Through aeroelastic effects, the various structural parameters of a wing can have significant effects on the flight dynamics of any size of aerial vehicle. If these parameters could be manipulated in flight, the aeroelastic interactions could, in turn, be leveraged for control purposes. If done properly, this approach has the potential to yield a significant improvement over conventional control surfaces for highly aeroelastic vehicles in terms of maneuverability. In this paper, the preliminary analysis of a proposed structural system with this capability is presented. The proposed system is a combination of a highly flexible conventionally configured wing structure, piezoelectric actuation, and a feedback loop. This system embeds a haptic system into the rear spar of the wing, the effects of which are adjustable by means of a gain parameter. The analysis presented in this paper shows the feasibility of the design and effectiveness of an unoptimized configuration, relocating the flexural axis by approximately 22%. This preliminary analysis establishes that the presented structural-parameter-actuation design, termed flexural-axis control, is practical and realizable. Presented as Paper 2012-1403 at the 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Honolulu, HI, 23-26 April 2012
Control of the Flexural Axis of a Wing with Piezoelectric Actuation
Journal of aircraft ; 52 , 2
2015
Aufsatz (Zeitschrift)
Englisch
Control of the Flexural Axis of a SUAS Wing with Piezoelectric Actuation
British Library Conference Proceedings | 2012
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