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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
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Volume & Issues
Volume 16, Issue 6 - Dec 2012
Volume 16, Issue 5 - Oct 2012
Volume 16, Issue 4 - Aug 2012
Volume 16, Issue 3 - Jun 2012
Volume 16, Issue 2 - Apr 2012
Volume 16, Issue 1 - Feb 2012
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Spray Characteristics of Nonimpinging-type Injector According to the Injection Pressure Variation and Angular Direction of Orifices
Jung, Hun ; Kim, Jong-Hyun ; Kim, Jeong-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 1~8
DOI : 10.6108/KSPE.2012.16.3.001
A water-flow test was carried out for the nonimpinging-type injector to be equipped on 70 N-class liquid-rocket engine under development. Breakup patterns of injector-spray transit from a smooth jet to wavy one as the injection angle increases, whereas spray-breakup lengths are inversely proportional to the injection pressure. It is confirmed that there exist ruffles on the surface of liquid column, which could be caught through the instantaneous spray images captured by high-speed camera. A phenomenon of spray shedding amplified at the specific pressure level of 0.93 MPa was an unexpected behavior of the injected stream and it is to be investigated further.
A Study on Ultrasonic Wave Propagation Model in Multi-Layer Media
Lim, Soo-Yong ; Kim, Dong-Ryun ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 9~15
DOI : 10.6108/KSPE.2012.16.3.009
This research simulates the ultrasonic wave propagation in multi-layered media using generalized formular of system response function. We made the artificial defect specimen of a rocket motor and compared with experimental wave forms. The simulation results are coincide with measured waves and we found that the pulse echo method is able to detect unbond defect at liner-propellant interface.
Agitation Effects of an Ultrasonic Standing Wave on the Dynamic Behavior of Methane/Air Premixed Flame
Seo, Hang-Seok ; Lee, Sang-Shin ; Kim, Jeong-Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 16~23
DOI : 10.6108/KSPE.2012.16.3.016
This study has been conducted to scrutinize agitation effects of an ultrasonic standing wave on the dynamic behavior of methane/air premixed flame. The propagating flame was caught by high-speed Schlieren images, through which local flame velocities of the moving front were analyzed in unprecedent detail. It is revealed that the propagation velocity agitated by the ultrasonic standing wave is greater than that without agitation at the stoichiometric ratio: the velocity enhancement diminishes as the equivalence ratio approaches upper flammability limit or lower flammability limit. Also, vertical locations of the wave-affected frontal distortions do not vary appreciably, unless the propagating-mode characteristics (pressure amplitude and driving frequency) of ultrasonic standing wave were not changed.
The Study of Anti-Releasing Bolt Manufactured by Expanding a Particular Part of Bolt Body
Kim, Dong-Jin ; Lee, Yeung-Jo ; Kim, Nam-Chun ; Lee, Jung-Bok ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 24~33
DOI : 10.6108/KSPE.2012.16.3.024
The present work has suggested the design methods of the bolt body for making the anti-releasing bolts and provided the changed properties of the bolt body after explosion. To prove this work, two models of the anti-releasing bolts, M10 and M20, are produced and the expansion properties of each model are experimentally obtained. This study verify that the expansion of the bolt body is reproducible and the expansion rate could be controlled by the combination of the design factors and the anti-releasing characteristics could be quantified. It also could provide the data that would be needed to make the bolts with the anti-releasing effect.
Pressure Control Law of Gas Generator Considering Combustion Volume Change
Park, Ik-Soo ; Lee, Jae-Yoon ; Choi, Ho-Jin ; Kim, Jung-Hoe ; Yoon, Hyun-Gull ; Lim, Jin-Shik ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 34~40
DOI : 10.6108/KSPE.2012.16.3.034
A pressure control law to regulate pressure of gas generator is suggested. To design a model based control law, the governing equation which consists of Robert and conservation equation is built and verified through the ground burning test. PID and nonlinear adaptive control laws are designed to analyze the loop response characteristics under the system which has varying eigen properties arisen from combustion volume change. It is suggested that new approach, gain scheduling design, is required to overcome the defects identified from numerical simulation results of the two control laws. The newly suggested scheme shows good control performance even under disturbances and measurement noise.
Optimal Conditions for Maximizing Altitude of Sounding Rocket
Lee, Sang-Hyeon ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 41~48
DOI : 10.6108/KSPE.2012.16.3.041
A study to determine the optimal jet conditions for maximizing altitude of the sounding rocket is conducted. The behavior of a simplified one-dimensional momentum equation including aerodynamic drag is investigated. The case where an analytic solution exists and the case where the mass flow rate is constant are calculated. The solutions are compared with numerical solutions. It is shown that there are the optimal jet conditions for maximizing altitude of a sounding rocket and the optimal condition is a function of the rocket mass ratio.
Rupture Prediction of the Rupture Disk Using Elasto-Plastic Analysis
Han, Houk-Seop ; Lee, Won-Bok ; Koo, Song-Hoe ; Lee, Bang-Eop ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 49~56
DOI : 10.6108/KSPE.2012.16.3.049
Rupture disks are a kind of safety device in high pressure equipment and they are used to control rupture pressure in the solid rocket motor. In this paper, a series of rupture experiments was performed using rupture disks made of AISI 316L and rupture pressure of rupture disks was calculated through various assumptions in relation between elasto-plastic material properties and true stress-strain curve. Experiment and FEA indicated rupture pressure is determined by size of rupture disks. As a result of elasto-plastic analysis, only multi-linear stress-strain curve was able to calculate meaningful estimations. Experimental results also showed rupture location are decided by the size of rupture disks. Experimental and FEA results will be applied to control rupture pressure of disks.
Design on High Efficiency and Light Composite Propeller Blade of High Speed Turboprop Aircraft
Kong, Chang-Duk ; Lee, Kyung-Sun ; Park, Hyun-Bum ; Choi, Won ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 57~68
DOI : 10.6108/KSPE.2012.16.3.057
In this study, designs of the high efficiency composite propeller blade for a high speed turboprop aircraft, which will be used for a next generation regional commercial aircraft in Korea, are performed. Both the vortex theory and the blade element theory are used for preliminary aerodynamic design and performance analysis of the propeller. Then the aerodynamic design result is confirmed through performance analysis using a commercial CFD code, ANSYS. The carbon/epoxy composite materials is used, and the skin-spar-foam sandwich type structure is adopted for improvement of lightness and structural stability. Finally, it is investigated that the proposed propeller blade has high efficiency and structural safety through both aerodynamic and structural analysis and experimental test of a prototype propeller blade.
Development of a Ejection Gas Generator for Precluding Erosive Burning by Using Bundle Cylindrical Grains
Oh, Seok-Jin ; Cha, Hong-Seok ; Jang, Seung-Gyo ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 69~76
DOI : 10.6108/KSPE.2012.16.3.069
An achieving method of highly progressive pressure gradient is presented to enhance the missile ejection system`s performance by using a gas generator in the condition of preventing erosive burning. To obtain and confirm a stable burning, a ground burning test was performed to evaluate the new methods of a radial-hole and a multi-row propellant grain. The test results show that a radial-hole grain takes good effect on erosive burning and not on ejection performance. On the other hand, a multi-row grain which reduces the length-to-diameter ratio(L/D) of grain is very effective to prevent the erosive burning and to enhance the ejection performance simultaneously.
Helium Quantity Estimation for LOx Tank Pressurization of a Restartable Pressure-fed Propulsion System
Cho, Gyu-Sik ; Jung, Young-Suk ; Oh, Seung-Hyub ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 77~81
DOI : 10.6108/KSPE.2012.16.3.077
In a cryogenic propellant tank the pressurant is contracted due to heat loss and the propellant itself evaporates. On a restartable propulsion system such phenomena are more intensive because the propellant contacts with the pressurant on the larger surface during the coast flight. Such heat and mass transfer phenomena should be considered for estimating the amount of pressurant. On the hypothesis that the heat and mass transfer quasi-equilibrium is achieved during the coast flight, the calculation process of the equilibrium pressure is presented. On the process the amount of loaded helium on the Falcon-1 second stage is calculated.
Estimation of Heat Transfer Coefficient at the Upper Layer of Cryogenic Propellant
Kwon, Oh-Sung ; Kim, Byung-Hun ; Kil, Gyoung-Sub ; Ko, Young-Sung ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 82~89
DOI : 10.6108/KSPE.2012.16.3.082
The temperature of cryogenic propellant in the propellant tank increases during flight due to heat input from surroundings. The propellant which temperature rises up over the required condition of turbo-pump remains as unusable propellant at the end of flight. In this paper the estimation method of the heat transfer coefficient at the upper layer of cryogenic propellant was presented. The heat transfer mode at the propellant upper layer was considered as conduction. Temperature distributions near propellant surface obtained from heat transfer coefficient were compared with test data to show the possibility of this method.
A Study on the Structural Analysis of Joint Part in Accordance with Adhesive Length of a Composite Rocket Motor Case
Jeon, Kwang-Woo ; Shin, Kwang-Bok ; Hwang, Tea-Kyung ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 90~96
DOI : 10.6108/KSPE.2012.16.3.090
In order to determine optimal design length of adhesive joint of a composite rocket motor case, stress analysis of joint part according to changes of adhesive length was done. Adhesive length has a range of 50 mm to 300 mm as design variables. The ratio of adhesive length without any stress gradient to initial non-stressed adhesive length was determined as evaluation criteria for selection of adhesive length, which called "stress gradient length ratio". The numerical result showed that stress gradient length ratio of joint part with adhesive length of more than 200 mm was increased very slowly with increase of adhesive length. It means that adhesive length of about 200 mm could be the optimal dimension to ensure the structural safety of joint part against internal pressure of 2,500 psi.
A Technical Trend of Manufacturing and Materials of Nozzle Extension for Thrust Chamber of Liquid Rocket
Lee, Keum-Oh ; Ryu, Chul-Sung ; Choi, Hwan-Seok ;
Journal of the Korean Society of Propulsion Engineers, volume 16, issue 3, 2012, Pages 97~103
DOI : 10.6108/KSPE.2012.16.3.097
The combustion chamber and nozzle of a liquid rocket engine should be protected from the high temperature combustion gas generated by the chamber. An upper-stage nozzle extension has a large expansion ratio, therefore, The light-weight refractory materials have been used since the weight impact on the launcher performance is crucial. Gas film cooling method was used before, but was not applicable nowadays. Ablative cooling method and radiative cooling method with niobium alloy, Ni-based superalloy and ceramic based composite have been used to this day.