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 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
Sympathetic Detonation Modeling of PBXN-109
Kim, Bohoon ; Kim, Minsung ; Yang, Seungho ; Oh, Sean ; Kim, Jinseok ; Choi, Sangkyung ; Yoh, Jai-Ick ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 1~11
DOI : 10.6108/KSPE.2014.18.5.001
Sympathetic detonation (SD) of high explosives occurs when a detonating donor initiates neighboring acceptors. The present study focuses on the hydrodynamic simulation of one-on-one sympathetic detonation of 155 mm charge filled with PBXN-109. Both unbuffered and buffered SD configurations are performed while changing the distance between each charge, in order to investigate the detonation sensitivity to a donor initiation. The cause of a SD is by a shock impact for the unbuffered case at a close range, while at a distant range, blast fragment penetration is the primary cause. The buffers can reduce the incident sensitivity to a SD by reducing the strengths of shock wave and impinging fragments.
A Study of Fuel-rich Solid Propellant Characteristic for Boron-bead Particle Size
Won, Jongung ; Choi, Sunghan ; Lee, Wonbok ; Kim, Junhyung ; Hwang, Gabsung ; Park, Bocksun ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 12~18
DOI : 10.6108/KSPE.2014.18.5.012
A study of gas generator Fuel-Rich propellant for air-breathing propulsion system was performed in this paper. General solid propellant comprises a mean of 60% or more oxidizing agents. but, to develop the fuel-rich solid propellant increased the content of the metal fuel and reduced the content of the oxidizing agents by approximately 30%. Very high amount of heat per volume of fuel into the metal having the Boron was used. Amorphous Boron Powder was applied to propellant as beads type and it allowed to design more amount of metal fuel in the fuel-rich propellant. And the Combustion characteristics and properties of fuel-rich solid propellant according to the Boron-bead sizes were confirmed.
Experimental Study and Performance Analysis of the Solid Rocket Motor with Pintle Nozzle
Jin, Jungkun ; Ha, Dong Sung ; Oh, Seokjin ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 19~28
DOI : 10.6108/KSPE.2014.18.5.019
Firing test of solid rocket motor with pintle-technology carried out and the measured pressure-time curve was compared with the values predicted by the internal ballistic and performance analysis. Without baffle, the measured combustion chamber pressure was similar with the predicted pressure at the beginning of combustion, but gradual increase in pressure, which was unexpected with the end-burning grain of which burning area is constant, was observed. A baffle was inserted to make uniform flow over the pintle. Unlike the thruster without baffle, the measured combustion chamber pressure was 1.4 times higher than the predicted value. Through the CFD simulation, 10% of total pressure loss of the flow was observed from combustion chamber to nozzle throat when the baffle was inserted. The measured pressure with baffle was predicted well by considering the total pressure loss in the internal ballistic modelling and performance analysis.
Assessment of Static Crack Resistance Behavior on Particulate Reinforced Composite for Solid Propellant
Seo, Bohwi ; Choi, Hoonseok ; Kim, Jaehoon ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 29~34
DOI : 10.6108/KSPE.2014.18.5.029
Particulate reinforced composite is composed of hard particles and polymer matrix. This material has been widely applied for engineering industry such as automobile, construction and aerospace. For the safe application, it is important to assess crack resistance behavior. Especially in aerospace industry, crack could cause significant problem when the material is used for solid rocket fuel. Therefore, it is inevitable to estimate the characteristics of the crack propagation. In this study, crack propagation tests were conducted using particulate reinforced composite under crosshead rate 2.54 mm/min in the range of temperature
. The strain contour of surface for specimen was generated using digital image correlation method.
Polymerization Behavior of Self-healing Agents for Damage Repair in Composite Materials
Oh, Jinoh ; Yoon, Sungho ; Jang, Seyong ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 35~42
DOI : 10.6108/KSPE.2014.18.5.035
Thermal analysis properties and adhesive properties of self-healing agents were evaluated through differential scanning calorimetry, reaction heat measurement, and adhesive shear test. D1E0, D3E1, D1E1, D1E3, and D0E1, depending on the mixing ratio of DCPD and ENB, were considered as self-healing agents. The amount of Grubbs` catalyst, depending on the type of self-healing agents, was varied from 0.1 wt% to 1.5 wt%. In the case of DCPD, the polymerization reaction occurred faster and the stabilized adhesive strength increased as the amount of catalyst increased; however, a large amount of catalyst was required. ENB had excellent reactivity with a small amount of the catalyst; however, high reaction heat was observed at the early stage of polymerization. Thermal analysis properties and adhesive properties of self-healing agents can be controlled by varying a mixing ratio of DCPD and ENB. Among the self-healing agents used for this study, the D3E1 would be one of the most preferable candidates with regard to maximum adhesive strength, reaching time to maximum adhesive strength, stabilized adhesive strength, and reaction heat.
High Speed Propulsion System Test Research Using a Shock Tunnel
Park, Gisu ; Byun, Jongryul ; Choi, Hojin ; Jin, Yuin ; Park, Chul ; Hwang, Kiyoung ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 43~53
DOI : 10.6108/KSPE.2014.18.5.043
Shock tunnels are known to be capable of simulating flow-field environments of supersonic and hypersonic flights. They have been operated successfully world-wide for almost half a century. As a consequence of the strong interest in hypersonic vehicles in Korea, attention has been given on this type of facility and so an intermediate-sized shock tunnel has lately been built at KAIST. In the light of this, this paper presents our tunnel performance and some of the model scramjet test data. The freestream flow used in this work replicates a supersonic combustor environment for a Mach 5.7 flight speed.
Rocket Plume Analysis with DSMC Method
Jeon, Woojin ; Baek, Seungwook ; Park, Jaehyun ; Ha, Dongsung ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 54~61
DOI : 10.6108/KSPE.2014.18.5.054
In this study, a plume exhausted from rocket nozzle is investigated by using an unstructured 2-dimensional axisymmetirc DSMC code at various altitude. The small back-pressure to total-pressure ratio(
) and large
represent low and high altitude condition, respectively. At low altitude, the plume shows a typical complicated structure (e.g. Mach disk) of underexpanded jet while the high altitude plume experiences plain expansion. The various features of exhaust plume is discussed including density, translational/rotational temperature, Mach number and Knudsen number. The results shows that even at 20 km altitude where the freestream Knudsen number is small as
, the transitional and rarefied flow regimes can occur locally within the plume. It confirms the necessity of DSMC computation at low altitude.
Numerical and Experimental Study on Infrared Signature of Solid Rocket Motor
Kim, Sangmin ; Kim, Mintaek ; Song, Soonho ; Baek, Gookhyun ; Yoon, Woongsup ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 62~69
DOI : 10.6108/KSPE.2014.18.5.062
Infrared signature of rocket plume plays an important role for detection, recognition, tracking and minimzing for low observability. Infrared signatures of rocket plume with reduced smoke propellant and smokeless propellant are measured. In order to estimate the infrared signature of rocket plume, CFD analysis for flow structure of plume is performed, and layered integration method for estimating of infrared signature is used. Numerical and experimental results were in good agreement. Both propellants had similar infrared signature. Strong peak at
region in the experimental results is appeared due to experimental error arising from the calibration procedure.
A Numerical Study on Flow and Heat Transfer Characteristics of Supersonic Second Throat Exhaust Diffuser for High Altitude Simulation
Yim, Kyungjin ; Kim, Hongjip ; Kim, Seunghan ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 70~78
DOI : 10.6108/KSPE.2014.18.5.070
A numerical study has been conducted to investigate flow and heat transfer characteristics of supersonic second throat exhaust diffusers for high altitude simulation. By changing pressure and configuration, flow and cooling characteristics of the diffuser have been studied. At the normal operation of the diffuser, there were high temperature regions over 3,000 K without cooling, especially near wall and in subsonic diffuser part. If the cooling system of the diffuser is added, flow velocity is increased due to the cooled wall temperature.
Development Test of Alcohol Burner for Turbopump Real-propellant Test Facility
Kim, Jin-Sun ; Han, Yeoung-Min ; Ko, Youngsung ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 79~86
DOI : 10.6108/KSPE.2014.18.5.079
A turbopump real-propellant test facility(TPTF) is to verify the performance of a turbopump unit(TPU) based on liquid oxygen and kerosene. One of the most important sub-facilities is a hot-gas generation system which makes the driving force of the TPU with an alcohol burner. The alcohol burner generates the required flow rates and temperature at the facility using high pressure air and ethanol. In the study, the verification tests of the alcohol burner which was manufactured entirely with domestic technology were performed and fabrication technique and operation skill for the burner could be obtained ahead of the construction of the facility. Two burners will be operated simultaneously for the real-propellant test of 75tf class turbopump and satisfy the power requirement from the turbine of the TPU.
Current Research Status on Flame Response Characteristics to Flow Disturbances
Seo, Seonghyeon ; Park, Yongjin ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 87~94
DOI : 10.6108/KSPE.2014.18.5.087
It becomes critical to understand an energy coupling mechanism between flow perturbations and combustion heat release rate fluctuations for the understanding of high-frequency combustion instabilities occurring in high-performance combustion/propulsion systems. A significant amount of experimental researches have been carried out to understand flame dynamic characteristics by use of flame transfer functions with artificial flow disturbances. Among them, there exist substantial studies on flame response by the excitation of inlet flow. Recently, experimental studies simulating transversal modes excited in actual combustion systems are under way.
Improvement of Heat of Reaction of Jet Fuel Using Pore Structure Controlled Zeolite Catalyst
Hyeon, Dong Hun ; Kim, Joongyeon ; Chun, Byung-Hee ; Kim, Sung Hyun ; Jeong, Byung-Hun ; Han, Jeong Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 18, issue 5, 2014, Pages 95~100
DOI : 10.6108/KSPE.2014.18.5.095
In hypersonic aircraft, increase of aerodynamic heat and engine heat leads heat loads in airframe. It could lead structural change of aircraft`s component and malfunctioning. Endothermic fuels are liquid hydrocarbon fuels which are able to absorb the heat load by undergoing endothermic reactions. In this study, exo-tetrahydrodicyclopentadiene was selected as a model endothermic fuel and experiments on endothermic properties were investigated with pore structure controlled zeolite catalyst using metal deposition. We secured the catalyst that had better endothermic performance than commercial catalyst. The object of this study is inspect catalyst properties which have effect on heat absorption improvement. Synthetic catalyst could be applied to system that use exo-THDCP as endothermic fuel instead of other commercial catalyst.