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本文总结了冲压发动机进气道设计的一些规律,阐明了使用冲压发动机作为导弹的动力,并应使进气道系统与导弹紧密结合为一体的问题。进气道设计利用互利相干的设计概念(弹前身、弹翼和外罩起预先压缩)和进气道设计参数(设计马赫数、压缩比、放气量)的折衷考虑,得到性能很好的外装式进气道。本文还对进气道数目、进气道的布局、空气动力格栅、亚音速扩压器的设计、亚临界稳定性等问题进行了分析。
This article summarizes some of the rules for the design of the intake passage of a ramjet engine, clarifies the issue of using a ramjet engine as a missile power and integrating the intake system with the missile. Intake design uses the compromise of mutually beneficial design concepts (projectile, pre-compression of the projectile and casing) and intake port design parameters (design Mach number, compression ratio, deflated volume) to obtain a very good performance Intake airway. The paper also analyzes the number of intake ports, the layout of intake ports, the design of aerodynamic grille, subsonic diffuser and subcritical stability.