摘要
文中进行了ATR（air-turbo-rocket）发动机总体性能研究，以验证其作为近空间飞行器动力系统的可行性。根据ATR的结构特点，建立了发动机性能和特性分析数学模型．编制了计算程序，在设计点计算和分析了燃料／空气比对ATR性能的影响。计算了非设计点性能．对比了不同推进剂的非设计点性能。计算结果表明ATR能够在宽的速度（0-4Ma）、高度（0-11km）范围内工作，单位推力可以达到1200N·s／kg，比冲达到7000N·s／kg。这一结果表明ATR发动机适合作为近空间飞行器的动力系统。
The overall performance of the air-turbo-rocket （ATR） was researched in this paper, and the feasibility of ATR to be used as the power system of near space vehicles was validated. A numerical model of performance and characteristics analysis for ATR was presented and the corresponding computer program was developed. The influence of the fuebair ration on ATR performance at design point was computed and analyzed in detail. The off-design performance of ATR was also computed. The performances of ATR with different propellants were compared at off-design points. The computation results indicated that ATR can operate within the wide range of Mach number（0-4） and altitude （0-11km）, and ATR possesses high specific thrust （1200 N · s/kg） and high specific impulse（7000 N · s/kg）. This result indicates that ATR could be used as the power system of near space vehicles.
出处
《弹箭与制导学报》
CSCD
北大核心
2009年第2期162-165,共4页
Journal of Projectiles,Rockets,Missiles and Guidance
