Vtol aircraft using fixed forward canted rotors to simulate rigid wing dynamics

Abstract

A vertical take-off and landing aircraft which uses fixed rotors for both VTOL and forward flight operations. The rotors form a synthetic wing and are positioned to achieve a high span efficiency. The rotors are positioned to even out the lift across the span of the synthetic wing. The synthetic wing may also have narrow front and rear airfoils which may provide structural support as well as providing lift during forward flight, or may have a single center wing. The wing rotors are tilted forward and provide some forward propulsion during horizontal flight.

What is claimed is: 
     
         1 . An aerial vehicle adapted for vertical takeoff and horizontal flight using rotors to simulate traditional wing aerodynamics, said aerial vehicle comprising:
 a main vehicle body;   a right side wing assembly, said right side wing assembly comprising:
 a right side wing: 
 a plurality of right side wing rotor assemblies wherein the spin axis of each of said right side wing rotor assemblies is tilted forward in a fixed position relative to the aircraft structure, said plurality of right side wing rotor assemblies adapted to remain under power during forward flight, said plurality of right side wing rotor assemblies comprising:
 a right side forward inboard rotor assembly forward of said right side wing, said right side forward inboard rotor assembly coupled to an inboard portion of said right side wing; 
 an right side rearward inboard rotor assembly rearward of said right side wing, said right side rearward inboard rotor assembly coupled to an inboard portion of said right wing; and 
 a right side outboard rotor assembly coupled to a tip of said right side wing; and 
 
   a left side wing assembly, said left side wing assembly comprising:
 a plurality of left side wing rotor assemblies wherein the spin axis of each of said left side wing rotor assemblies is tilted forward in a fixed position relative to the aircraft structure, said plurality of left side wing rotor assemblies adapted to remain under power during forward flight, said plurality of left side wing rotor assemblies comprising:
 a left side forward inboard rotor assembly forward of said left side wing, said left side forward inboard rotor assembly coupled to an inboard portion of said left side wing; 
 an left side rearward inboard rotor assembly rearward of said left side wing, said left side rearward inboard rotor assembly coupled to an inboard portion of said left wing; and 
 a left side outboard rotor assembly coupled to a tip of said left side wing; and 
 
   a horizontal thrusting rear rotor assembly adapted to provide horizontal thrust during regular flight.   
     
     
         2 . The aerial vehicle of  claim 1  wherein the spin axis of said right side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 8-12 degrees, and wherein the spin axis of said left side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 8-12 degrees. 
     
     
         3 . The aerial vehicle of  claim 1  wherein the spin axis of said right side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 5-15 degrees, and wherein the spin axis of said left side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 5-15 degrees. 
     
     
         4 . The aerial vehicle of  claim 1  wherein the spin axis of said right side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 5-20 degrees, and wherein the spin axis of said left side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 5-20 degrees. 
     
     
         5 . The aerial vehicle of  claim 2  wherein said aerial vehicle does not have controllable control surfaces. 
     
     
         6 . The aerial vehicle of  claim 2  wherein said right side rotor assemblies and said left side rotor assemblies comprise:
 an electric motor; 
 a top central hub coupled to a rotating portion of said electric motor; and 
 a plurality of blades coupled to said central hub. 
 
     
     
         7 . The aerial vehicle of  claim 6  wherein said top central hub is a flattened hub. 
     
     
         8 . The aerial vehicle of  claim 6  wherein the ratio of the diameter of said top central hub to the diameter of a sweep of said plurality of blades is greater than 0.25. 
     
     
         9 . The aerial vehicle of  claim 6  wherein the ratio of the diameter of said top central hub to the diameter of a sweep of said plurality of blades is greater than 0.30. 
     
     
         10 . The aerial vehicle of  claim 6  wherein said right side rotor assemblies and said left side rotor assemblies further comprise an undercowling extended rearward of said top central hub. 
     
     
         11 . The aerial vehicle of  claim 9  wherein said right side rotor assemblies and said left side rotor assemblies further comprise an undercowling extended rearward of said top central hub. 
     
     
         12 . The aerial vehicle of  claim 1  wherein each of said plurality of right side rotor assemblies has a mating left side rotor assembly approximately equidistant from a center line of said aircraft on a line through the approximate center of mass of said aerial vehicle. 
     
     
         13 . The aerial vehicle of  claim 2  wherein each of said plurality of right side rotor assemblies has a mating left side rotor assembly approximately equidistant from a center line of said aircraft on a line through the approximate center of mass of said aerial vehicle. 
     
     
         14 . The aerial vehicle of  claim 4  wherein each of said plurality of right side rotor assemblies has a mating left side rotor assembly approximately equidistant from a center line of said aircraft on a line through the approximate center of mass of said aerial vehicle. 
     
     
         15 . An aerial vehicle adapted for vertical takeoff and horizontal flight using rotors to simulate traditional wing aerodynamics, said aerial vehicle comprising:
 a main vehicle body;   a right side wing assembly, said right side wing assembly comprising:
 a right side wing: 
 a plurality of right side wing rotor assemblies wherein the spin axis of each of said right side wing rotor assemblies is tilted forward in a fixed position relative to the aircraft structure, said plurality of right side wing rotor assemblies adapted to remain under power during forward flight, said plurality of right side wing rotor assemblies comprising:
 a right side forward inboard rotor assembly forward of said right side wing, said right side forward inboard rotor assembly coupled to an inboard portion of said right side wing; 
 an right side rearward inboard rotor assembly rearward of said right side wing, said right side rearward inboard rotor assembly coupled to an inboard portion of said right wing; 
 a right side forward outboard rotor assembly forward of said right side wing, said right side forward outboard rotor assembly coupled to an outboard portion of said right side wing; 
 an right side rearward outboard rotor assembly rearward of said right side wing, said right side rearward outboard rotor assembly coupled to an outboard portion of said right wing; and 
 
   a left side wing assembly, said left side wing assembly comprising:
 a plurality of left side wing rotor assemblies wherein the spin axis of each of said left side wing rotor assemblies is tilted forward in a fixed position relative to the aircraft structure, said plurality of left side wing rotor assemblies adapted to remain under power during forward flight, said plurality of left side wing rotor assemblies comprising:
 a left side forward inboard rotor assembly forward of said left side wing, said left side forward inboard rotor assembly coupled to an inboard portion of said left side wing; 
 an left side rearward inboard rotor assembly rearward of said left side wing, said left side rearward inboard rotor assembly coupled to an inboard portion of said left wing; and 
 a left side forward outboard rotor assembly forward of said left side wing, said left side forward outboard rotor assembly coupled to an outboard portion of said left side wing; 
 an left side rearward outboard rotor assembly rearward of said left side wing, said left side rearward outboard rotor assembly coupled to an outboard portion of said left wing; and 
 
   a horizontal thrusting rear rotor assembly adapted to provide horizontal thrust during regular flight.   
     
     
         16 . The aerial vehicle of  claim 15  wherein the spin axis of said right side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 8-12 degrees, and wherein the spin axis of said left side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 8-12 degrees. 
     
     
         17 . The aerial vehicle of  claim 15  wherein the spin axis of said right side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 5-15 degrees, and wherein the spin axis of said left side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 5-15 degrees. 
     
     
         18 . The aerial vehicle of  claim 15  wherein the spin axis of said right side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 5-20 degrees, and wherein the spin axis of said left side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight in the range of 5-20 degrees. 
     
     
         19 . The aerial vehicle of  claim 16  wherein said aerial vehicle does not have controllable control surfaces. 
     
     
         20 . The aerial vehicle of  claim 16  wherein said right side rotor assemblies and said left side rotor assemblies comprise:
 an electric motor; 
 a top central hub coupled to a rotating portion of said electric motor; and 
 a plurality of blades coupled to said central hub. 
 
     
     
         21 . A method for flying of a vertical take-off and landing aircraft with fixed forward tilted rotors, said method comprising the steps of:
 powering up a plurality of right side wing rotor assemblies wherein the spin axis of each of said right side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight and a plurality of left side wing rotor assemblies wherein the spin axis of each of said left side wing rotor assemblies is tilted forward at an angle to the normal of the horizontal flight line of the aerial vehicle in nominal forward flight;   lifting off the aerial vehicle into a pitched up vertical take-off and landing configuration, thereby producing predominantly vertical thrust from said plurality of right side wing rotor assemblies and said plurality of left side wing rotor assemblies;   gaining altitude using said vertical thrust;   pitching the aerial vehicle forward in order to gain a forward thrust component from said forward tilted plurality of right side wing rotor assemblies and plurality of left side wing rotor assemblies;   increasing power to a horizontally thrusting rotor, thereby increasing the forward speed of the aerial vehicle and increasing the amount lift provided by the wings of said aerial vehicle; and   flying in a forward flight mode by decreasing the power to said plurality of right side wing rotor assemblies and said plurality of left side wing rotor assemblies such that the ratio of lift provided by said forward tilted plurality of right side wing rotor assemblies and plurality of left side wing rotor assemblies to that of the wings is in the range of 0.05 to 0.50.   
     
     
         22 . The method of  claim 21  wherein the ratio of lift provided by said forward tilted plurality of right side wing rotor assemblies and plurality of left side wing rotor assemblies to that of the wings is in the range of 0.10 to 0.35. 
     
     
         23 . The method of  claim 21  further comprising engaging in maneuvers of the aerial vehicle by differentiating the thrust provided by different wing rotor assemblies. 
     
     
         24 . The method of  claim 22  further comprising engaging in maneuvers of the aerial vehicle by differentiating the thrust and torque provided by different wing rotor assemblies. 
     
     
         25 . The method of  claim 21  further comprising engaging in maneuvers of the aerial vehicle solely by differentiating the thrust and torque provided by different wing rotor assemblies. 
     
     
         26 . The method of  claim 22  further comprising engaging in maneuvers of the aerial vehicle solely by differentiating the thrust and torque provided by different wing rotor assemblies.