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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society for Aeronautical & Space Sciences
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Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 41, Issue 12 - Dec 2013
Volume 41, Issue 11 - Nov 2013
Volume 41, Issue 10 - Oct 2013
Volume 41, Issue 9 - Sep 2013
Volume 41, Issue 8 - Aug 2013
Volume 41, Issue 7 - Jul 2013
Volume 41, Issue 6 - Jun 2013
Volume 41, Issue 5 - May 2013
Volume 41, Issue 4 - Apr 2013
Volume 41, Issue 3 - Mar 2013
Volume 41, Issue 2 - Feb 2013
Volume 41, Issue 1 - Jan 2013
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Thermomechanical Analysis of Composite Structures in Pyrolysis and Ablation Environments
Choi, Youn Gyu ; Kim, Sung Jun ; Shin, Eui Sup ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 597~604
DOI : 10.5139/JKSAS.2013.41.8.597
A coupled thermomechanical analysis of composite structures in pyrolysis and ablation environments is performed. The pyrolysis and ablation models include the effects of mass loss, pore gas diffusion, endothermic reaction energy, surface recession, etc. The thermal and structural analysis interface is based upon a staggered coupling algorithm by using a commercial finite element code. The characteristics of the proposed method are investigated through numerical experiments with carbon/phenolic composites. The numerical studies are carried out to examine the surface recession rate by chemical and mechanical ablation. In addition, the effects of shrinkage or intumescence during the pyrolysis process are shown.
Finite Element Model Updating and Validation of Satellites for Coupled Load Analysis
Lim, Jae Hyuk ; Kim, Kyung-Won ; Kim, Sung-Hoon ; Hwang, Do-Soon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 605~612
DOI : 10.5139/JKSAS.2013.41.8.605
When developing medium satellites or large satellites, coupled load analysis(CLA) is performed in order to verify satellite design as a final assessment under launch environment. Maximum acceleration, gap between adjacent parts, internal loads obtained from CLA are used to assess the safety of satellite design by comparing them with the allowable loads of every component. To achieve reliable CLA results, satellite FE model have to be properly updated to match with the sine vibration test results. In this paper, the validation procedure of satellite FE model and its results are discussed.
Static Strength of Composite Single-Lap Shear Joint Specimen Using Z-pinning Patch
Choi, Ik-Hyeon ; Lim, Cheol-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 613~618
DOI : 10.5139/JKSAS.2013.41.8.613
In this paper a new concept on z-pinning technology named by authors as `z-pinning patch` will be introduced, which advantage is easy application at manufacturing site of composite structures. Using the trial manufactured z-pinning patch, the z-pinned composite single-lap shear joint specimens were successfully manufactured and tested to check the improvement of joint strengths. The z-pin`s material is stainless steel and its surface was machined as zagged shape and chemically corroded to improve joint force with composite materials.
A Study on the Modeling of PoF Estimation for Probabilistic Risk Assessment based on Bayesian Method
Kim, Keun Won ; Shin, Dae Han ; Choi, Joo-Ho ; Shin, KiSu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 619~624
DOI : 10.5139/JKSAS.2013.41.8.619
To predict the probabilistic service life, statistical factors should be included to consider the uncertainty of parameters. Generally the probabilistic analysis is one of the common methods to account the uncertainty of parameters on the structural failure. In order to apply probabilistic analysis on the deterministic life analysis, it would be necessary to introduce Probability of Failure(PoF) and conduct risk assessment. In this work, we have studied probabilistic risk assessment of aircraft structures by using PoF approach. To achieve this goal, the Bayesian method was utilized to model PoF estimation since this method is known as the proper method to express the uncertainty of parameters. A series of proof tests were also conducted in order to verify the result of PoF estimation. The results from this efforts showed that the PoF estimation model can calculate quantitatively the value of PoF. Furthermore effectiveness of risk assessment approach for the aircraft structures was also demonstrated.
Reliability Prediction of a Pin Puller
Lee, Hyo-Nam ; Jang, Seung-Gyo ; Oh, Jong-Yun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 625~631
DOI : 10.5139/JKSAS.2013.41.8.625
Reliability of a pin puller was predicted by Monte Carlo simulation. The prediction method is based on the stress-strength interference model that failure occurs if the stress exceeds the strength. In this study, the strength is considered as the energy delivered by combustion of pyrotechnics to retreat the pin to a predetermined position, whereas the stress is regarded as the energy required to resist the pin movement. The former mainly depends on the amount of pyrotechnic charge and the latter is governed by several friction forces and the energy dissipation within locking mechanism. Both the variables of stress and strength were computed using an analytical performance model. The method presented here, not depending upon a large number of test item, can be applicable to predict the reliability of other kinds of pyrotechnic devices.
Combustion Performance Test of Syngas Gas in a Model Gas Turbine Combustor - Part 1 : Flame Stability
Lee, Min Chul ; Joo, Seong Pil ; Yoon, Jisu ; Yoon, Youngbin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 632~638
DOI : 10.5139/JKSAS.2013.41.8.632
This paper describes on the flame stability and combustion instability of coal derived synthetic gas especially for gases of Buggenum IGCC in Netherlands and Taean IGCC in Korea. These combustion characteristics were observed by conducting ambient-pressure elevated-temperature combustion tests in GE7EA model combustor when varying heat input and nitrogen dilution ratio. Flame stability map is plotted according to the flame structure by dividing all regimes into six, and only regime I and II are identified to be stable. Both syngases of Taean and Buggenum with nitrogen integration corresponds to regime II in which syngas burnt stably and flame coupled with outer recirculation flow. Stable regime of Buggenum is larger than that of Taean when considering only
/CO ratio due to higher content of hydrogen. However, when considering nitrogen dilution, syngas of Taean is burnt more stably than that of Buggenum since more nitrogen in Buggenum has negative effect on the stability of flame.
Combustion Performance Test of Syngas Gas in a Model Gas Turbine Combustor - Part 2 : NOx/CO emission Characteristics, Temperature Characteristics and Flame Structures
Lee, Min Chul ; Yoon, Jisu ; Joo, Seong Pil ; Yoon, Youngbin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 639~648
DOI : 10.5139/JKSAS.2013.41.8.639
This paper describes on the NOx/CO emission characteristics, temperature characteristics and flame structures when firing coal derived synthetic gas especially for gases of Buggenum and Taean IGCC. These combustion characteristics were observed by conducting ambient-pressure elevated-temperature combustion tests in GE7EA model combustor when varying heat input and nitrogen dilution ratio. Nitrogen addition caused decrement in adiabatic flame temperature, thus resulting in the NOx reduction. At low heat input condition, nitrogen dilution raised the CO emission dramatically due to incomplete combustion. These NOx reduction and CO arising phenomena were observed at certain flame temperature of
, respectively. As increasing nitrogen dilution, adiabatic flame temperature and combustor liner temperature were decreased and singular points were detected due to change in flame structure such as flame lifting. From the results, the effect of nitrogen dilution on the NOx/CO and flame structure was examined, and the test data will be utilized as a reference to achieve optimal operating condition of the Taean IGCC demonstration plant.
Flap Design Optimization for KLA-100 Aircraft in compliance with Airworthiness Certification
Park, Jinhwan ; Tyan, Maxim ; Nguyen, Nhu Van ; Kim, Sangho ; Lee, Jae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 649~656
DOI : 10.5139/JKSAS.2013.41.8.649
High-lift devices have a major influence on takeoff, landing and stall performance of an aircraft. Therefore, a slotted flap design optimization process is proposed in this paper to obtain the most effective flap configuration from supported 2D flap configuration. Flap deflection, Gap and Overlap are considered as main contributors to flap lift increment. ANSYS Fluent 13.0.0
is used as aerodynamic analysis software that provides accurate solution at given flight conditions. Optimum configuration is obtained by Sequential Quadratic Programing (SQP) algorithm. Performance of the aircraft with optimized flap is estimated using Aircraft Design Synthesis Program (ADSP), the in-house performance analysis code. Obtained parameters such as takeoff, landing distance and stall speed met KAS-VLA airworthiness requirements.
Flight Loads Analysis of Aircraft with High Aspect Ratio Flexible Wing by Using MSC/NASTRAN
Jang, Seyong ; Kim, Sangyong ; Kim, Youngyup ; Cho, Changmin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 657~664
DOI : 10.5139/JKSAS.2013.41.8.657
The flight loads analysis was carried out on the aircraft with high aspect ratio flexible wings by using commercial software MSC/NASTRAN. The aerodynamic model for flight loads analysis was corrected, compared with results of the wind tunnel test. And in-house program was developed for pre and post works. In-house program enabling management of much data automatically consists of three modules: `Construction of the mass distributed model`, `Selection of critical load cases`, `Generation of external loads for structural design`. By utilizing these techniques and programs, the procedure of flight loads analysis was established for effective development of an aircraft.
Study on through the thickness stresses in the corner radius of a laminated composite structure
Kim, Sung Joon ; Hwang, In Hee ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 665~672
DOI : 10.5139/JKSAS.2013.41.8.665
One of the major causes of stiffness and strength degradations in laminated composite structures is the delamination between composite layers. In most engineering applications, laminated composite structures have certain curvatures. If the curved composite structure is subjected to bending that tends to flatten the composite structures, through the thickness stresses can be generated in the thickness direction of the composites. Under normal operation open mode delamination could occur at the sites of peak interlaminar stress. This paper describes a technique to determine radial direction stress of a laminated composite structure using a curved beam. Stacking sequence effects of interlaminar stress were studied. The radial location and intensity of the open mode delamination stress were calculated and compared with the results obtained from the analytical solution and finite element method.
Photogrammetric Techniques for Safe Separation Flight Test
Kim, Sang-Jin ; You, Heung-Cheol ; Reu, Taekyu ; Park, Jeong Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 8, 2013, Pages 673~679
DOI : 10.5139/JKSAS.2013.41.8.673
Photogrammetric techniques were used to analyze separation characteristics of store in safe separation flight test. In this analysis, we used single camera method to analyze 6 degrees of freedom of separated store. We established instrumentation requirements based on theoretical background of photogrammetry and guidelines of MIL-HDBK-1763. We applied the photogrammetry to flight test and extracted separation trajectory. We empirically estimated the input variables uncertainties of photogrammetry and its effects on separation trajectory. Using this trajectory which includes the photogrammetric error, we analyzed the safety of separation.