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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 20, Issue 2 - Apr 2016
Volume 20, Issue 1 - Feb 2016
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Numerical Analysis of the High-Subsonic Cavity Flows over a Curved Wall
Ye, A Ran ; Das, Rajarshi ; Kim, Heuy Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 1~7
DOI : 10.6108/KSPE.2016.20.1.001
Most of the work has been done till now focused on flows over wall mounted cavities in a straight wall where the incoming flow is uniform. However, the investigation on such kind of flow over a cavity mounted on the curved walls has been seldom reported in the existing literatures. In the present study, the numerical analysis was performed to investigate the cavity flow mounted on the curved walls. The effects of wall shape, the curvature radius and the flow Mach number, were investigated for high-subsonic flows. The results show that the static pressure of cavity floor increases as the L/R increases. This effect is found to be more significant when the flow Mach number is higher. The cavity drag for the curved walls are higher as compared with that of straight wall.
Design of Compliant Joint for Pyro-shock Isolation
Han, Houkseop ; Lim, Daehyun ; Kim, Jinyong ; Lee, Young-won ; Park, Sunghan ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 8~13
DOI : 10.6108/KSPE.2016.20.1.008
The purpose of the pyro-shock compliant joint is to isolated vibration using the compliant material in order to prevent the shock generated by pyro propulsion at the electronics equipment. The performance of the pyro-shock compliant joint can be determined by measuring bending natural frequency and transmissibility. In this study, we established the design requirements based on bending natural frequency and transmissibility results of the reference model. We developed a compliant material with sufficient shock compliant properties and a pyro-shock compliant joint for the new rocket. This results can be used to develop a pyro-shock compliant joint for any rocket using the compliant material and performance measurement.
Effect of AP Particle Size on the Physical Properties of HTPB/AP Propellant
Yim, Yoo Jin ; Park, Eun Ji ; Kwon, Tae Ha ; Choi, Seong Han ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 14~19
DOI : 10.6108/KSPE.2016.20.1.014
The viscosity and mechanical property of HTPB/AP composite solid propellant are profoundly affected by particle size of AP. In HTPB/AP propellant formulated by two mode of AP size such as
, the propellant was found to be much less viscose at end of mix when coarse/fine AP ratio is ranged from 70/30 to 60/40 due to high solid packing fraction. It was shown that the toughness of tensile strength test for HTPB/AP propellant increased with the increase in coarse AP. Considering both lower viscosity and better tensile strength, the optimum ratio of AP coarse/fine was estimated to be 70/30.
The Nonlinear Combustion Instability Prediction of Solid Rocket Motors
Hong, Ji-Seok ; Moon, Hee-Jang ; Sung, Hong-Gye ; Um, Won-Seok ; Seo, Seonghyeon ; Lee, Do-hyung ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 20~27
DOI : 10.6108/KSPE.2016.20.1.020
The prediction of combustion instability is important to avoid an obvious threat to the structural safety and the motor performance because it affects the apparent response function of the propellant, the burning rate, and a mean flow Mach number at the local surface. The combustion instability occurs in case acoustic waves were coupled with the combustion/flow dynamic frequency. In this paper, an acoustic instability model is derived from the nonlinear wave equation for analysing acoustic dynamics in solid rocket motors. The chamber pressure and burning rate effects on combustion instability have been investigated.
Gain Scheduling Controller Design and Performance Evaluation for Thrust Control of Variable Thrust Solid Rocket Motor
Hong, SeokHyun ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 28~36
DOI : 10.6108/KSPE.2016.20.1.028
Theoretical model of a variable thrust solid rocket motor with a pintle nozzle was derived. For the chamber pressure control, classical model linearization and proportional-intergral controller was used. And then two types of gain scheduling controller were suggested to imporve controller performance for the non-linear propulsion model. Considering characteristics of systems, control gains were scheduled by chamber pressure or free volume. Step responses of each controllers were compared. As a result, the proper control algorithm about characteristics of variable thrust rocket motor was suggested.
Burning Properties of Uncured HTPB Propellant
Kim, Nakhyun ; Kim, Jungeun ; Hong, Myungpyo ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 37~42
DOI : 10.6108/KSPE.2016.20.1.037
In this study, we examined the burning rate of the uncured propellant (with and without a curing agent application) in order to inspect the process of the HTPB solid propellant. The burning rate of the uncured propellant, that did not contain the curing agent, was approximately 9.7 mm/s at 1000 psi. In relation to the curing time, the burning rate was constant. The propellant, with the curing agent application, was approximately 8.1 mm/s showed a tendency of slowing as it burned. When the cure reaction rate was low, in accordance to the time, there were small changes in burn rate. However, when the cure reaction rate was high, the difference in burning rate was increased. The burning rate of a fully-cured propellant was approximately 6.8 mm/s, which appeared to be the lowest in order.
Combustion Characteristics of the Atomized Hydrocarbon Liquid-fuel Spray Injected through a Slit-jet Nozzle
Kim, Min Sung ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 43~49
DOI : 10.6108/KSPE.2016.20.1.043
An experimental study was performed to investigate the combustion characteristics of the liquid hydrocarbon fuel atomized by an ultrasonic oscillator. Configuration of the flame was caught by the DSLR camera, and images were analyzed in detail through a post-processing. Temperature of the flame zone was measured using thermocouple. It is resulted that the flame area is proportional to the mass flow rate of carrier gas as well as the voltage applied to the ultrasonic oscillator. Temperature of the flame zone is measured and analyzed according to variation in the operating condition of the burner, too.
Synthesis of a Nitrogen-rich Insensitive Energetic Material, DNAM(Dinitroammeline)
Sul, Minjung ; Kim, Minjun ; Kim, Jinseuk ; Kim, Seunghee ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 50~57
DOI : 10.6108/KSPE.2016.20.1.050
We studied the Lab-scale process for the development of DNAM in aspect of safety and overall efficiency. Melamine is used for starting material of process, DNAM was synthesized by oxidation and nitration reaction. In order to optimize the process parameters with the product in higher yield and purity, a systematic study with variation of different parameters like molar ratio of nitrating mixture, conditioning time and order of reactant was carried out. The optimized reaction conditions for the synthesis of DNAM were : conditioning time of
hour and nitrating mixture in 1:1.4 molar ratio. In order to proceed a stable reaction, melamine was added with enough time to relieve reaction heat. From these reaction condition, DNAM could be obtained in a yield of more than 60%.
Localized Development of Propellant Mixer
Kim, Kyungmoo ; Khil, Taeock ; Hong, Myungpyo ; Doh, Yeunsung ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 58~68
DOI : 10.6108/KSPE.2016.20.1.058
The propellant mixer for charging of solid rocket motors is one of the most important equipments. For the propellant mixer is export control item, it's hard to purchase it directly from abroad. The Mixer was developed locally to overcome export control which precludes us from import. This paper includes the introduction for general mixers and the process of mixer development progressed by LIGNex1. Finally, The mixer is verified the performance using measurements of clearance between blade-blade and blade-bowl and flow simulation with ADINA.
Construction and Start-up Test of Hot-firing Test Facility for KSLV-II Combustion Chamber
Lee, Kwang-Jin ; Yi, Seung Jae ; Seo, Daeban ; Hwang, Chang Hwan ; Woo, Seongphil ; Im, Ji-Hyuk ; Jeon, Junsu ; So, Younseok ; Kim, Chae-Hyoung ; Kim, Sunghyuk ; Kim, Seung-Han ; Cho, Namkyung ; Han, Yeoung Min ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 69~75
DOI : 10.6108/KSPE.2016.20.1.069
This paper covers the result of construction and start-up tests of the KSLV(Korea Space Launch Vehicle)-II combustion chamber hot-firing test facility. This facility was constructed from 2012 to 2014. Start-up test of this facility began in the second half of 2014. Oxidizer cold flow test, fuel cold flow test and cooling water cold flow test were carried out as start-up test. Afterward, ignition test of combustion chamber was accomplished. The result of ignition test is applied to set up start-up sequence of KSLV-II combustion chamber and utilized as base line data for hot-firing test of low and normal design point.
Performance Analysis of a Float-Type Fuel Supply Valve through Flight Tests
Jung, Sungmin ; Park, Jeong-Bae ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 76~81
DOI : 10.6108/KSPE.2016.20.1.076
At negative-g condition, a float-type valve can open the passage of fuel in order to it flows continuously through a pressurized fuel tank system. Since specialized test conditions and high-cost supports are required, it is truly difficult to test the valve in a real high-speed test. Therefore, this paper contains performance analysis of a float-type fuel supply valve through flight tests conducting roll and negative-g maneuvers.
Research about Thermoacoustic Resonance Ignition
Seo, Seonghyeon ; Kang, Sang Hun ; Bae, Jong Yeol ; Lee, Jin Young ;
Journal of the Korean Society of Propulsion Engineers, volume 20, issue 1, 2016, Pages 82~89
DOI : 10.6108/KSPE.2016.20.1.082
The unique phenomenon that jet flow kinetic energy is converted to thermal energy through thermoacoustic resonance can be applied for the multiple ignition of liquid rocket engines. The present article includes the basic principle and theory behind the phenomenon as well as major outstanding, previous research works. The thermoacoustic phenomenon is affected by underexpanded jet flow characteristics from a nozzle, geometries of a nozzle and a resonance tube, and chemical composition of jet flow. The paper concludes with discussion what should be considered as crucial issues for the future research on the development of a multiple ignition system of liquid rocket engines.