摘要
对建立的腹部S型进气道及前机身模型,采用多层快速多级子方法计算雷达散射截面,研究了进气道唇口斜切方式、上下唇边锯齿化、S型弯道长度、等直段安装吸波导流环和前机身形状对腹部进气道头向RCS的影响,并分析进气道与前机身的耦合散射特性。通过计算进气道参数改变前后的电磁散射特性,找出影响腹部进气道头向雷达散射截面的主要因素和RCS减缩方法,并对各种减缩方法的减缩效果作了对比分析。研究结果为腹部进气道的头向RCS减缩提供了技术依据。
The Radar Cross Section （RCS） of Ventral Inlet has been investigated,with the method of Multilevel fast multipole algorithm for the established ventral S- inlet and fore body＇s three- dimensional model. It includes the influence of the oblique type of inlet lip, hackle lips, the length of S- bend, flow deflector and the shape of fore body on head- on RCS of ventral inlet and the analysis of the inlet and fore body＇s coupling scattering characteristics. Radar Cross Section Reduction （RCSR） and the main factor which affect head- on RCS of ventral inlet are found by comparing the performance of different parameter. This paper affords a technological basis for head- on RCSR of ventral inlet.
出处
《航空计算技术》
2009年第6期67-70,共4页
Aeronautical Computing Technique
关键词
进气道
隐身技术
雷达散射截面
air inlet
stealth technique
radar cross section
