US2021362849A1PendingUtilityA1

Vertical take-off and landing aircraft

65
Assignee: ARCHER AVIATION INCPriority: May 19, 2020Filed: May 19, 2020Published: Nov 25, 2021
Est. expiryMay 19, 2040(~13.8 yrs left)· nominal 20-yr term from priority
Inventors:Geoffrey C. BowerThomas P. MunizBrett AdcockAdam GoldsteinCalder Richmond HughesZachary Robert Timm Hazen
B64D 27/34B64D 31/16B64D 27/357B64C 27/52B64C 27/28B64C 29/0008B64C 29/0025B64C 27/54B64C 29/00B64C 27/26B64C 29/0033B64C 9/00B64D 27/24
65
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Claims

Abstract

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

Claims

exact text as granted — not AI-modified
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.

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