In this work, the ablation behavior of monolith ZrB2-30 vol%SiC (Z30S) composites were studied under various oxy-acetylene flame angles. Typical oxidized microstructures (SiO2/SiC-depleted/ZrB2-SiC) were observed when the flame to Z30S was arranged vertically. However, formation of the outmost glassy SiO2 layer was hindered when the Z30S was tilted. The SiC-depleted region was fully exposed to air with reduced thickness when highly tilted. Traces of the ablated and island type SiO2 were observed at intermediate flame angles, which clearly verified the effect of flame angle on the ablation of the SiO2 layer. Furthermore, the observed maximum surface temperature of the Z30S gradually increased up to 2,200 °C proving that surface amorphous silica was continuously removed while monoclinic ZrO2 phase began to be exposed. A proposed ablation mechanism with respect to flame angles is discussed. This observation is expected to contribute to the design of complex-shaped UHTC applications for hypersonic vehicles and re-entry projectiles.

Stainless steel, a type of steel used for high-temperature parts, may cause damage when exposed to high temperatures, requiring additional coatings. In particular, the Cr2O3 product layer is unstable at 1000oC and higher temperatures; therefore, it is necessary to improve the oxidation resistance. In this study, an aluminide (Fe2Al5 and FeAl3) coating layer was formed on the surface of STS 630 specimens through Al diffusion coatings from 500oC to 700oC for up to 25 h. Because the coating layers of Fe2Al5 and FeAl3 could not withstand temperatures above 1200oC, an Al2O3 coating layer is deposited on the surface through static oxidation treatment at 500oC for 10 h. To confirm the ablation resistance of the resulting coating layer, dynamic flame exposure tests were conducted at 1350oC for 5–15 min. Excellent oxidation resistance is observed in the coated base material beneath the aluminide layer. The conditions of the flame tests and coating are discussed in terms of microstructural variations.

Stainless steel is being used in various industries such as automobile and aerospace for its cheap manufacturing cost and excellent mechanical properties. However, stainless steel failed to stably protect a specimen with a Cr2O3 protective layer at temperatures above 1000 ℃. Thus, improving the high temperature flame resistance of the specimen through additional surface coating was needed. In this study, multilayer coatings of YSZ and Al2O3 were performed on SUS 304 specimens using pack cementation coatings and thermal plasma spray. The multilayer coated specimen showed enhanced thermal properties due to the coated layers. The microstructures and phase stability are discussed together with flame conditions at 1350 ℃.

Ablative material in a rocket nozzle is exposed to high temperature combustion gas, thus undergoes complicated thermal/chemical change in terms of chemical destruction of surface and thermal decomposition of inner material. Therefore, method for conjugate analysis of thermal response inside carbon/phenolic material including rocket nozzle flow, surface chemical reaction and thermal decomposition is developed in this research. CFD is used to simulate flow field inside nozzle and conduction in the ablative material. A change in material density and a heat absorption caused by the thermal decomposition is considered in solid energy equation. And algebraic equation under boundary layer assumption is used to deduce reaction rate on the surface and resulting destruction of the surface. In order to test the developed method, small rocket nozzle is solved numerically. Although the ablation of nozzle throat is deduced to be higher than the experiment, shape change and temperature distribution inside material is well predicted. Error in temperature with experimental results in rapid heating region is found to be within 100 K.

4방향성(4D)탄소섬유 프리폼을 각각 polyfurfury1 alcohol과 석탄계 핏치로 함침하는 방법과 CVI방법에 의하여 열분해 탄소로 증착하는 방법을 채택하여 4방향성 탄소/탄소 복합재를 제작하였다. 아크플라즈마 토치 및 지상연소 시험에 의하여 이들의 삭마특성을 비교 관찰하였다. 4D 탄소/탄소 복합재의 기공도는 밀도가 증가할 수록 감소하였으며, 고밀도화된 시편일 수록 삭마저항성이 우수하게 나타났다. CVI-핏치계 4D 탄소/탄소 복합재가 내삭마 성능이 가장 우수하였다. 삭마거동은 결합재의 종류와 복합재의 밀도 및 기공도에 크게 의존함을 알 수 있었다.

PAN계 탄소섬유와 페놀수지를 이용하여 rod를 인발성형 한 후, 다른 섬유분율을 갖는 두종류의 hexagonal type 4D 프리폼을 제작하였다. 석탄계 핏치를 가압함침 탄화공정을 통하여 함침한 후 탄화와 고온열처리를 하였다. 이와 같은 공정을 반복하여 고밀도화된 4D CRFC를 제조하였다. 열충결 시험 후 새로운 크랙이 생성되었을 뿐만 아니라 기존의 크랙이 확장되었으며 이와 같은 크랙들은 공기와의 접촉면을 제공하여 중량감소를 보였다. 공기 산화 저항성을 고온열처리 공정을 거친 것이 약 20% 우수하게 나타났다. 4D CFRC의 밀도와 섬유의 분율이 높을 수록 삭마 저항성이 커지고, 삭마량은 시간에 따라 선형적으로 증가하였으며 type II가 type I보다 삭마저항성이 우수하였다. 삭마 메카니즘을 관찰한 결과 1차적으 기질의탈리가 먼저 일어난 다음 섬유가 삭마되었다.

탄소/페놀릭 복합재의 삭마 미세구조와 특성에 대하여 설명하였다. 삭마현상은 추진제와 산화제 사이의 반응에 의한 수증기와 탄산가스의 몰분율에 의해 좌우된다. 그러나, 이 연구논문은 삭마현상이 탄소섬유의 직조형태, 직조밀도, tow크기에 의해서도 변화될 수 있음을 주사전자현미경, 밀도, 열전도도. 삭마표면등을 통해 설명했다. 3가지의 직조형태중, 3K8HS 직조구조가 3K twill구조나 12K8HS구조보다 우수한 내삭마성을 보임을 설명했다.