涡轮增压固体冲压发动机热力循环分析  

Analysis on thermodynamic cycle performance for turbocharged solid propellant ramjet

作　　者：莫然[1] 刘佩进[1] 刘洋[1] 杨飒[1] 

机构地区：[1]西北工业大学燃烧热结构与内流场重点实验室,西安710072

出　　处：《固体火箭技术》2011年第5期598-602,共5页Journal of Solid Rocket Technology

摘　　要：针对未来导弹对推进系统高比冲、宽马赫、大空域的要求,将空速域宽广的空气涡轮火箭(ATR)和比冲性能好的固体火箭冲压发动机(SPR)进行集成,提出了涡轮增压固体冲压发动机(TSPR)的概念,对其进行热力循环分析,验证此组合概念发动机的原理可行性,建立了其热力循环分析模型。利用该模型在典型弹道上对ATR、SPR和TSPR的热力循环性能进行了比较。结果表明,TSPR比循环功最大,热效率稍低于ATR,在大空速域范围飞行时,综合性能优越。The concept of turbocharged solid propellant ramjet（TSPR）,a combined engine of SPR and ATR is proposed.This engine needs to meet the requirements for future propellant system including a higher specific impulse,a broader Mach number operational range and flight altitude variation.The thermodynamic analysis of TSPR was discussed,and corresponding thermodynamic cycle model was developed.The thermodynamic performance of TSPR,ATR and SPR was compared in a flight trace.The results show that TSPR,has the highest specific net work output during a cycle,and the thermal efficiency is slightly lower than ATR.It possesses superior integrated performance when flying in a broader Mach number operational range.

关 键 词：涡轮增压固体冲压发动机 固体火箭冲压发动机 空气涡轮火箭 热力循环分析 比循环功 热效率 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]