| Abstrakt: |
The stresses that occurred on the structures of a flying wing aircraft exemplified by the Flying-V structures (inspired by the design of Dr. Justus Benad of TU Delft) were evaluated using the finite element method to ensure a safe cruise condition. Two materials, i.e., aluminum alloy and carbon/epoxy composites, were defined in the analysis of the conceptual sub-structures (frame, longeron-stringer, spar-fuselage, ribs, spar wing, and upper and lower skin). These conceptual sub-structures do not necessarily represent the actual design of the Flying-V, although they may be adopted as the initial step. Structural optimization was performed with two objectives: (i) to minimize the sub-structural thickness of fully aluminum aircraft and (ii) to minimize the sub-structural thickness and laminate stacking sequence of fully composite aircraft. To this end, the stresses and wing-tip deflection were minimized. The analysis showed that carbon/epoxy composite is a feasible material to minimize the wing-tip deflection and weight compared to the aluminum alloy. The minimization of wing-tip deflection and weight was possible using a composite lay-up of quasi-isotropic, either (0/45/-45/90)s or (0/45/90/-45)s. Here, the finite element analysis provides a path to further the structural optimization of the non-conventional flying wing aircraft. [ABSTRACT FROM AUTHOR] |
