Control System for an Aircraft

• US 20080180272A1
• Filed: 04/24/2007
• Published: 07/31/2008
• Est. Priority Date: 01/31/2007
• Status: Active Grant

• Current Assignee: Patrick L. Scherer
• Original Assignee: Patrick L. Scherer
• Inventors: Scherer, Patrick L.
• Granted Patent: US 7,793,890 B2
• Time in Patent Office: Days
• US Class Current: 340/825.72
• CPC Class Codes: A63H 30/04 using wireless transmission

Abstract

A control system for an aircraft includes a main unit and a separate auxiliary unit in communication with the main unit. The main unit includes an arm support allowing attachment to an arm of an operator. The main unit also includes a control stick supported by the structural element and movable in a plurality of directions. The main unit further includes sensors for sensing movement of the control stick. The auxiliary unit includes a transmitter for sending a transmitter signal encoding the movement of the control stick to the aircraft.

Claims

1. A control system for an aircraft comprising:

a main unit having a structural element;

said structural element including an arm support for attachment to an arm of an operator;

said main unit including a control stick supported by said structural element and movable in a plurality of directions;

said main unit further including at least one control stick sensor operatively connected to said control stick for sensing movement of said control stick and generating a control stick sensor signal corresponding to the movement of said control stick;

an auxiliary unit separate from said main unit;

said auxiliary unit including a transmitter in communication with said at least one sensor for sending a transmitter signal to the aircraft corresponding to the control stick sensor signal for controlling the aircraft.

2. A control system as set forth in claim 1 wherein said auxiliary unit further includes a battery for providing electrical power to said transmitter.

3. A control system as set forth in claim 1 further comprising a cable interconnected between said main unit and said auxiliary unit for providing communication between said at least one sensor and said transmitter.

4. A control system as set forth in claim 1 further comprising a wireless interface for providing communication between said at least one sensor and said transmitter.

5. A control system as set forth in claim 1 wherein said at least one control stick sensor is further defined as a first sensor for sensing movement of said control stick in along a first path and a second sensor for sensing movement of said control stick along a second path different from said first path.

6. A control system as set forth in claim 5 wherein said first sensor generates a pitch signal during movement of said control stick along said first path for moving an elevator of the aircraft.

7. A control system as set forth in claim 5 wherein said second sensor generates a roll signal during movement of said control stick along said second path for moving ailerons of the aircraft.

8. A control system as set forth in claim 1 wherein said main unit further includes a throttle button.

9. A control system as set forth in claim 8 wherein said main unit includes a third sensor operatively connected to said throttle button for sensing movement of said throttle button and generating a throttle signal corresponding to a position of said throttle button.

10. A control system as set forth in claim 1 wherein said auxiliary unit further includes a joystick.

11. A control system as set forth in claim 10 wherein said auxiliary unit further includes a fourth sensor operatively connected to said joystick for sensing movement of said joystick and generating a yaw signal corresponding to the movement of said joystick.

12. A control system for an aircraft comprising:

a structural element including an arm support for attachment to an arm of an operator;

a guide piece supported by said structural element and defining an elongated slot;

a control stick having an upper end and a lower end;

a pin disposed in said control stick between said upper and lower ends and defining a first pivot axis with said pin slidably disposed in said elongated slot such that said control stick pivots about said pivot axis and simultaneously slides along said elongated slot within a vertical plane;

a sensor mounted to said structural element and operatively connected to said control stick for sensing movement of said control stick and generating a sensor signal corresponding to the movement of said control stick in said vertical plane; and

a transmitter in communication with said sensor for sending a transmitter signal to the aircraft corresponding to the sensor signal for control of the aircraft.

13. A control system as set forth in claim 12 wherein said pin is disposed approximate to said lower end of said control stick.

14. A control system as set forth in claim 12 wherein said lower end of said control stick engages said sensor.

15. A control system as set forth in claim 12 wherein said guide piece is rotatable about a second pivot axis such that said control stick is simultaneously movable in a horizontal plane.

16. A control system as set forth in claim 15 wherein said second pivot axis is transverse to said first pivot axis.

17. A control system as set forth in claim 12 wherein said control stick includes a throttle button for controlling the throttle of the aircraft.

18. A control system as set forth in claim 17 wherein said control stick includes a throttle locking mechanism for locking the position of the throttle button and maintaining a constant throttle of the aircraft.

19. A control system for an aircraft comprising:

a structural element including an arm support for attachment to an arm of an operator;

a control stick supported by said structural element;

at least one sensor mounted to said structural element and operatively connected to said control stick for sensing movement of said control stick and generating a sensor signal corresponding to the movement of said control stick;

a transmitter in communication with said at least one sensor for sending a transmitter signal to the aircraft corresponding to the sensor signal for control of the aircraft; and

an attachment apparatus disposed on said structural element for allowing attachment of a line connecting said structural element to the aircraft.

20. A control system as set forth in claim 19 further comprising a guide piece supported by said structural element for supporting said control stick.

21. A control system as set forth in claim 20 wherein said guide piece is rotatable about an axis such that said control stick is movable in a horizontal plane.

22. A control system as set forth in claim 21 further comprising a locking mechanism engagable with said guide piece for locking said guide piece in place and preventing movement of said control stick in said horizontal plane.

23. A control system as set forth in claim 22 wherein said locking mechanism is integrated with said attachment apparatus.