Tailboom-stabilized VTOL aircraft

Abstract

A disclosed flying craft includes a suspension structure having a first end and a second end, a lift unit, and a payload unit. The lift unit includes a nacelle and a tailboom, and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimzes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

1 . A method of operating a flying machine comprising: 
 (a) providing a flying machine including a propulsion subsystem, a tailboom, and a pair of wing panels pivotally coupled to the tailboom;    (b) operating the flying machine in a first mode wherein its propulsion subsystem provides an aerial motive force predominantly countering gravity and the wing panels are oriented generally downward; and    (c) transitioning the flying machine to a second mode wherein its propulsion subsystem provides an aerial motive force predominantly parallel to the ground and the wing panels develop a substantial portion of lifting force generated by the flying machine;    (d) wherein, when transitioning from the first mode to the second mode, an airstream resulting from motion of the flying machine parallel to the ground pushes the wing panels into an operating position extending substantially orthogonal to the tailboom.    
   
   
       2 . The method of  claim 1  wherein the flying machine lacks any actuator to move the wing panels into the operating position.  
   
   
       3 . The method of  claim 1  wherein horizontal speed at the transition of part (d) is about 122 knots.  
   
   
       4 . The method of  claim 1  wherein the wing panels are oriented substantially parallel to the tailboom when the flying machine is operating in the first mode.  
   
   
       5 . The method of  claim 1  wherein providing the flying machine comprises providing a rotor as part of the propulsion subsystem.  
   
   
       6 . The method of  claim 5  wherein: 
 (a) providing the flying machine comprises providing a rotor having a pair of blade sets; and    (b) operating the flying machine comprises power-rotating the blades of one set in an opposite direction to blades of the other set.    
   
   
       7 . A flying apparatus comprising: 
 (a) a propulsion subsystem;    (b) a tailboom pivotally coupled to the propulsion subsystem;    (c) a pair of wing panels (i) pivotally coupled to the tailboom, (ii) movable, in response to force from an airstream resulting from motion of the flying apparatus in transition from vertical to horizontal flight, from a first position to a second position extending substantially orthogonal from the tailboom, and structured to develop a substantial portion of lifting force generated by the lift unit during horizontal flight.    
   
   
       8 . The apparatus of  claim 7  wherein the lift unit lacks any actuator to move the wing panels into the operating position.  
   
   
       9 . The apparatus of  claim 7  wherein the wing panels are oriented substantially parallel to the tailboom in the first position.  
   
   
       10 . The apparatus of  claim 7  wherein the propulsion subsystem includes a rotor.  
   
   
       11 . The apparatus of  claim 10  wherein the rotor includes a pair of blade sets structured to be power-rotated such that blades of one rotor set rotate in an opposite direction to blades of the other rotor set.