A Study And Design Of Dual-Redundancy Brushless Direct Current Electric Actuator

Servo system is the key component of flight control system, and its performance directly determines the flight quality and safety of the aircraft. Improving the quality of components or designing optimization and other measures enhance the reliability of the system, but come at a cost. The redundancy technology can effectively heighten electro-mechanical actuator system reliability. Therefore, the study of dual-redundancy electric actuator control system design has great significance for increasing the reliability of the aircraft.On the basis of understanding the development status of redundant actuator, this paper proposes a new design scheme of dual redundancy electric actuator system. According to the requirements of dual-redundancy electric actuator control system,such as mechanical structure and design performance etc., the motor is selected. Based on the model of the dual redundancy electric actuator, the characteristics of the double channel control structure is analyzed. And the system redundancy resources, fault analysis, redundancy management and other content are introduced. The hardware system is designed with DSP + CPLD as core architecture, and the power management unit, control unit, drive unit, signal acquisition unit, communication unit and other key parts are analyzed in detail. In the part of software design, the design process of the filter module, signal acquisition module, communication module and so on are introduced. Based on the theoretical analysis, the full digital three closed loop control law is designed. The control logic software based on CPLD is designed, and the function of BLDC motor commutation,motor speed calculation and system fault protection are finished.A comprehensive test is carried out on the prototype of double redundancy engineering. The experiment verifies the correctness and rationality of the designed hardware software and control strategy. The verification results show that the dual redundancy BLDC servo system designed in this paper requires design performance. The research results have important reference value for the development of high reliable electric actuator.