A flexible wing with conformal control surfaces for optimum trim of a tailless air vehicle

Investigations are conducted to alter the spanwise wing load distribution and reduce the induced drag of a flexible wing by utilizing Active Aeroelastic Wing (AAW) technology and aeroelastic tailoring subject to trimmed flight of a tailless HALE UAV. The work is demonstrated by Finite Element modeling and analysis of a composite slender wing for the UAV. The AAW technology for a wing of multiple control surfaces is implemented by employing conformal trailing edge, conventional hinged control surface and a combination. The effects and performances of these different trailing edge sets are evaluated and compared. Moreover, two aeroelastic tailoring optimizations are posed for passive lift distribution control for minimum active control demand based on different objective functions. The design philosophy of an adaptive wing is hence explored and discussed in this investigation.