Sebastian Seemann
EADS Innovation Works, TCC6 Energy and Propulsion, Munich, Germany
Clemens Schlegel
Schlegel Simulation GmbH, Freising, Germany
Ladda ner artikel
http://dx.doi.org/10.3384/ecp12076425Ingår i: Proceedings of the 9th International MODELICA Conference; September 3-5; 2012; Munich; Germany
Linköping Electronic Conference Proceedings 76:44, s. 425-432
Publicerad: 2012-11-19
ISBN: 978-91-7519-826-2
ISSN: 1650-3686 (tryckt), 1650-3740 (online)
Replacing hydraulic primary flight control actuators by electromechanical actuators imposes the problem of reduced reliability. This problem may be overcome by using redundant actuators what in turn increases the system complexity. The appropriate redundancy level must be assessed and in case of failures the system must be reconfigured in order to maintain a minimum performance level to meet aircraft safety regulations. Modeling and simulation of such a failsafe redundant electromechanical system in Modelica is described in this paper. Sample simulation results are given.
Electromechanical actuation; redundancy; fail safety; over-determined kinematics; swashplate; flight control; helicopter
[1] W. Bittner. Flugmechanik der Hubschrau-ber; Springer Verlag; 2005.
[2] A. Naubert. Pyrotechnic Jam-Relief Mech-anism for Electromechanical Actuators in Flight Control Applications; Proceedings of the Actuator12 International Conference; Bremen; Germany; 2012
[3] European Aviation Safety Agency. Certification Specifications for Large Rotorcraft (CS29); Köln; Germany; 2003
[4] S. Seemann; M. Christmann; P. Jänker. Con-trol and Monitoring Concept for a Fault-Tolerant Electromechanical Actuation Sys-tem; Proceedings of the R3ASC International Conference; Toulouse; France; 2012
[5] B. K. Walker; E. Gai. A New Approach to Fault-Tolerant Helicopter Swashplate Control; AIAA Aircraft Design; Systems and Technology Meeting; Forth Worth; USA; 1983
[6] www.modelica.org
[7] www.3ds.com/de/products/catia/portfolio/dymola
[8] T. Wu; S. Bozhko; G. Asher; P. Wheeler. Fast Reduced Functional Model of Electro-mechanical Actuators for More-Electric Aircraft Power System Study; SAE Technical Paper 2008-01-2859; Nov.2008
[9] S. Bozhko; T. Wu; C.I. Hill; G. Asher. Accelerated simulation of complex aircraft electrical power system under normal and faulty operational scenarios; in Proc. IEEE IECON 2010; Nov.2010; pp 333-338
