A rotorcraft comprising of a fuselage, a plurality of arms on which electric motors driving propellers are mounted, one or a plurality of pivoting rotor supports on which thrust generating rotors with one or a plurality of blades attach. The rotor supports are substantially vertical when the aircraft is flying vertically, hovering, or on the ground, and tilted with respect to the aircraft when the aircraft has a forward motion component. The rotors are configured to be powered on the ground, in hover, or in vertical flight, and spin in autorotation in horizontal flight.

A vertical take-off and landing aircraft includes a primary rotor unit having a rotor axis, an upper rotor system, and a lower rotor system. The upper rotor system includes an upper swashplate configured to translate along the rotor axis and not configured to tilt relative to the rotor axis and a pair of top blades configured to rotate about the rotor axis. Translation of the upper swashplate causes a pitch of each of the top blades to change equally. The lower rotor system includes a lower swashplate configured to translate along the rotor axis and not configured to tilt relative to the rotor axis and a pair of bottom blades configured to rotate about the rotor axis. Translation of the lower swashplate causes a pitch of each of the bottom blades to change equally. The aircraft further includes a plurality of secondary rotors each having fixed-pitch rotor blades.

A vertical take-off and landing aircraft includes a primary rotor unit having a rotor axis, an upper rotor system, and a lower rotor system. The upper rotor system includes an upper swashplate configured to translate along the rotor axis and not configured to tilt relative to the rotor axis and a pair of top blades configured to rotate about the rotor axis. Translation of the upper swashplate causes a pitch of each of the top blades to change equally. The lower rotor system includes a lower swashplate configured to translate along the rotor axis and not configured to tilt relative to the rotor axis and a pair of bottom blades configured to rotate about the rotor axis. Translation of the lower swashplate causes a pitch of each of the bottom blades to change equally. The aircraft further includes a plurality of secondary rotors each having fixed-pitch rotor blades.

A part-carrying apparatus includes a base portion. A shaft extends from the base portion. At least two mechanically driven arms are coupled to the shaft. Each arm has a first end coupled to the shaft and an opposite second end distal from the shaft. A part is coupled to the shaft. The part is configured to capture information about an environment around the part-carrying apparatus. A locking nut is coupled to the shaft. The locking nut comprises at least two positions. An unlocked position includes wherein the second end of each respective arm of the at least two mechanically driven arms is configured to extend away from the base portion when the locking nut is in the unlocked position. A locked position includes wherein the second end of each respective arm of the at least two mechanically driven arms is configured to extend towards the base portion when the locking nut is in the locked position.