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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 19, Issue 6 - Dec 2015
Volume 19, Issue 5 - Oct 2015
Volume 19, Issue 4 - Aug 2015
Volume 19, Issue 3 - Jun 2015
Volume 19, Issue 2 - Apr 2015
Volume 19, Issue 1 - Feb 2015
Selecting the target year
A Correlation between the Pressure Oscillation of Combustion Chamber and Thrust Response in a 70 N-class Hydrazine Thruster
Jung, Hun ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 1~8
DOI : 10.6108/KSPE.2015.19.3.001
A ground hot-firing test(HFT) was accomplished to draw a correlation between the pressure oscillation intensity of combustion chamber and thrust response characteristics in a 70 N-class hydrazine thruster which has been developed recently. Monopropellant grade hydrazine was adopted as a propellant for the HFT, and combustion-chamber characteristic length, propellant injection pressure were applied as test parameters. It was confirmed that the decrease of thrust-chamber diameter and injection pressure augmented the pressure oscillation of stagnation chamber in the test condition specified, and the oscillation hampered the pulse response performance of test models.
Effect of Particle Loading Ratio on Fluid Characteristics and Particle Distribution in Particle-laden Coaxial Jet
Yoon, Jungsoo ; Yoon, Youngbin ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 9~19
DOI : 10.6108/KSPE.2015.19.3.009
Experimental research on characteristics of particle-laden jet by using a coaxial injector was conducted in order to design fuel and oxidizer injectors of the supercavitation underwater vehicle.
particles was simultaneously injected to obtain particle and fluid velocity. Small particles(
) and large particles represent fluid and fuel characteristics respectively. Small particles, which was processed using PIV algorithms, and one for the large particles processed using PTV algorithms. Fluid phase axial velocity increases according to particle loading ratio increases, and particles are located at the outside of the high vorticity region in a mixing layer of a coaxial injector.
Dynamic Modeling and Characteristics Analysis of Solid Rocket Motor with Multi Axis Pintle Nozzles
Ki, Taeseok ; Hong, Seokhyun ; Park, Ik-soo ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 20~28
DOI : 10.6108/KSPE.2015.19.3.020
Performance parameters of solid rocket motor with multi axis pintle nozzles were analyzed theoretically and modeled. For figuring out the governed variable of dynamic characteristics of system, dynamic analysis was done by using established model. To present characteristics of this system, the model should include not only internal ballistics of propulsion unit but also actuating system to move pintle. For solid rocket motor with multi axis pintle nozzles, not only performance of steady state but also dynamic characteristic of transient state is important design parameter to precise thrust control. Therefore, response time of open-loop system was analyzed by using established model and requirement about response time was satisfied by controlling pressure.
A Numerical Study on a Supersonic Turbine Performance Characteristics with Different Nozzle-Rotor Axial Gap Spacings
Jeong, Sooin ; Choi, Byoung-ik ; Kim, Kuisoon ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 29~38
DOI : 10.6108/KSPE.2015.19.3.029
In this study, 3-dimensional URANS simulation was performed to analyze the effect of the nozzle-rotor axial gap spacing of a supersonic impulse turbine on turbine performance. The computations were conducted for four different axial gap cases corresponding to about 6%, 10%, 20% and 30% of the blade height, respectively. The results show a good agreement with previous studies and the turbine efficiency decreases drastically in certain range. It is examined that the turbine performance characteristics could change depending on the influence of leading edge shock to the nozzle outlet. It is also found that the entropy rise distributions along the span differ from each other.
Numerical Study on the CO and NO of Rocket Plume as the Type of Water Injection in the Flame Guiding Duct
Kim, Seong-Lyong ; Kim, Seung-Han ; Han, Yeoungmin ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 39~46
DOI : 10.6108/KSPE.2015.19.3.039
A numerical study has been conducted on CO after burning and NO generation of the rocket plume as the cooling water injected to the rocket plume. The present study shows that the cooling water has a role of increasing the degree of CO after burning and reducing NO generation. However the effect varies as the injection configuration of the cooling water. When the cooling water is injected at the side of the plume, NO generation is dramatically reduced while the degree of CO after burning is relatively low. When the cooling water is injected at the side and the center of the plume, CO after burning is highly increased and NO generation is also dramatically reduced.
A Preliminary Configuration Design of Methane/Oxygen Bipropellant Small-Rocket-Engine through Theoretical Performance Analysis
Bae, Seong Hun ; Jung, Hun ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 47~53
DOI : 10.6108/KSPE.2015.19.3.047
Design parameters required for Methane/oxygen bipropellant small-rocket-engine were derived through a theoretical performance analysis. The theoretical performance of the rocket engine was analyzed by using CEA and optimal propellant mixture ratio, characteristic length, and optimal expansion ratio were calculated by assuming chemical equilibrium. A coaxial-type swirl injector was chosen because of its outstanding atomization performance and high combustion efficiency compared to other types of injector and also a bell nozzle with 80% of its full length was designed. The rocket engine configuration with 1.72 MPa of chamber pressure, 0.18 kg/s in total propellant mass flow, and O/F ratio of 2.7 was proposed as a ground-firing test model.
Nonlinear Acceleration Controller Design for DACS Type Kill Vehicle
Lee, Chang-Hun ; Kim, Tae-Hun ; Jun, Byung-Eul ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 54~64
DOI : 10.6108/KSPE.2015.19.3.054
This paper deals with an acceleration controller design for a kill vehicle equipped with a divert and attitude control system (DACS). In the proposed method, the attitude control system (ACS) is used to produce the thrust command to nullify angle-of-attack. For the angle-of-attack control, a nonlinear angle-of-attack controller is proposed based on the feedback linearization methodology. Since the flight path angle is identical to the attitude angle under the condition of zero angle-of-attack, the divert control system (DCS) can directly produce the lateral acceleration which is demanded from the guidance loop. In the proposed method, we can minimize the aerodynamic uncertainty due to the propulsive force. Additionally, we can simplify the operation logic of DCS and ACS. In this paper, nonlinear simulations are performed to show the performance of the proposed method.
Variable Inlet Design for Hypersonic Engines with a Wide Range of Flight Mach Numbers
Kang, Sang Hun ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 65~72
DOI : 10.6108/KSPE.2015.19.3.065
In present study, a supersonic inlet for dual mode ramjets or RBCC/TBCC engines with a wide range of flight Mach numbers is designed. A conical variable inlet configuration is chosen for the inlet design. Geometric relations with angles of compression cones and conical shock waves are used for the design of the inlet configuration. The performance of the supersonic inlet is confirmed by the numerical analysis. The capture area ratio is maintained around 100% from Mach 3 to 8 conditions.
High Altitude Test Facility for Small Scale Liquid Rocket Engine
Kim, Taewoan ; Kim, Wanchan ; Kim, Sunjin ; Han, Yeoungmin ; Ko, Youngsung ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 73~82
DOI : 10.6108/KSPE.2015.19.3.073
A high altitude test facility which includes supersonic diffuser and ejector has been developed to simulate atmospheric pressure at 25 km using a 500 N class small scale liquid rocket engine. Also high altitude simulation test for the small scale liquid rocket engine was performed to verify the facility`s performance. The experimental facility consists of high altitude simulation device, propellants supply system and coolant supply system. Low pressure condition corresponding to about 27 km(0.021 bar) altitude atmosphere was successfully simulated and a small scale liquid rocket engine thrust level was confirmed at the simulated condition by the high altitude test facility verification test.
A Study on the Thermal Shock Resistance of Sintered Zirconia for Electron Beam Deposition
Oh, Yoonsuk ; Han, Yoonsoo ; Chae, Jungmin ; Kim, Seongwon ; Lee, Sungmin ; Kim, Hyungtae ; Ahn, Jongkee ; Kim, Taehyung ; Kim, Donghoon ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 83~88
DOI : 10.6108/KSPE.2015.19.3.083
Coating materials used in the electron beam (EB) deposition method, which is being studied as one of the fabrication methods of thermal barrier coating, are exposed to high power electron beam at focused area during the EB deposition. Therefore the coating source for EB process is needed to form as ingot with appropriate density and microstructure to sustain their shape and stable melts status during EB deposition. In this study, we tried to find the optimum powder condition for fabrication of ingot of 8 wt% yttria stabilized zirconia which can be used for EB irradiation. It seems that the ingot, which is fabricated through bi-modal type initial powder mixture which consists of tens of micro and nano size particles, was shown better performance than the ingot which is fabricated using monolithic nanoscale powder when exposed to high power EB.
Water Performance Test of Pumps for a 7 Ton Class Rocket Engine
Hong, Soonsam ; Kim, Daejin ; Choi, Changho ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 89~95
DOI : 10.6108/KSPE.2015.19.3.089
Performance test was conducted for an oxidizer pump and a fuel pump for a 7 ton class rocket engine, by using water. The pumps were driven by an electric motor. The hydrodynamic performance and the suction performance were measured at flow ratio of the design and off-design conditions. Head-flow curve, efficiency-flow curve, and head-cavitation number curve were obtained. It is confirmed that the pumps can satisfy the design requirements of hydrodynamic performance in terms of the head and the efficiency. The pumps also satisfied the design requirements of suction performance.
The Study on the Synthesis of Propellant with High Nitrogen Content
Lee, Woonghee ; Kim, Minjun ; Park, Youngchul ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 3, 2015, Pages 96~102
DOI : 10.6108/KSPE.2015.19.3.096
Traditional propellants emit toxic gases such as carbon dioxide and hydrogen chloride during combustion which are harmful to the environment. This study established a synthetic process of a high nitrogen containing derivative of tetrazine, 3,3-Azobis(6-Amino-1,2,4,5-Tetrazine) (DAAT), which can be applied as solid fuels for a solution to environmental concerns. Also, this paper described the detailed process and the analytic results of properties, which were not mentioned in previous reports. The compound was characterized by NMR, IR spectroscopy, and thermal, impact, and friction stability were measured. In addition, the heats of formation (
) and detonation properties (pressure and velocity) of DAAT were calculated using Gaussian 09 and EXPLO5 programs.