Abstract: A support structure for an aircraft includes a structural member having a generally planar shape, a longitudinal axis defining a longitudinal direction and a transverse axis orthogonal to the longitudinal axis, and a plurality of rounded holes formed along the longitudinal direction. Each rounded hole has a respective major axis with a major length and a minor axis orthogonal to the major axis with a minor length that is less than the major length. Each rounded hole is oriented with its major axis rotated more than 0 degrees and less than 90 degrees from the longitudinal axis of the structural member. The structural member is configured for bearing external loads acting on the structural member in a principal loading direction that is not parallel with the longitudinal axis or the transverse axis. Each rounded hole may be oriented with its major axis aligned generally parallel with the principal loading direction.

Abstract: Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.

Abstract: Embodiments for commercial freighter configuration for aircraft with composite wings. One embodiment is cargo floor structure for a wing center section of an aircraft. The cargo floor structure includes over wing floor beams extending longitudinally between a rear spar and a front spar of the aircraft. The over wing floor beams are coupled with an upper skin panel of a composite wing. The cargo floor structure also includes intercostals extending spanwise across the over wing floor beams. The intercostals suspended over the upper skin panel of the composite wing. The cargo floor structure also includes a truss box structure disposed between a middle pair of the over wing floor beams and configured to shear a spanwise load from the intercostals into the upper skin panel of the composite wing.