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针对C/C喉衬喷管小推力长时间工作固体火箭发动机,分别开展了含铝、不含铝两种推进剂状态的地面试验。根据燃烧室压强及发动机推力测试曲线计算了喷管喉径的瞬变值,对比研究了喉衬的烧蚀、沉积过程,指出含铝推进剂发动机C/C喉衬先后经历初始沉积、沉积消融、持续烧蚀、烧蚀与沉积交替四个阶段,而推进剂不含铝时则没有明显的初始沉积与沉积消融。讨论了推进剂配方、燃烧室压强、喷管结构等因素对喉衬烧蚀、沉积的影响,并提出了相应的改善措施。
For the C / C throat lining small thrust thrust long time working solid rocket engine, respectively, carried out with aluminum, aluminum-free two propellant state of the ground test. According to the pressure in the combustion chamber and the engine thrust test curve, the transient value of nozzle throat diameter was calculated. The ablation and deposition process of throat lining were contrastively analyzed. It was pointed out that the C / C throat lining of aluminum bearing propellant engine experienced the initial deposition and deposition ablation , Continuous ablation, ablation and deposition alternate four stages, while the propellant does not contain aluminum, there is no obvious initial deposition and sedimentation ablation. The effects of propellant formula, pressure of combustion chamber, nozzle structure on the ablation and deposition of throat lining were discussed, and the corresponding improvement measures were put forward.