氢氧发动机大尺寸薄壁C/C-SiC复合材料喷管设计与研究

C/C-SiC Composite Materials Nozzle Extension Design and Investigation for LOX/LH_2 Rocket Engine

为了有效提高发动机比冲和推质比,研究了大尺寸薄壁C/C复合材料喷管技术。通过法兰连接和闭锁装置实现了喷管各段的连接;通过预制体与致密化技术研究,突破了C/C-Si C材料长时间抗氧化技术;通过从制造工艺稳定性和型面控制等方面的研究,实现了大尺寸薄壁旋转件精确型面的生产加工,使出口直径为1060.8mm的C/C-SiC喷管通过100s的高空模拟试车考核,试车后结构完好。研究结果表明:大尺寸薄壁C/C复合材料喷管的成功研制为后续其在上面级发动机上的应用奠定了基础。

The need to increase the payload capacity of the current launchers drives rocket engine designers to seek higher thrust level, specific impulse and thrust to weight ratio. The use of high exit ratio nozzle extension is an efficient way to reach these objectives. Flange and latching system can achieve connections between the cones. Tremendous breakthroughs that significantly upgraded theC/C-SiC material antioxygenic property have been achieved thanks to the technology investigation of performs and densification. It become true that the profile of the large expansion ratio nozzle extension is exactly controlled through techniques stabilization and controlling profile. The C/SiC-C nozzle extension at the exit diameter of 1060.8mm has been successfully tested at high altitude level for the entire test duration of 100s. Furthermore, successful testing of this nozzle extension will pave the way for application of a complete extendable nozzle extension in the future.