Wind Energy Kite Tail

Abstract

The present disclosure relates to an aerial vehicle with a horizontal tailplane disposed along a bottom edge of a vertical tailfin. Namely, the aerial vehicle includes an empennage attached to the fuselage via a tail boom and a tail coupling. The empennage includes a vertical tailfin that extends below the tail coupling. The empennage also includes a tube arranged along a leading edge of the vertical tailfin and below the tail coupling of the aerial vehicle. The empennage additionally includes one or more rotating actuators and a horizontal tailplane. The horizontal tailplane is coupled to the tail via the tube and includes a continuous leading edge and a cutout. The one or more rotating actuators are configured rotate the horizontal tailplane about an axis of the tube. At least a portion of the vertical tailfin is configured to pass through the cutout.

What is claimed is: 
     
         1 . A system comprising:
 a ground station;   a tether; and   an aerial vehicle, wherein the aerial vehicle is coupled to the ground station using the tether, wherein the aerial vehicle comprises:
 a fuselage; and 
 an empennage coupled to the fuselage via a tail boom and a tail coupling, wherein the empennage comprises:
 a vertical tailfin, wherein at least a portion of the vertical tailfin extends below the tail coupling; 
 a tube arranged along a leading edge of the vertical tailfin and below the tail coupling; 
 an actuator; and 
 a horizontal tailplane, wherein the horizontal tailplane comprises a continuous leading edge and a cutout, wherein the horizontal tailplane is coupled to the empennage via the tube, wherein the actuator is configured to rotate the horizontal tailplane about an axis of the tube, wherein the cutout comprises an open slot in the horizontal tailplane, wherein at least a portion of the vertical tailfin is configured to pass through the cutout. 
 
   
     
     
         2 . The system of  claim 1 , wherein the tube is further arranged proximate to an intersection of a bottom surface of the vertical tailfin and the leading edge of the vertical tailfin. 
     
     
         3 . The system of  claim 1  further comprising a controller configured to carry out operations, wherein the operations include:
 causing the actuator to rotate the horizontal tailplane about the tube based at least on an operational mode of the aerial vehicle, wherein the operational mode comprises one of a forward flight mode or a hover mode. 
 
     
     
         4 . The system of  claim 3 , wherein the aerial vehicle further comprises a hybrid motor configured to generate electricity while the aerial vehicle is operating in the forward flight mode. 
     
     
         5 . The system of  claim 1 , wherein the horizontal tailplane is a stabilator. 
     
     
         6 . The system of  claim 1 , wherein the horizontal tailplane comprises an elevator portion. 
     
     
         7 . The system of  claim 1 , wherein the horizontal tailplane comprises at least one of a servo tab or an anti-servo tab. 
     
     
         8 . The system of  claim 1 , wherein the horizontal tailplane comprises a split stabilizer having a port portion and a starboard portion, wherein the port and starboard portions are independently rotatable about the tube. 
     
     
         9 . The system of  claim 1 , wherein the aerial vehicle is a wind energy kite. 
     
     
         10 . The system of  claim 1 , wherein the tube comprises a plurality of bonded carbon fiber sheets. 
     
     
         11 . An aerial vehicle comprising:
 a fuselage; and   an empennage attached to the fuselage via a tail boom and a tail coupling, wherein the empennage comprises:
 a vertical tailfin, wherein at least a portion of the vertical tailfin extends below the tail coupling; 
 a tube arranged along a leading edge of the vertical tailfin and below the tail coupling; 
 an actuator; and 
 a horizontal tailplane, wherein the horizontal tailplane comprises a continuous leading edge and a cutout, wherein the horizontal tailplane is coupled to the empennage via the tube, wherein the actuator is configured to rotate the horizontal tailplane about an axis of the tube, wherein the cutout comprises an open slot in the horizontal tailplane, and wherein at least a portion of the vertical tailfin is configured to pass through the cutout. 
   
     
     
         12 . The aerial vehicle of  claim 11 , wherein the tube is further arranged proximate to an intersection of a bottom surface of the vertical tailfin and the leading edge of the vertical tailfin. 
     
     
         13 . The aerial vehicle of  claim 11 , wherein the aerial vehicle is configured to operate an operational mode, wherein the operational mode comprises one of a forward flight mode or a hover mode. 
     
     
         14 . The aerial vehicle of  claim 13 , further comprising:
 a plurality of hybrid motors configured to generate electricity while the aerial vehicle is operating in the forward flight mode.   
     
     
         15 . The aerial vehicle of  claim 11 , wherein the horizontal tailplane is a stabilator. 
     
     
         16 . The aerial vehicle of  claim 11 , wherein the horizontal tailplane comprises an elevator portion. 
     
     
         17 . The aerial vehicle of  claim 11 , wherein the horizontal tailplane comprises at least one of a servo tab or an anti-servo tab. 
     
     
         18 . The aerial vehicle of  claim 11 , wherein the horizontal tailplane comprises a split stabilizer having a port portion and a starboard portion, wherein the port and starboard portions are independently rotatable about the tube. 
     
     
         19 . The aerial vehicle of  claim 11 , wherein the aerial vehicle is a wind energy kite. 
     
     
         20 . The aerial vehicle of  claim 11 , wherein the horizontal tailplane is coupled to the tube via the actuator, wherein the actuator comprises a servo motor, wherein the cutout is disposed along a centerline of the horizontal tailplane and aft of the continuous leading edge.