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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 9, Issue 4 - Dec 2005
Volume 9, Issue 3 - Sep 2005
Volume 9, Issue 2 - Jun 2005
Volume 9, Issue 1 - Mar 2005
Selecting the target year
An Acoustic Analysis for the Determination of a Simulating Duct and for the Suppression of Combustion Instabilities in a Flight Model Gas Generator
Kim Hong Jip ; Kim Seong-Ku ; Han Yeoung-Min ; Choi Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 1~9
An acoustic analysis of a fuel-rich gas generator for the drive of a turbopump in a liquid rocket engine has been performed and the length of a duct has been determined by comparing the resonant frequency of unstable acoustic modes to simulate an flight model gas generator, A practical short-length simulating duct has been determined by considering 1 or 2 wavelength of the unstable modes. Length adjustment of duct to turbopump can be a method to suppress a combustion instability problem by decoupling of acoustic mode and combustion characteristics. This method has been set up and validated with acoustic analysis and hot firing tests.
Performance Prediction on a Partially Admitted Single-Stage Axial-Type Turbine
Cho Chong-Hyun ; Cho Soo-Yong ; Kim Soo-Yong ; Choi Sang-Kyu ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 10~17
A performance prediction model is developed for partially admitted axial-type turbines. Losses generated within the turbine are classified to the windage loss, expansion loss and mixing loss. The developed loss model is compared with an experimental result. The results predicted with the developed model agree well with the experimental results than those predicted with several other models because this model considers three different kinds of losses. Moreover, this model predicts well the performance even the partial admission is changed. So, this model could be applied to predict the performance of partially admitted axial turbine and it has a high accurate performance.
A Study on Structural Safety Evaluation of let Vane under very High Temperature and Dynamic Pressure
Park Sunghan ; Lee Sangyeon ; Park Jongkyoo ; Kim Wonhoon ; Moon Soonil ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 18~24
To evaluate structural safety factor of the jet vane for the thrust deflection system under the dynamic pressure and very high temperature(2700
) of the combustion gas flow, the high temperature tension tests of refractory metals and 3-D nonlinear numerical simulations are performed. Through the analysis of high temperature structure behavior for jet vane, the structure safety of jet vane is evaluated, and numerical results are compared with static ground tests of jet vanes. It has been found that most of structural and thermal loading is concentrated on the vane shaft which worked as safe under 1400
. From the comparison of static ground tests and numerical results, the evaluation criterion using the vane load and shaft displacement is more useful to estimate the structural safety than using the equivalent stress.
Analytical Investigation on Temperature Rise of Liquid Oxygen in Propellant Tank
Cho Namkyung ; Jeong Yonggahp ; Kim Youngmog ; Jeong Sangkwon ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 25~37
For pump-fed rocket propulsion system, the temperature of LOX to be supplied to turbopump inlet should be satisfied with pump inlet temperature requirement during all operating stages, as excessive temperatures can result in cavitation due to reduction in NPSH, thus either damaging the pump or adversely affecting pump performance rise. So exact estimation of LOX temperature rise is absolutely needed for developing reliable propulsion system. This paper presents systematic analysis scheme for estimating inner process of cryogenic propellant tank which is needed for LOX temperature rise. And this paper presents LOX temperature rise and thermal stratification for all rocket operating stages including cooling, filling, waiting, pre-pressurization and firing, with the application of buoyancy driven boundary layer theory.
Preliminary Design Study of the Scramjet Engine Intake
Kang Sang Hun ; Lee Yang Ji ; Yang Soo Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 38~48
For the development of Scramjet engine technology, intake designing processes are investigated. The basic geometry is determined by the inviuld relation such as shock wave relations and geometric relations. Furthermore, bleed duct is installed for preventing boundary layer development and shock wave impingement. Performance of the designed intake is validated by numerical analysis. As a result, double- wedge intake showed better characteristics in total pressure recovery than single-wedge intake.
Numerical Simulation of Turbulent Heat Transfer in a Channel with One Wavy Wall
Park Tae-Seon ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 49~59
Turbulent heat transfer over a fully-developed wavy channel is investigated by a turbulence model. The nonlinear k- f - f
model of Park et at. is slightly modified and their explicit algebraic heat flux model is employed. The Reynolds number is fixed at Re
=6760 and the wave configuration is varied in the range of 0
0.15 and 0.25
4.0. In order to verify model performances, a large eddy simulation is performed for the selected cases. The model performance is shown to be generally satisfactory. By using k-
model, the enhancement of heat transfer and the characteristics of turbulent flow in wavy wall are investigated. Finally, the influence of wavy configuration on heat transfer is scrutinized.
Development of Non-Electric and Delay-Type Explosive Bolt
Lee YeungJo ; Kim DongJin ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 60~65
The present work has developed non-electric and delay-type explosive bolt that does not need electric power supply device and has the delay function in the operation. Non-electric power supply system enables separation device system to be minimized. In order to prove the mechanism of the operation, the power of air resistance caused from aviation object used to ignite the initiator. we can be founded from the present work that the changes in the operation load influence directly the ignition of the initiator. The design of non-electric and delay type of explosive bolt is the most suitable for the separation system that is necessary to reduce the velocity of aviation object and safe landing of parachute system.
Study on the Temperature Characteristic of Pressurization System Using Cryogenic Helium Gas
Chung Yonggahp ; Kim Yoo ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 66~73
The pressurization system in a liquid rocket propulsion system provides a controlled gas pressure in the ullage space of the vehicle propellant tanks. It is advantage to employ a hot gas heat exchanger in the pressurization system to increase the specific volume of the pressurant and thereby reduce over-all system weight. A significant improvement in pressurization-system performance can be achieved, particularly in a cryogenic system, where the gas supply is stored inside the cryogenic propellant tank. In this study liquid nitrogen was used instead of liquid oxygen as a simulant. The temperature characteristic of cryogenic pressurant is very important to develop some components in pressurization system. Numerical modeling and test data were studied using SINDA/FLUINT Program and PTF(Propellant-feeding Test facility).
Characteristics of Liquid Rocket Engine Simulation System Using Control Valve
Lee Joons-Youp ; Jung Tae-Kyu ; Han Sang-Yeop ; Kim Young-Mog ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 74~84
This paper include the investigation of finding the system characteristics of facility by simulating open-type turbo-pump fed system, which has commercial control valves, using AMESIM (Advanced Modeling Environment Simulation) commercial software. After developing a flight-type control valve on the basis of the results, the system characteristics of facility for control and valve tests is estimated. Especially, one of purposes of this paper is to find PID value of each commercial control valve in the facility for system test. To find suitable control logic, PI and PID modes are also compared. This paper also introduces design parameters of valve and equipment for thrust control and TDS simulation, which are using control valves.
Numerical Analysis on Radiative Heating of a Plume Base in Liquid Rocket Engine
Sohn Chae Hoon ; Kim Young-Mog ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 85~91
Radiative heating of a liquid rocket base plane due to plume emission is numerically investigated. Calculation of flow and temperature fields around rocket nozzle precedes and thereby realistic plume shape and temperature distribution inside the plume are obtained. Based on the calculated temperature field, radiative transfer equation is solved by discrete ordinate method. With the sample rocket plume, the averaged radiative heat flux reaching the base plane is calculated about 5 kw/m
at the flight altitude of 10.9 km. This value is small compared with radiative heat flux caused by constant-temperature (1500 K) plume emission, but it is not negligibly small. At higher. altitude (29.8km), view factor between the base plane and the exhaust plume is increased due to the increased expansion angle of the plume. Nevertheless, the radiative heating disappears since the base plane is heated to high temperature (above 1000 K due to convective heat transfer.
Cooling Performance Enhancement of a Rocket Engine Injector Face Plate
Cho Won Kook ; Seol Woo Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 92~100
An optimal fuel manifold is suggested to improve the cooling performance of an injector face plate. The cooling performance at the center area of the injector face plate is to be augmented while the spatial injection uniformity is maintained. The comparison of the cooling performance of f candidates gives the conclusion that the dividing plate from 2-3 injector .ow to 9-10 injector. row is an optimal. The maximum face plate temperature decreases by 27
while the injection uniformity is close to that of the original design. The pressure drop in the fuel manifold of the optimal design is also same as the original design.
Investigation of Premixed Flame Instability with Heat and Momentum Losses
Kang Sang Hun ; Baek Seung Wook ; Im Hong Geun ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 101~119
For MEMS applications, the effects of the momentum and heat loss on the stability of laminar premixed flames in a narrow channel are investigated by high-fidelity numerical simulations. A general finding is that momentum loss promotes the Saffman-Taylor (S-T) instability which is additive to the Darrieus-Landau (D-L) instabilities, while the heat loss effects result in an enhancement of the diffusive-thermal (D-T) instability. These effects are also valid in nonlinear behavior of the premixed flame. The simulations of multiple cell interactions are also conducted with heat and momentum loss effects.
A Study on the Risk Reduction Method for Liquid Rocket Test Facility
Lee Jung-Ho ; Kim Yong-Wook ; Bershadskiy V. A. ; Kang Sun-Il ; Cho Sang-Yeon ; Oh Seung-Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 120~126
The method of decreasing the ecological risk for the LRE(Liquid Rocket Engine) test is developed, working on the cryogenic oxidizer and the high-boiling fuel(Kerosene). This Method is based on the study that contains a technical solution method and an accident occurrence range for decreasing of accident probability and damage. This paper contains schematic on the all risk circumstance bring to accident, block-diagram for an accident growth process in case of the propellant leakage, technical solution method and risk reduction evaluation method. It will be used to alternative method for the risk reduction of complex technical systems.
Transient performance behaviour of the CRW type UAV propulsion system during flight mode transition considering valve operation
Kong Changduk ; Park Jongha ; Yang Sooseok ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 127~132
In order to investigate transient behavior, of the CRW(Canard Rotor Wing) type UAV(Uninhabited Aerial Vehicle) propulsion system during flight mode transition considering flow control valve operation, the propulsion system was modelled using SIMULINK commercial program. The valve system is to control the gas flow of the rotary duct system and the main duct system, and the analysis was performed with an assumption that the total gas mass flow of the main engine is the same as summation of the rotary duct flow and the main duct flow, and with consideration of valve loss, flow rate and effective area in valve angle variation. The performance analysis was carried out during flight mode transitions from the rotary flight mode to the fixed wing flight mode and vice versa mode at altitude of 1km, flight Mach number 0.1 and maximum engine rpm.
Review of Cryogenic Propellant Densification Technology
Cho Namkyung ; Han Sangyeop ; Kim Youngmog ; Jeong Sangkwon ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 133~144
Enhancements to propellants provide an opportunity to either increase performance of an existing launch vehicle. One of the promising technologies is the use of densified cryogenic propellants such as liquid hydrogen and liquid oxygen. The main advantage of densified cryogenic propellants is the increase in propellant mass fraction. Increased propellant mass fraction means increased payload mass to orbit. This paper reviews the basic principles and current technology trends for cryogenic propellant densification technologies. Several promising densification methods are presented focused on liquid oxygen densification. Engine and vehicle performance analyses are also presented to quantify the potential performance benefits of densified propellants in an overall system. And suggestions of application scheme for satellite launch vehicle is made.
Status of Sub-Orbital Space Tourism Business
Kim Kyoung-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 3, 2005, Pages 145~152
Worldwide there is strong interest in the field of commercial space business, especially 100km altitude sub-orbital Space Tourism. This was soared to by the two-times flight success of SpaceShipOne by Scaled Composites Inc. It reached an altitude of 100km at Oct. 4, 2004. This demonstrates a paradigm change from government-driven space challenge and exploration to commercial space business. Therefore this report provides various insights into the commercial space tourism market, such as current demand for space travel, size of the market, growth potential of the market, technology, etc.