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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 3, Issue 4 - Dec 1999
Volume 3, Issue 3 - Sep 1999
Volume 3, Issue 2 - Jun 1999
Volume 3, Issue 1 - Mar 1999
Selecting the target year
Thermal Behavior of Spacecraft Liquid-Monopropellant Hydrazine(
) Propulsion System
Kim, Jeong-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 1~11
Thermal behavior of spacecraft propulsion system utilizing monopropellant hydrazine (
) is addressed in this paper. Thermal control performance to prevent propellant freezing in spacecraft-operational orbit was test-verified under simulated on-orbit environment. The on-orbit environment was thermally achieved in space-simulation chamber and by the absorbed-heat flux method that implements an artificial heating through to the spacecraft bus panels enclosing the propulsion system. Test results obtained in terms of temperature history of propulsion components are presented and reduced into duty cycles of the avionics heaters which are dedicated to thermal control of those components. The duty cycles are subsequently converted into the electrical power required in the operational orbit. Additionally, cyclic temperature of each component, which was made under thermal-balanced condition of spacecraft, is compared to the acceptable design range and justified from the viewpoint of system verification.
Electrical Noise Reduction in the Electromagnetic Shaker System using a Class-D Amplifier
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 12~22
Operation of an electromagnetic shaker system using a Class-D amplifier may cause unacceptable electromagnetic interference to another electronic system, requiring the user to take whatever steps are necessary to correct the interference. A differential amplifier in a Class-D amplifier is used to decrease the effect of a common-mode noise voltage in a shaker system. To prevent a ground loop, a transformer is inserted in another shaker system. These methods show reduction of the unwanted vibration which has occurred before. A transformer in a charge amplifier was used to prevent a ground loop in a shaker system using a Class-AB amplifier a few years ago, but it was susceptible of noise in a shaker system using a Class-D amplifier. Hence we corrected a ground loop between a charge amplifier and a vibration control/analysis system without a transformer. The usefulness of this approach is illustrated by the results of experiments.
Thermal Decomposition of Phase Stabilized Ammonium Nitrate (PSAN)
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 23~30
The thermal decomposition of phase stabilized ammonium nitrate(PSAN) was studied by means of thermogravimetric analysis(TGA). In this study, potassium nitrate and zinc oxide were used as the phase stabilizers in the range of contents from 0 wt.% to 8 wt.%. The kinetics and mechanism for the decomposition were evaluated using integral methods. It was found that the thermal kinetic parameters such as activation energy(I) and frequency factor(A) increase with the increase of the stabilizer contents, and the mechanism of decomposition also changes.
The study on the properties of PGN binder
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 31~37
Recently, the development of propellant trends toward minimum smoke signature, insensitivity and high performance. PSAN has been used as a oxidizer for less sensitive minimum smoke propellant. Unfortunately, it provides low performance to propellant. Energetic polymers such as GAP and PGN are frequently proposed for use in minimum smoke Propellants to overcome the energy Penalty imposed by using AN as the oxidizer. In this study the mechanical properties, glass transition temperature and viscosity of PGN and EPGN binder were investigated.
Effects of momentum ratio and mixture ratio on combustion efficiency in liquid rocket engine
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 38~43
An experimental study was carried out, in order to set up the procedure for evaluation of hot fire test, to investigate the effect of mixture on combustion performance and combustion stability , and to determine the optimum design condition for designing the liquid rocket engine.
/Kerosene uni-element liquid rocket engine(thrust 24
, chamber pressure 200 psia) using impinging streams doublet injector was designed, and ground hot-fire test was carried out. To prevent or reduce the hard start during ignition period, two step ignition method was used. This was accomplished by maintaining about 25% of the designed operating pressure doting transient period, then chamber pressure was built up to the designed operating pressure. Maximum combustion efficiency was at O/F ratio 3.6, and combustion efficiency is decreased with increasing momentum ratio.
An experimental study for the prediction of combustion performance of the Unlike Impinging Quadlet Injector
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 44~50
For the prediction of combustion performance of the Unlike Impinging Quadlet Injector (OOOF type), mixing efficiency, mixing characteristic velocity, and efficiency of mixing characteristic velocity were obtained from the cold test. Water/kerosene were used for simulants, The momentum ratio of oxidizer and fuel were mixing correlating parameter. Orifice discharge coefficient, spray pattern and mass distribution were measured. As a result, invasion-depth had strong effect on mixing efficiency, mixing characteristic velocity, and efficiency of mixing characteristic velocity. Mixing efficiency and efficiency of mixing characteristic velocity showed maximum value for momentum ratio 1.67(TMR = 2.5), and fuel rich state showed larger decreasing ratio than oxidizer rich state.
An Experimental Study on the Characteristics of the Vitiated Air Heater in the Ramjet Engine Ground-Testing
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 51~57
Temperature and velocity controlling of air at inlet position of Ramjet combustor is important under Ramjet engine grounding-test condition since temperature of inlet air increases due to compression process by supersonic flow at inlet position of Ramjet combustor. In this study, Vitiated Air Heater methodology was used to control temperature of air that is inducted into Ramjet combustor. Temperature and velocity of air at Vitiated air heater exit, which is inducted into Ramjet combustor, were measured to evaluate Vitiated air heater system developed in this study. It is shown that temperature and velocity of inducted air can be well controlled using Vitiated air heater system developed in this study, and we could make a Vitiated Air which is almost same with real air.
A CFD Study of the Supersonic Ejector-Pump Flows
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 58~66
The flow characteristics of supersonic ejectors is often subject to compressibility, unsteadiness and shock wave systems. The numerical works carried out thus far have been of one-dimensional analyses or some Computational Fluid Dynamics(CFD) which has been applied to only a very simplified configuration. For the design of effective ejector-pump systems the effects of secondary mass flow on the supersonic ejector flow should be fully understood. In the present work the supersonic ejector-pump flows with a secondary mass flow were simulated using CFD. A fully implicit finite volume scheme was applied to axisymmetric compressible Navier-Stokes equations. The standard two-equation turbulence model was employed to predict turbulent stresses. The results obtained showed that the flow characteristics of constant area mixing tube types were nearly independent of the secondary flow rate, but the flow fields of ejector system with the second-throat were strongly dependent on the secondary flow rate due to the effect of the back pressure near the primary nozzle exit.
An Experimental Study of Supersonic Underexpanded Jet Impinging on an Inclined Plate
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 67~74
Problems created by supersonic jet impinging on solid objects or ground arise in a variety of situations. For example multi-stage rocket separation, deep-space docking, V/STOL aircraft, jet-engine exhaust, gas-turbine blade, terrestrial rocket launch, and so on. These impinging jet flows generally contain a complex structures. (mixed subsonic and supersonic regions, interacting shocks and expansion waves, regions of turbulent shear layer) This paper describes experimental works on the phenomena (surface pressure distribution, flow visualization) when underexpanded supersonic jets impinge on the perpendicular, inclined plate using a supersonic cold-(low system. The used supersonic nozzle is convergent-divergent type, exit Mach number 2, The maximum on the plate when it was inclined was much larger than perpendicular plate, owing to high pressure recoveries through multiple shocks. Surface pressure distribution as to underexpanded ratio showed similar patterns together.
Performance Test of a Jet vane type Thrust Vector Control System
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 75~82
Theoretical analysis and performance test of Jet vane type Thrust Vector Control(TVC) were conducted using supersonic cold-flow system. The use of TVC Systems an in particular jet vanes, are currently being researched for use in air launch, ship launch, underwater launch and high altitude maneuvering of tactical missiles and rockets. The necessity to generate control forces to rapidly change the course of the missile is frequently required when traditional, exterior aerodynamic surfaces are unable to produce these forces, when the flow over the control surface is insufficient. This situation can occur at launch, or high angles of attack of the control surfaces. Jet vanes peformed well at all altitudes and environmental conditions, and jet vanes are extremely effective at deflection angles up to as high as
, make them ideal for the launch and maneuver applications. In this study, performance test of supersonic cold-flow system and visualization of supersonic jet was conducted, and shape and deflection angle effect of two types of jet vanes are investigated.
Effects of Two Phase Flow on Erosion Characteristic in a Rocket Nozzle
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 83~92
A numerical analysis of two phase flow in the solid rocket nozzle was conducted. Stoke number was defined over the various aluminum oxide(
) particle sizes and particle trajectories were treated by Lagrangian approach. Particle stability was considered by the definition of Weber number in a rocket nozzle. Large particles are divided after the nozzle throat as the flow accelerates rapidly. The division of particles changes the particle distribution at the nozzle exit. From the above results, it was found that the nozzle converge section surface might be affected by aluminum oxide particles. Also, Mechanical erosion rate of nozzle surface was predicted for different materials.
A Study on Engine Health Monitoring using Linear Gas Path Analysis for Turboprop Engine
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 93~103
The steady-state performance analysis program for turboprop engine which was used for a small, middle industrial aircraft and a basic trainer aircraft was developed and linear Gas Path Analysis method was applied to Engine Health Monitoring for Turboprop engine. This program was compared with TURBOMARCH program which is well known with performance and power according to flight Mach No. at the standard atmospheric condition to prove a steady-state performance analysis program. From the result, inlet, exit temperature and pressure of each component had error within 3% and especially power according to flight Mach No. had error within 2.4% so that this program could be assured. To make sure if linear Gas Path Analysis is reasonable four cases were selected. The first is the case that fouling is occurred in compressor only. The second is the case that fouling is occurred in compressor and erosion is occurred in turbine. The third is the case that erosion is occurred in both compressor and turbine and power turbine at the same time. Finally, the case that fouling and erosion are occurred in compressor, compressor turbine and power turbine was selected. Different parameters were selected impartially among the independent parameters so that the effect of measurement parameter selection was observed. From the result, the more measurement parameters the smaller RMS error and even though the number of measurement parameters was the same, the RMS error was obtained differently according to which measurement parameters were selected. The case using eight instrument parameters of case IV-4 had small error comparably and was economic and it was important to select optimal number of measurement and optimal measurement parameters.
An Overview of the Gas Turbine & Tubomachinery Business at Samsung Aerospace Ind.,Ltd.
Journal of the Korean Society of Propulsion Engineers, volume 3, issue 4, 1999, Pages 104~108
Samsung Aerospace Ind., Ltd. (SSA) has been involved in gas turbine and turbomachinery businesses since 1980. An overview is given of its gas turbine overhaul, parts manufacturing, and industrial turbo machinery businesses. It is hoped that interested people will find the current status and capabilities of Korean gas turbine industry as represented by SSA's Gas Turbine & Turbomachinery Division.