Abstract
electromechanical actuator (EMA) as the integrated actuation system used in more aircraft has the advantages of both small size and high power density. Dual-redundancy permanent magnet brushless machine system used in EMA improves aircraft control actuator working reliability. The system topology is proposed by the analysis of different kinds of redundancy running modes and structures of dual-redundancy machine. The cause and consequence of unequal torque in two redundancy machines are analyzed. The equal torque is realized by using crossed-feedback control and piecewise linear interpolation methods. Experimental results show that the method can effectively eliminate torque unequal. The experimental results show that the proposed control strategies are suituble for this system operation under different various complicated conditions such as in the rated operation, step response and frequency response.
Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callDisclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
