Abstract:
A rotor blade assembly includes a rotor blade (504) comprising an inboard end (506) and an outboard end (508). A composite yoke fitting (502) made from a composite material is attached to the rotor blade (504). The composite yoke fitting (502) includes an outboard portion (510) inserted into the inboard end (506) of the rotor blade (504), an inboard portion (512), and a flexure region (514) about which the rotor blade (504) is configured to flex. The inboard portion (512) and the flexure region (514) are outside the rotor blade (504).
Abstract:
Some examples of techniques to cost-effectively embed fiber optic cables (306) in laminate structures and to terminate the fiber optic cables (306) on the surface of the laminate for robust and easily-repairable connections can be implemented in rotorcraft composites (302). To position a cable (306) in the rotorcraft composite (302), a length of a fiber optic cable (306) is embedded between layers of a composite rotorcraft material (300). The length of the fiber optic cable (306) is oriented in a substantially S-shape between the layers. An end of the length of the substantially S-shaped fiber optic cable (306) is extended to an edge of the composite rotorcraft material (300). The end of the length of the substantially S-shaped fiber optic cable (306) is terminated at the edge of the composite rotorcraft material (300) in either a storage area or easily machinable embedded connection.
Abstract:
A rotorcraft rotor blade assembly (100) includes an upper skin portion (104) extending substantially a full span of the rotor blade assembly (100) and a lower skin portion (106) extending substantially the full span of the rotor blade assembly (100). Each of the upper skin portion (104) and the lower skin portion (106) is configured to carry at least substantially 30% of rotor blade assembly (100) loads.
Abstract:
A rotorcraft rotor blade assembly (100) includes an upper skin portion (104) extending substantially a full span of the rotor blade assembly (100) and a lower skin portion (106) extending substantially the full span of the rotor blade assembly (100). Each of the upper skin portion (104) and the lower skin portion (106) is configured to carry at least substantially 30% of rotor blade assembly (100) loads.