先驱体转化陶瓷基复合材料技术precursor-derived ceramic matrix composite-part1.ppt

(2) Satellite Propulsion for use in Combustion chambers for apogee - and attitude - control engines for satellites : In-use refractory heavy metals (Re, Ir) high density (21) high cost C/SiC: besides the benefits in nozzle extension, further simplification of the construction method by reducing the individual components (single - piece construction), hence reduced test effort; increase in the permissible wall temperatures of currently 1900 to ～ 2200 K (with suitable layer system), hence increase of engine performance. reduction of engine mass of 30 to 50 %. (2) Satellite Propulsion Figure PIP - C/SiC combustion chamber (left) and during hot test (right). (Space Transportation Corp.) (2) Satellite Propulsion Figure PIP - C/SiC combustion chamber (left) and during hot test (right). Figure PIP - C/SiC combustion chamber (left) and during hot test (right). Figure EAM PIP - SICARBON production model. (2) Satellite Propulsion Due to the low specific weight, the high specific strength over a large temperature range, the low CTE, the good chemical and erosion resistance with hypergolic propellants, their good damage tolerance, and the feasibility of manufacturing a single piece reinforced ceramic combustion chamber combined with a nozzle extension, the Astrium’s LPI - C/SiC was defined as baseline material for the development of the new European Apogee Motor EAM . C/SiC ? NEXT GENERATION MATERIALS (2) Satellite Propulsion hot structures thermal protection systems for future re-useable space transportation vehicles. (3) Thermal protection systems (TPS) Figure Articles made of C/SiC in X-38 space plane (3) Thermal protection systems (TPS) Figure nose cone and wing leading edge in X-38 (C/SiC) (3) Thermal protection systems (TPS) Thanks for your attention! WITH so big a thruster, the mass is only less than 5kg. * * Precursor-derived Ceramic Matrix Composites hfhu_nudt@nudt.edu.cn Contents 1 Introduction of C/SiC and PIP Process 2 Precursors f