A rotor system includes a drive hub, a set of rotor blades extending radially from the drive hub, and a set of tension-torsion straps connecting the rotor blades to the drive hub. The drive hub has a rotor mast opening extending along a mast axis. The rotor system is configured to rotate about the mast axis. The drive hub further has a set of mounting slots for mounting the tension-torsion straps. The mounting slots are arranged along a circle around the drive hub, each mounting slot extending through the drive hub along a respective mounting axis. The mounting axis of each of the mounting slots is biased relative to the mast axis. The tension-torsion straps are mounted to the drive hub at their corresponding mounting slots.

A structural member for use in a rotor system which rotates about a rotational axis includes a pin which extends substantially perpendicular to the rotational axis, a filler component positioned adjacent the pin, and a plurality of layers of composite material having fibers oriented lengthwise along a central axis which is perpendicular to the rotational axis. The plurality of fibers in the layers of composite material is wrapped about the pin and the filler component such that the fibers extend along the central axis and the plurality of layers form an opening filled by the filler component and which decreases as a function of distance from the pin along the central axis.

A structural member for use in a rotor system which rotates about a rotational axis includes a pin which extends substantially perpendicular to the rotational axis, a filler component positioned adjacent the pin, and a plurality of layers of composite material having fibers oriented lengthwise along a central axis which is perpendicular to the rotational axis. The plurality of fibers in the layers of composite material is wrapped about the pin and the filler component such that the fibers extend along the central axis and the plurality of layers form an opening filled by the filler component and which decreases as a function of distance from the pin along the central axis.

A rotor blade assembly of an aircraft having a rotor hub including a structural member having an inboard end and an outboard end, the structural member being connectable with the rotor hub. A spar surrounds the structural member and extends at least partially along a rotor blade axis. A pitch bearing assembly supports the spar relative to the structural member. The pitch bearing assembly includes an inboard pitch bearing mounted to the inboard end of the structural member and an outboard pitch bearing mounted to the outboard end of the structural member. The rotor blade assembly additionally includes a centrifugal assembly including a centrifugal bearing disposed between the inboard pitch bearing and the outboard pitch bearing relative to the rotor blade axis.

A rotor blade for a rotary wing aircraft includes a rotor hub including a first flex-beam attachment member and a flex-beam assembly. The flex-beam assembly includes a flex-beam support member having an attachment end and a wrapping end. A first flex-beam includes a first end, a second end and an intermediate portion. The first end of the first flex-beam is connected at the first flex-beam attachment member and the second end of the first flex-beam being connected to the attachment end of the flex-beam support member. A second flex-beam includes first end portion, a second end portion and an intermediate section. The first end portion of the second flex-beam is connected at the first flex-beam attachment member, the second end portion of the second flex-beam being connected at the second flex-beam attachment member and the intermediate section extending about the wrapping end of the flex-beam support member.

A vertical takeoff and landing (VTOL) vehicle that includes a flight controller and a rotor. During a vertical landing state, during which the VTOL vehicle is performing a vertical landing, the flight controller decides whether to switch from the vertical landing state to a self adjusting state and in the event it is decided to do so, the flight controller switches from the vertical landing state to the self adjusting state. During the self adjusting state, the flight controller generates a control signal for a rotor where the control signal causes: (1) the rotor to rotate during the self adjusting state and (2) the VTOL vehicle to stay in place during the self adjusting state, such that an occupant is able to enter or exit the VTOL vehicle during the self adjusting state.

A vertical takeoff and landing (VTOL) vehicle that includes a flight controller and a rotor. During a vertical landing state, during which the VTOL vehicle is performing a vertical landing, the flight controller decides whether to switch from the vertical landing state to a self adjusting state and in the event it is decided to do so, the flight controller switches from the vertical landing state to the self adjusting state. During the self adjusting state, the flight controller generates a control signal for a rotor where the control signal causes: (1) the rotor to rotate during the self adjusting state and (2) the VTOL vehicle to stay in place during the self adjusting state, such that an occupant is able to enter or exit the VTOL vehicle during the self adjusting state.

Embodiments are directed to a pitch horn assembly for an aircraft comprising a pitch horn rotatably coupled to a connector pin along a first axis using a first set of spherical bearings. The connector pin is rotatably coupled to a housing along a second axis using a second set of spherical bearings. A crank is fixedly coupled to the connector pin, wherein the pitch horn and the crank are configured to commonly rotate relative to the housing.

Embodiments are directed to a pitch horn assembly for an aircraft comprising a pitch horn rotatably coupled to a connector pin along a first axis using a first set of spherical bearings. The connector pin is rotatably coupled to a housing along a second axis using a second set of spherical bearings. A crank is fixedly coupled to the connector pin, wherein the pitch horn and the crank are configured to commonly rotate relative to the housing.

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.