“…[1][2][3][4] Motivated by specic application in aerospace eld, the maximum service temperature of SiC f /Ti can reach up to 800 C for a long term or up to 1000 C for a short term, which is primarily limited by the bre/matrix interfacial stability and matrix material selection. 5,6 The SiC f / Ti has been considered as a candidate material for blades in turbojet engines, due to the corresponding high shear strength, transverse property and suitable retention of strength under 538 C. 7 Additionally, as the service temperature reaches up to 600-800 C, the compressor bling fabricated by the SiC f /Ti through corresponding structural design can reduce the weight by approximately 40-70%, as compared to the conventional titanium alloy material, thereby highly improving the thrust weight ratio of turbojet engines. 1,8 In contrast to the previous applications in a propulsion system requiring long term stability, the SiC f /Ti is also a potential material for short term applications (<1 hour), as oen important for space or hypersonic ight vehicles.…”