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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 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
Performance Evaluation on Characteristic Length Variation of
/Kerosene Bipropellant Rocket Engine
Jo, Sung-Kwon ; Jang, Dong-Wuk ; Kim, Jong-Hak ; Yoon, Ho-Sung ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 1~8
In addition to the previous study for development of a 1,200 N-class bipropellant rocket engine with concentrated hydrogen peroxide, the effect of characteristic length and thrust measurement were experimentally evaluated. Tests with characteristic lengths of 0.95, 1.07, and 1.20 m were performed and
and Isp efficiencies were increased as increasing characteristic length. The maximum
and Isp efficiencies were 98.4% and 93.1% respectively. Based on the evaluation of the designed engine, the optimized characteristic length was proposed in using the engine adapted decomposed hydrogen peroxide and the engine performance at vacuum-level was evaluated using thrust and Isp efficiency at the designed equivalence ratio. As a result, 218.4 s at sea-level, 253.3 s at vacuum-level, and vacuum thrust of 1035.3 N can be estimated.
A New Test Method to Evaluate Influence of
to Rubber Insulator in Solid Propellant Rocket Motor
Lee, Hyung-Sik ; Kang, Yoon-Goo ; Lim, Soo-Yong ; Oh, Jong-Yun ; Lee, Kyung-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 9~14
In solid propellant rocket motors,
, one of combustion products, can be accumulated inside a combustion chamber. A special rocket motor was designed and tested to simulate thermal reaction of rubber insulator affected by the deposited slag. We successfully demonstrated through a dynamic radioscopy that the slag was deposited at the location as designed. In this paper we present a new test method which can simulate a high temperature and pressure environment in combustion chamber to evaluate material characteristics of rubber insulator and can provide design data to decide its thickness for a new solid rocket motor. The solid rocket motor, which has an average chamber pressure of 770 psia and a burning time of 50 seconds, was tested. The results show that erosion of EPDM insulator is more affected by a gas velocity rather than by the thermal reaction of slag with a high thermal capacity.
A Study on the Fischer-Tropsch Synthesis for Production of Hydrocarbon from Syngas under Gas Phase and Supercritical Phase
Kim, Chul-Ung ; Jeong, Soon-Yong ; Jeong, Kwang-Eun ; Chae, Ho-Jeong ; Kim, Tae-Wan ; Park, Hyun-Joo ; Lee, Sang-Bong ; Kim, Jung-Hyun ; Han, Jeong-Sik ; Jeong, Byung-Hun ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 15~21
With petroleum reserves dwindling, interest has been increasing worldwide in Fischer-Tropsch synthesis (FT) as a method of producing synthetic liquid fuels and chemicals from coal, natural gas or biomass. In general, FT synthesis is operated through the gas phase fixed-bed reaction system. Recently, there are lots of study in supercritical fluid due to unique characteristics such as the quick diffusion of reactant gas, effective removal of reaction heat, and the in-situ extraction of high molecular weight hydrocarbon, such as wax. In this study, our major aim is to obtain a deeper insight into the effect of the type of support on the reaction performance over a supported cobalt catalyst in a fixed bed reactor.
Experimental Study of Spray Characteristics on the Throttleable Dual Manifold Injector
Youn, Jung-Soo ; Kim, Sung-Hyuk ; Yoon, Young-Bin ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 22~30
There is a many way of LPRE throttling methods, high-pressure-drop systems, dual-manifold injector, gas injection, multiple chambers, pulse modulation and movable injector components. Especially dual-manifold injector is essentially combines two fixed-area injectors into a common structure, with independent feed systems controlling flow to each injector manifold. In this paper, using indirect photography and liquid film thickness measurement with various injection pressure and tangential entry diameter to decide stability of spray over a wide thrust range in dual manifold injector.
Visualization of Internal Flows in the Wall-injected Test Model of a SRM
Kim, Do-Hun ; Lee, In-Chul ; Koo, Ja-Ye ; Cho, Yong-Ho ; Kang, Moon-Jung ; Kim, Yoon-Gon ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 31~39
The flowfield in a solid rocket motor was simulated at the wall-injection test model, which has a fin-slot grain and submerged nozzle, and visualized by a smoke-wire. The high speed CCD camera captured the visualized images around the nozzle inlet through the grain center port. The vortical tube structure and circumferential flow patterns at the nozzle throat were visualized. The radial momentum transfer caused by the shear-interactions of slot-outlet flow, fin-base flow and grain port flow from upstream worked as the source of these phenomena.
Development of a Velocity Compounded Impulse Turbine for the 75ton Liquid Rocket Engine Application
Jeong, Eun-Hwan ; Lee, Hang-Gi ; Park, Pyun-Goo ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 40~46
A velocity-compounded(VC) turbine of the 75ton turbopump was developed as an improved performance backup for a single-rotor base-line turbine. Curvic coupling was used for the connection between rotors and shaft. High temperature torsion test and spin test was performed for the curvic coupling design validation. Aerodynamic performance test revealed that the developed VC turbine can generate 20.5% higher specific power than the base-line turbine. It has been measured that
rotor of the subject turbine generates 74.1% of total power at design operating condition.
The Characteristics and its Development Trends of Thermoplastic Propellants
Kim, Kyung-Moo ; Kim, In-Chul ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 47~57
All solid rocket propellants are divided in two basic classes according to chemical state: homogeneous(double base) and heterogeneous (composite). Today, composite propellants are extensively used as power sources covering the range from gas generators and small rocket systems to large launch vehicles in space programs. The development of composite rocket propellants in the past was mainly directed to thermoset polymers. But, the thermoset composite propellants have the complication in formulation and fabricating process to adapt to rocket system requirements. In contrast to the thermoset propellant, the PVC plastisols composite propellants have the advantages in the view of loss in manufacturing process, low cost of raw material, and stability of the handling process even though moderate ballistic and mechanical properties. It is predicted that the application field of this class will be used more widely than any other classes.
Conceptual Design of a Turbopump Adopting a Planetary Gear System
Kim, Jin-Han ; Jeong, Eun-Hwan ; Choi, Chang-Ho ; Jeon, Seong-Min ; Kim, Jin-Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 58~63
The present paper describes a conceptual design of a turbopump which employs a planetary gear system. In a launcher system, weight is one of the most important design factor. In turbopump systems using propellants such as kerosene, or methane, single shaft systems are employed because of simplicity. One of the main disadvantages of this system, however, is the same rotational speed of both pumps and a turbine which forces to operate under non-optimum condition. To operate each component in optimum or favorable rotational speeds, a planetary gear system seems to be the best choice when the compactness and efficiency of a turbopump system is considered. A conceptual design and feasibility of the turbopump system adopting a planetary gear system is suggested.
Development of the Spherical Flange Used in a Cryogenic High Pressure Pipe
Moon, Il-Yoon ; Moon, In-Sang ; Yoo, Jae-Han ; Lee, Soo-Young ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 64~69
The spherical flange was designed to apply to a cryogenic high pressure pipe of a liquid rocket engine. It is designed that the spherical flange is able to be assembled and kept airtight up to
of the axial misalignment between the combined components. It increases the degree of freedom of the engine assembly. The spherical flange is composed of a ball and socket joint, a metal seal, spherical type bolts and washers. The prototype was verified by leak test at the room temperature and the cryogenic temperature. Additionally the strength test and the destructive test were performed at the room temperature.
Development Status and Study of the Sounding Rocket
Kim, Jin-Yong ; Rho, Tae-Ho ; Lee, Won-Bok ; Suh, Hyuk ; Rhee, Young-Woo ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 70~79
This paper presents development status of sounding rockets containing scientific payload and telemetry at home and abroad. The case of outside, United States is launching sounding rockets in 20-30 flights per year by the NASA program which offers to carry payload weights of 38-680 kg and altitude of 88-1500 km. Europe is launching in 4-5 flights per year by the ESA program. The case of Korean sounding rockets was successful with the launch of three times(KSR-I,II,III), but Korea lags far behind the advanced countries in the field of development technologies for space launch vehicle. We expect that our scientific and industrial technologies will be improved through the research and development of sounding rockets. In this study we proposed necessity and future direction of development in domestic sounding rockets.
Development of Vacuum Refueling Process for Fuel Tank
Park, Jeong-Bae ; Min, Seong-Ki ; Lee, Se-Young ; Kim, Young-Shin ; Lee, Jong-Chul ; Jang, Ki-Won ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 80~85
The air in the fuel tank could cause oxidation of fuel during storage, and it also reduced the fuel transfer performance. To find better procedure for refueling of aircraft fuel tank, the vacuum refueling process was proposed to reduce the air in the fuel tank. In this study, the vacuum refueling process was established and tested, it could be helpful to find out what happened during vacuum refueling. Also the revised vacuum refueling process was proposed to reduce the air and refueling time.
A Study on GUI type On-line Condition Monitoring Program for A Turboprop Engine Using LabVIEW
Kong, Chang-Duk ; Kim, Keon-Woo ; Kim, Ji-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 15, issue 3, 2011, Pages 86~93
Recently, development and application of condition monitoring and diagnostic system for improvement of durability and reliability and reduction of operating cost is generalized in the aircraft propulsion system. Expecially, for reliable operation of the high altitude and a long time and condition monitoring system to identify faults and degradations of its propulsion system should be needed. This work proposed a GUI-based On-line condition monitoring program using LabVIEW by PT6A-67 turboprop engine. The proposed on-line condition program can monitor the real engine performance as well as the trend through precise comparison between performance results calculated by the base performance simulation program and measuring engine performance signals. In the development phase of this monitoring system, a signal generation module is proposed to evaluate the proposed on-line monitoring system.