Design and Testing of a Morphing Wing for an Experimental UAV.

摘要

A morphing concept for wing drag reduction for a small UAV is presented. The results of a computational assessment of the morphing concept benefits are shown. 14% to 30% drag reduction in different flight stages serve as motivation for the construction of a prototype. Design requirements of the morphing mechanism structure are pointed out and constructive solutions are shown. Feasibility and functionality of the constructive solutions are discussed briefly. Wind tunnel test results are not available yet.