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本文对超音速燃烧冲压发动机设计参数进行优化。从产生推力与发动机热力循环两方面综合分析得到了以下结果:作为空天飞机动力装置的超音速燃烧冲压发动机,在M_H=6-6.6飞行范围内,按照等面积和等M数分段加热的热力循环设计时,比冲最大;在M_H=6.6-10飞行范围内,按照等面积和等温分段加热的热力循环设计时,比冲最大。从而得到最佳设计参数,并在此基础上,用一元流方法计算了有面积变化,有化学反应、摩擦和散热损失时,超音速燃烧冲压发动机的性能。
In this paper, the design parameters of supersonic combustion ramjet engine are optimized. The following results are obtained from the analysis of the generated thrust and the thermodynamic cycle of the engine: As a supersonic combustion ramjet engine of a space flight aircraft, it is heated in steps of M_H = 6-6.6 in terms of area and equal number of M In the thermodynamic cycle design, the specific impulse is the largest; in the case of the M_H = 6.6-10 flight range, the specific impulse is the maximum when it is designed according to the thermodynamic cycle design with equal area and isothermal section heating. Based on this, the performance of supersonic combustion ramjet engine with area change, chemical reaction, friction and heat loss was calculated by using the unary flow method.