Abstract
This paper presents a new design for the core of a span-morphing unmanned aerial vehicle (UAV) wing that increases the spanwise length of the wing by fifty percent. The purpose of morphing the wingspan is to increase lift and fuel efficiency during extension, to increase maneuverability during contraction, and to add roll control capability through asymmetrical span morphing. The span morphing is continuous throughout the wing, which is comprised of multiple partitions. Three main components make up the structure of each partition: a zero Poisson’s ratio honeycomb substructure, telescoping carbon fiber spars and a linear actuator. The zero Poisson’s ratio honeycomb substructure is an assembly of rigid internal ribs and flexible chevrons. This innovative multi-part honeycomb design allows the ribs and chevrons to be 3D printed separately from different materials in order to offer different directional stiffness, and to accommodate design iterations and future maintenance. Because of its transverse rigidity and spanwise compliance, the design maintains the airfoil shape and the cross-sectional area during morphing. The telescoping carbon fiber spars interconnect to provide structural support throughout the wing while undergoing morphing. The wing model has been computationally analyzed, manufactured, assembled and experimentally tested.
Highlights
The aerodynamic properties of conventional airplane wings can be altered using flaps, slats, and ailerons on the exterior of the wing
910, connected rigid photopolymer as one piece. This was replaced in the proposed design by an assembly the aerodynamic loads without significant transverse deformations, while still featuring the spanwise of flexible interconnecting beams as or “chevrons”
To test the spanwise compliance of the assembled partition, the structure was oriented with the ribs parallel to the floor, known weights were hung from the partition to induce extension, and the resulting displacements were measured
Summary
The aerodynamic properties of conventional airplane wings can be altered using flaps, slats, and ailerons on the exterior of the wing. Ajaj et al [9] used flexible elastomeric skin on their GNATSpar wing design with 5% pre-tension This 0.5 mm-thick latex skin increased the required actuation force and had a significant Poisson’s effect that resulted in a nonuniform airfoil shape along the span. The new design features an assembled honeycomb substructure made of flexible chevrons, integrated with rigid internal ribs This results in spanwise compliance to enable morphing, with a transverse rigidity to effectively carry the aerodynamic loads. Addition, telescoping carbon fiber tubes are used to replace the idea of sliding ribs on a fixed spar, presented that come from printing one large complicated structure in a single. Thepartitions testing results qualitatively confirmed all and the effectiveness of the design
Sign-in/Register to view highlights & summary 
Published Version (
Free)
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call