(國防科技大學(xué) 航天與材料工程學(xué)院，
國防科技重點(diǎn)實(shí)驗(yàn)室， 長沙 410073)
摘 要: 針對(duì)固體火箭發(fā)動(dòng)機(jī)喉襯的使用工況， 提出并采用先驅(qū)體轉(zhuǎn)化法制備了一種新型的復(fù)合材料， 2D Cf/SiC-Cu材料（其中Cu作為發(fā)汗劑），對(duì)其力學(xué)性能和燒蝕性能進(jìn)行了考察。 結(jié)果表明： 采用先驅(qū)體轉(zhuǎn)化法可以制備出力學(xué)性能較好的2D Cf/SiC-Cu材料，彎曲強(qiáng)度、 剪切強(qiáng)度和斷裂韌性分別達(dá)到263 MPa， 27.7 MPa和15.7 MPa·m1/2。 材料密度為2.24 g/cm3， 在氧乙炔焰中燒蝕60 s后， 材料結(jié)構(gòu)保持完整，力學(xué)性能仍能滿足喉襯材料的使用要求， 質(zhì)量損失為0.124 g。 因此， 2D Cf/SiC-Cu材料具有較低的密度、良好的力學(xué)性能和較好的抗燒蝕性能， 是一種有希望的固體火箭發(fā)動(dòng)機(jī)喉襯備選材料。
關(guān)鍵字: 2D Cf/SiC-Cu材料； 先驅(qū)體轉(zhuǎn)化； 燒蝕性能； 力學(xué)性能
（ Key Laboratory of Advanced Ceramic Fibers and Composites,
College of Aerospace and Materials Engineering,
National University of Defense Technology, Changsha 410073, China）
Abstract: Based on the working environments of the solid rocket nozzle throat, a proposal to improve anti-ablative property of 2D Cf/SiC composites by introduction of Cu into C/SiC composites and decreasement of surface temperature through Cu transpiration was presented. 2D Cf/SiC-Cu composites were prepared by precursor infiltration and pyrolysis. The mechanical properties and ablative properties were investigated. The flexural strength, shear strength and fracture toughness of the 2D Cf/SiC-Cu composites reach 263 MPa, 27.7 MPa and 15.7 MPa·m1/2, respectively. The desity of the samples is 2.24 g/cm3, and the samples mass loss is 0.124 g when exposed for 60 s in a flowing oxyacetylene torch environment. The mechanical properties of 2D Cf/SiC-Cu composites could still satisfy the requirements of the solid rocket nozzle throat. Compared to other throat materials, 2D Cf/SiC-Cu composites has lower density and better ablative properties.
Key words: 2D Cf/SiC-Cu composites； preceramic polymer pyrolysis； ablative properties； mechanical properties
