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 15, Issue 6 - Dec 2011
Volume 15, Issue 5 - Oct 2011
Volume 15, Issue 4 - Aug 2011
Volume 15, Issue 3 - Jun 2011
Volume 15, Issue 2 - Apr 2011
Volume 15, Issue 1 - Feb 2011
Selecting the target year
Thermal Decomposition of High Speed Aircraft Fuel in Supercritical Phase
Kim, Joong-Yeon ; Park, Sun-Hee ; Chun, Byung-Hee ; Kim, Sung-Hyun ; Jeong, Byung-Hun ; Han, Jeong-Sik ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 1~9
Researches on hypersonic aircraft technologies have been carried out to increase flight speeds. However, increase in flight speeds causes heat loads that could lead structural change of aircraft's component. Researches on cooling technologies using endothermic fuels are progressing in the USA, France and Russia to treat the heat loads. Endothermic fuels are liquid hydrocarbon aircraft fuels which are able to absorb the heat loads by undergoing endothermic reactions, such as thermal and catalytic cracking. In this study, methylcyclohexane, n-octane, and n-dodecane were selected as model endothermic fuels and experiments in endothermic properties were implemented. Experimental conditions were supercritical condition of each model fuels in which actual endothermic fuels were exposed. The object of this study is to identify endothermic properties of the model endothermic fuels and to predict endothermic properties of actual fuels such as kerosene fuels.
Improvement of Cooling Effects of Pylon Injector for Scramjet Combustor
Lee, Sang-Hyeon ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 10~18
A new film cooling method to protect the pylon injector from aerodynamic heating for a scramjet combustor is proposed and verified with numerical methods. The conditions for the Mach 8 flight at an altitude of 35km are considered. Air is considered as a coolant. Three-dimensional Navier-Stokes equations with
SST turbulence model are used. A downward injection of coolant from the top of the pylon gives higher cooling effects with less mass flow rate of coolant than the upward coolant injection from bottom of the pylon. Also, the downward injection shows little flow separation due to the favorable pressure gradient and does not disturb the flowfields near pylon injector, which results in reduction of pressure losses.
A Study on the Combustion Performance with Variation of Fuel Injection Hole Configuration at Supersonic Combustion
Lee, Kyung-Jae ; Kang, Sang-Hun ; Lee, Yang-Ji ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 19~26
In order to investigate the effect of fuel injection hole configuration within the scramjet combustor, experiment and quasi-one-dimensional analysis was performed. And the results were compared with experiment and analysis result which were performed in 2008 with same facility and test condition. Fuel injection hole size was decreased and quantity was increased. However the depth of fuel penetration and flow quantity of fuel were maintained. As a test result, combustion performance was increased significantly with no-cavity injector and slightly with plain-cavity. However, combustion performance with zigzag-cavity was decreased.
Numerical Analysis and Design of the 2-D Variable Convergent-Divergent Thrust Vectoring Nozzle
Kim, Yoon-Hee ; Kang, Hyung-Seok ; Choi, Seong-Man ; Chang, Hyun-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 27~34
A numerical analysis was peformed for the supersonic aircraft with variable pitch thrust vector nozzle. Based on the requirement of the mixed turbofan engine of the supersonic aircraft, two dimensional thrust vector nozzle with variable pitch angle was designed. To investigate the effect of the thrust vectoring nozzle, the numerical analysis was conducted by using Fluent under the several pitch deflection angle.
Effect of Control Method and Plunger Profile of Variable Valve on Flow Control of a Liquid Rocket Engine
Lee, Joong-Youp ; Huh, Hwan-Il ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 35~47
Dynamic characteristics of a flow control valve, which plays an important role in thrust and O/F control of liquid rocket engines, have been analyzed by the AMESim simulator modeling. The speed control method was proposed for the control of the flow valve equipped with a BLDC motor. The experimental results demonstrated the feasibility of systematical application as well as the performance of the speed control method. Moreover, the speed control method for BLDC motor is much simpler than the P control method in complex flow systems. With the speed control method, the control flow characteristics were evaluated according to plunger shapes. Consequently, same plunger shape proved to be more efficient in the mixture ratio control operated by two flow valves. It was also shown that the appropriate modification of plunger shapes could reduce the mixture ratio perturbation by 0.5%.
Thermal Stability Improvement of Liquid Fuel by Using Some Additives
Park, Sun-Hee ; Kim, Joong-Yeon ; Chun, Byung-Hee ; Han, Jeong-Sik ; Jeong, Byung-Hun ; Kim, Sung-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 48~53
We investigated thermal stability improvement of exo-tetrahydrodicyclopentadiene (exo-THDCP) with thermal stabilizers (additives). The reaction products were sample during the reactions. The compositions of products were determined by gas chromatography-mass spectrometry (GC-MS) to measure thermal decomposition products of exo-THDCP and to specify mechanism for thermal stabilizers. Hydrogen donors (thermal stabilizers) such as 1,2,3,4-tetrahydroquinoline (THQ), benzyl alcohol (BnOH) increased thermal stability of exo-THDCP. These materials donated hydrogen to radical of exo-THDCP produced after initiation of exo-THDCP. We found that stabilization of exo-THDCP radicals decreased activity of primary products of exo-THDCP and lowered formation of secondary products (above-
Study on the Expansion Technique of Compressor Characteristic Map to Sub-Idle Range
Jun, Yong-Min ; Choi, Jong-Su ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 54~59
Reliable starting capability of a gas turbine engine calls the engine industry's attention recently. So far the gas turbine engine performance researches have focused on the range between idle to Max rpm, but recent attention on the starting has brought interests in the range of "Sub-dile". As component characteristic maps are essential for the starting research, various kinds of studies have been doing and proposing ways to expand the existing maps toward sub-idle range. In this paper, previous studies were discussed and a new method suggested and validated.
Supersonic Flow Air Data Acquisition Algorithm Using Total Pressure Sensors
Choi, Jong-Ho ; Lee, Jae-Yoon ; Yoon, Hyun-Gull ; Lim, Jin-Shik ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 60~65
The development of an air data acquisition algorithm has been described in the supersonic flow at the preliminary design stage with pressure data acquisition device composed of major three total pressure sensors and two static pressure sensors which are installed on the surface of a cone type supersonic inlet. Through this algorithm, Mach number, angle of attack and sideslip angle can be very easily derived with simple interpolation algorithm and predefined data tables. The available range of Mach number is 1.6 to 4.0, angle of attack,
and sideslip angle,
. In preliminary design stage, the data tables applied to the developed algorithm are constructed with data driven by Taylor Maccoll equation. The present algorithm would be useful to get supersonic flow air data for the various aerial vehicles and their flight tests.
Measurement of Spray Distribution of Swirl Injector by Tomography Method at High Pressure Condition
Park, Gu-Jeong ; Cho, Seong-Ho ; Chung, Jae-Mook ; Kim, Tae-Sung ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 66~71
The spray distribution at high pressure condition was measured by the Tomography method. The constructed spray distribution was compared with the images by Indirect Photography method so that the spray size confirmed and took the boundary of the distribution. It confirmed that the Tomography applies to construct the distribution at high pressure.
Preliminary Performance Analysis of a Dual Combustion Ramjet Engine
Byun, Jong-Ryul ; Ahn, Joong-Ki ; Yoon, Hyun-Gull ; Lim, Jin-Shik ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 72~81
In order to understand the operation characteristics and major design parameters of a dual combustion ramjet engine, a fundamental analysis model based on gasdynamics and thermodynamic theories was established. The preliminary performance analysis was accomplished and the results clearly describe the intimate relationship between air inlets, gas generator, and supersonic combustor. The methodology presented provides a means for quantitatively determining the geometries of the gas generator and supersonic combustor and assessing the effects on performance of each of the engine components. Also the design results for a basic configuration were provided.
Localized Plastic Deformation in Heat-Resistant Alloy and Combined Two-Back Stress Hardening Model
Yun, Su-Jin ; Lee, Sang-Yeun ; Park, Dong-Chang ; Yoon, Hyun-Gul ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 82~88
In the present work, FEM analyses are carried out to investigate the fractures occurred within the structural part in the course of combustion experiment. The loss of structural integrity stems from the localized deformation and the damage induced due to a severe change in the thermal load. Moreover, the two-back stress evolution model is proposed using the Armstrong-Frederick and the Phillips' rules to depict the plastic deformation, and the continuum damage mechanics is also incorporated into the present model. It is noted that the present model is able to formulate a wide range of constitutive description with ease. The numerical results depicts that a severe strain localization and damage evolution can be obtained depending on the dominant back stress.
Planning of Integrated Test for Propulsion System of Space Launch Vehicle
Cho, Sang-Yeon ; Kim, Sang-Heon ; Bershadesky, V. ; Oh, Seung-Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 89~95
Korea Space Launch Vehicle II (KSLV-II) planned to launch in 2021 is 3 stage rocket which can inject 1.5 ton satellite in low earth orbit. KSLV-II will adapt the newly developed liquid rocket engines for its propulsion system of each stage. For the evaluation of development level for rocket engine, integrated system test performed in appropriate facility is needed. In this study, test article and major parameters for certifying the propulsion system of KSLV-II were reviewed and optimum test cycle and test duration for satisfying system reliability requirement were illustrated.
Research Trends of Spray and Combustion Characteristics Using a Gelled Propellant
Hwang, Tae-Jin ; Lee, In-Chul ; Koo, Ja-Ye ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 5, 2011, Pages 96~106
There are many advantages in applying gel propellant to a gel propulsion system. These include higher performances, the energy management of liquid propulsion system, reliable storability and low leakage characteristics. Additionally, gel propulsion system are preferable to the high density impulse of propulsion system. Also, when compared to liquid propellants, the gel propellants acquire greater heat energy. Gel propellants achieve a high specific impulse when metal particles with aluminum and boron are added. With respect to atomization, an inactive process occurs due to the variable viscosity of the metal particles and gelling agents. To improve the defect of atomization and combustion characteristics of gel propellant, a variety of issues related to spray and combustion is introduced here.