Conceptual Design and Sizing of a Wing-Tip Extension Mechanism for HALE UAV

Abstract

Studies in a multidisciplinary optimization frame work have been carried out to show the benefit of span extension for High Altitude Long Endurance (HALE) Unmanned Aerial Vehicles (UAV) in terms of increasing their loiter performance. Various aspects have been considered in a multidisciplinary optimization framework such as extension mechanism weight penalties, wet wing fuel tank capacity reductions, and lift distribution over the wings. These considerations are made in terms of empirical relations to check feasibility and optimum span extension. The purpose of this paper is to generate a detailed design of a wing tip extension mechanism for a HALE UAV. Load estimates that drive the extension mechanism dimensions are discussed. Based on these load values, appropriate mechanism driving toques and powers have been calculated and hence appropriate motor selections have been done. Actual results of the detailed design can be compared to empirical estimates cited in earlier work. The final paper will describe the calculation procedure followed and the detailed results.