초록 ▼

The electrical harness system is configured for routing a harness between a rotor yoke and a rotor blade. A recess in an inboard cap member is configured to house a connector and an associated harness. As the recess extends along a radial path in the chordwise direction of the rotor blade, the harne

The electrical harness system is configured for routing a harness between a rotor yoke and a rotor blade. A recess in an inboard cap member is configured to house a connector and an associated harness. As the recess extends along a radial path in the chordwise direction of the rotor blade, the harness is configured to lie within the recess. Operationally induced centrifugal forces promote positioning the slack of harness within the recess, while the slack in the harness remains available for relative dynamic movements between the rotor blade and the rotor yoke. Such a routing of the harness reduces aerodynamic drag and minimizes damage that could otherwise occur to the harness.

대표청구항 ▼

1. A rotor blade, comprising: an airfoil shaped body;a root end portion that is inboard from the airfoil shaped body;a cap member at the root end portion, the cap member having a recessed portion; anda first connector member coupled to a wall within the recessed portion; wherein the recessed portion

1. A rotor blade, comprising: an airfoil shaped body;a root end portion that is inboard from the airfoil shaped body;a cap member at the root end portion, the cap member having a recessed portion; anda first connector member coupled to a wall within the recessed portion; wherein the recessed portion is configured to house a harness coupled to a second connector member, the second connector member configured for mating to the first connector member. 2. The rotor blade according to claim 1, wherein the first connector member is located toward a leading edge portion of the recessed portion. 3. The rotor blade according to claim 1, wherein the wall has a surface that is approximately normal to an adjacent inner surface of the recessed portion. 4. The rotor blade according to claim 1, wherein the first connector member has a threaded portion configured for receiving a second connector member. 5. The rotor blade according to claim 1, wherein the first connector member is an electrical power connector for providing electrical power to a system in the rotor blade. 6. The rotor blade according to claim 1, wherein the first connector member is an electrical signal connector. 7. The rotor blade according to claim 1, wherein the first connector member is a hydraulic connector. 8. The rotor blade according to claim 1, wherein a leading edge portion of the recessed portion is located further toward a tip end of the rotor blade as compared to a portion of the recessed portion at a centerline of the root end. 9. The rotor blade according to claim 1, wherein a trailing edge portion of the recessed portion is located further toward a tip end of the rotor blade as compared to a portion of the recessed portion at a centerline of the root end. 10. A rotor blade, comprising: an airfoil shaped body;a root end portion that is inboard from the airfoil shaped body;a cap member at the root end portion, the cap member having a recessed portion; anda connector member coupled to a wall within the recessed portion; wherein a trailing edge portion of the recessed portion provides a housing for a slack portion of a harness coupled to the connector member; wherein the trailing edge portion of the recessed portion is located further toward a tip end of the rotor blade as compared to a portion of the recessed portion at a centerline of the root end. 11. The rotor blade according to claim 10, wherein operational centrifugal forces act to press the slack portion of the harness into the recessed portion. 12. A rotor hub for an aircraft, the rotor hub, comprising: a rotor mast;a yoke coupled to the rotor mast;a rotor blade coupled to the yoke, the rotor blade having a recessed portion at a root end portion;a first connector mounted to a wall of the recessed portion;a damper coupled between the rotor blade and the yoke; anda harness coupled to a second connector, the second connector mountable to the first connector; wherein the harness is routed between the damper and the first connector along the recessed portion; andwherein the harness extends between the first connector and the yoke. 13. The rotor hub according to claim 12, wherein a leading edge portion of the recessed portion is located further toward a tip end of the rotor blade as compared to a portion of the recessed portion at a centerline of the root end. 14. The rotor hub according to claim 12, wherein a trailing edge portion of the recessed portion is located further toward a tip end of the rotor blade as compared to a portion of the recessed portion at a centerline of the root end. 15. A rotor hub for an aircraft, the rotor hub, comprising: a rotor mast;a yoke coupled to the rotor mast;a rotor blade coupled to the yoke, the rotor blade having a recessed portion at a root end portion;a first connector mounted to a wall of the recessed portion; anda harness coupled to a second connector, the second connector mountable to the first connector; wherein the recessed portion is configured to house the harness coupled to a second connector member, the second connector member configured for mating to the first connector member. 16. A rotor hub for an aircraft, the rotor hub, comprising: a rotor mast;a yoke coupled to the rotor mast;a rotor blade coupled to the yoke, the rotor blade having a recessed portion at a root end portion; anda first connector mounted to a wall of the recessed portion;a harness coupled to a second connector, the second connector mountable to the first connector; wherein a trailing edge portion of the recessed portion provides a housing for a slack portion of the harness as operational centrifugal forces act to press the slack portion of the harness into the recessed portion.