摘要
对 2种隐身飞机的仿真模型进行了雷达散射特性测试与分析 .其所采取的隐身措施是 :控制散射波峰的方向与数量 ,增大占位比 ,表面金属化 ,三倾斜式进气道及舵面缝隙菱形槽设计 .主要结果和结论是 :2种隐身飞机在头向附近的雷达散射截面 (RCS)不大于 5dB·m2 ,说明现代战斗机非常重视头向的隐身 .减少强散射方向的数目有利于飞机隐身 .垂尾倾斜后与机身或机翼仍构成不完整的二面角具有较强散射 .采取隐身措施总的效果是使飞机重要的头向和侧向暴露距离减小、总体可探测范围减小。
Radar scattering characteristics of two stealth fighter models were tested and analyzed. The models were stealed with the following procedures: controlling the radiating directions and numbers of main scatter sources, increasing the occupation ratio, surface metalizing, leaning the intake lips in three directions, and designing the gaps of the aileron as rhombus. The main results and conclusions are as follows: RCS values of both models are less than 1 m 2, meaning that the stealth characteristic in nose direction is of great importance to the design of modern fighter. It is of benefit to stealth to reduce the number of scattering directions. Incomplete dihedral reflector constructed with the leaned tailer and wing, fuselage or stabilizer is a strong scattering source.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2003年第2期147-150,共4页
Journal of Beijing University of Aeronautics and Astronautics
关键词
隐身飞机
模型试验
雷达散射
invisible aircraft
model tests
analysis
radar reflection
