Turbocraft

• US 5,149,012 A
• Filed: 09/10/1991
• Issued: 09/22/1992
• Est. Priority Date: 09/10/1991
• Status: Expired due to Fees

• Current Assignee: RENE L Valverde Revocable Trust Dated 13 May 1993
• Original Assignee: Rene L. Valverde
• Inventors: Valverde, Rene L.
• Primary Examiner(s): BAREFOOT, GALEN L
• Application Number:
  US07/757,326
• Time in Patent Office: 378 Days
• Field of Search: 244/12.2, 244/23 C, 244/12.3, 244/23 R, 244/52, 244/60, 244/62, 244/17.19, 244/12.1, 244/36, 244/53 R
• US Class Current: 244/12.2
• CPC Class Codes: B64C 27/20 Rotorcraft characterised by having shrouded rotors, e.g. flying platforms
• CPC Class Codes: B64C 29/0008 having its flight directional axis horizontal when grounded
• CPC Class Codes: B64C 29/0025 the propellers being fixed relative to the fuselage
• CPC Class Codes: B64C 39/001 Flying saucers

Abstract

An aircraft having a substantially circular body having a profile in the direction of flight as a profile of an airplane wing, at least two concentric counter-rotating turbo-blade assemblies within said body for effecting a vertical lifting air stream through said assemblies. Power generating devices and devices for coupling the power generating devices to the turbo-blade assemblies for maintaining them in rotary motion. It also includes thrusting devices coupled to the power generating devices for applying horizontal thrust to the aircraft, retro-boosting devices including a plurality of combustion chambers located below the turbo-blade assemblies for boosting said vertical lifting airstream. Also included is a compressed air plenum disposed below said turbo-blade assemblies in fluid communication with the combustion chambers and to the intake portion of the power generating means for supplying oxygen for sustaining combustion in said combustion chambers and for sustaining power in said power generating means, including upper vanes disposed above said turbo-blade assemblies for ingesting air, and lower vanes disposed below said compressed air plenum for exhausting air, and respective upper and lower vane control means.

Claims

1. An aircraft comprising a substantially circular body having a profile in the direction of flight as a profile of an airplane wing, at least two concentric counter-rotating turbo-blade assemblies disposed within said body for effecting a vertical lifting air stream through said assemblies, power generating means having an intake portion, means for coupling said power generating means to said turbo-blade assemblies for maintaining them in rotary motion, thrusting means coupled to said power generating means for applying horizontal thrust to said aircraft, retro-boosting means including a plurality of combustion chambers disposed proximal to said turbo-blade assemblies for boosting said vertical lifting airstream, a compressed air plenum in fluid communication with said combustion chambers and with the intake portion of said power generating means for supplying oxygen for sustaining combustion in said combustion chambers and for sustaining power in said power generating means, upper vanes disposed above said turbo-blade assemblies for ingesting air, and lower vanes disposed below said compressed air plenum for exhausting air, and respective upper and lower vane control means.

2. Aircraft according to claim 1 including means for injecting fuel into said combustion chambers, and means for igniting a compressed fuel-air mixture in said combustion chambers.

3. Aircraft according to claim 1, wherein said means for coupling said power generating means include gear wheel assemblies having drive input and drive output respectively engaging said power generating means to said turbo-blade assemblies.

4. Aircraft according to claim 1, including at least one jet engine system in said power generating means, wherein said means for coupling said power generating means include a gate valve disposed in a tail pipe section of said jet engine system for diverting a portion of jet engine exhaust gases, a circular exhaust manifold in fluid communication with said gate valve, and a plurality of nozzles disposed along said circular exhaust manifold for projecting said portion of jet engine exhaust gases toward blades disposed on said turbo-blade assemblies.

5. Aircraft according to claim 1, including a propeller in said horizontal thrusting means, wherein said power operating means include a power shaft coupled to said propeller.

6. Aircraft according to claim 4, wherein said horizontal thrusting means include an exhaust gas manifold in fluid communication with said jet engine system for effecting a horizontal thrust in said aircraft.

7. Aircraft according to claim 1, including a plurality of radially extending rotor blades on said turbo-blade assemblies disposed circumferentially on said turbo-blade assemblies, and rotating means for rotating said rotor blades about a radially extending axis for controlling said vertical lifting airstream.

8. Aircraft according to claim 7, including rotor blade control means, wherein said turbo-blade assemblies are divided into sectors defined by planes through said vertical axis, and steering means coupled to said rotor blade control means for independently controlling said rotating means in each of said sectors for controlling pitch and roll of said aircraft.

9. Aircraft according to claim 1, wherein said at least two counter-rotating turbo-blade assemblies are stacked vertically separated from one another.

10. Aircraft according to claim 1, wherein said at least two counter-rotating turbo-blade assemblies are disposed concentrically within at least one common plane perpendicular to the vertical axis of the circular body.

11. Aircraft according to claim 10, including at least two stator-blade assemblies fixed to the aircraft structure, disposed under said counter-rotating blade assemblies for redirecting the airstream.

12. Aircraft according to claim 11, wherein each rotating blade of said turbo-blade assemblies is supported at each end.

13. Aircraft according to claim 1, including wings extending radially from said substantially circular body, ailerons pivotally attached to said extensions, and winglets extending vertically at an angle from the ends of said wings.

14. Aircraft according to claim 1, including horizontal stabilizing surfaces disposed at the rear of said substantially circular body, elevator means pivotally attached to said stabilizing surfaces, and rudder means attached at the rear of said substantially circular body.

15. Aircraft according to claim 3, including a yaw control propeller disposed in a vertical plane, and coupling means for variably coupling said yaw control propeller to said power generating means.

16. Aircraft according to claim 4, including exhaust nozzles in said motion control means, disposed at the periphery of said circular body, and means to control said exhaust nozzles.

17. Aircraft according to claim 1, including a rocket system disposed at the rear of said aircraft to increase said horizontal thrusting power, and means to control said rocket system.

18. Aircraft according to claim 1 including at least one reciprocating engine in said power generating means.

19. An aircraft having an aircraft body having a profile in direction of flight as a profile of an airplane wing, comprising at least two counter-rotating turboblade assemblies within said body for effecting a vertical lifting air stream through said assemblies;

power generating means;

coupling means for coupling said power generating means to said turboblade assemblies for maintaining them in rotary motion;

thrusting means coupled to the power generating means for applying horizontal thrust to the aircraft;

a compressed air plenum disposed downstream of said turboblade assemblies in fluid communication with said power generating means for supporting combustion in said power generating means;

a plurality of rearward facing exhaust air vanes in fluid communication with said compressed air plenum for imparting forward thrust to the aircraft;

a plurality of adjustable lower exhaust air vanes in fluid communication with said compressed air plenum for selectively imparting lifting and forward thrust to the aircraft;

a plurality of upper vanes for ingesting air to said turboblade assemblies; and

control means for controlling said upper and lower vanes and said rearward facing nozzles.

20. An aircraft according to claim 19, having a retroboosting arrangement which includes at least one combustion chamber having a compressed air intake in fluid communication with said compressed air plenum, fuel-injection means for creating a combustible fuel-air mixture in said combustion chamber, ignition means for igniting said combustible fuel air mixture, and a downward and/or rearward facing exhaust nozzle for expelling combusted fuel-air mixture for creating increased lift and/or horizontal thrust.

21. An aircraft according to claim 19 including a plurality of directional control nozzles disposed at selected points at the periphery of said aircraft body, said directional control nozzles in fluid communication with said compressed air plenum, and control valves in said directional nozzles for controlling airborne attitude of said aircraft.

22. An aircraft according to claim 21, having a pilot'"'"'s position including means for vectoring said control nozzles and including nozzle control linkage connecting the pilot'"'"'s position with said control nozzles.

23. An aircraft comprising:

a body having a profile in direction of flight as a profile of an airplane wing;

a part of the body having a plurality of air intake openings;

at least one air compressor in said body having an air inlet fluidly communicating with said air intake openings and an outlet;

a compressed air plenum having an air intake port fluidly communicating with said outlet of the air compressor;

a plurality of rearward facing exhaust openings rearward facing from said body fluidly communicating with said air plenum for effecting horizontal thrust of said aircraft;

a plurality of bottom air exhaust outlets fluidly communicating with said air plenum;

power generating means drivingly coupled to said air compressor having combustion air intake ports fluidly communicating with said air plenum;

a plurality of control air outlets disposed at selected points of the periphery of said body fluidly communicating with said air plenum for controlling airborne attitude of said aircraft; and

control linkage for controlling air flow at said air intake openings, said rearward facing exhaust openings, said combustion air intake means, said control outlets and said bottom air exhaust outlets.

24. A method of controlling an aircraft having a body with a profile in direction of flight like an airplane wing, a compressor in the body receiving airflow from air intake openings in the body, a compressed air plenum receiving air from the air intake openings, a power generator coupled to the compressor, the method which comprises the steps of:

driving the compressor with the power generator;

drawing air into the compressor from the air intake openings;

compressing with the compressor air in the compressed air plenum;

exhausting air from the air plenum through rearward facing exhaust openings for generating thrust to the aircraft;

exhausting air from the air plenum through bottom openings in the body for generating lift to the aircraft;

exhausting air from the air plenum to the power generator for sustaining combustion in the power generator;

exhausting air through control air outlets for controlling airborne attitude of the aircraft; and

controlling with control linkage the flow of air from said air intake openings, air flow to said power generating means, said bottom exhaust outlets, said rearward facing exhaust openings and said control air outlets.