VERTICAL TAKE-OFF AND LANDING AIRCRAFT
A vertical take-off and landing aircraft includes a fuselage, at least one wing connected to the fuselage, a plurality of rotors connected to the at least one wing for providing lift for vertical take-off and landing of the aircraft and a plurality of proprotors connected to the at least one wing and tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft
1 . A vertical take-off and landing aircraft comprising:
a fuselage;
at least one wing connected to the fuselage;
a plurality of rotors connected to the at least one wing for providing lift for vertical take-off and landing of the aircraft; and
a plurality of proprotors connected to the at least one wing and tiltable between lift configurations for providing lift for vertical take-off and landing of the aircraft and propulsion configurations for providing forward thrust to the aircraft.
2 . The aircraft of claim 1 , wherein the plurality of rotors are rearward of the at least one wing and the plurality of proprotors are forward of the at least one wing.
3 . The aircraft of claim 2 , comprising a plurality of booms mounted to the at least one wing, each boom mounting one rotor and one proprotor to the at least one wing.
4 . The aircraft of claim 1 , wherein a first proprotor is forward of a second proprotor that is adjacent to the first proprotor.
5 . The aircraft of claim 1 , wherein a first proprotor is mounted at a higher position on the aircraft than a second proprotor that is adjacent to the first proprotor.
6 . The aircraft of claim 1 , wherein each rotor has only two blades.
7 . The aircraft of claim 6 , wherein each rotor is configured to fix the two blades in position during forward flight.
8 . The aircraft of claim 6 , wherein each proprotor has greater than two blades.
9 . The aircraft of claim 1 , wherein a first rotor of the plurality of rotors is canted relative to a second rotor of the plurality of rotors such that a rotational axis of the first rotor is non-parallel with a rotational axis of the second rotor.
10 . The aircraft of claim 9 , wherein a cant angle of any rotor or proprotor is such that a respective burst disc cannot intersect with passengers or a pilot.
11 . The aircraft of claim 9 , wherein a cant angle of any rotor or proprotor is such that a respective burst disc cannot intersect with any flight-critical component.
12 . The aircraft of claim 1 , wherein a first proprotor of the plurality of proprotors is canted relative to a second proprotor of the plurality of proprotors such that a rotational axis of the first proprotor is non-parallel with a rotational axis of the second proprotor.
13 . The aircraft of claim 1 , further comprising a control system configured to actively alter a tilt of at least one proprotor to generate yawing moments during hover.
14 . The aircraft of claim 1 , wherein attack angles of blades of the proprotors are collectively adjustable during flight.
15 . The aircraft of claim 1 , wherein propulsion is provided entirely by the proprotors.
16 . The aircraft of claim 1 , wherein a range of tilt of the proprotors is greater than ninety degrees.
17 . The aircraft of claim 1 , wherein the at least one wing provides the lift required during cruising.
18 . The aircraft of claim 1 , wherein the at least one wing is a high wing mounted to an upper side of the fuselage.
19 . The aircraft of claim 1 , wherein the at least one wing has control surfaces.
20 . The aircraft of claim 1 , wherein all of the rotors and proprotors are mounted to the at least one wing.
21 . The aircraft of claim 1 , wherein the aircraft is electrically powered.
22 . The aircraft of claim 1 , wherein the aircraft is manned.