Double-Blown Wing Vertical Takeoff and Landing Aircraft

Abstract

A vertical or short takeoff and landing (V/STOL) aerial vehicle comprising: a wing having a leading edge and a trailing edge; a thrust rotor operatively coupled with the wing; and a lift rotor operatively coupled with the wing. The thrust rotor may comprise a first propeller having a first fixed axis of rotation that is substantially horizontal. The first propeller may be positioned forward of the leading edge. The lift rotor may comprise a second propeller having a second fixed axis of rotation that is substantially perpendicular to said first fixed axis of rotation. The wing may be operatively coupled with a fuselage.

What is claimed is: 
     
         1 . A vertical or short takeoff and landing (V/STOL) aerial vehicle comprising:
 a wing having a leading edge and a trailing edge;   a thrust rotor operatively coupled with the wing,
 wherein the thrust rotor comprises a first propeller having a first fixed axis of rotation that is substantially horizontal, and 
 wherein the first propeller is positioned forward of the leading edge; and 
   a lift rotor operatively coupled with the wing,
 wherein the lift rotor comprises a second propeller having a second fixed axis of rotation that is substantially perpendicular to said first fixed axis of rotation. 
   
     
     
         2 . The V/STOL aerial vehicle of  claim 1 , wherein the wing includes a trailing edge flap. 
     
     
         3 . The V/STOL aerial vehicle of  claim 2 , wherein the thrust rotor is configured to generate a horizontal thrust force. 
     
     
         4 . The V/STOL aerial vehicle of  claim 3 , wherein the lift rotor is configured to generate a vertical thrust force. 
     
     
         5 . The V/STOL aerial vehicle of  claim 3 , wherein the trailing edge flap is configured to redirect at least a portion of the horizontal thrust force to generate a vertical force. 
     
     
         6 . The V/STOL aerial vehicle of  claim 2 , wherein the trailing edge flap is configured to pivot between a horizontal position and a substantially vertical position. 
     
     
         7 . The V/STOL aerial vehicle of  claim 2 , wherein the trailing edge flap is configured to interact with the flow through the lift rotor and the thrust rotor to produce a suction force that increases the vertical force. 
     
     
         8 . The V/STOL aerial vehicle of  claim 1 , wherein the thrust rotor and the lift rotor are coupled to a common structural component. 
     
     
         9 . The V/STOL aerial vehicle of  claim 1 , wherein the trailing edge flap deflects downwardly between 75 degrees and 90 degrees when in the substantially vertical position. 
     
     
         10 . The V/STOL aerial vehicle of  claim 1 , further comprising a second lift rotor to generate a vertical thrust force to provide pitching moment control forces. 
     
     
         11 . The V/STOL aerial vehicle of  claim 1 , wherein a normal pitching moment from the lift rotor is trimmed by an upload that adds to the vertical force. 
     
     
         12 . The V/STOL aerial vehicle of  claim 1 , wherein the lift rotor is only driven while the V/STOL aerial vehicle is in hover mode or traveling at a horizontal airspeed below the wing's stall speed. 
     
     
         13 . The V/STOL aerial vehicle of  claim 1 , wherein the second propeller is oriented to minimize drag when the V/STOL aerial vehicle is in wing-borne flight mode. 
     
     
         14 . The V/STOL aerial vehicle of  claim 1 , wherein the wing comprises four lift rotors and four thrust rotors. 
     
     
         15 . The V/STOL aerial vehicle of  claim 1 , further comprising a horizontal stabilizer surface configured to provide control while the V/STOL aerial vehicle is a horizontal flight mode. 
     
     
         16 . The V/STOL aerial vehicle of  claim 15 , wherein the horizontal stabilizer surface is aft of the wing. 
     
     
         17 . The V/STOL aerial vehicle of  claim 16 , wherein the horizontal stabilizer surface is positioned higher than the wing, thereby minimizing a downwash effect of the lift rotor. 
     
     
         18 . The V/STOL aerial vehicle of  claim 16 , wherein the horizontal stabilizer surface pivots as a single unit. 
     
     
         19 . The V/STOL aerial vehicle of  claim 18 , wherein the horizontal stabilizer surface is configured to align with an airflow resulting from a downwash effect. 
     
     
         20 . The V/STOL aerial vehicle of  claim 1 , wherein the horizontal thrust force is approximately aligned with the direction of flight.