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介绍一种机体与推进部件整体化的远程高速飞行器的设计步骤,它包括1)建立性能判据;2)改变发动机和机体参数使性能最佳;3)寻找一种结构方案,使其具有所要求的这些参数。还对超音速燃烧和亚音速燃烧冲压发动机性能进行了近似分析并与相应的机体参数结合考虑。提供计算示例说明如何将这种设计步骤用到以超音速燃烧冲压发动机为动力装置的、巡航马赫数为6的导弹的预先设计中。
The design procedure for a long-range high-speed aircraft with integrated body and propulsion components is described, which includes 1) establishing performance criteria; 2) changing engine and body parameters to optimize performance; 3) finding a structural solution that These parameters are required. An approximate analysis of the performance of supersonic and subsonic combustion engine was also made and combined with the corresponding body parameters. Calculations are provided to illustrate how this design procedure can be used in a pre-design of a missile with a cruise Mach 6, powered by a supersonic combustion ramjet engine.