System, method and apparatus for ground-based manipulation and control of aerial vehicle during non-flying operations

• US 20090045283A1
• Filed: 01/08/2008
• Published: 02/19/2009
• Est. Priority Date: 01/11/2007
• Status: Active Grant

• Current Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Original Assignee: Lockheed Martin Corporation (Martin Marietta Corporation)
• Inventors: Renshaw, Kevin J.
• Granted Patent: US 8,079,545 B2
• Time in Patent Office: Days
• US Class Current: 244/50
• CPC Class Codes: B64F 1/224 Towing bars

Abstract

A device for controlling an aircraft during non-flying operations has a retractable tiller that extends with the nose landing gear of the aircraft. Ground crew use the control device to maneuver the aircraft for various ground-based operations. The tiller provides left and right directional input to the steering of the nose wheel. The tiller also provides throttle and brake controls, such as a twist-grip handle on the tiller. The throttle and brake controls are spring-loaded to an engine idle and braked position. Separate brakes also may be provided for additional braking control. The control device also includes various auxiliary controls for additional operations such as wing fold, tail hook extension and retraction, launch bar extension and retraction, etc. Other functions including engine start, engine shutdown, a vehicle system built in test and other functions and tests also may be provided on the control device.

Claims

1. An aircraft, comprising:

an aircraft body having flight controls for controlling flight operations of the aircraft; and

a ground operations control device mounted to the aircraft body for maneuvering the aircraft strictly during non-flying operations, such that the ground operations control device is separate and independent from the flight controls, and the ground operations control device is inactive during flight of the aircraft.

2. An aircraft according to claim 1, wherein the ground operations control device is retractable.

3. An aircraft according to claim 1, wherein the ground operations control device provides at least some direct mechanical control of the aircraft.

4. An aircraft according to claim 1, wherein the ground operations control device is extended with the landing gear.

5. An aircraft according to claim 4, wherein the ground operations control device extends and retracts with a nose landing gear, and is located in a bay of the nose landing gear during flight of the aircraft.

6. An aircraft according to claim 1, wherein the aircraft is an unmanned aerial vehicle.

7. An aircraft according to claim 1, wherein the ground operations control device comprises a tiller that protrudes from a front portion of the aircraft body and is adjacent a centerline of the aircraft body.

8. An aircraft according to claim 1, wherein the ground operations control device is attached to a steering control via a pivot that provides direct left and right directional inputs to a steering of a nose wheel of the aircraft.

9. An aircraft according to claim 1, wherein the ground operations control device has throttle and brake controls comprising a combined, single motorcycle-style, twist-grip handle providing clockwise and counter-clockwise rotation for applying throttle and braking functions.

10. An aircraft according to claim 9, wherein the throttle and brake controls are spring-loaded to an unbiased, engine idle position such that release of the throttle and brake controls return the aircraft to an engine idle position and activate wheel brakes of the aircraft.

11. An aircraft according to claim 9, further comprising a separate brake handle for separate and additional braking control of the aircraft, including differential braking of left and right side brakes.

12. An aircraft according to claim 1, wherein the ground operations control device further comprises auxiliary controls for operations including wing fold, tail hook extension and retraction, launch bar extension and retraction, engine start, engine shutdown, and a vehicle system built in test (BIT).

13. A method of manipulating an aircraft during non-flying operations, comprising:

(a) providing an aircraft having flight controls for controlling flight operations of the aircraft, and ground operations controls for controlling non-flying operations of the aircraft;

(b) starting an engine of the aircraft via the ground operations controls;

(c) taxiing the aircraft into a launch position by controlling it with the ground operations controls;

(d) launching, flying and landing the aircraft by controlling it with the flight controls; and

then

(e) after the aircraft has landed, taxiing the aircraft to a parked position and shutting down the engine by controlling the aircraft with the ground operations controls.

14. A method according to claim 13, wherein the ground controls are separate and independent from the flight controls, and the ground controls are inactive during flight of the aircraft.

15. A method according to claim 13, wherein, during step (d), the ground operations controls are retracted into the aircraft after launch, and extended from the aircraft during landing.

16. A method according to claim 13, wherein steps (c) and (e) comprise a crewman manually engaging the ground operations controls with a hand of the crewman to directly mechanically manipulate the ground operations controls.

17. A method according to claim 13, wherein the aircraft is an unmanned aerial vehicle.

18. A method according to claim 13, wherein the ground operations controls comprise a tiller that protrudes from a front portion of the aircraft and is adjacent a centerline of the aircraft.

19. A method according to claim 13, wherein the ground operations controls are attached to a steering control via a pivot that provides direct left and right directional inputs to a steering of a nose wheel of the aircraft.

20. A method according to claim 13, wherein the ground operations controls have throttle and brake controls comprising a combined, single motorcycle-style, twist-grip handle providing clockwise and counter-clockwise rotation for applying throttle and braking functions.

21. A method according to claim 20, wherein the throttle and brake controls are spring-loaded to an unbiased, engine idle position such that release of the throttle and brake controls return the aircraft to an engine idle position and activate wheel brakes of the aircraft.

22. A method according to claim 20, further comprising a separate brake handle for separate and additional braking control of the aircraft, including differential braking of left and right side brakes.

23. A method according to claim 13, wherein the ground operations controls further comprise auxiliary controls for operations including wing fold, tail hook extension and retraction, launch bar extension and retraction, engine start, engine shutdown, and a vehicle system built in test (BIT).