Ultralight helicopter and control system

• US 5,370,341 A
• Filed: 04/05/1994
• Issued: 12/06/1994
• Est. Priority Date: 04/05/1994
• Status: Expired due to Fees

• Current Assignee: Ross Leon
• Original Assignee: Ross Leon
• Inventors: Leon, Ross
• Primary Examiner(s): Bucci, David A.
• Assistant Examiner(s): BIDWELL, ANNE
• Application Number:
  US08/223,175
• Time in Patent Office: 245 Days
• Field of Search: 244/17.11, 244/903, 244/900, 244/17.23, 244/222, 244/904, 244/901
• US Class Current: 244/17.11
• CPC Class Codes: B64C 27/10 arranged coaxially
• CPC Class Codes: B64C 31/028 Hang-glider-type aircraft; Microlight-type aircraft

Abstract

An ultralight helicopter has a pair of counter-rotating rotor assemblies which in combination yield zero net angular momentum when rotating at equal speeds. A single motor drives both rotors through a counter-rotating bevel gear set coupled to a pair of concentrically nested output shafts. In an alternative embodiment, the motor is coupled to the rotors through a hydraulic drive system which includes a hydraulic pump and at least one hydraulic motor driving each of the rotor assemblies. The pilot is advantageously suspended in a "hang-glider" type harness from a single hang point positioned proximate the center of lift of the helicopter. A control bar is fixedly mounted to the frame and is grasped by the pilot suspended in the harness. The pilot maneuvers the helicopter in both the pitch and roll directions by manipulating the control bar. The pilot shifts his own center of gravity relative to the center of gravity of the helicopter while grasping the control bar to thereby maneuver the helicopter.

Claims

1. A helicopter comprising:

a frame;

an engine mounted on said frame;

at least one rotor assembly mounted on said frame and coupled to said engine for rotation, said at least one rotor assembly having a plurality of rotors;

a rotor pitch control mechanism to adjust the pitch of said plurality of rotors;

a throttle control mechanism to adjust the rotational speed of said at least one rotor assembly; and

a pilot containing carrier assemblage connected to said frame, said carrier assemblage being moveable relative to said frame by said pilot during flight in order to provide for pitch and roll adjustments of the helicopter.

2. The helicopter of claim 1 comprising a pair of counter-rotating rotor assemblies, the combined rotation of said pair of rotor assemblies resulting in approximately zero net angular momentum delivered to said frame.

3. The helicopter of claim 2 wherein said pair of rotor assemblies have a common axis of rotation.

4. The helicopter of claim 1 wherein said carrier assemblage is a harness in which said pilot is suspended from a hang point positioned proximate the center of lift of the helicopter.

5. The helicopter of claim 1 further comprising:

a control bar fixed to said frame, said control bar being manipulated by said pilot to shift the center of gravity of said pilot in said carrier assemblage relative to the center of gravity of the helicopter to control the pitch and roll of the helicopter.

6. The helicopter of claim 5 wherein said throttle control mechanism is adjustable via a throttle control actuator on said control bar.

7. The helicopter of claim 5 wherein said at least one rotor assembly includes variable pitch rotors.

8. The helicopter of claim 7 wherein said variable pitch rotors are adjustable via a variable pitch actuator on said control bar.

9. The helicopter of claim 1 further comprising:

a plurality of safety straps connecting said carrier assemblage to said frame to prevent inadvertent contact by the pilot with said frame.

10. The helicopter of claim 1 wherein said throttle control mechanism includes means for setting and temporarily maintaining a specific rotor assembly speed.

11. The helicopter of claim 1 wherein said engine is coupled to said at least one rotor assembly via a gearbox.

12. The helicopter of claim 1 wherein said engine is coupled to said at least one rotor assembly via a hydraulic drive system, said hydraulic drive system comprising a hydraulic pump and at least one hydraulic motor driving each said rotor assembly.

13. The helicopter of claim 1 further comprising:

a tail assembly connected to said frame, said tail assembly including a tail rudder to provide added stability to the helicopter during forwardly directed flight.

14. The helicopter of claim 1 wherein said engine is mounted to said frame on vibration dampening mounts.

15. The helicopter of claim 1 wherein the total empty weight of the helicopter is not greater than 254 pounds.

16. A helicopter comprising:

a frame;

an engine mounted on said frame;

a pair of counter-rotating coaxial rotor assemblies mounted on said frame and coupled to said engine for rotation, the combined rotation of said pair of rotor assemblies resulting in approximately zero net angular momentum delivered to said frame, said rotor assemblies each having a plurality of variable pitch rotors;

a rotor pitch control mechanism to adjust the collective pitch of said plurality of variable pitch rotors, said variable pitch rotors being adjustable via a variable pitch actuator;

a throttle control mechanism to adjust the rotational speed of said rotor assemblies, said throttle control mechanism being adjustable via a throttle control actuator;

a harness in which a pilot is suspended from a hang point positioned proximate the axis of rotation of said rotor assemblies, said harness being moveable relative to said frame by said pilot during flight;

a control bar fixed to said frame, said control bar being manipulated by said pilot to shift the center of gravity of said pilot in said harness relative to the center of gravity of the helicopter to control the pitch and roll of the helicopter, said throttle control actuator and said variable pitch actuator being located on said control bar; and

a tail assembly connected to said frame, said tail assembly including vertical and horizontal stabilizers to provide added stability to the helicopter during forwardly directed flight.

17. The helicopter of claim 16 further comprising:

a plurality of safety straps connecting said harness to said frame to prevent inadvertent contact by said pilot with said frame.

18. The helicopter of claim 16 wherein said throttle control mechanism includes means for setting and temporarily maintaining a specific rotor assembly speed.

19. The helicopter of claim 16 wherein said engine is coupled to said rotor assemblies via a gearbox.

20. The helicopter of claim 16 wherein said engine is coupled to said rotor assemblies via a hydraulic drive system, said hydraulic drive system comprising a hydraulic pump and at least one hydraulic motor driving each said rotor assembly.

21. The helicopter of claim 16 wherein said engine is mounted to said frame on vibration dampening mounts.

22. The helicopter of claim 16 wherein the total empty weight of the helicopter is not greater than 254 pounds.