研究了整体式固体火箭冲压发动机的应用性能。
Applications of integral solid propellant rocket ramjets arc researched.
首先建立研究静止增程固体火箭冲压发动机补燃室燃烧特性的物理和数学模型。
Physical and mathematic model of investigating combustion characteristics of secondary combustion chamber for static extended solid rocket ramjet was established.
应用概率密度函数非预混模型，对固体火箭冲压发动机补燃室内的湍流燃烧进行了数值模拟。
The numerical simulation of turbulent combustion in the afterburner of solid rocket ramjet was performed by applying the probability density function non -premixed mode.
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