固体推进剂空气涡轮火箭发动机的热力循环分析

固体推进剂空气涡轮火箭发动机SPATR（Solid Propellant Air-Turbo-Rocket）是一种吸气式推进装置。本文根据SPATR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气发生器出口参数、压气机压比对SPATR性能的影响。计算了海平面和高空飞行条件下的非设计点性能，对比了不同固体推进剂的推力和比冲性能以及SPATR燃烧室中贫燃和富燃状态下的非设计点性能。计算结果表明SPATR能够在宽的速度（0～3Ma）、高度（0~12km）范围内工作，当燃烧室内油气比为当量油气比时，单位推力可以达到1200Nf/(kg/s)，比冲达到7000Nf/(kg/s)。

Thermodynamic cycle analysis of solid propellant air-turbo-rocket

Solid propellant air-turbo-rocket (SPATR) is an air-breathing propulsion system. A numerical model of performance and characteristics analysis for SPATR was presented and the corresponding computer program was written according to the operation characteristics of SPATR. The influence on the SPATR performance at design point caused by the gas generator exit parameters and compressor pressure ratio had been computed and analyzed in detail. The off-design perform-ance of SPATR at sea level and high altitude had also been computed. The performance of thrust and specific impulse for SPATR with different solid propellant had been compared at off-design points, and the off-design performance comparison had been made between fuel-rich and oxygen-rich. The computation results indicated that SPATR operates within wide range of Maeh number (0 ～3) and altitude (0～12 km), and SPATR possesses high specific thrust (1 200 N/(kg/s)) and high specific impulse (7000 N/ (kg/s)) when fuel-air ratio of combustor equals fuel-air ratio.