复合调节固冲发动机性能分析  

Performance study of compound-adjustable ducted rockets

作　　者：邵明玉[1] 王志刚[1] 陈凤明[1] 

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《固体火箭技术》2015年第4期481-486,共6页Journal of Solid Rocket Technology

摘　　要：阐述了现行固冲发动机固定几何简单结构进气道和喷管的主要问题,提出了进气道和喷管的调节需求,并对进气道可调、喷管可调及进气道/喷管复合调节固冲发动机性能进行了对比分析。结果表明,单独进气道调节时,因喷管喉道面积较大,大部分情况下推力和比冲性能下降;喷管调节可使进气道保有的最佳性能充分发挥,发动机性能提高;进气道/喷管复合调节可完善发动机高速巡航时的热力循环,大幅提高固冲发动机的性能。The major problems of current ducted rockets with fixed-geometry inlet / nozzle are summarized,and the adjustment demand of variable-geometry inlet / nozzle for ramjet thermodynamic cycle is listed as well. Next,the performances of ducted rockets with fixed-geometry,adjustable inlet,adjustable nozzle and compound-adjustable inlet / nozzle are compared and analyzed. Results show that： inlet adjustment decreases the engine performance in most case due to the larger nozzle throat; nozzle adjustment gives a full play to optimum performance of inlet,therefore enhances engine performance; the inlet / nozzle compound-adjustment improves the ramjet thermodynamic cycle during high speed cruising,which greatly increases the performance of ducted rocket.

关 键 词：固体火箭冲压发动机 复合调节 进气道 喷管 

分 类 号：V438[航空宇航科学与技术—航空宇航推进理论与工程]