Development of a reliable electro-mechanical actuator for primary control surfaces in small aircrafts

This paper lays the foundation for the development of an innovative electro-mechanical actuator for flight-control surfaces. The main features of the enhanced system will be the introduction of new sensor types and health monitoring capabilities. A dedicated test bench has been developed in order to perform endurance tests, leading the mechanical components to failure. In this view, a Condition Monitoring (CM) algorithm is expected to assess the progressive faults degradation, estimating their progression and the Remaining Useful Life (RUL) of related subsystems. Based on the development of new hardware and software components, the REPRISE project is expected to deliver a significant contribution to the More Electric Aircraft mission.

[1]  R. J. Frye,et al.  Advanced secondary power system for transport aircraft , 1985 .

[2]  Marios M. Polycarpou,et al.  Fault Detection and Isolation Scheme in Continuous Time Nonlinear Stochastic Dynamical Systems , 2003 .

[3]  Daming Lin,et al.  A review on machinery diagnostics and prognostics implementing condition-based maintenance , 2006 .

[4]  Alberto Luigi Cologni,et al.  Modeling and Identification of an Electro-Hydrostatic Actuator , 2010 .

[5]  S. J. Cutts,et al.  A collaborative approach to the More Electric Aircraft , 2002 .

[6]  E. Peter Carden,et al.  Vibration Based Condition Monitoring: A Review , 2004 .

[7]  Y. C. Yeh,et al.  Triple-triple redundant 777 primary flight computer , 1996, 1996 IEEE Aerospace Applications Conference. Proceedings.

[8]  Alireza Behbahani,et al.  Control Strategy for Electro-Mechanical Actuators Versus Hydraulic Actuation Systems for Aerospace Applications , 2010 .

[9]  Stuart Galloway,et al.  Demonstrating the more electric engine: a step towards the power optimised aircraft , 2011 .

[10]  Bulent Sarlioglu,et al.  More Electric Aircraft: Review, Challenges, and Opportunities for Commercial Transport Aircraft , 2015, IEEE Transactions on Transportation Electrification.

[11]  Laura Baxerres,et al.  Health Monitoring for the Flight Control EMAs , 2015 .

[12]  Ming Zhang,et al.  Circuit Failure Prediction and Its Application to Transistor Aging , 2007, 25th IEEE VLSI Test Symposium (VTS'07).

[13]  Yuanjun Zhou,et al.  The reliability prediction of an Electro-Mechanical Actuator of aircraft with the hybrid redundant structure , 2008, 2008 IEEE Vehicle Power and Propulsion Conference.

[14]  Gerald Burt Kliman,et al.  Methods of Motor Current Signature Analysis , 1992 .

[15]  C.S. Byington,et al.  A model-based approach to prognostics and health management for flight control actuators , 2004, 2004 IEEE Aerospace Conference Proceedings (IEEE Cat. No.04TH8720).

[16]  Mohamed El Hachemi Benbouzid.  A review of induction motors signature analysis as a medium for faults detection , 2000, IEEE Trans. Ind. Electron..

[17]  Robert Navarro,et al.  Performance of an Electro-Hydrostatic Actuator on the F-18 Systems Research Aircraft , 1997 .

[18]  Fabio Previdi,et al.  Modeling and identification of an Electro-Hydraulic Actuator , 2016, 2016 12th IEEE International Conference on Control and Automation (ICCA).

[19]  Abhinav Saxena,et al.  Experimental Validation of a Prognostic Health Management System for Electro-Mechanical Actuators , 2011 .

[20]  Pascal Traverse,et al.  A family of fault-tolerant systems: electrical flight controls, from Airbus A320/330/340 to future military transport aircraft , 1995, Microprocess. Microsystems.