HELICOPTER WITH TWO OR MORE ROTOR HEADS

• US 20120241553A1
• Filed: 10/13/2011
• Published: 09/27/2012
• Est. Priority Date: 07/20/2010
• Status: Abandoned Application

• Current Assignee: Wilke, Paul
• Original Assignee: Wilke, Paul
• Inventors: Wilke, Paul
• Application Number:
  US13/187,451
• Publication Number:
  US 20120241553A1
• Time in Patent Office: Days
• US Class Current: 244/17.13
• CPC Class Codes: B64C 27/08 with two or more rotors

Abstract

A helicopter with two or more rotor heads with full swash plate control and a novel control scheme to allow for propulsion in the horizontal plane in all directions, allowing the aircraft to fly in all directions in a truly horizontal fashion. Furthermore, a manual input device to control the additional control freedoms thus gained, and an electronic control system that combines manual inputs with inputs from sensors and translates these inputs into directions for the actuators of the two or more swash plates in order to control the aircraft, taking into account the novel control scheme.

Claims

1. A helicopter, comprising:

a helicopter fuselage;

at least two swash plates connected to said helicopter fuselage;

at least two rotor heads, where each of said at least two rotor heads is connected to a respective one of said at least two swash plates; and

a control system connected to each of said at least two swash plates and to each of said at least two rotor heads, where the control system permits full control of each respective swash plate for each of said at least two rotor heads.

2. The helicopter of claim 1, where the helicopter fuselage has a horizontal plane, and where the control system includes means for adjusting each of said at least two swash plates according to a novel control scheme such that propulsion force can be generated in the horizontal plane at each of said at least two rotor heads, to permit horizontal flight of said helicopter in all directions.

3. The helicopter of claim 1, where the helicopter fuselage has a horizontal plane and a vertical axis, and where the control system includes means for adjusting each of said at least two swash plates according to a novel control scheme such that propulsion force can be generated in the horizontal plane at each of said at least two rotor heads, to permit rudder control over all rotation about the vertical axis.

4. The helicopter of claim 1, where the fuselage includes a member mounted between said at least two rotor heads such that said member reduces the interaction of downwash from each of said at least two rotor heads and said fuselage.

5. The helicopter of claim 1, further comprising:

a manual input device connected to said control system, said input device including a sliding platform and a joystick, where a user may control steering the aircraft along the horizontal plane by moving the sliding platform so as to mimic the desired movements in the horizontal plane by the helicopter, and where the joy stick is connected to said sliding platform, said joystick connected to said control system for exercising elevator and aileron control of said at least two rotor heads.

6. The helicopter of claim 1, where said control system further comprises:

six manual inputs, where each of said six manual inputs represents one of six orthogonal directions;

at least one gyroscope for each rotational axis to be stabilized; and

at least one accelerometer for each longitudinal axis to be stabilized;

where the control system combines the six manual inputs with inputs from said at least one gyroscope and said at least one accelerometer, to generate the commands to steer the at least two swash plates such that propulsion force can be generated in the horizontal plane at each of said at least two rotor heads, to permit horizontal flight of said helicopter in all directions.

7. The helicopter of claim 6, where the control system includes a network of decentralized computers.

8. The helicopter of claim 7, where said network of decentralized computers includes at least one computer connected to each of said at least two swash plates.

9. A method for controlling a helicopter, comprising;

connecting at least two swash plates to a fuselage of said helicopter;

connecting a rotor head to each of said at least two swash plates;

connecting a control system to said at least two swash plates and to each said rotor head; and

sending control signals through said control system to said at least two swash plates and to each said rotor head to control each of said at least two swash plates.

10. The method of claim 9, where said control system includes a manual input device connected to said control system, said input device including a sliding platform and a joystick, where a user may control steering the aircraft along the horizontal plane by moving the sliding platform so as to mimic the desired movements in the horizontal plane by the helicopter, and where the joy stick is connected to said sliding platform, said joystick connected to said control system for exercising elevator and aileron control of said at least two rotor heads.

11. The method of claim 9, where said control system further includes:

six manual inputs, where each of said six manual inputs represents one of six orthogonal directions;

at least one gyroscope for each rotational axis to be stabilized; and

at least one accelerometer for each longitudinal axis to be stabilized; and

combining in the control system the six manual inputs with inputs from said gyroscopes and said accelerometers,;

generating in the control system commands to steer the at least two swash plates such that propulsion force can be generated in a horizontal plane at each of said at least two rotor heads, to permit horizontal flight of said helicopter in all directions.

12. The method of claim 11, where said control system includes a network of decentralized computers.

13. The method of claim 12, where said network of decentralized computers includes at least one computer connected to each of said at least two swash plates.