Hybrid tilt propeller/tilt wing aircraft

An aircraft comprising:

• a fuselage;
• a first wing and a second wing, the first wing and the second wing each comprising:
• an inner portion immovably fixed to the fuselage and extending from the fuselage, the inner portion is an inboard portion;
• and
• an outer portion rotatably coupled to the inner portion and extending away from the inner portion to a tip of the respective wing, the outer portion is an outboard portion;
• a first propeller between the inner portion of the first wing and the outer portion of the first wing, wherein the outer portion of the first wing extends beyond the first propeller to the tip of the first wing, the first propeller being configured to rotate together with the outer portion of the first wing relative to the inner portion of the first wing;
• a second propeller between the inner portion of the second wing and the outer portion of the second wing, wherein the outer portion of the second wing extends beyond the second propeller to the tip of the second wing, the second propeller being configured to rotate together with the outer portion of the second wing relative to the inner portion of the second wing;
• and
• an empennage comprising a third wing and a third propeller mounted to the third wing, wherein the third wing and the third propeller are configured to rotate together with respect to the fuselage,
• wherein the aircraft is configured to control movement of the aircraft in all directions without cyclic control of the first propeller, the second propeller, and the third propeller, and
• wherein the outboard portion of each of the first wing and the second wing is tilted with the respective first propeller of the first wing and the second propeller of the second wing.

An aircraft comprising:

• a fuselage;
• a first wing and a second wing, the first wing and the second wing each comprising:
• an inner portion immovably fixed to the fuselage and extending from the fuselage;
• an outer portion rotatably coupled to the inner portion and extending away from the inner portion to a tip of the respective wing;
• a first propeller between the inner portion of the first wing and the outer portion of the first wing, the first propeller being configured to rotate together with the outer portion of the first wing relative to the inner portion of the first wing;
• a second propeller between the inner portion of the second wing and the outer portion of the second wing, the second propeller being configured to rotate together with the outer portion of the second wing relative to the inner portion of the second wing;
• and
• an empennage comprising a third wing and a third propeller mounted to the third wing, wherein the third wing and the third propeller are configured to rotate together with respect to the fuselage,
• wherein the aircraft is configured to control movement of the aircraft in all directions without cyclic control of the first propeller, the second propeller, and the third propeller, and
• wherein the third wing is a channel wing comprising a semi-circular portion that defines a space that accommodates at least a portion of the third propeller.