas flow field. In this paper an attempt is made to develop an analytical model to study the effect of nozzle inlet/exit pressure ratio, particle/gas loading and the particle diameter effect on gas-solid suspension flow. The effect of the particle/gas loading on the mass flow, Mach number, thrust coefficient and static pressure variation through the nozzle is analyzed. The results obtained show that the presence of particles seems to reduce the strength of the shock wave. It is also found that smaller the particle diameter is, bigger will be the velocity as bigger particle will have larger slip velocity. The suspension flow of smaller diameter particles has almost same trend as that of single phase flow with ideal gas as working fluid. Depending on the ambient pressure, the thrust coefficient is found to be higher for larger particle/gas loading or back pressure ratio.
Assessment and Validation of Turbulence Models for the Optimal Computation of Supersonic Nozzle Flow
Kam, Ho Dong ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 18~25
DOI : 10.6108/KSPE.2013.17.1.018
Assessment and validation of RANS turbulence models are conducted for the optimal analysis of supersonic converging-diverging nozzle through the comparison between computational results and experimental data. One/two equation turbulence closures such as Spalart-Allmaras, RNG k-
, and k-
SST are employed to simulate the two-dimensional nozzle flow. Computational results with the turbulence models mentioned fairly well predict shock structure of the nozzle-inside and pressure distribution along the wall. Especially, SST model among the employed ones shows the best agreement to experimental results.
Characteristic Equation to Determine Optimal Ejection Conditions of Sounding Rocket: Analytic Solution Cases
Lee, Sang-Hyeon ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 26~34
DOI : 10.6108/KSPE.2013.17.1.026
An analytic approach to determine the optimal conditions for maximizing altitude of a sounding rocket is suggested. The behavior of the one-dimensional momentum equation including thrust, gravitational force and aerodynamic drag force is investigated. For the case where an analytic solution exists, a characteristic equation for determining optimal condition for maximizing altitude at the burn-out state and that for maximizing altitude at the stationary state are developed and verified with numerical experiments.
Research on the Torque and Starting Characteristics of a Turbopump Turbine
Jeong, Eunhwan ; Lee, Hang-Gi ; Park, Pyun-Goo ; Hong, Moongeun ; Kim, Jinhan ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 35~41
DOI : 10.6108/KSPE.2013.17.1.035
Torque characteristics of a turbopump turbine was analyzed using the turbine performance test result. Specific torque of the subject turbine could be expressed as a linear function of corrected rotor speed at a fixed pressure ratio and it has been confirmed by the test result. It also found that corrected rotor speed-specific torque characteristics does not change anymore if the turbine pressure ratio is set bigger than a certain value. Using the turbine torque characteristics and pyro-starter performance test results, rotational speed development behavior of the turbopump was predicted. Prediction revealed that the lap time reaching 50% of turbopump design speed is less than 0.7 second. Effect of the thermal loss between pyro-starter and turbopump was negligible.
Aerodynamics Characteristics on a Canard-Controlled Projectile
Park, Young-Ha ; Je, Sang-Eon ; Cho, Soo-Yong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 42~51
DOI : 10.6108/KSPE.2013.17.1.042
An experimental study was conducted on a subsonic wind tunnel to obtain aerodynamic coefficients for various situations in order to control the direction of a projectile. The angle of attack on the projectile was varied from
and the roll angle of canard was changed from
. The angle of attack on the canard was adjusted from
and various inlet velocities were applied. Maximum Reynolds number based on the diameter of projectile was
. The measured aerodynamic coefficients showed the same results for the various inlet velocities, and the highest effect on the canard was shown when the canard was set to the roll angle of
Study of the Supersonic Ejector-Diffuser System with a Mixing Guide Vane
Kong, Fanshi ; Jin, Yingzi ; Kim, Heuydong ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 52~60
DOI : 10.6108/KSPE.2013.17.1.052
Ejector-diffuser system makes use of high-pressure primary stream to entrain the low-pressure secondary stream through pure shear action between two streams. In general, the flow field in the ejector-diffuser system is highly complicated due to turbulent mixing, compressibility effects. A fatal drawback of the ejector system is in its low efficiency. Many works have been done to improve the performance of the ejector system, but not yet satisfactory. In the present study, a mixing guide vane was installed at the inlet of the secondary stream for the purpose of the performance improvement of the ejector system. A CFD method has been applied to simulate the supersonic flows inside the ejector-diffuser system. The present results obtained were validated with existing experimental data. The mixing guide vane effects are discussed in terms of the entrainment ratio, total pressure loss as well as pressure recovery.
Compressibility Correction Effects of Two-equation Turbulence Models for a Supersonic Through-type Pintle Nozzle with Large Scale Separation Flow
Heo, Junyoung ; Jung, Junyoung ; Sung, Hong-Gye ; Yang, June-Seo ; Lee, Ji-Hyung ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 61~69
DOI : 10.6108/KSPE.2013.17.1.061
Numerical simulations have been performed for assessment of compressibility correction of two-equation turbulent models suitable for large scale separation flows perturbed by a pintle strokes. Two-equation turbulence models, the low Reynolds k-
and the k-
SST models with or without compressibility correction proposed by Wilcox and Sarkar are evaluated. The detail flow structures are observed and static pressures along nozzle wall are compared with experimental results. Mach disk location and pressure recovery profiles in flow separation region are noticeably distinct between turbulent models of k-
SST. The compressible effect corrections to those models improve resolving of separation flow behaviors. The compressibility corrections to k-
model have provided very comparable results with test data.
Study on Component Map Generation and Performance Simulation of 2-spool Separate Flow Type Turbofan Engine Using SIMULINK
Kong, Changduk ; Kang, MyoungCheol ; Park, Gwanglim ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 70~79
DOI : 10.6108/KSPE.2013.17.1.070
In this work, a steady-state performance modeling and off-design performance analysis of the 2-spool separate-flow turbofan engine named (BR715-56) which is a power plant for the narrow body commercial aircraft is carried out for engine performance behaviors investigation and condition monitoring using a commercial code MATLAB/SIMULINK. Firstly, the engine component maps of fan, high pressure compressor, high pressure turbine and low pressure turbine are generated from similar component maps using the scaling method, and then the off-design performance simulation model is constructed by the mass flow matching and the work matching between components. The model is developed using SIMULINK, which has advantages of easy steady-stare and dynamic modelling and user friendly interface function. It is found that the off-design performance analysis results using the proposed model are well agreed with the performance analysis results by GASTURB at various operating conditions.
Development of Practical Integral Condition Monitoring System for A Small Turbojet Engine Using SIMULINK and LabVIEW
Kong, Changduk ; Kho, Seonghee ; Park, Gilsu ; Park, Gwanglim ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 80~88
DOI : 10.6108/KSPE.2013.17.1.080
In currently developed engine condition monitoring systems, most field engine maintenance engineers have difficulties to use them in fields due to complexity, unpractical use, lack of understanding, etc. Therefore a practical usable engine condition monitoring system must be needed. This work proposes a practical performance condition monitoring of a small turbojet engine through comparing between the on-line performance monitoring data and the initial clean performance data calculated by the base engine performance model. Moreover the proposed monitoring system checks the gas path components` on-line health condition through comparing the component performance characteristics between the running engine represented as a deteriorated engine or a degraded engine and the base engine performance model represented as a clean engine. The proposed condition monitoring system is coded in a friendly GUI type program for easy practical application by a commercial tool, MATLAB/SIMULINK and LabVIEW.
Research on the Low-Frequency Combustion Characteristics of an Oxygen-Rich Preburner
Moon, Insang ; Moon, Ilyoon ; Ha, Seong-Up ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 89~96
DOI : 10.6108/KSPE.2013.17.1.089
Combustion pressures were measured to study combustion stability for an oxygen rich preburner by both of static and dynamic pressure sensors. The resolutions of each static and dynamic pressure sensor are the 1,000 Hz and 25,600 Hz, respectively. The nominal combustion pressure of the preburner was 200 bar but 80 bar was used at the several initial tests for the safety reason. Two stage ignition was applied to reduce the ignition impact for every tests including the tests with 200 bar combustion pressure. The tests lasted for 10 sec. max. and a little fluctuations of pressure was observed during the main mode. The measured pressures were studied by FFT analysis and no noticeable frequency coupling was found. Thus the preburner can be regarded as stable and it can be utilized for further study on staged combustion cycle liquid rocket engine.
Prestudy on Expendable Turbine Engine for High-Speed Vehicle
Kim, YouIl ; Hwang, KiYoung ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 97~102
DOI : 10.6108/KSPE.2013.17.1.097
A prestudy on expendable turbine engine for high-speed vehicle was conducted. After two possible mission profiles were established to decide the engine requirements, design point analysis was performed with the values of design parameter which were obtained from similar class engines, references, etc. The results showed that specific net thrust and specific fuel consumption with turbine inlet temperature of 3,600 R are 2,599.4 ft/s and 1.483 lb/(lb*h) respectively at the flight condition of sea level, Mach 1.2. It was also found that major design parameters for determining maximum net thrust were turbine inlet temperature for low supersonic and transonic flight speed and compressor exit temperature for high supersonic flight speed from the results of performance analysis on the two possible mission profiles. In addition, simple turbojet engine with an axial compressor, a straight annular combustor, an one stage axial turbine and a fixed throat area converge-diverge exhaust nozzle was proposed as the configuration of simple low cost lightweight turbine engine.
Thermal Barrier Coating Durability Testing Trends for Thrust Chamber of Liquid-propellant Rocket Engine
Lee, Keum-Oh ; Ryu, Chul-Sung ; Lim, Byoung-Jik ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 17, issue 1, 2013, Pages 103~115
DOI : 10.6108/KSPE.2013.17.1.103
Durability testing method trends of the thermal barrier coating(TBC) for the combustion chamber of the liquid-propellant rocket engine have been investigated. Many types of the durability testing method such as the mechanical tests to measure surface cohesion force, the thermal fatigue tests with laser, furnace, burner or plasma, the small scale combustion tests using injectors, and the thermo-mechanical fatigue tests were observed. The TBC with sufficient durability can be selected for the use of combustion chamber through such specimen-level tests and the durability can be verified by the tests using the real scale combustion chambers.