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 5, Issue 4 - Dec 2001
Volume 5, Issue 3 - Sep 2001
Volume 5, Issue 2 - Jun 2001
Volume 5, Issue 1 - Mar 2001
Selecting the target year
Evaluation of Impact Characteristics for High Strength Structural Steel at Low Temperature
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 1~9
Impact tests are performed on the high strength structural steel that is being developed for the submarine material. Especially, the impact characteristics of this structural steels at low temperatures are investigated by charpy impact testing. Hyperbolic tangent curve fitting method is used to evaluate the LSE(lower shelf energy), USE(upper shelf energy) and DBTT(ductile-brittle transition temperature). Proportional equations between charpy impact energy and lateral expansion are obtained using the test results. Effect of temperature on the fracture appearance is investigated by using SEM.
Study of Supersonic Jet Impinging on a Jet Deflector
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 10~18
In this paper, Supersonic jets impinging on a wedge were investigated in order to acquire fundamental design data for jet deflectors. Surface pressure distributions and pressure contours were obtained using a cold flow tester producing Mach 2 supersonic jets. Schlieren system was used to visualize the flow structure on the wedge surface. Numerical computations were performed and compared with the experimental results. Both results were in good agreement. The results showed that underexpansion ratio did not affect on the surface pressure distribution when the wedge is located at the nozzle exit. With increasing underexpansion ratio, pressure recovery decreased as the wedge is located farther from the nozzle exit. In the pressure contour, it was possible to locate the region where the peak pressure on the wedge surface was occurred.
Development of the Pilot-Tube to Measure Flight Altitude and Velocity
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 19~24
The Pilot-Tube is the device that measures velocity and altitude of high speed vehicle. Accurate measurements of speed and altitude are essential to the safe and efficient operation of aircraft. For the purpose of determining optimal design parameters of Pilot-Tube such as nose inlet configuration, nose shape, static hole configuration, and static hole location, subsonic flow field was calculated numerically and analyzed. A Pilot-Tube was manufactured based on numerical flow field analysis, and pressure and air velocity was measured experimentally in the wind tunnel. As a result manufacturing and design technologies of the Pilot-Tube were acquired to make flight-device
Computations on Passive Control of Normal Shock-Wave/Turbulent Boundary-Layer Interactions
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 25~32
A passive control method of the interaction between a weak normal shock-wave and a turbulent boundary-layer was simulated using two-dimensional Navier-Stokes computations. The inflow Mach number just upstream of the normal shock wave was 1.33. A porous plate wall having a cavity underneath was used to control the shock-wave/turbulent boundary-layer interaction. The flows through the porous holes and inside the cavity were investigated to get a better understanding of the flow physics involved in this kind of passive control method. The present computations were validated by some recent wind tunnel tests. The results showed that downstream of the rear leg of the
-shock wave the main stream inflows into the cavity, but upstream of the rear leg of the
-shock wave the flow proceeds from the cavity toward to the main stream. The flow through the porous holes did not choke fur the present shock/boundary layer interaction.
Study of the Operation Characteristics of the Supersonic Steam Ejector System
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 33~40
In order to investigate the operating characteristics of a supersonic steam ejector, the axisymmetric, compressible, Reynolds-averaged, Wavier-Stokes computations are performed using a finite volume method. The secondary and back pressures of the ejector system with a second throat are changed to investigate their effects on the suction mass flow. Three operation modes of the steam ejector system, the critical mode, subcritical mode and back flow mode, are discussed to predict the critical suction mass flow. The present computations are validated with some experimental results. The secondary and back pressures of the supersonic steam ejector significantly affect the critical suction mass flow. The present computations predict the experimented critical mass flow with fairly good accuracy A good correlation is obtained for the critical suction mass flow. The present results show that provided the primary nozzle configuration and secondary pressure are blown, we can predict the critical mass flow with good accuracy.
Numerical Analysis of Combustion Characteristics in a Liquid Propellant Rocket Engine with Split-triplet Injector Elements
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 41~51
Combustion characteristics of a KSR-III liquid rocket engine with split-triplet (F-O-O-F) type injector elements are investigated numerically from the viewpoints of engine performance and combustion flowfield. To evaluate numerical analysis of liquid rocket engine with radial type injector arrangement, 2-D axisymmetric and 3-D calculations are carried out and the prediction of engine performance for design and off-design conditions is in a good agreement with hot-firing tests. According to 2-D axisymmetric and 3-D calculations, the prediction error is 3∼5 % from the standpoint of performance. Numerical results of combustion characteristics calculated through 3-D analysis agree well with hot-firing tests qualitatively at injector plate. Decreasing impinging angle and changing radial type injector arrangement to H type injector arrangement reduce effectively local high-temperature region. Also, it is examined that those affect the performance seriously. In conclusion, it is revealed that both injector arrangement and impinging angle are critical parameters to affect the performance and combustion characteristics of the liquid rocket engine.
Analytical Study on the Launching System with Gas Generator
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 52~59
In this study, a technique has been developed to analyze the performance of the launching system using a gas generator of solid propellant. The physical model which described the thermodynamic behaviors of all launching devices from gas generator to canister and the dynamic behavior of missile was established, applying the empirical coefficients in the heat loss model. The processes of combustion, flow, and heat transfer inside the chamber of gas generator and the launching system were simulated by numerical method. The theoretical analysis guided the optimal design of gas generator and system, which made the launching system satisfy the requirements of good performance and high reliability.
A study on the adhesion of HTPB liner and PCP propellant
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 60~70
The study of compatible liner with ADP-505 propellant based PCP was performed. HTPB/DDl was chosen as a binder of liner in order to prohibit migration of nitroester plasticizer from propellant. The possible formulations for liner were screened by peel test of EPDM insulation/liner, propellant/liner and insulation/liner/propellant. Also, the adhesion tests including tension and shear were conducted. The adhesion of liner and propellant fumed out to be very good. The peel value was shown 1.5∼1.8 daN/cm, tensile force was 5.5∼6.0bar and shear force was 4.2∼5.0bar. In the samples of insulation/liner/propellant, they also have shown good adhesion properties. The peel, tensile and shear strength were 1.8 daN/cm, 5.0∼6.0bar and 4.5∼5.0bar, respectively.
Combustion of ethyl alcohol and kerosene fuel droplets in atmospheric pressure
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 71~78
This paper presents the results of an experimental investigation on the combustion of single droplets arrays of Ethyl alcohol and kerosene fuel droplets in atmospheric pressure. The initial droplet diameters, d
, were nominally 1.3~1.8mm, and inter-droplet separation distance l(l/do=1.31~2.60). experimental results indicate that burning rate constants(K) of ethyl alcohol and kerosene droplets were independent of initial droplet size as 0.0083, 0.0095
/sec. For 1-D droplet array's kerosene fuel droplet, burning rate constants(K) decreases with decreasing normalized inter-droplet distance. Normalized inter-droplet distance has stronger effect on 2nd fuel droplet than 3rd fuel droplet. When normalized inter-droplet distance is larger than 2.60, the effect of droplet spacing on droplet life is very small.
Modeling Scheme for the Six-components Force Measurements of Solid-propellant Rocket Motors
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 79~86
The six-components force measurements systems for rocket motors are used to measure multi components force generated by TVC(Thrust Vector Control) motors. This paper suggested the modeling scheme which is used in preliminary design and test analysis procedure and which can be applied to the existing other test stand in operation. The model whose parameters are determined by least square method makes the design engineer build the test stand to satisfy all kinds of requirements such as accuracy, operating condition and structural stability without tradeoff among the requirements. The experimental results shows that the proposed model has better accurate performances than those of other existing model.
Review on Airbreathing Propulsion Technology for Missile Application
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 87~99
Technical status and prospect of the subsonic airbreathing propulsion system composed of jet engine fuel feeding system and air intake for missile application is described herein, including analysis of some present airbreathing missiles. Comprehension on this can be applicable both to blow deeply about the same type missiles and to get some basic idea of unmanned air vehicle's and light aircraft's propulsion system.
Micro Propulsion System
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 3, 2001, Pages 100~107
Miro propulsion device is a literally very small propulsion system The reason why such a small propulsion system is required is that micro satellites are considered as substitutions for conventional satellites to reduce cost; the fabrication of micro satellites enables us to produce mass production Microrockets have relatively high values of thrust/weight ratio due to the cube law; weight is proportional to volume and thrust is proportional to area. Accordingly, downsizing makes the ratio of thrust/weight ratio high However, conventionally ignorable facts are not negligible any more in small scale systems. for chemical micro rockets, downsizing causes lots of heat loss as surface to volume ratio increases, which results in the destruction of radical ions. For thrusters using plasma, the generation of strong magnetic field for plasma is very difficult. Also, in the aspect of flow dynamics, the effects of drag and viscosity are important parameters in low Re flows. When these problems are solved, micro propulsion systems can be commercialized and result in spin-off effects in many fields.