带进气道的面对称布局战术导弹气动特性工程估算

The engineering prediction method for aerodynamic characteristics of the symmetrical tactical missile configuration with inlet

随着导弹技术的不断发展和非接触式作战样式的出现,需要有一套快速的工程方法来估算带进气道的战术导弹的空气动力性能。针对带有进气道的面对称布局战术导弹,基于大量的研究和实验结果以及工程经验,把进气道视作极小展弦比的部件,建立了进气道法向力与压心计算的简化模型,采用部件组合法发展了一种适用于带有进气道的布局形式、计及非线性影响的战术导弹气动力和动导数工程估算方法及程序,计算结果与实验数据吻合较好。

Along with the development of tactical missile technology and the appearance of un-contact campaign pattern, the engineering method is required to fleetly estimate aerodynamic performance of tactical missile with inlet. For the symmetrical tactical missile configuration with inlet, taking inlet as a component with tiny aspect, a simpler model has been built for calculating inlet normal force and pressure center. We can predict the aerodynamic forces as well as dynamic derivatives for the whole missile using component composed-discomposed method. The calculated results and those obtained from the experiment agreed perfectly.