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.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2011年第5期598-602,共5页
Journal of Solid Rocket Technology
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
turbocharged solid propellant ramjet（TSPR）
air-turbo-rocket（ATR）
solid propellant ramjet（SPR）
thermodynamic cycle analysis
specific net work output during a cycle
thermal efficiency
