With the continuous development of advanced fighters towards tailless and flying wing layouts, diverse control surfaces have become the mainstream design. To study the influence of spoiler control surface on the radar cross-section (RCS) of a tailless fighter, a calculation method is presented. The deflection angle of the spoiler is controlled by the fixed mode, linear mode, and smooth mode. The results show that the opening action of the spoiler will break the original stealth characteristics of the aircraft at the key azimuth angles of the head and tail. As the elevation angle increases, this adverse effect will spread to the side. The influence of the different dynamic deflection modes of the spoiler on the aircraft RCS is analyzed. Compared with the linear dynamic deflection mode, the smooth dynamic deflection mode is conducive to the reduction in the average RCS at the given head azimuth. The presented method is effective to study the influence of the spoiler deflection on the electromagnetic scattering characteristics of the tailless aircraft.

中文翻译：

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扰流板混合偏转对无尾战斗机雷达截面的影响

随着先进战机不断向无尾翼和飞翼布局发展，多样化的操纵面成为主流设计。为研究扰流板操纵面对无尾战机雷达截面（RCS）的影响，提出了一种计算方法。扰流板的偏转角由固定模式、线性模式和平滑模式控制。结果表明，扰流板的开启动作将在头尾关键方位角处打破飞机原有的隐身特性。随着仰角的增加，这种不利影响会扩散到侧面。分析了扰流板不同动态偏转模式对飞机RCS的影响。与线性动态偏转模式相比，平滑的动态偏转模式有利于降低给定头方位角的平均RCS。该方法有效地研究了扰流板偏转对无尾翼飞机电磁散射特性的影响。