(國防科技大學 航天與材料工程學院，
國防科技重點實驗室， 長沙 410073)
摘 要: 針對固體火箭發(fā)動機喉襯的使用工況， 提出并采用先驅體轉化法制備了一種新型的復合材料， 2D Cf/SiC-Cu材料（其中Cu作為發(fā)汗劑），對其力學性能和燒蝕性能進行了考察。 結果表明： 采用先驅體轉化法可以制備出力學性能較好的2D Cf/SiC-Cu材料，彎曲強度、 剪切強度和斷裂韌性分別達到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， 材料結構保持完整，力學性能仍能滿足喉襯材料的使用要求， 質量損失為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)動機喉襯備選材料。
關鍵字: 2D Cf/SiC-Cu材料； 先驅體轉化； 燒蝕性能； 力學性能
（ 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
