A rotor assembly for an aircraft comprising: a plurality of rotor blades; and an upper rotor hub assembly including at least one mounting member (402, 404) each mounting member comprising: a central section comprising a pivot coupler configured to allow the mounting member and rotor blades to teeter relative to the aircraft; first and second inner cylinders extending from the central section, the first and second inner cylinders comprising apertures defining a track; two mounting brackets disposed at opposite ends of the central section, each mounting bracket fixedly coupled to one of the plurality of rotor blades, the mounting brackets comprising first and second outer cylinders that slidingly receive the first and second inner cylinders, the outer cylinders comprising pin-receiving apertures; and a blade pitch adjustment linkage coupled to the mounting brackets and the central section, the blade pitch adjustment linkage configured to automatically adjust a blade pitch of the rotor blades based on a rotational velocity of the rotor blades and to synchronize the blade pitch of the rotor blades, wherein the blade pitch adjustment linkage comprises pins extending through the apertures in the outer and inner cylinders such that when the outer cylinders slide relative to the inner cylinders, the pins slide through the tracks, thereby causing rotation of the outer cylinders relative to the inner cylinders. a plurality of rotor blades; and an upper rotor hub assembly including at least one mounting member (402, 404) each mounting member comprising: a central section comprising a pivot coupler configured to allow the mounting member and rotor blades to teeter relative to the aircraft; first and second inner cylinders extending from the central section, the first and second inner cylinders comprising apertures defining a track; two mounting brackets disposed at opposite ends of the central section, each mounting bracket fixedly coupled to one of the plurality of rotor blades, the mounting brackets comprising first and second outer cylinders that slidingly receive the first and second inner cylinders, the outer cylinders comprising pin-receiving apertures; and a blade pitch adjustment linkage coupled to the mounting brackets and the central section, the blade pitch adjustment linkage configured to automatically adjust a blade pitch of the rotor blades based on a rotational velocity of the rotor blades and to synchronize the blade pitch of the rotor blades, wherein the blade pitch adjustment linkage comprises pins extending through the apertures in the outer and inner cylinders such that when the outer cylinders slide relative to the inner cylinders, the pins slide through the tracks, thereby causing rotation of the outer cylinders relative to the inner cylinders. a central section comprising a pivot coupler configured to allow the mounting member and rotor blades to teeter relative to the aircraft; first and second inner cylinders extending from the central section, the first and second inner cylinders comprising apertures defining a track; two mounting brackets disposed at opposite ends of the central section, each mounting bracket fixedly coupled to one of the plurality of rotor blades, the mounting brackets comprising first and second outer cylinders that slidingly receive the first and second inner cylinders, the outer cylinders comprising pin-receiving apertures; and a blade pitch adjustment linkage coupled to the mounting brackets and the central section, the blade pitch adjustment linkage configured to automatically adjust a blade pitch of the rotor blades based on a rotational velocity of the rotor blades and to synchronize the blade pitch of the rotor blades, wherein the blade pitch adjustment linkage comprises pins extending through the apertures in the outer and inner cylinders such that when the outer cylinders slide relative to the inner cylinders, the pins slide through the tracks, thereby causing rotation of the outer cylinders relative to the inner cylinders.