Morphing wing-tip open loop controller and its validation during wind tunnel tests at the IAR-NRC

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DOIResolve DOI: https://doi.org/10.13111/2066-8201.2016.8.3.4
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Name affiliation
  1. National Research Council of Canada. Aerospace
FormatText, Article
Journal titleINCAS Bulletin
ISSN20668201
22474528
Volume8
Issue3
Pages41–53
Subjectmorphing wing; wind tunnel tests; open loop controller; communication hardware; electrical actuators; pressure kulite sensors
Abstract
In this project, a wing tip of a real aircraft was designed and manufactured. This wing tip was composed of a wing and an aileron. The wing was equipped with a composite skin on its upper surface. This skin changed its shape (morphed) by use of 4 electrical in-house developed actuators and 32 pressure sensors. These pressure sensors measure the pressures, and further the loads on the wing upper surface. Thus, the upper surface of the wing was morphed using these actuators with the aim to improve the aerodynamic performances of the wing-tip. Two types of ailerons were designed and manufactured: one aileron is rigid (non-morphed) and one morphing aileron. This morphing aileron can change its shape also for the aerodynamic performances improvement. The morphing wing-tip internal structure is designed and manufactured, and is presented firstly in the paper. Then, the modern communication and control hardware are presented for the entire morphing wing tip equipped with actuators and sensors having the aim to morph the wing. The calibration procedure of the wing tip is further presented, followed by the open loop controller results obtained during wind tunnel tests. Various methodologies of open loop control are presented in this paper, and results obtained were obtained and validated experimentally through wind tunnel tests.
Publication date
LanguageEnglish
Peer reviewedYes
NPARC number23000782
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Record identifierf552a752-f66a-4707-8e41-393fec44d017
Record created2016-09-20
Record modified2020-03-16
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