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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 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
Analysis of Thermo Chemically Decomposing Composites for Rocket Thermal Insulators
Lee, Sunpyo ; Lee, Jung-Youn ;
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 1~11
A theory for time-dependent, high temperature ablation of poroelastic carbon composite insulators is applied using finite element methods to determine material properties from experimental data. The theory contains important revisions to that in Lee, Salamon and Sullivan by making a sharp distinction between Biots constants and permeability and setting both to analytical functions of porosity. The finite element program and material modeling has been modified to (1) more closely adhere to porous-material theory, (2) include a newly discovered analytical simplification and (3) refine the material property descriptions. Application to experimental problems and comparisons with data permit determination of Biots constants and permeability and their evolution with respect to matrix decomposition and clearly show how material parameters affect the material response, e.g., amplitude and the location of peaks with respect to temperature. In particular, the response is very sensitive to permeability and dominated by it.
Injector Discharge Characteristics of Liquid Rocket Engine
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 12~19
The discharge characteristics of the oxidizer injector of liquid rocket engine were investigated. The discharge performance was obtained numerically which agreed quantitatively with the measured data. The discharge coefficient is proportional to the cavitation number for cavitating flow and constant for non-cavitating flow. The Reynolds number, however, affects little the discharge coefficient. The discharge coefficient decreased slightly as the Reynolds number increased because the friction loss decreased relatively at high Reynolds number flow.
The Study of Nondestructive Test about Impact Damage of Plate Composite Materials
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 20~30
This study represents the Nondestructive Test about impact damage of composite materials made by different lay-up patterns and degrees. For this study, they were examined by the drop test on composite materials of two type lap-up patterns with fabric and unidirectional prepreg and examined nondestructive test of those. Nondestructive methods were X-ray test with
penetrant and Ultrasonic C-scan. The defect detectability of X-ray and Ultrasonic test was compared according to defect species. And the amounts of damage on impacted zone wert compared according to impact energy on two type test specimens. At results, Ultrasonic test was more effective to detect delamination and Penetrant X-ray test was more effective to detect matrix crack and fiber fracture. There were some differences in defect shapes and grades according to lay-up patterns and degrees, and the trend appeared that matrix crack, delamination, fiber fracture occured and increasing defects sizes according to increasing impact energy.
A study on the vibration characteristics of carbon/epoxy propeller shaft
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 31~39
Composite propeller shafts for a vehicle have major advantages such as reduction of vibration, noise, and weight. A propeller shaft was designed with a carbon/epoxy composite material using the finite element method(FEM), and prototype shafts for tests were manufactured by the filament winding manufacturing process. In order to verify the design procedure by FEM, Two kinds of experimental tests were carried out using a FFT analyzer with impact hammers and a critical speed measuring apparatus for measurement of natural frequencies and critical speeds. The difference between the FEM analysis result and the test result was less than 3.4%, showing FEM analysis results to be acceptable. The parametric study was focused on determining the factor affecting the vibration and strength characteristics of the propeller shaft based on FEM. In investigation of the change in natural frequency without an increase in propeller shaft weight, it was found that the winding angle is the most significant factor affecting the vibration and strength characteristics.
Research and Development of KSR-III Apogee Kick Motor
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 40~49
The basic research on AKM(Apogee Kick Motor) for space launch vehicle was carried out. AKM which will be used as 3rd stage solid rocket motor in 3-stage Korean Sounding Rocket(III) has been developing. KM is a solid rocket motor using composite propellant based on HTPB and is composed of composite motor case and submerged nozzle. To develop KM rocket motor satisfing a given set of requirement, firstly the full-scale KM with diameter 520mm was designed, then sub-scale motors reduced about 60% were manufactured and tested. Full-scale ground firing test is accomplished two times.
The Secondary Chamber Pressure Characteristics of Sonic/Supersonic Ejector-Diffuser System
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 50~56
The present study is an experimental work of the soni
ersonic air ejector-diffuser system. The pressure-time dependence in the secondary chamber of this ejector system is measured to investigate the steady operation of the ejector system. Six different primary nozzles of two sonic nozzles, two supersonic nozzles, petal nozzle, and lobed nozzle are employed to drive the ejector system at the conditions of different operating pressure ratios. Static pressures on the ejector-diffuser walls are to analyze the complicated flows occurring inside the system. The volume of the secondary chamber is changed to investigate the effect on the steady operation. the results obtained show that the volume of the secondary chamber does not affect the steady operation of the ejector-diffuser system but the time-dependent pressure in the secondary chamber is a strong function of the volume of the secondary chamber.er.
A Study on the Determination of the Performance Correction Factors of Solid Rocket Motors
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 57~66
The precise prediction of the performance is essential to develope the system at the development of propulsion system since no experimental data are available. The accuracy of 1on the total system's performance as well as itself, which depends on how the correction fac
, and so on, are determined in accurate. However some of the design factors are dete engineer's experience or the similar test data if they are available, so far. This study was the method of the determination of correction factors of both
and thrust in direct. The bas is to define the detail performance loss mechanism of solid rocket motors, might be occurre and to calculate in quantitative those correction factors from the performance loss mechanism the test results, the model of this study can predict those factors less than 1% error, in additi physical variances of each loss mechanism.
Verification Test of KSR-III Liquid Propellant Rocket Prototype Engine
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 67~74
Based on the national space development project, the necessity of developing liquid propellant rocket engine is revealed to secure the basic technology for the development of individual artificial-satellite launcher. Consequently, KARI (Korea Aerospace Research Institute) is developing a liquid propellant rocket engine for the KSR-III. Currently, a prototype engine using kerosene/LOx which produces 13-ton thrust is designed, fabricated and tested. In this paper, test procedure and technique for liquid propellant rocket engine are introduced with the analysis of static and dynamic test data.
Dynamic Characteristic Analysis of KSR-III Propulsion Feeding System
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 75~82
KSR-III propulsion feeding system is designed to feed a certain amount of propellant to engine by the end of combustion. The oscillation of propellant to engine would cause combustion instability and thrust oscillation and POGO phenomenon. This article deal with analysis performed such as the effect of rocket acceleration on the propulsion system and POGO analysis to ensure the performance of KSR-III
The Characteristics of Mixing and Combustion in the Combustor with Turbulence Generator
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 83~93
A swirler with turbulence generator is designed and manufactured for generating many small-scale eddies in the combustor which contribute to enhancing mixing effect between fuel and air. The method results in not only the disadvantage of pressure loss but also the advantage of promoting combustion and reducing NOx. For the purpose of the study, four kinds of swirler with different turbulence generator area (0%, 3%, 7%, and 12% of reducing flow area) are designed to confirm the effect of mixing according the variation in the area of the turbulence generator. The mixing of combustor in the radial direction is significantly improved and the distributions of flames and temperature are well distributed throughout the cross section of a combustor as area of swirl generator is increased.
Study of the Shock Structure of Supersonic, Dual, Coaxial, Jets
Journal of the Korean Society of Propulsion Engineers, volume 5, issue 4, 2001, Pages 94~101
The shock structure of dual coaxial jet is experimentally investigated. Eight different kinds of coaxial, dual nozzles are employed to observe the major features of the near field shock structure on the supersonic, coaxial, dual jets. Four convergent-divergent supersonic nozzles having the Mach number 2.0 and 3.0 are used to compare the coaxial jet flows discharging from two sonic nozzles. The primary pressure ratio is changed in the range between 1.0 and 10.0, and the assistant jet ratio from 1.0 to 4.0. The results show that the impinging angle, nozzle geometry and pressure ratio significantly affect the near field shock structure, Mach disk location and Mach disk diameter.