Rotating wing aircraft with tip-driven rotor and rotor-guide ring

Abstract

A helicopter includes a main rotor guided and protected in minor impacts by a guide-ring. In selected embodiments, the rotor is powered by an electric motor employing a magnetic field generator carried by the main rotor and stator coils installed on the guide-ring. The helicopter's main rotor thus effectively functions as the rotor of the electric power plant of the helicopter. In selected embodiments, the rotor's blades are arranged so as to create an opening in the center of the rotor, allowing pilot ejection or deployment of a parachute capable of safely lowering the helicopter in case of an emergency.

1 . A helicopter comprising:
 a. a fuselage;   b. a first rotor guide-ring positioned above the fuselage and forming a plane of rotation;   c. a plurality of first supports attaching the first rotor guide-ring to the fuselage;   d. a first main, longitudinally extending rotor in the plane of rotation and having distal ends, the distal ends being rotatably carried by the first rotor guide-ring; and   e. an electric motor capable of rotating the first main rotor,   wherein the plurality of first supports comprises a plurality of first adjustable supports capable of altering the plane of rotation relative to the fuselage.   
     
     
         2 . The helicopter of  claim 1 , wherein the electric motor comprises at least one electrical coil circumferentially disposed in the first rotor guide-ring and a magnet disposed on each distal end of the first main rotor proximate the first rotor guide-ring. 
     
     
         3 . The helicopter of  claim 1 , wherein the first main rotor comprises a plurality of rotor blades joined flexibly at the center of the wing to allow rotor articulation. 
     
     
         4 . The helicopter of  claim 1 , wherein the plurality of first adjustable supports comprises telescoping supports. 
     
     
         5 . The helicopter of  claim 1 , further comprising a second main rotor disposed in a second rotor guide-ring, the second main rotor being capable of counter-rotating with respect to the first main rotor. 
     
     
         6 . The helicopter of  claim 5 , wherein the fuselage is disposed between the first main rotor and the second main rotor. 
     
     
         7 . The helicopter according to  claim 5 , further comprising a plurality of second supports attaching said second rotor guide-ring to said first rotor guide-ring. 
     
     
         8 . The helicopter according to  claim 7 , wherein the plurality of second supports comprises telescoping supports. 
     
     
         9 . The helicopter according to  claim 5 , further comprising a plurality of second supports attaching said second rotor guide-ring to said fuselage. 
     
     
         10 . The helicopter according to  claim 8 , wherein the plurality of second supports comprises telescoping supports. 
     
     
         11 . The helicopter of  claim 1 , wherein:
 the first main rotor comprises a center ring substantially concentric with the first rotor guide-ring and a plurality of rotor blades attached to the center ring, and   the helicopter further comprises an ejectable pilot seat deployable to eject a pilot of the helicopter through the center ring.   
     
     
         12 . The helicopter of  claim 1 , wherein:
 the first main rotor comprises a center ring substantially concentric with the first rotor guide-ring and a plurality of rotor blades attached to the center ring, and   the helicopter further comprises a parachute deployable through the center ring to lower the helicopter safely.   
     
     
         13 . The helicopter of  claim 1 , further comprising a power-tapping shaft attached to the first main rotor, the power-tapping shaft rotating together with the first main rotor and the power-tapping shaft being driven by the first main rotor. 
     
     
         14 . A helicopter comprising:
 a. a fuselage;   b. a first rotor guide-ring positioned above the fuselage and forming a plane of rotation;   c. a plurality of first supports attaching the first rotor guide-ring to the fuselage;   d. a rotor assembly consisting of a first main, longitudinally extending rotor having distal ends, the distal ends being rotatably carried by the first guide-ring; and   e. an electric motor capable of rotating the first main rotor,   wherein the electric motor comprises a linear induction motor to generate a magnetic wave along said first rotor guide-ring.   
     
     
         15 . A method of achieving vertical lift by a rotating wing aircraft having a fuselage and at least one rotating wing, the method comprising the steps of:
 a. providing a rotor guide-ring attached to and above said fuselage, said guide-ring defining a plane of rotation;   b. rotatably disposing said at least one longitudinally extending rotating wing in said rotor guide-ring, said at least one rotating wing having distal ends;   c. providing an electric motor to rotate said at least one rotating wing from the perimeter of said at least one rotating wing; and   d. adjusting the plane of rotation of said rotor guide-ring with respect to said fuselage thereby to control the plane of rotation of the rotating wing.   
     
     
         16 . The method of  claim 15 , wherein the step of providing an electric motor comprises:
 providing a source of an alternating electric current;   providing at least one electrical coil for receiving the alternating electric current, the at least one electrical coil being circumferentially disposed in said rotor guide-ring; and   providing one or more magnets disposed on said at least one rotating wing proximate with said rotor guide-ring.   
     
     
         17 . A method of generating vertical lift by a rotating wing aircraft having a fuselage, a first rotor, and a second rotor, the method comprising the steps of:
 a. providing a first rotor guide-ring attached to said fuselage;   b. providing a second rotor guide-ring attached to said fuselage;   c. rotatably disposing said first rotor in said first rotor guide-ring;   d. rotatably disposing said second rotor in said second rotor guide-ring;   e. providing a first electric motor to rotate said first rotor from tips of said first rotor; and   f. providing a second electric motor to rotate said second rotor, said second rotor being capable of counter-rotating with respect to said first rotor.   
     
     
         18 . A method of aerial transportation comprising the steps of:
 a. providing a helicopter having a fuselage and a rotor guide-ring attached to and above said fuselage, said rotor guide-ring defining a plane of rotation;   b. providing a longitudinally extending main rotor having a plurality of distal tips, the main rotor being rotatably disposed in said rotor guide-ring;   c. providing an electric motor to rotate said main rotor from the distal tips of the rotor, thereby generating lift; and   d. adjusting the plane of said guide-ring with respect to said fuselage thereby to control the plane of rotation of the main rotor.   
     
     
         19 . A helicopter comprising:
 a. a fuselage;   b. a plurality of telescoping supports;   c. a rotor guide-ring attached to and above the fuselage by the telescoping supports and forming a plane of rotation;   d. a longitudinally extending main rotor having distal tips, the distal tips being rotatably disposed in the rotor guide-ring, the main rotor being guided by the rotor guide-ring; and   e. a main motor driving the main rotor from the perimeter of the main rotor.   
     
     
         20 . The helicopter according to  claim 19 , further comprising:
 a nozzle; and   one or more ducts channeling a portion of air pushed by the main rotor to the nozzle,   wherein the nozzle discharges the channeled air so as to counteract torque of the main motor.   
     
     
         21 . The helicopter according to  claim 19 , further comprising an anti-torque rotor counteracting torque of the main rotor. 
     
     
         22 . The helicopter according to  claim 21 , further comprising a second motor driving the anti-torque rotor. 
     
     
         23 . The helicopter according to  claim 21 , further comprising a power-tapping shaft and a transverse gear set coupling power from the main rotor to the anti-torque rotor. 
     
     
         24 . The helicopter according to  claim 19 , further comprising at least one propeller capable of generating forward propulsion. 
     
     
         25 . The helicopter according to  claim 19 , further comprising at least one pair of turbine engines attached to the fuselage and capable of generating forward propulsion and directional control. 
     
     
         26 . The helicopter according to  claim 19 , wherein said main rotor comprises at least one S-shaped wing. 
     
     
         27 . The helicopter according to  claim 19 , further comprising a central shaft, wherein said main rotor is rotatably supported on said central shaft. 
     
     
         28 . The helicopter according to  claim 27 , wherein said central shaft comprises:
 at least one power cable; and   a plurality of control wires.   
     
     
         29 . The helicopter according to  claim 19 , wherein said main rotor further comprises a plurality of blades widening towards the perimeter. 
     
     
         30 . A method of propelling a longitudinally extending rotor having distal tips in a rotary-wing aircraft having a fuselage and a circular guide-rail attached to and above said fuselage and forming a plane of rotation, comprising the steps of:
 a. movably disposing said rotor distal tips within said circular guide-rail;   b. using a linear induction motor to generate a magnetic wave along said circular guide-rail; and   c. propelling said rotor by said magnetic wave,   wherein the rotor is propelled at an angular velocity that generates lift sufficient to levitate said aircraft.   
     
     
         31 . The method of  claim 30 , further comprising providing an electromagnetic suspension to magnetically levitate said rotor in said circular guide-ring using said electromagnetic suspension. 
     
     
         32 . The method of  claim 30 , further comprising providing an electrodynamic suspension to magnetically levitate said rotor in said circular guide-ring using said electrodynamic suspension. 
     
     
         33 . A rotary-wing aircraft consisting essentially of:
 a. a fuselage;   b. a circular guideway attached to and above said fuselage and forming a plane of rotation;   c. a longitudinally extending rotor having distal tips and being movably disposed within said circular guideway;   d. a plurality of electromagnets disposed in said guideway;   e. a linear induction motor; and   f. at least one source of electric power to charge said electromagnets and said linear induction motor,   wherein the distal tips of said rotor are magnetically levitated within said circular guideway supported by electromagnetic suspension forces generated by said electromagnets and the distal tips of said rotor are propelled by a traveling magnetic wave generated by said linear induction motor and said electromagnets.   
     
     
         34 . The rotary-wing aircraft of  claim 33 , wherein said circular guideway comprises a circular monorail disposed in a protective guide-ring attached to said fuselage. 
     
     
         35 . A rotary-wing aircraft comprising:
 a. a fuselage;   b. a circular guideway attached to and above said fuselage and forming a plane of rotation;   c. a longitudinally extending rotor having distal tips and being movably disposed on said circular guideway;   d. a plurality of electrically conductive strips or coils disposed in said circular guideway;   e. a plurality of superconducting magnets disposed at the tips of said rotor;   f. a linear induction motor; and   g. at least one source of electric power,   wherein the distal tips of said rotor are magnetically levitated within said circular guideway supported by electrodynamic suspension generated by opposing forces between said superconducting magnets and said electrically conductive strips and the distal tips of said rotor are propelled by a traveling magnetic wave generated by said linear induction motor.   
     
     
         36 . The rotary-wing aircraft of  claim 35 , wherein said circular guideway comprises a circular monorail disposed in a protective guide-ring attached to said fuselage. 
     
     
         37 . A method of achieving vertical flight for a rotary-wing aircraft having a fuselage, a circular guideway positioned above the fuselage and forming a plane of rotation, and a longitudinally extending main rotor having distal tips which are movably disposed within said circular guideway, the method comprising:
 a. generating a traveling magnetic wave along said circular guideway; and   b. propelling the distal tips of said main rotor by said traveling magnetic wave to generate lift for the vertical flight.   
     
     
         38 . A helicopter comprising:
 a. at least one rotor guide-ring that forms a plane of rotation;   b. a fuselage positioned below and suspended from said at least one rotor guide-ring by means of at least one support;   c. at least one longitudinally extending main rotor having distal ends, the distal ends being rotatably carried by said at least one rotor guide-ring; and   d. at least one motor supported on said at least one rotor guide-ring capable of rotating said at least one main rotor,   wherein the support is adjustable to allow alteration of the plane of rotation of the main rotor relative to the fuselage.   
     
     
         39 . A method of achieving vertical lift by a rotating wing aircraft having a fuselage and at least one longitudinally extending rotating wing having distal ends, the method comprising the steps of:
 a. providing at least one guide-ring that forms a plane of rotation and is attached to and positioned above said fuselage by means of at least one support;   b. rotatably disposing the distal ends of said at least one rotating wing in said at least one guide-ring; and   c. providing a motor to rotate said at least one rotating wing from one or more tips of said at least one rotating wing,   wherein the support is adjustable to allow alteration of a plane of rotation of the rotating wing relative to the fuselage.   
     
     
         40 . A rotating wing aircraft comprising:
 a. a fuselage;   b. a plurality of supports attached to the fuselage;   c. a guide-ring that forms a plane of rotation and is attached to and above said fuselage by said supports;   d. a longitudinally extending main rotor having distal ends rotatably disposed in said guide-ring, said main rotor being guided by said guide-ring; and   e. at least one motor driving said main rotor from one or more tips of said main rotor,   wherein the plurality of supports comprises a plurality of adjustable supports to allow alteration of the plane of rotation of the main rotor relative to the fuselage.   
     
     
         41 . A rotating wing aircraft comprising:
 a. a fuselage having a cylindrical duct substantially in the center of said fuselage;   b. a guide-ring situated on a cross-section of said cylindrical duct;   c. a main rotor rotatably disposed on said guide-ring, said main rotor being guided by said guide-ring; and   d. at least one motor driving said main rotor from one or more tips of said main rotor.   
     
     
         42 . The helicopter of  claim 1 , wherein the distal ends of the first main, longitudinally extending rotor comprise magnets and move substantially frictionlessly within the first rotor guide-ring. 
     
     
         43 . The helicopter of  claim 14 , wherein the distal ends of the first main, longitudinally extending rotor comprise magnets and move substantially frictionlessly within the first rotor guide-ring. 
     
     
         44 . The helicopter of  claim 19 , wherein the distal tips of the main rotor move substantially frictionlessly within the rotor guide-ring. 
     
     
         45 . The helicopter of  claim 38 , wherein the distal ends of the first main, longitudinally extending rotor comprise magnets and move substantially frictionlessly within the first rotor guide-ring. 
     
     
         46 . The helicopter of  claim 40 , wherein the distal ends of the first main, longitudinally extending rotor comprise magnets and move substantially frictionlessly within the first rotor guide-ring.