通过导弹/发动机一体化设计的计算,验证了SPATR发动机在先进火力支援系统(AFSS—Advanced Fire SupportSystem)中的可用性。利用飞航导弹/涡扇发动机一体化设计思路,建立了AFSS/SPATR发动机一体化设计的约束分析和任务分析模型,并给出...通过导弹/发动机一体化设计的计算,验证了SPATR发动机在先进火力支援系统(AFSS—Advanced Fire SupportSystem)中的可用性。利用飞航导弹/涡扇发动机一体化设计思路,建立了AFSS/SPATR发动机一体化设计的约束分析和任务分析模型,并给出了算例和分析。简述了AFSS任务剖面和约束条件的给定、导弹的质量组成及SPATR发动机模型。对AFSS的约束分析和任务分析计算结果表明,建立的AFSS/SPATR发动机一体化约束分析与任务分析模型合理可行;采用SPATR的AFSS具有超音速飞行能力(H=3～5 km,Ma=1.8),比采用固体火箭发动机的导弹航程更远,并具有盘旋待机能力。展开更多
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 a...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 performance 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 Mach number(0~3) and altitude(0~12 km),and SPATR possesses high specific thrust(1 200 N/(kg/s)) and high specific impulse(7 000 N/(kg/s)) when fuel-air ratio of combustor equals fuel-air ratio.展开更多
文摘通过导弹/发动机一体化设计的计算,验证了SPATR发动机在先进火力支援系统(AFSS—Advanced Fire SupportSystem)中的可用性。利用飞航导弹/涡扇发动机一体化设计思路,建立了AFSS/SPATR发动机一体化设计的约束分析和任务分析模型,并给出了算例和分析。简述了AFSS任务剖面和约束条件的给定、导弹的质量组成及SPATR发动机模型。对AFSS的约束分析和任务分析计算结果表明,建立的AFSS/SPATR发动机一体化约束分析与任务分析模型合理可行;采用SPATR的AFSS具有超音速飞行能力(H=3～5 km,Ma=1.8),比采用固体火箭发动机的导弹航程更远,并具有盘旋待机能力。
文摘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 performance 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 Mach number(0~3) and altitude(0~12 km),and SPATR possesses high specific thrust(1 200 N/(kg/s)) and high specific impulse(7 000 N/(kg/s)) when fuel-air ratio of combustor equals fuel-air ratio.
