Cable routing through rotatable-wing aircraft spars

Abstract

A cable routing system described herein relates to facilitating the rotation of wings and a fuselage of a rotatable-wing aircraft via a load transfer structure. In one embodiment, the cable routing system includes a first hollow shaft extending through a first wing attached to a fuselage of an aircraft and a second hollow shaft extending through a second wing attached to the fuselage. The hollow shafts rotate about a pitch axis independently of the fuselage. The cable routing system also includes a load transfer structure coupled to adjacent outlets of the hollow shafts that are within the fuselage. Cables within the hollow shafts exit the adjacent outlets perpendicularly away from a longitudinal axis of the hollow shafts. The load transfer structure facilitates rotation of the hollow shafts.

Dependencies are inferred from the claim text.