The rapid development of Unmanned Aerial Vehicles (UAVs) requires high safety and reliability standards. The flap control system, being the lifting equipment of a UAV, directly determines whether the aircraft can fly safely. Therefore, it is necessary to improve the reliability of the flap control system to enhance the overall reliability of the UAV. For UAVs with engine and fuselage fusion, the narrow central fuselage space cannot meet the installation requirements of a centralized coaxial drive architecture and cannot accommodate a traditional dual redundancy system. Thus, it is essential to study a flap redundancy architecture suitable for such UAVs to improve system reliability. Focusing on the weakest link in system reliability, this paper proposes a multi-channel double redundancy flap control system that utilizes electrical redundancy technology. This system enables fault mode recognition and redundancy control switching, thereby significantly improving overall system reliability.