机翼前缘后掠角对飞机RCS影响的数值模拟

Numerical Simulation of Wing Leading Edge Sweep Angle Under the RCS Influence

摘要:

为了在飞机总体设计时改善其隐身性能,对机翼前缘后掠角参数化可调的飞机三维数字样机的RCS特性进行了研究。使用CATIA软件,建立机翼前缘后掠角参数化可调的飞机三维数字样机；基于物理光学法和等效电磁流法,采用RCSAnsys软件,使用X波段雷达对飞机进行探测,雷达入射波的俯仰角在-15°、0°和15°条件下,数值模拟机翼前缘后掠角在-30°~+60°之间变化时飞机的RCS特性,并对数值模拟结果进行数理统计分析。在机翼前缘后掠角变化的条件下,飞机RCS特性数值模拟结果表明:飞机头向RCS峰值之一的方位角与机翼前缘后掠角的角度相等；飞机头向RCS算术平均值特性为直机翼大、前掠翼和后掠翼小、大后掠翼更小；飞机侧向和尾向的RCS算术平均值变化相对不大。

Abstract:

In this paper, the RCS characteristics of the aircraft 3-D digital prototype with a parametric adjustable wing leading edge sweep angle was studied,in order to improve stealth performance in the aircraft conceptual design. The CATIA was used to establish aircraft 3-D prototype. RCSAnsys and X-band radar were used to detect the aircraft based on physical optics and the equivalent electromagnetic flow method. In the radar incident wave pitch angle of -15°, 0° and 15°, it conducted numerical simulation on RCS of the aircraft when the wing leading edge sweep angle varied between -30° and 60°. And then statistical analysis on the simulation results were conducted. In the condition of mutative wing leading edge sweep angle, the numerical simulation results of the aircraft RCS showed that the azimuth angle of the aircraft prior to the RCS peak equaled to the wing leading edge sweep angle and the features of the arithmetic mean of the aircraft prior to the RCS were that the bigger the straight wing, the smaller the forward-swept wing and swept wing and the even smaller the large swept wing, and relatively little change happed to the arithmetic mean value of the RCS of the aircraft lateral and tail.