On-off and proportional-integral controller for a morphing wing. Part 1: actuation mechanism and control design

  1. Get@NRC: On-off and proportional-integral controller for a morphing wing. Part 1: actuation mechanism and control design (Opens in a new window)
DOIResolve DOI: http://doi.org/10.1177/0954410011408226
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Journal titleProceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
Pages131145; # of pages: 15
SubjectActuation control; Actuation mechanism; Control design; Electrical current; Heating phase; Integrated controllers; Morphing wings; Output current; PI Controller; Proportional integral controllers; Rectangular wings; SMA actuators; SMA wire; Smart actuators; Stability margins; System architectures; Time response; Turbulent transition; Vertical displacements; Wing surface; Wing trailing edge; Airfoils; Bode diagrams; Computer simulation; Integrated control; Phase stability; Root loci; Flexible wings
AbstractThe main objective of this research work is the development of an actuation control concept for a new morphing actuation mechanism made of smart materials, which is built from a shape memory alloy (SMA). Two lines of smart actuators were incorporated to a rectangular wing to modify the upper wing surface, made of a flexible skin, with the intention to move the laminarto- turbulent transition point closer to the wing trailing edge. After a brief introduction of the morphing wing system architecture and requirements, the actuation lines' design and instrumentation are presented. The integrated controller controls the SMA actuators via an electrical current supply, so that the transducer position can be used to eliminate the deviation between the required values for vertical displacements (corresponding to the optimized airfoils) and their physical values. The final configuration of the integrated controller is a combination of a bi-positional (on-off) controller and a PI (proportional-integral) controller, due to the two heating and cooling phases of the SMA wires' interconnection. This controller must behave like a switch between the cooling and the heating phases, situations where the output current is 0 A, or is controlled by a PI type law. The PI controller for the heating phase is optimally tuned using integral and surface minimum error criteria (Ziegler-Nichols). The controller is numerically tested on the linear identified system in terms of time response, Bode diagram, amplitude and phase stability margins, and root-locus.
Publication date
AffiliationAerospace; National Research Council Canada
Peer reviewedYes
NPARC number21270198
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Record identifierad984a8a-a6c1-49fd-a227-4b2cc5c27362
Record created2014-01-10
Record modified2016-05-09
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