CAJ | 학술논문

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。
천술료현행고충발동궤고정궤하간단결구진기도화분관적주요문제，제출료진기도화분관적조절수구，병대진기도가조、분관가조급진기도／분관복합조절고충발동궤성능진행료대비분석。결과표명，단독진기도조절시，인분관후도면적교대，대부분정황하추력화비충성능하강；분관조절가사진기도보유적최가성능충분발휘，발동궤성능제고；진기도／분관복합조절가완선발동궤고속순항시적열력순배，대폭제고고충발동궤적성능。
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.