Abstract: A rotor assembly comprises a rotor hub and rotor-blade assemblies. The rotor hub comprises rotor-blade supports. Each rotor-blade assembly is coupled to a respective one of the rotor-blade supports and comprises a flap axle, a hub connector, a rotor blade, and a torsion strap. The flap axle extends through a respective one of the rotor-blade supports and has a central flap-axle axis. The hub connector is pivotable relative to a rotor-blade support about the central flap-axle axis and defines a central hub-connector axis. The rotor blade is coupled to and is pivotable relative to the hub connector, and, together with the hub connector, is pivotable relative to a respective one of the rotor-blade supports about the central flap-axle axis. The torsion strap has a first end, coupled to the rotor blade, and a second end, through which the flap axle passes.

Abstract: A rotor assembly comprises a rotor hub and rotor-blade assemblies. The rotor hub comprises rotor-blade supports. Each rotor-blade assembly is coupled to a respective one of the rotor-blade supports and comprises a flap axle, a hub connector, a rotor blade, and a torsion strap. The flap axle extends through a respective one of the rotor-blade supports and has a central flap-axle axis. The hub connector is pivotable relative to a rotor-blade support about the central flap-axle axis and defines a central hub-connector axis. The rotor blade is coupled to and is pivotable relative to the hub connector, and, together with the hub connector, is pivotable relative to a respective one of the rotor-blade supports about the central flap-axle axis. The torsion strap has a first end, coupled to the rotor blade, and a second end, through which the flap axle passes.

Abstract: A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.

Abstract: A system and method for improving fuel storage within the wing of an aircraft. In one exemplary embodiment, the system and method eliminate the traditional spars and ribs, and any spanwise and cordwise connecting vertical webs, within a wing. Instead, the system comprises a plurality of modified flared spars, each having a length defined by an angled hat section, to form a wing structure. The modified flared spars may also comprise one or more lengths defined by a specialized section configured to accommodate a portion of a box section, or any other internal component of the wing. The system and method may also involve a contiguous fuel bladder of any size/type. The fuel bladder for the wing may comprise a fabric coated or impregnated with an elastomeric material that may include a polyurethane dispersion layer combined with a sealant.