Abstract: An aircraft may include a fuselage, a propulsion assembly configured to produce thrust for the aircraft, and a gimballing mechanism articulatably coupling the propulsion assembly to the fuselage and configured to rotate the propulsion assembly about a first axis of rotation defined through a center of mass of the propulsion assembly, and rotate the propulsion assembly about a second axis of rotation defined through the center of mass of the propulsion assembly. The first axis of rotation may be perpendicular to the second axis of rotation. The first axis of rotation may be perpendicular to the second axis of rotation.

Abstract: An aircraft may include a body structure and a propulsion system coupled to the body structure and including a mounting shaft and a rotor. The rotor may include a rotor hub and a set of rotor blades, wherein the rotor is configured to orient the set of rotor blades at a first collective blade angle during a first flight mode and orient the set of rotor blades at a second collective blade angle during a second flight mode. The propulsion system may further include a motor coupled to the rotor and configured to rotate the rotor in a first rotational direction in the first flight mode to produce thrust in a first thrust direction and rotate the rotor in a second rotational direction opposite the first rotational direction in the second flight mode to produce thrust in a second thrust direction opposite the first thrust direction.

Abstract: An aircraft may include a body structure, a tail section articulatably coupled to the body structure and including a tail structure, a propulsion system coupled to the tail structure and configured to produce thrust for the aircraft, and a stabilizer coupled to the tail structure, and an actuation system configured to articulate the tail section relative to the body structure to change a thrust vector of the propulsion system and an angle of attack of the stabilizer during flight. The actuation system may be configured to articulate the tail section about at least two perpendicular rotational axes. The propulsion system may be configured to produce the thrust in a first thrust direction in a first flight mode (e.g., a rotor-borne flight mode) and to produce the thrust in a second thrust direction in a second flight mode (e.g., a wing-borne flight mode).