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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 14, Issue 6 - Dec 2010
Volume 14, Issue 5 - Oct 2010
Volume 14, Issue 4 - Aug 2010
Volume 14, Issue 3 - Jun 2010
Volume 14, Issue 2 - Apr 2010
Volume 14, Issue 1 - Feb 2010
Selecting the target year
Preliminary Analysis of Power Systems for 1-ton class Electric Powered PAV
Yun, Dong-Ik ; Huh, Hwan-Il ; Yang, Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 1~8
In this paper, we present some results of technical surveys, power analyses, and weight estimation on electric propulsion systems for 1-ton class Personal Air Vehicles(PAV) applications. When hybrid electric propulsion is adopted, its power performance using fuel cells and batteries in inferior to that of internal combustion engines. However, hybrid electric propulsion systems may replace IC engines when energy density and power density reach 0.75 kW
hr/kg and 2.5 kW/kg, respectively.
The Study of Aerodynamic Characteristics of Ram-jet with Different Intake
Park, Soon-Jong ; Park, Jong-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 9~16
The SFRJ(Solid Fuel Ram-Jet) propulsion is attractive for projectiles because of the combination of high propulsive performance and low system complexity more than conventional projectiles. The Objective of this research was to characterize the inlet aerodynamic characteristics (center-body & pitot type) in SFRJ. Diffuser static pressure & combustion chamber pressure was tested and the AoA was changed
at Mach number of 3.0 for performance estimate. The performance study of inlet was carried out with the Schlieren system and Supersonic cold-flow system. Under mach 3.0, the center-body showed twice higher total pressure recovering ratio than the pitot type. A Computational fluid dynamic solution is applied internal flow of inlet and the solutions are compared with experimental results.
A Pseudo 3-Dimensional Structure of the Liquid-propellant Spray Emerging from Nonimpinging-type Injector
Jung, Hun ; Kim, Jeong-Soo ; Park, Jeong ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 17~24
This study was performed to make a close inquiry into a pseudo 3-dimensional structure of the liquid-propellant spray emerging from nonimpinging-type injector. Spray configuration near the injector exit was captured by a high-speed camera, and then its periodic phenomena (shedding) was observed. Detailed spatial structure of spray was investigated by spray characteristic parameters (velocity, diameter, volume flux, etc.) with the aid of a Dual-mode Phase Doppler Anemometry (DPDA). Experiment was carried out at various locations along the geometric axis of the nozzle orifice and on the plane normal to the spray stream with the injection pressures of 17.2 to 27.6 bar.
A Fundamental Study of Thrust-Vector Control Using a Dual Throat Nozzle
Shin, Choon-Sik ; Kim, Heuy-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 25~30
Dual throat nozzle(DTN) is recently attracting much attention as a new concept of the thrust vectoring technique. This DTN is designed with two throats, an upstream minimum and a downstream minimum at the nozzle exit, with a cavity in between the upstream throat and exit. In the present study, a computational work has been carried out to analyze the performance of a dual throat nozzle(DTN) at various mass flow rate of secondary flow and nozzle pressure ratios(NPR). Two-dimensional, steady, compressible Navier-Stokes equations were solved using a fully implicit finite volume scheme. The present computational results were validated with some experimental data available. Based upon the present results, The control effectiveness of thrust-vector is discussed in terms of the thrust coefficient and the discharge coefficient.
Slow Cook-Off Test and Evaluation for HTPE Insensitive Propellants
Yoo, Ji-Chang ; Kim, Chang-Kee ; Kim, Jun-Hyung ; Lee, Do-Hyung ; Min, Byung-Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 31~37
This study was carried out to investigate the thermal decomposition and execute EIDS slow cook-off test for the propellant ingredients and 2 kinds of HTPE propellants. The thermal analysis of the propellant ingredients used in this study showed that the thermal stability of these materials decreases in the following order : AP > HTPE > AN > BuNENA. In addition, propellant HTPE 002 containing AN showed that an endothermic process at around
corresponding to the solid phase change(II
I) of AN was followed by the exothermic process of BuNENA/AN mixture up to
. In EIDS slow cook-off tests, HTPE 001 and HTPE 002 reacted at around
respectively, and both of them showed sudden temperature increase curves at
. The critical temperatures,
, of thermal explosion for the propellants HTPE 001 and HTPE 002, were obtained from both the non-isothermal curves at various heating rates and Semenov's thermal explosion theory. Kissinger's method that was used to calculate
was also employed to obtain the activation energies for thermal decompositions.
The Effect of the Variation of Pressure Ratio on the Characteristics of Lateral Forces in an Over-Expanded Nozzle
Lee, Jong-Sung ; Kim, Heuy-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 38~44
The shock wave and boundary layer interaction patterns in an over-expanded rocket nozzle are associated with the production of undesirable side-forces during the start-up and shut-down processes of the engine. In the present work, a computational study is carried out to investigate the effect of the transient nozzle pressure ratio (NPR) on the flow fields inside the nozzle. The unsteady, compressible, axisymmetric, Navier-Stocks equations with SST k-
turbulence model are solved using a fully implicit finite volume scheme. NPR is varied from 2.0 to 10.0, in order to simulate the start-up and shut-down processes of the rocket engine. It is observed that the interaction patterns and the hysteresis phenomenon strongly depend on the time variation of NPR, leading to significantly different characteristics in the lateral forces.
Simulation of Separation Mechanism by Modeling a Propellant Actuated Device
Oh, Seok-Jin ; Lee, Do-Hyung ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 45~52
This paper presents a mathematical-physical model to predict the performance of a gas pusher used as a separation system powered by a gas generator. A quasi-steady model is used in order to aid ballistic analysis for a propellant actuated device(PAD). The empirical coefficients of heat loss and friction were determined from experiments. The analytical approach of combustion, flow and movement of a piston inside the chamber of the PAD, consisted of a gas generator and a gas pusher, was simulated by numerical method based on the grain configuration design of the gas generator. The prediction method developed can be usefully applied to the design of separation mechanism systems.
Pressure Recovery in a Supersonic Ejector of a High Altitude Turbofan Engine Testing Chamber
Omollo, Owino George ; Kong, Chang-Duk ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 53~59
This research aims in finding a more optimal ejector size for evacuating engine exhaust gasses and 20% of the cell cooling air. The remaining 80% of cell cooling air pumped into the test chamber is separately exhausted from the test chamber via a discharge port fitted with flow control valves and vacuum pump. Unlike its predecessor this configuration utilizes a smaller capture area to improve pressure recovery. The modified ejector size has a diameter of 1100mm enough to evacuate 66kg/s jet engine exhaust in addition to about 20%, 24kg/s of the cell cooling air tapped from the sterling chamber. This configurations has an area ratio of the engine exit and ejector inlet of about 1.2. Simulation results of the proposed ejector configuration, indicates improved pressure recovery.
Effect of Groove Shape of Blade Tip on Tip Surface Heat Transfer Coefficient Distributions of a Turbine Cascade
Nho, Young-Cheol ; Jo, Yong-Hwa ; Lee, Yong-Jin ; Kim, Hark-Bong ; Kwak, Jae-Su ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 60~68
In this study, the conventional plane tip, double squealer tip, and various groove tip blades were tested in a linear cascade in order to measure the effect of the tip shapes on tip surface heat transfer coefficient distributions. Detailed heat transfer coefficient distributions were measured using a hue-detection based transient liquid crystals technique. Two tip gap clearances of 1.5% and 2.3% of blade span were investigated and the Reynolds number based on cascade exit velocity and chord length was
. Results showed that the overall heat transfer coefficients on the tip surface with various grooved tips were lower than those with plane tip blade. The overall heat transfer coefficient on grooved along suction side tip was lower than that on the squealer tip.
Study on 1,200 N-class bipropellant rocket engine using decomposed
Jo, Sung-Kwon ; An, Sung-Yong ; Kim, Jong-Hak ; Yoon, Ho-Sung ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 69~78
As part of preliminary study for development of 1,200 N-class bipropellant rocket engine with the concentrated hydrogen peroxide, bipropellant engine elements were designed and experimentally tested. The catalysts of
added Pb as an additive were compared to achieve high decomposition performance and the catalytic reactor with
added Pb was designed and its decomposition efficiency of 97.2% was achieved. The autoignition tests of kerosene by decomposed hydrogen peroxide were carried out under various equivalence ratios to ignite without additional ignition sources. Autoignition were achieved in all experimental conditions and
efficiencies at each condition were at or above 90%. From the measured thrust results, the highest value was 830 N which is in corresponds with 1,035 N at vacuum level assuming
The Performance Modeling of a Low Bypass Turbofan Engine for Supersonic Aircraft
Choi, Won ; You, Jae-Ho ; Lee, Il-Woo ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 79~88
This paper dealt with the performance modeling of a low bypass turbofan engine for supersonic aircraft. The Pratt and Whitney F100-PW-229 engine has been employed for low bypass turbofan engine performance modeling. Generally, the complete commercially-classified informations concerning the engine are unknown. The components' generic characteristics and assumptions made in order to build the F100-PW-229 engine performance model using by the published data from the open literature as basic data are described. Through the comparison of engine performance model's analysis data using Gasturb11 with engine deck data showed that the engine performance model was evaluated to be properly constructed.
The State of the Art and Application of Actuator in Aerospace
Yoon, Gi-Jun ; Park, Ho-Youl ; Jang, Ki-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 89~102
In this paper, a study on the future-oriented actuator introduces the future technology and future direction in aerospace and several industry fields. In particular, the mechanical linkage or hydraulic and pneumatic actuators which have the higher output-to-weight ratio have been used a lot in the past as the aircraft's flight control device. Most recently, Fly-By-Wire system has been used in aircraft and the flight control system has been changed in more electric and all electric systems. Electrohydraulic actuators and electric actuators have been developed continually, because they have better efficiency, safety and lower cost for the flight control system of aircraft. Also, to improve the weight condition, accuracy and response of actuator, new field actuators using new materials have been developed. In this paper we clearly proposed the actuator design and detailed technology development trend for next generation actuation system in aerospace and new field.
A Development of the Thrusters for Space-Vehicle Maneuver/ACS and Their Application to Launch Vehicles
Kim, Jeong-Soo ; Jung, Hun ; Kam, Ho-Dong ; Seo, Hang-Seok ; Su, Hyuk ;
Journal of the Korean Society of Propulsion Engineers, volume 14, issue 6, 2010, Pages 103~120
A development history of the thrusters used for space-vehicle orbit maneuver/attitude control is reviewed with their performance characteristics. Especially, a scrutiny is made for the current and practical application of TVC/Gimbal/Thrusters to the roll/pitch/yaw-axis control of each stage of launch vehicles. It is well perceived that a precise 3-axis attitude control system (ACS) must be equipped on the final stage of space launch vehicles (SLV) for an attainment of orbit-insertion accuracy. Under the superior reliability as well as moderate performance features, the monopropellant hydrazine thrusters occupy most of the SLV's 3-axis ACS currently operated. Domestic development status of the medium-thrust-level thruster is shortly introduced, finally.