국내 최대 기계 및 로봇 연구정보

기술보고서

기술보고서 게시판 내용
타이틀	C/C Composites for Rocket Chmber Applications part2 Fabrication and Evaluation Tests of Rocket Chamber
저자	Masahiro SATO, Makoto TADANO, Shuichi UEDA, Yukio KURODA, Kazuo KUSAKA, Takeshi Suemitsu, Satoshi Hasegawa, Yukinori Kude
Keyword
URL	http://send.nal.go.jp/send/jpn/dlpdf.php3/naltr01268.pdf?id=NALTR0001268
보고서번호	NAL TR-1268
발행년도	1995.5
출처	NAL (National Aerospace Laboratory of Japan)
ABSTRACT	Carbon fiber-reinforced carbon matrix (C/C) composites coated with SiC are promising candidates for use in the main structual materials of the body of spaceplanes and combustion chambers of rocket engines,because of their superior properties of high specific strength,specific modulus,and fracture strength at high temperatures.However,C/C composite has poor resistance to oxidation,and protection from the oxidating environment is crucial.Conventional C/C composites for use in the high-temperature components of rocket engines are coated with SiC.However,due to the difference in the thermal expansion rates of teh SiC coating layer and the base materials,cracks occur in the SiC coating layer during the coating process,and oxygen diffuses to the base material through the cracks during repeated temperature cycling in the rocket combustion environment.To protect the base materials from oxidation at high temepratures,we have employed SiC C/C-coated composites with a modified matrix and also developed SiC C/C functionally gradient materials (FGMs).In this test series,three kinds of combution chambers were constructed for the Reaction Control System (RCS) subscale engine of H-II Orbiting Plane (HOPE): (1)Conventional C/C composited,(2) SiC C/C-coated composites with a modified matrix,and (3) SiC C/C FGMS.Firing tests were performed at sea level at a temperature around 2000K using nitrogen tetroxide (NTO)/monomethyl hydrazine (MMH) propellant to evaluate the durability of these chambers.This test series showed that conventional C/C composite developed no microcracked and delamination in the coating layer at 1940K/ Modified matrix C/C composite also did not suffer microcracks