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针对以火箭基组合循环(RBCC)发动机作为水平起飞两级入轨(TSTO)运载器第一级动力系统的方案,建立了进气道-燃烧室-尾喷管一体化流道耦合性能快速计算模型,初步设计了RBCC发动机一体化内流道。RBCC发动机使用变结构进气道,采用支板/凹腔相结合实现火焰稳定的燃烧室以及单侧膨胀尾喷管;应用经过校验的性能分析模型进行RBCC燃烧室性能快速计算;对比分析了性能分析模型与三维数值计算获得的发动机出口状态参数对于飞行器后体流场的影响性;完成了RBCC为动力的两级入轨方案飞行器动力系统的性能分析与计算;分析评估了飞行弹道条件下RBCC推进系统的性能。计算结果表明:飞行器起飞质量280t时,可以完成运送4t载荷进入近地轨道的任务。
Aiming at the scheme that the rocket-based combined cycle (RBCC) engine is used as the first-stage power system of the horizontal take-off two-stage orbit (TSTO) carrier, a fast calculation of coupling performance of the inlet- Model, a preliminary design of the RBCC engine integrated inner runner. The RBCC engine uses a variable structure intake port, a flame-stabilized combustion chamber with a combination of a support plate and a cavity, and a single-sided swollen tail nozzle. The calibrated performance analysis model is used to quickly calculate the performance of the RBCC combustion chamber. Performance analysis model and three-dimensional numerical calculation of the engine outlet state parameters on the impact of the aircraft body flow field; completed RBCC-powered two-stage orbit into the program of the powertrain performance analysis and calculation; analysis and evaluation of the flight trajectory conditions RBCC advances system performance. The calculation results show that when the mass of the aircraft is 280t, the task of transporting 4t payload into orbit can be accomplished.