VERTICAL TAKEOFF AND LANDING AIRCRAFT
An aircraft with a forward swept wing is configured to transition between vertical flight and forward flight. The aircraft includes propellers attached laterally along the wing. The propellers may be stacked propellers with two or more co-rotating rotors. The aircraft also includes booms attached along the wing and at each free end of the wing. The booms can include boom control effectors configured to direct airflow below a propeller. The aircraft includes one or more cruise propellers, configured to operate during forward flight to generate lift. The aircraft can also include control surfaces on the wings and tail that may tilt during takeoff and landing to yaw the vehicle.
1 . An aircraft having a center of gravity, the aircraft comprising:
a fuselage;
a forward swept wing mounted to the fuselage, the wing having a port segment and a starboard segment, each segment extending outwardly from the fuselage to a free end, wherein the free end of each segment is a forward most region of the wing;
a tail region extending from the fuselage; and
a set of propellers configured such that an aerodynamic center is approximately aligned with the center of gravity during a mode of operation, the set including a first propeller, a second propeller, and a third propeller, wherein the first propeller and the second propeller are coupled to the wing, and the third propeller is coupled to the tail region.
2 . The aircraft of claim 1 , further comprising:
a first wing boom attached along the starboard segment of the wing; and
a second wing boom attached along the port segment of the wing,
wherein the tail region includes a tail boom.
3 . The aircraft of claim 2 , further comprising:
a third wing boom attached to a free end of the starboard segment of the wing; and
a fourth wing boom attached to a free end of the port segment of the wing.
4 . The aircraft of claim 2 , wherein at least one of the first wing boom, the second wing boom, or the tail boom includes a boom control effector configured to direct airflow generated by a propeller.
5 . The aircraft of claim 2 , wherein at least one of the first wing boom, the second wing boom, or the tail boom is hollow and is configured as a resonator tuned to a frequency of a propeller during the mode of operation.
6 . The aircraft of claim 2 , wherein at least one of the first wing boom, the second wing boom, or the tail boom is configured to retain a battery.
7 . The aircraft of claim 2 , wherein the first wing boom is attached to an approximate mid-point of the starboard segment of the wing and the second wing boom is attached to an approximate mid-point of the port segment of the wing.
8 . The aircraft of claim 2 , wherein the first and second propellers are coupled to the first and second wing booms, respectively.
9 . The aircraft of claim 8 , further comprising
a fourth propeller coupled to a third wing boom, wherein the third wing boom is coupled to the starboard segment of the wing; and
a fifth propeller coupled to a fourth wing boom, wherein the fourth wing boom is coupled to the port segment of the wing.
10 . The aircraft of claim 1 , further comprising:
a fourth propeller coupled to the tail region of the aircraft, wherein at least one of the first propeller, the second propeller, the third propeller, and the fourth propeller includes a set of co-rotating propellers.
11 . The aircraft of claim 1 , wherein an angle formed by the starboard segment of the wing and the fuselage is less than 20 degrees.
12 . The aircraft of claim 1 , further comprising:
a set of cruise propellers coupled to each free end of the wing, wherein each cruise propeller rotates in a plane substantially orthogonal to the wing.
13 . The aircraft of claim 1 , wherein the first propeller, the second propeller, and the third propeller have substantially equal diameters.
14 . The aircraft of claim 1 , wherein the first propeller rotates in a direction opposite to a rotational direction of the second propeller during the mode of operation.
15 . The aircraft of claim 1 , wherein at least one of the first propeller, the second propeller, or the third propeller is configured to recess within an internal cavity of the aircraft during a second mode of operation.
16 . The aircraft of claim 1 , wherein the tail region includes a T-tail having a fin with a rudder configured to control yaw motion of the aircraft and a tail plane attached perpendicularly to the fin.
17 . The aircraft of claim 16 , wherein the tail plane includes a tail control surface configured to rotate about an axis parallel to the tail plane to control the pitch of the aircraft.
18 . The aircraft of claim 1 , wherein a total area of the set of propellers has a disc loading of less than 15 pounds per square foot.
19 . The aircraft of claim 1 , further comprising four seats, disposed within the fuselage, oriented in two rows, wherein the two rows are tiered such that one row of seats is elevated above the other row of seats.
20 . The aircraft of claim 1 , wherein the first propeller is attached to a free end of the starboard segment of the wing and the second propeller is attached to a free end of the port segment of the wing.