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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 18, Issue 6 - Dec 2014
Volume 18, Issue 5 - Oct 2014
Volume 18, Issue 4 - Aug 2014
Volume 18, Issue 3 - Jun 2014
Volume 18, Issue 2 - Apr 2014
Volume 18, Issue 1 - Feb 2014
Selecting the target year
Optimal Design of Two-Dimensional Hypersonic Intake Geometry
Kim, Chae-Hyoung ; Jeung, In-Seuck ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 1~10
DOI : 10.6108/KSPE.2014.18.6.001
The optimal method to intuitively and systematical design hypersonic intakes is reported. In Mach 7 flow condition, the hypersonic intake model designed by theoretical approach is corrected by CFD(Computational Fluid Dynamics) analysis based on viscous flow condition, leading to the optimum hypersonic intake model. For performance comparison with CFD analysis, the double ramp intake is superior to the single ramp intake. Furthermore, in the off-design condition, the performance of the designed hypersonic intake is little degraded.
Visualization of Transient Ignition Flow-field in a 50 N Scale N
Kim, Dohun ; Park, Jaehyeon ; Yu, Myunggon ; Lee, Kyungeun ; Koo, Jaye ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 11~18
DOI : 10.6108/KSPE.2014.18.6.011
The combustion flowfield at the near-injector region of a 50 N scale
thruster was visualized using shadowgraph technique. The explosive ignition was occurred at the design spray condition, and the expanding combustion gas quenched the flame immediately. Approximately after 83 ms from the initial ignition, the propellant spray was re-ignited, and the flame was stabilized after 23 ms elapsed. In the increased oxidizer flow rate condition, the transient pressure at the moment of ignition was smoother than explosive ignition, and the blow down phenomenon was not appeared in the same operating sequence. In addition, the flame was stabilized within 17 ms, and it is caused by improved propellants mixing before ignition.
Characteristics of the Pressure Instability in a Hydrazine Thruster with Various Length-to-Diameter Ratio of Catalyst-bed
Jung, Hun ; Kim, Jong Hyun ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 19~26
DOI : 10.6108/KSPE.2014.18.6.019
A ground hot-firing test (HFT) was carried out to make a close examination into the pressure instability for the 70 N-class hydrazine thruster under development. Monopropellant grade hydrazine was adopted as a propellant for the HFT, and catalyst-bed was filled with
catalyst. In order to investigate the effects of thrust-chamber diameter on combustion stability, evaluation tests for the development models were performed on three kinds of lower thrust chambers having the length-to-diameter ratio (L/D) of 1.03, 1.13, and 1.26. As results, it was found that low frequency instability (~ 50 Hz) was inherent in the models, and in addition, increase of the L/D and decrease of the operating pressure led to an amplification of pressure oscillation in the test condition specified.
Plume Density Simulation of KM Residual Thrust Using DSMC Method
Choi, Young-In ; Kim, Keun-Taek ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 27~33
DOI : 10.6108/KSPE.2014.18.6.027
2nd stage of KSLV-I, NaRo-Ho, performs CCAM not to collide with Naro Science Satellite. At that moment, the satellite should pass through the Plume Density area which was generated by KSLV-I KM residual thrust. Therefore, it is necessary to predict Plume Density field of KM residual thrust and guarantee the safety of the trajectory of payload. In this paper, DSMC method was used to simulate Plume Density by KM residual thrust and the simulation showed that the trajectory of Naro Science Satellite was safe.
Thrust Control of Hybrid Propulsion System for Lunar Exploration
Moon, Keunhwan ; Han, Seongjoo ; Kim, Hakchul ; Kim, Kyehwan ; Kim, Jinkon ; Moon, Heejang ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 34~41
DOI : 10.6108/KSPE.2014.18.6.034
A feasibility study of thrust control of hybrid propulsion system for lunar exploration is presented. The thrust control experiments were performed by controlling the oxidizer mass flow rate where the thrust modulation is carried by using a ball valve and a stepping motor. The gaseous oxygen (GOX) and the HDPE (High Density PolyEthylene) were used for the oxidizer and solid fuel, respectively. It was found that the thrust levels were stable without much fluctuation during the modulation period, and that the thrust was exactly controlled with target thrust modulation ratio of 53% and 32%.
Development of a Small Jet Engine Performance Test Device by Applying the Real-time Gas Turbine Engine Simulator
Kho, Seonghee ; Kong, Changduk ; Ki, Jayoung ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 42~49
DOI : 10.6108/KSPE.2014.18.6.042
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.
A Survey on Health Monitoring and Management Technology for Liquid Rocket Engines
Cha, Jihyoung ; Ha, Chulsu ; O, Suheon ; Ko, Sangho ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 50~58
DOI : 10.6108/KSPE.2014.18.6.050
This paper is about a short survey on the recent research activities regarding health monitoring and management for liquid rocket engines. For this, we investigate the precedent techniques developed in advanced space-industry countries which are USA, EU, Russia, Japan and China. Particularly, we focus on the technologies applied in China, a recently joined to the advanced space-industry countries in this field. Then we discuss some important points to be considered to apply to the development of the Korea Space Launch Vehicle KSLV-II and other related projects.
Life Firing Test of 1 N-class Monopropellant Thruster Development Model -Part I: Environmental Test and Steady State Performance
Won, Su-Hee ; Kim, Su-Kyum ; Jun, Hyoung-Yoll ; Lee, Jun-Hui ; Park, Su-Hyang ; Lee, Jae-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 59~67
DOI : 10.6108/KSPE.2014.18.6.059
Acceptance level random vibration and life firing test for development model of 1 N-class monopropellant thruster have been performed. From the results of random vibration, the natural frequency of the dual thurst module composed of 1 N-class development model thrusters was higher than the part level requirement(>100 Hz) and the structural robustness was verified. Thrust decrease of steady sate was below 7% and thrust instability was within
in the life firing test using over 20 kg propellant throughput. The computerized tomography for catalyst bed showed a less than 7% of catalyst loss and it revealed the design appropriateness of the current thruster development model.
Life Firing Test of 1 N-class Monopropellant Thruster Development Model -Part II: Pulse Mode Performance
Won, Su-Hee ; Kim, Su-Kyum ; Jun, Hyoung-Yoll ; Lee, Jun-Hui ; Park, Su-Hyang ; Lee, Jae-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 68~74
DOI : 10.6108/KSPE.2014.18.6.068
During the life firing test of 1 N-class thruster development model, pulse mode performance and performance changes were examined. The deviation of pulse mode response time according to thruster feed pressure was relatively small and the resultant ignition delay, response time, tail-off time were 32-35 ms, 86-91 ms, 89-98 ms, respectively. For the stabilized pulse region the impulse bit revealed the outstanding reproducibility of 1.41, 1.32, 2.10% at
. During the life firing test, the impulse bit was decreased with limited amounts, therefore the pulse mode performance could be considered to be maintained. The thrust centroid was also maintained during the life firing test.
Conceptual Design of KSLV-II Launch Complex Flame Deflector
Oh, Hwayoung ; Kang, Sunil ; Kim, Daerae ; Lee, Jungil ; Um, Hyungsik ; Huh, Hwanil ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 75~81
DOI : 10.6108/KSPE.2014.18.6.075
The flame deflector should be constructed to minimize the induced environmental effects on the launch vehicle and to minimize the exhaust impingement effects on the launch complex structures during the lift-off operation. Therefore, it should be designed to avoid recirculation and reverse flow of rocket exhaust plumes. The circumstance around launch complex and characteristics of launch vehicle should be taken into consideration for the flame deflector design. In this paper, we designed the flame deflector reflecting KSLV-II 1st engine characteristics and analyzed the effect of exhaust plumes related to change geometry by means of computational flow analysis.
Design, Test and Evaluation on the PSD with Thermal Barrier Type for Subscale Dual Pulse Rocket Motor
Kim, Jinyong ; Kwon, Taeha ; Lee, Wonbok ; Cho, Wonman ; Lee, Bangeop ; Yun, Namgyun ; Rhee, Youngwoo ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 82~87
DOI : 10.6108/KSPE.2014.18.6.082
Dual pulse rocket motor has a rocket motor with different pulse grains divided by a pulse separation device such as a fragile bulkhead or a thermal barrier type. It distributes thrust energy very effectively via pulse separation device to improve range and terminal velocity of a missile. This paper contains the thermal barrier design and experimental analysis through ground firing tests of small dual pulse motors. The results will be applied to the design, test and evaluation of the scale up dual pulse rocket motor.
Development of Spinning Process for Manufacturing Liquid Rocket Engine Thrust Chamber
Lee, Keumoh ; Ryu, Chulsung ; Heo, Seongchan ; Choi, Hwanseok ; Choi, Younho ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 6, 2014, Pages 88~95
DOI : 10.6108/KSPE.2014.18.6.088
Spinning process to inner wall has been applied for reducing the weight of regenerative cooling chamber of liquid propellent rocket engine. The fractures of the blanks of cylinder part and nozzle throat part have been observed during spinning processes. In order to overcome the problem, the mandrel and the blank shape have been modified, and the inner wall was successfully manufactured through the modifications. The manufactured spinning prototype of nozzle throat part was successfully bulged without cracking and necking, and it was confirmed to secure sufficient formability necessary for fabricating thrust chamber.