• Proceedings of the Computational Structural Engineering Institute Conference
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• 2010.04a
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• pp.68-71
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• 2010

극심한 고온 및 고압 환경에 노출되기 쉬운 항공우주 구조물에서 발생하는 기계적 삭마 현상을 해석하기 위하여 영역/경계 분할법을 적용한 삭마 해석 모델을 제안하였다. 영역 및 경계는 상변화 현상에 의한 비선형 거동을 하는 삭마 부영역과 선형 거동을 하는 선형 열탄성 부영역, 공유면, 경계 공유면으로 분할하였다. 삭마 재료 내부의 열분해 반응은 엔탈피 방법을 이용하였으며, 표면 침식 반응은 공기역학적 전단 응력과 삭마 재료의 전단 강도를 기반으로 매칭 기법을 이용하였다. 화학적 및 열적 삭마는 고려하지 않았으며, 간단한 수치 해석을 통해서 기본적인 기계적 삭마 특성을 분석하였다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.141-143
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• 2006

It is well known that there are three mechanisms in the nozzle surface regression, namely ablation, mechanical erosion and chemical corrosion. There are Analogies among these three mechanisms. In order to compare the order of the magnitude of these mechanism, the analogy was adapted and the Mach number of the gas flow was expressed by the nozzle shape(location).

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.119-122
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• 2005

Ablation phenomena is very complicated because it includes momentum, energy and mass transfer, chemical reactions as well as phase change. In this paper, ablation at the rocket nozzle throat is modeled as unsteady one dimensional axi-symmetric with proper boundary conditions and field equation is solved numerically. Analytical results are compared with measured ablation data from firing experimental liquid rocket engine. Test variables are combustion pressure and mixture ratio. for low combustion pressure and low mixture ratio, the discrepancy between analysis and experiments are large but for the normal rocket operation range, two results show a simliar trend with maximum discrepancy of $100\%$.

• Bulletin of the Korean Space Science Society
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• 2003.10a
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• pp.74-74
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• 2003

로켓엔진의 연소실에서는 고온의 연소가스로부터 다량의 열이 발생하기 때문에 이로부터 연소실을 보호하기 위한 방법이 필수적으로 요구된다. 한국 최초의 액체 로켓인 KSR-III 로켓의 주엔진인 KL-3 엔진에서는, 연소실을 보호하기 위한 방법으로 실리카/페놀(Silica/Phenolic) 내열재를 이용하는 용융냉각 방식을 채택하였다 용융냉각 방식은 내열재와 고온의 연소가스와의 물리ㆍ화학적 상호작용에 의해 삭마가 발생하게 되는데, 이러한 삭마는 연소실에서도 가장 고온부인 노즐목에 집중적으로 발생하는 경향이 있다. 그러나 노즐목에서 삭마의 진행은 노즐목의 크기를 증가시키고 연소압 및 추력을 감소시키는 부작용을 초래하게 된다. 본 연구에서는 이러한 열적 삭마에 의한 노즐목 크기의 증가량을 알아내기 위해 KL-3 엔진 노즐목의 형상을 측정하고자 시도하였으며, 노즐목의 삭마에 영향을 미치는 주요 인자를 확인하고 진행과정을 고찰하였다. 노즐목의 형상 측정을 위해서는 기존에 사용하던 3차원 변위 측정기를 이용한 방식의 접근이 곤란함에 따라 영상처리 기법을 도입한 측정 방식을 고안하여 사용하였으며, 이 장비는 만족스런 성능을 보여주었다. 시험결과를 통해서 삭마에 영향을 주는 주요 인자로 분무형태, 연소시간, 연소 온도를 제시하였고 이 중에서 분무형태는 삭마 형상에, 연소 시간 및 연소온도는 삭마량에 주로 영향을 끼친다는 것을 알 수 있었다. 또한 시간에 따른 삭마의 진행이 3개의 구간으로 나누어 설명할 수 있음을 밝혔는데, 노즐목이 원형을 그대로 유지하며 삭마진행이 미미한 구간, 원형에서 벗어나 요철형상이 발달하면서 삭마진행이 가속되는 구간, 요철형상이 이미 정착되어서 요철의 깊이만 증가하되 삭마량은 미미한 구간이다. 결과적으로 60초 연소 후 노즐목 면적 증가율은 +5.82% 정도이며, 이에 따른 연소압 및 추력의 감소 또한 1% 미만으로 미비하였다. 따라서 본 KL-3 엔진에 사용된 내열재의 내열 성능은 임무를 수행하기에 적절하다고 판단하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.6
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• pp.54-63
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• 2015

We present a microscopic understanding of the chemical erosion due to combustion product on the nozzle throat using molecular dynamics simulations. The present erosion process consists of molecule-addition step and equilibrium step. First, either $CO_2$ or $H_2O$ are introduced into the system with high velocity to provoke the collision with graphite surface. Then, the equilibrium simulation is followed. The collision-included dissociation and its influence on the erosion is emphasized and the present molecular observations are compared with the macroscopic chemical reaction model.

• Journal of the Korean Society of Propulsion Engineers
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• v.14 no.5
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• pp.32-44
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• 2010

A two-dimensional thermal response and ablation analysis code for predicting charring material ablation and shape change on solid rocket nozzle is presented. The thermogravimetric analysis (TGA) techniques have been used to characterize the thermal decomposition constants for Arrhenius parameters. Two heterogeneous reactions involving carbon and the oxidizing species of $H_2O$ and $CO_2$ are considered and determined by Zvyagin's ablation model and kinetic constants. The moving boundary problem and mesh moving are solved by remeshing-rezoning method in MSC-Marc-ATAS program. The difference between the calculated and experimental value of char and ablation thickness is up to 20%. For the performance prediction of thermal protection systems, this method will be integrated with a three-dimensional finite-element thermal and structure analysis code through the real time sensing of in-depth temperature and heat flux.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.8
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• pp.597-604
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• 2013

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.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.6
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• pp.523-530
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• 2017

Laser-Induced Breakdown Spectroscopy (LIBS) which a plasma is irradiated at a specific wavelength depending on the material when a high-energy laser is irradiated, and a Raman spectroscopy which measures rotation and vibration in molecules as light-scattering phenomenon occurs, are attracting attention as a space exploration technology because of the advantages of high accuracy and real-time analysis, and the ability to perform long-range detection. In this study, the tendency of the laser spectrum according to the change of the soil component was analyzed by laser spectroscopy and the two - dimensional chemical distribution was conducted based on the trend of laser spectrum. We have also established the environment of Mars (4-7 torr) and lunar atmosphere (<1 torr) in experimental setup, to prove that it is possible to measure by difference of soil chemical composition using LIBS and Raman spectroscopy even in artificial space environment.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.425-429
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• 2011

The development of metal plasma generated by high laser irradiance and its effect on the surrounding air using shadowgraph images after laser pulse termination are studied; hence the formation of laser supported detonation and combustion processes has been investigated. The core of the paper is in detecting chemical reaction using X-Ray Diffraction (XRD) between ablated aluminum plasma and oxygen from air by inducing high power laser pulse (>1000 mJ/pulse) and conduct a quantitative comparison of chemically reactive laser initiated waves with the classical detonation of exploding aluminum (dust) cloud in air. This study may suggest a new approach of initiating detonation from metal sample in its bulk form without the need of mixing nano-particles with oxygen for initiation.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.1
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• pp.36-44
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• 2018

The thermal response of carbon/phenolic used in a solid rocket nozzle liner was analyzed. In this paper, the numerical analysis of the thermal response of carbon/phenolic consists of (1) the integration equation of the boundary layer to obtain the convective heat transfer coefficient of the combustion gas on the rocket nozzle wall and (2) 1-D finite difference method for heat conduction of carbon/phenolic to calculate the ablation, char, and temperature. The calculated result was compared with the result of a blast-tube-type test motor. It is found that the calculated result shows good agreement with the thermal response of the test motor, except at the vicinity of the throat insert.