Citation:
Xie J, Yang ZC, Guo SJ; Trim optimizations of an adaptive tailless aircraft with composite wing. Advanced Materials Research, February 2011, vol. 213, pp334-338
Abstract:
This paper investigates aeroelastic tailoring and optimal trailing edge control
surface deflection to minimize induced drag for a HALE UAV flying wing
configuration. The analysis process is conducted on the Finite Element(FE) model
of a composite slender wing. Genetic Algorithm(GA) is employed to
aeroelastically tailor the wing by setting the composite ply orientation. The
study examined conformal and traditional flaps and explored two optimization
formulations to minimize drag. The impacts of the conformal control surface are
recognized as required deflection saving which can be translated to drag
reduction. The results also show that the control demands for the optimal trim
can be further reduced if the wing is properly tailored