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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 13, Issue 6 - Dec 2009
Volume 13, Issue 5 - Oct 2009
Volume 13, Issue 4 - Aug 2009
Volume 13, Issue 3 - Jun 2009
Volume 13, Issue 2 - Apr 2009
Volume 13, Issue 1 - Feb 2009
Selecting the target year
A Study on the Formulation and Mechanical Properties of AN-based Composite Solid Propellant for an Application to Gas Generators
Park, Jeong ; Kim, Jeong-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 5, 2009, Pages 1~6
A development of a composite solid propellant is carried out for an application to gas generators as an energy source of rocket system. With HTPB as a propellant binder which has 80% of particle loading ratio, a favorable rheology, and moderate curing properties at the range of
, AN is selected as the first kind of oxidizer having the characteristics of a low flame temperature, minimal particle residual as well as nontoxic products. AP is the second oxidant for ballistic property control. A series of experiments for the improvement of physical properties were conducted and resulted in the propellant formulation having 30% of strain rate at 8 bar of max. stress.
Numerical and Experimental Investigation on the Supersonic Impulse Turbine Design Performance Estimation Methodology
Jeong, Eun-Hwan ; Park, Pyun-Goo ; Lee, Hang-Gi ; Kim, Jin-Sun ; Kim, Dae-Jin ; Kim, Jin-Han ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 5, 2009, Pages 7~14
A methodology of design performance estimation for the supersonic impulse turbine was investigated. Relations of similarity condition and test nozzle area ratio were derived. Comparison of efficiencies between the turbines with real nozzle and test nozzle are made numerically and experimentally. The CFD results and test result confirmed that the turbine with test nozzle was able to predict real turbine performance. In addition, design performance of the supersonic impulse turbine also could be estimated using real nozzle in air-medium test. In this case, design efficiency was found at the pressure-ratio and velocity-ratio of similarity condition of test nozzle.
Combustion Stability Analysis on Hot-firing Test Results of Regenerative Cooling Combustion Chamber
Ahn, Kyu-Bok ; Lim, Byoung-Jik ; Lee, Kwang-Jin ; Han, Yeoung-Min ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 5, 2009, Pages 15~20
Hot-firing tests were performed on two 30 tonf-class regenerative cooling combustion chambers, with different injector distribution and wall cooling method. In the paper, the combustion stability test results were analyzed and presented. The pressure fluctuation and stability rating test(SRT) results of the combustion chambers were examined to evaluate combustion stability. The combustion chambers exhibited satisfactory results on combustion stability. The RMS values of the chamber pressure fluctuation were less than 3% of the chamber pressure and the decay time of artificial pressure peaks was measured to be around 10% of the reference decay time. It is interesting that the RMS values of pressure fluctuation in the combustion chamber with film cooling are smaller than those in the chamber with cooling injectors at the periphery row.
An Experimental Study on Design and Starting Characteristics of a Sub-scale Diffuser for Simulating High-Altitude Environment
Lee, Yang-Suk ; Jeon, Jun-Su ; Ko, Young-Sung ; Yang, Jae-Jun ; Kim, Sun-Jin ; Kim, Jung-Hoon ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 5, 2009, Pages 21~28
This experimental study was performed to find the important design parameters and the starting characteristics of a supersonic exhaust diffuser. The experimental study was carried out on a scaled down model of straight cylindrical supersonic exhaust diffuser, in order to evaluate the effects of operating fluid(air, nitrogen), the diffuser inlet area over the primary nozzle throat area(
), the inlet pressure of primary nozzle, diffuser length over diffuser inner diameter(
) and existence or nonexistence of diffuser divergence. The test results showed that the starting pressure increased with decrease in diameter of primary nozzle, and the measured starting pressure of the diffuser had approximately 90~98% efficiency as compared with the predicted starting pressure. Also, the diffuser was started at all case, regardless of
(above 8.4) and diffuser divergence. The result of this study can be used as an essential database for developing a simulated high-altitude facility for real-scale model.
Estimation of Feeding Performance of Pneumatic System
Cho, Nam-Kyung ; Chung, Yong-Gahp ; Shin, Dong-Soon ; Cho, In-Hyun ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 5, 2009, Pages 29~40
Pneumatic system is widely applied to ground facility and launcher on-board system. One of the important aspects of pneumatic system is to meet pressure and flow rate requirements of gas consumers. In this paper, a systematic analytical approach for pneumatic system is proposed, which uses and systematically combines previous studies. The proposed analytical method is that pressure/flow calculation using conservation equations are combined with sonic limit check at vena contracta of the components of pneumatic system, which checks the installed components whether they are merely pressure loss elements or flow limiting element of the system. In this paper, gas consumers are categorized and simulated using the proposed method. The results reveal that the feeding performance of general pneumatic system can be properly estimated using the proposed approach.
A Study on the Reduction of Supersonic Cavity Pressure Oscillations Using a Sub-Cavity System
Shin, Choon-Sik ; Jeong, June-Chang ; Suryan, Abhilash ; Kim, Heuy-Dong ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 5, 2009, Pages 41~47
Numerical computations were carried out to analyze the effect of a sub-cavity at several inlet Mach numbers on the control of cavity-induced pressure oscillations in two-dimensional supersonic flow. The present passive control method, the sub-cavity applied to the front wall of a square cavity, was studied for the inlet Mach numbers of 1.50, 1.83 and 2.50. The results show that the sub-cavity is effective in reducing the oscillations, and a resultant amount of the reduction depended on the inlet Mach number, the length of flat plate, and the depth of sub-cavity used as an oscillation suppressor.
Auto-ignition Characteristics of Paraffin and PE Hybrid Rocket with
An, Sung-Yong ; Jin, Jung-Kun ; Jung, Eun-Sang ; Kwon, Se-Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 5, 2009, Pages 48~56
The auto-ignition tests of hybrid rockets with the concentrated hydrogen peroxide as an oxidizer were presented. Auto-ignition was successfully demonstrated by injecting decomposed gases from
into paraffin or polyethylene fuels. In addition, restart and instant ignition were realized with this rocket. For stable combustion, a higher
value was required for the paraffin combustion compared with PE. On the other hand, much faster response time was demonstrated in case of a paraffin, which was 13 and 30 ms at ignition delay and rise time respectively.
A Study on Modeling Program Development of an Environmental Control System
Yoo, Young-Joon ; Lee, Hyung-Ju ; Kho, Seong-Hee ; Ki, Ja-Young ;
Journal of the Korean Society of Propulsion Engineers, volume 13, issue 5, 2009, Pages 57~63
A modeling and simulation program for an environmental control system (ECS) of a pod installed under wings of an aircraft was developed in order to estimate the system‘s performance during a flight. First, through the system configuration analysis in the main operational condition of the aircraft system, an ECS configuration adopting an air cycle machine (ACM) was selected. Therefore the modeling program was developed to simulate the ECS with an ACM. Second, the sensitivity analyses on performance variation of main components were conducted to complete the conceptual design of the ECS. A design point for the system and its components was obtained through the analysis with the modeling and simulation program. The design point for the system and components was obtained through the analysis with the modeling and simulation program. Third, in order to study the feasibility of the ECS configuration, off-design performances of the ECS on various flight conditions, such as take off, maneuver, cruise and landing etc were estimated. Dynamic characteristics were analyzed by transient performance evaluations.