To enhance the safety and operational reliability of existing airborne actuator drive units and address the incompatibility issue with backup flight control systems when the primary flight control system fails, this paper proposes a design strategy for a novel actuator drive unit based on permanent magnet brushless motors (PMBLMs). The data bus input end of this actuator drive unit employs 2 FlexRay buses as the physical link layer for external communication and designs a novel question-and-answer data transmission protocol. An input selection function node is set up in the comprehensive judgment of input data, utilizing bus health monitors and power supply voltage amplitude comparisons to complete the judgment and selection of input. In the data computation and processing stage, an independent dual-channel data control function centered on a Field-Programmable Gate Array (FPGA) is implemented, achieving dual closed-loop control of the actuator position and motor speed. The actuator mechanism of the actuator drive unit consists of a PMBLM and its power conversion circuit. Finally, a prototype of the actuator drive unit is built using existing actuators in the laboratory, and various key functional nodes of the actuator drive unit are tested and analyzed. The results verify that the actuator drive unit exhibits stable bus communication, low feedback signal acquisition error, complete fault monitoring functions, and high closed-loop control accuracy, providing a new approach for the design optimization of civilian aircraft airborne actuator drive units.