飞翼布局飞机因其控制面尺寸大、开裂式阻力方向舵动作而牺牲其部分低可探测性能，为解决在考虑舵面偏转时求解全航迹动态雷达散射截面（RCS）的问题，提出一种无需预先计算离散化静态RCS的动力学联合电磁学的仿真方法。基于增量动态逆控制设计位置回路、航迹回路、姿态回路和角速度回路，建立具有多操作面特性的飞翼布局飞机动力学模型。分割飞翼布局飞机的舵面为独立模型，并同步飞行航迹过程中的舵面偏转角度使模型执行旋转运算。提出基于动力学联合电磁学的动态RCS求解算法，避免姿态角实时变化导致计算量指数级增长。为验证提出仿真方法的可行性，设计3类动态RCS对比仿真实验，包括考虑舵面偏转、舵偏朝向或背离雷达站和不同雷达工作频率环境。仿真结果表明：舵面偏转对飞翼布局飞机飞行过程中RCS的影响不可忽视，并验证了所提方法能有效求解考虑舵面偏转的飞翼布局飞机的全航迹动态RCS。

Flying wing aircraft sacrifice some low-observability performance due to their large control surface dimensions and split-tail rudder operation. To address the challenge of solving for the full-trajectory dynamic Radar Cross Section （RCS） while accounting for control surface deflection， a simulation method combining dynamics and electromagnetics is proposed that eliminates the need for precomputing discretized static RCS. Based on incremental dynamic inverse control， position， trajectory， attitude， and angular velocity loops are designed to establish a dynamic model of the flying wing aircraft with multi-control-surface characteristics. The control surfaces of the flying wing aircraft are segmented into independent models， synchronizing their deflection angles during flight to execute rotational operations. A dynamic RCS solution algorithm based on combined electromagnetics and dynamics is proposed， avoiding exponential computational growth caused by real-time attitude angle variations. To validate the feasibility of the proposed simulation method， three types of dynamic RCS comparison simulations are designed： considering control surface deflection， control surface deflection toward or away from the radar station， and different radar operating frequency environments. Simulation results demonstrate that control surface deflection significantly impacts the RCS of flying wing aircraft during flight. The proposed method is validated as capable of accurately solving the full-trajectory dynamic RCS of flying wing aircraft considering control surface deflection.