Dynamic RCS simulation of flying wing with control surface deflections

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.