端面燃烧发动机中提高推进剂比冲的试验研究

Study on Enhancement of Propellant Specific Impulse in End-Burning Solid Rocket Motor Test

针对端面燃烧发动机中存在喉部烧蚀使燃烧室压强下降进而导致比冲下降的现象,从推进剂燃速、铝粉含量、喉衬材料和结构4个不同方面提高燃烧室压强,分析对复合固体推进剂比冲性能的影响。结果表明:提高推进剂燃速和将石墨喉衬材料更换为钨渗铜材料,比冲提高;降低推进剂铝粉含量,喉部烧蚀现象得到改善,但比冲降低;优化石墨喉衬结构,比冲提高量最大,为最佳方案。

The analysis was made to study effect of increased chamber pressure on specific impulse of solid composite propellant in terms of propellant burning rate,aluminium content,throat insert material and structure thereof,in view of specific impulse decrease phenomenon due to decreased chamber pressure caused by throat erosion in end-burning solid rocket motor.The results showed that increased burning rate and copper infiltrated tungsten instead of graphite for throat insert material contribute to enhanced specific impulse;reduced aluminum content allowed for throat erosion has mitigation but leads to decreased specific impulse;optimized structure of graphite throat insert as the optimum option is the most significant increase in specific impulse.