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 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
Coolant Effect on Gas Generator Propellant
Baek Gookhyun ; Yim Yoo-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 1~8
The effect of coolants has been studied on the burning properties of low burning rate HTPB/AP composite propellant containing Oxamide or Melamine as coolant for the gas generator. With increasing the content of coolant, the burning rate and the flame temperature could be lowered and the effect on flame temperature was about the same for two coolants. However due to the different thermal decomposition properties of coolant, the burning rate of Melamine propellant was found to abnormally decrease if
AP was partially replaced with
Combustion Characteristics of HTPB/AP/Zr Propellant
Min Byoung-Sun ; Hyun Hyung-Soo ; Yim Yoo-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 9~16
Zirconium(Zr) addition to formulation of HTPB/AP propellants, was shown to be less specific impulse than aluminum(Al) by the theoretical calculation because of the lower flame temperature and higher molecular weight of Zr oxide. It was found that the burning rate was faster with the finer size of Zr and the more content of
Zr the faster burning rate is in HTPB/AP/Zr propellants caused by the more conduction energy transfer from Zr flame to the burning surface. Also the burning rate of HTPB/AP/Zr propellant could be reduced by addition of 150nm Al, depending on AP size distribution in formulation with Butacene and
A Study on Dynamic Performance and Response of Turbo Shaft Engine for SUAV
Park Jun-Cheol ; Roh Tae-Seong ; Choi Dong-Whan ; Yang Soo-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 17~24
In this study, the GSP and in-house numerical codes have been used for analyses of the on-design, static off-design and dynamic off-design performances. Through the various missions including altitude, velocity, and power variations the static engine performance have been investigated. The dynamic engine performances based on these complicated variations have been also analyzed. Especially, the power, engine rpm and heat overload characteristics of the turbine have been estimated with the response time through the control of the throttle setting rather than the power setting. It could be applied to the FADEC system as an engine control device.
Failure Prediction of Thermo-Chemically Decomposing Composite for Rocket Thermal Insulators
Lee, Sun-Pyo ; Lee, Jung-Youn ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 25~31
The theory developed in a preceding paper  for poroelastic composite material behavior under thermal and gas diffusion is applied to thermo-chemical decomposition of a carbon-phenolic composite rocket nozzle liner under typical operating conditions. Specifically, the structural component simulated is the cowl ring for which distributions of pressure in the material pores, temperature and across-ply stress are presented. The results for particular composite designs show that across-ply failure occurs due to tensile stress in the material which is indicative of plylift. This prediction corroborates observations of plylift in a nozzle cowl. Simulations suggest designs to avoid plylift in the cowl zone.
Change of Piping-System Dynamics with Installation of Pogo Suppression Device
Lee Jun Kyoung ; Lee Sang Yong ; Lee Han Ju ; Oh Seung Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 32~39
The effectiveness of the pogo suppression device (PSD) on the response of the piping system simulating the fuel (or oxidizer) supply lines of the rocket engines was investigated. The system response defined as the ratio of the flow rate to the pressure in the main tube was obtained for various PSD gas volumes
and three different baffle hole diameters (5, 50, 115mm). Existence of a gas volume in the PSD reduced the system resonance frequency. With a larger gas volume, the resonance frequency became lower, but only slightly, while the fluctuations of the main tube pressure and the flow rate damped down considerably. The resonance frequency decreased with the increase of the PSD inlet restriction (or the decrease of the baffle hole diameter), though slightly. However, with a larger inlet restriction, the PSD pressure wave showed a delayed response with the smaller amplitude compared to the pressure variation in the main tube.
Properties of HTPB/AP/Butacene Propellants
Kim Changkee ; Yoo Jichang ; Hwang Gabsung ; Yim Yoojin ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 40~45
In the present work, the effect of formulation on friability of HTPB/AP propellants including Betacene and
has been studied. The mechanical properties and burning rate of the propellants were measured using Inston tensile tester and strand burner, respectively. Friability was calculated from shot-gun and closed bomb test data. The result showed that friability was higher, as the content of Butacene or AP
in the propellant formulations was increased.
Temperature and Humidity Aging Characteristics of Composite Solid Propellant
Lee Kyung-Joo ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 46~53
We have analyzed the temperature and humidity aging test results of a composite solid propellant. The temperature aging test was performed to evaluate the storage life of a propellant, while the humidity aging test could provide the hygroscopicity of Ammonium Perchlorate(AP) exposed to .elative humidity (RH) 10, 30,
environment. A specimen was used in the temperature test, and a block of propellant from the actual motor was used in the humidity test. We report that the 4-month storing at 60 degree is equivalent to the 10-year 60 degree condition. The composite solid propellant with HTPB binder showed signs of hardening with time lapse but the effect of humidity up to RH
was not noticeable.
Fuel System Design of the Smart UAV
Kong Chang-Duk ; Kang Myoung-Cheol ; Lee Chang-Ho ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 54~61
In this study, the fundamental design procedure for the Smart UAV fuel supply system was set up, and the preliminary design was performed to meet the vehicle system requirements. The fuel system layout was determined through consideration of vehicle system requirements, and then fuel tank layout, design of components such as booster pump, jet pump, pipe, vent system, weight estimation, etc. were carried out. Based on this fuel system layout, operational reliability analysis was carried out.
The Way of Determinating the Optimal Parameters of the Propellant Tank Pressurization Gas in the Feeding System for Liquid Rocket Engine
Bershadskiy V.A. ; Cho Kie-Joo ; Lim Seok-Hee ; Jung Young-Suk ; Cho Gyu-Sik ; Oh Seung-Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 62~69
The design method to calculate the main features of propellant tank pressurization system during the development procedure of propellant feed system of the liquid rocket engine was suggested. We have considered the influences of parameters of pressurization gas on the efficiency of the thermodynamic processes in the tank. The optimum value of temperature and velocity of pressurization gas at the entrance of tank are obtained by the suggested way.
The Starting Behaviour of a Supersonic Ejector Equipped with a Converging-Diverging Diffuser
Park GeunHong ; Kim SeHoon ; Jin JungKun ; Kwon SeJin ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 70~77
An axisymmetric supersonic ejector equipped with a converging-diverging diffuser was built and pressure at various locations along the ejector-diffuser system was recorded with emphasis on the supersonic starting of the secondary flow. In order to find the effects of the opening size of the secondary flow, a number of openings were used with a constant primary pressure. Supersonic starting was possible only for d/D, the ratio of the opening diameter and the diffuser throat diameter, less than 0.306. for larger values of d/D, the ejection begins at subsonic secondary flow condition. With the closure of the opening, the primary flow brings the normal shock downstream of the converging-diverging diffuser And the starting of the ejector continues even after the closure was removed.
Reactive Fields Analysis of Hybrid Combustor Under Different Arrangements of Oxidizer Injectors
Cho Sung-Chan ; Kim Soo-Jong ; Lee Seung-Chul ; Kim Jin-Kon ; Koo Ja-Yae ; Moon Hee-Jang ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 78~88
The combustion characteristics of End-Burning hybrid combustor using different types of injector system are numerically investigated to visualize the temperature fields in the combustion chamber The basic characteristics of combustion with different O/F ratio is also analyzed in order to capture the main behavior of diffusion flame inside the swirl induced hybrid combustion chamber It was found that the arrangement of oxidizer injectors give strong effect on the temperature field dominating mixing between fuel and oxidizer. The results show that among five different oxidizer injectors arrangement, the counter flow injector has the highest mixing efficiency. However, the observed high wall temperature presence near the oxidizer injectors remains to be solved.
A Study on Thermal Characteristics of Stratospheric Airship Influenced by Solar Radiation
Kim Min-Jung ; Lee Dae-Won ; Roh Tae-Seong ; Choi Dong-Whan ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 89~96
This study has been performed on the mechanism of heat transfer between stratospheric airship and its surroundings while the airship is staying in the air at the altitude of 20km. The computational grid of airship has been generated and the results influenced by the number and the shape of grids have been compared. The temperature distributions have been obtained through this thermal analysis considering three modes of heat transfer - conduction, convection and radiation - in stratospheric conditions. Based on the airship's surface and inner temperature variations, the influence of temperature distributions on the helium envelope and the payload has been predicted.
A Simple Calculational Method by using Modified Von Mises Transformation applied to the Coaxial Turbulent Jet Mixing
Choi Dong-Whan ;
Journal of the Korean Society of Propulsion Engineers, volume 9, issue 2, 2005, Pages 97~104
A simple but efficient grid generation technique by using the modified compressible form of stream function has been formulated. Transformation of a physical plane to a streamline plane, the Von Mises Transformation, has been widely used to solve the differential equations governing flow phenomena, however, limitation arises in low velocity region of boundary layer, mixing layer and wake region where the relatively large grid spacing is inevitable. Modified Von Mises Transformation with simple mathematical adjustment for the stream function is suggested and applied to solve the confined coaxial turbulent jet mixing with simple
turbulence model. Comparison with several experimental data of axial mean velocity, turbulent kinetic energy, and Reynolds shear stress distribution shows quite good agreement in the mixing layer except in the centerline where the turbulent kinetic energy distributions were somewhat under estimated. This formulation is strongly suggested to be utilized specially for free turbulent mixing layers in axisymmetric flow conditions such as the investigation of mixing behavior, jet noise production and reduction for Turbofan engines.