UNIVERSAL HITCH ADAPTER AND SYSTEM

• US 20170305214A1
• Filed: 04/20/2016
• Published: 10/26/2017
• Est. Priority Date: 04/20/2016
• Status: Active Grant

• Current Assignee: Roderick James Gray
• Original Assignee: Roderick James Gray
• Inventors: Gray, Roderick James
• Granted Patent: US 10,166,826 B2
• Time in Patent Office: Days
• CPC Class Codes: B60D 1/02 Bolt or shackle-type couplings
• CPC Class Codes: B60D 1/248 for measuring, indicating or displaying the weight
• CPC Class Codes: B60D 1/62 involving supply lines, electric circuits, or the like
• CPC Class Codes: B60P 3/11 for carrying aircraft
• CPC Class Codes: B60W 2720/106 Longitudinal acceleration
• CPC Class Codes: B60W 30/18 Propelling the vehicle
• CPC Class Codes: B64F 1/224 Towing bars
• CPC Class Codes: B64F 1/225 Vehicles specially adapted therefor, e.g. aircraft tow tractors
• CPC Class Codes: Y02T 50/80 Energy efficient operational measures, e.g. ground operations or mission management

Abstract

A universal hitch adapter system includes a universal hitch adapter with at least one force sensor operable to measure push-and-pull forces and coupled to a) one of a front end and a rear end of an aircraft tractor and b) an aircraft tow bar coupled to a nose gear of an aircraft. The system also including a memory; a user input interface operable to receive a user'"'"'s selection of one of a plurality of aircrafts stored in the memory and a user'"'"'s input associated with one of a shear pin; a processor operably configured to determine at least one shear pin breaking force threshold for each of the plurality of aircrafts based on the user'"'"'s input; and an indicator operable to emit an alert as a result of the force sensor measuring a force that meets or exceeds the at least one shear pin breaking force threshold.

Claims

1. An aircraft tractor comprising:

a front end and a rear end opposite the front end;

an aircraft tractor hitch; and

a universal hitch adapter system including;

at least one force sensor disposed between one of the front end and the rear end and the aircraft tractor hitch;

at least one input operable to receive force measurements from the at least one force sensor;

a memory storing a plurality of aircrafts thereon;

a user input interface operable to receive a user'"'"'s selection of one of the plurality of aircrafts stored in the memory; and

at least one processor communicatively coupled to the at least one input, the memory, and the user input interface and operably configured to determine, based on the user'"'"'s selection of one of the plurality of aircrafts, at least one sheer pin breaking force threshold.

2. The aircraft tractor in accordance with claim 1, further comprising:

an indicator communicatively coupled to the at least one processor and operably configured to emit an alert as a result of the at least one force sensor measuring a force transmitted on an aircraft tow bar coupled to the aircraft tractor hitch that meets or exceeds the at least one shear pin breaking force threshold.

3. The aircraft tractor in accordance with claim 1, further comprising:

an accelerator pedal; and

an electronic control line communicatively coupled to the accelerator pedal; and

wherein the at least one processor is communicatively coupled to the electronic control line and the at least one processor is further operable to automatically prevent acceleration of the aircraft tractor, via the electronic control line, as a result of the at least one force sensor measuring a force that meets or exceeds the at least one shear pin breaking force threshold.

4. The aircraft tractor in accordance with claim 1, further comprising:

an accelerator pedal; and

an electronic control line communicatively coupled to the accelerator pedal; and

wherein the at least one processor is communicatively coupled to the electronic control line and the at least one processor is further operable to automatically prevent acceleration of the aircraft tractor, via the electronic control line, as a result of the at least one force sensor sensing an aircraft load without the at least one processor having received the user'"'"'s selection of one of the plurality of aircrafts.

5. The aircraft tractor in accordance with claim 1, wherein:

the universal hitch adapter further includes a steel insert operably configured to support the at least one force sensor, the steel insert including a first coupling member and a second coupling member opposite the first coupling member with the at least one force sensor interposed therebetween; and

the first coupling member is coupled to the front end of the aircraft tractor and the second coupling member is coupled to the aircraft tractor hitch.

6. The aircraft tractor in accordance with claim 5, wherein:

the steel insert is of a hardened steel material.

7. The aircraft tractor in accordance with claim 5, wherein:

the steel insert further comprises at least two parallel stress plates, each of the at least two parallel stress plates defining an aperture through which the at least one force sensor is disposed and each of the at least two parallel stress plates translatable relative to one another about the at least one force sensor so as to impart push-and-pull forces from an aircraft tow bar on the at least one force sensor.

8. A universal aircraft tractor hitch adapter system comprising:

at least one force sensor disposed between one of a front end and a rear end of an aircraft tractor and an aircraft tractor hitch; and

a universal control device including;

at least one input operable to receive force measurements from the at least one force sensor;

a memory storing a plurality of aircrafts thereon;

a user input interface operable to receive a user'"'"'s selection of one of the plurality of aircrafts stored in the memory; and

at least one processor communicatively coupled to the at least one input, the memory, and the user input interface and operably configured to determine, based on the user'"'"'s selection of one of the plurality of aircrafts, at least one sheer pin breaking force threshold.

9. The universal aircraft tractor hitch adapter system in accordance with claim 8, wherein:

the at least one processor is operably configured to transmit an alert as a result of the at least one force sensor measuring a force transmitted on an aircraft tow bar coupled to the aircraft tractor hitch that meets or exceeds the at least one shear pin breaking force threshold.

10. The universal aircraft tractor hitch adapter system in accordance with claim 9, further comprising:

a steel insert operably configured to support the at least one force sensor, the steel insert including a first coupling member and a second coupling member opposite the first coupling member with the at least one force sensor interposed therebetween, the first coupling member coupled to the front end of the aircraft tractor and the second coupling member coupled to the aircraft tractor hitch.

11. The universal aircraft tractor hitch adapter system in accordance with claim 10, wherein:

the steel insert further comprises at least two parallel stress plates, each of the at least two parallel stress plates defining an aperture through which the at least one force sensor is disposed and each of the at least two parallel stress plates translatable relative to one another about the at least one force sensor so as to impart push-and-pull forces from the aircraft tow bar on the at least one force sensor.

12. The universal aircraft tractor hitch adapter system in accordance with claim 11, wherein:

the steel insert is of a hardened steel material.

13. The universal aircraft tractor hitch adapter system in accordance with claim 9, wherein:

the at least one processor is communicatively coupled to an electronic control line for an accelerator pedal of the aircraft tractor and the at least one processor is further operable to automatically prevent acceleration of the aircraft tractor, via the electronic control line, as a result of the at least one force sensor measuring a force that meets at or exceeds the at least one shear pin breaking force threshold.

14. The universal aircraft tractor hitch adapter system in accordance with claim 9, wherein:

the at least one processor is further operable to automatically prevent acceleration of the aircraft tractor as a result of the at least one force sensor sensing an aircraft load without the at least one processor having received the user'"'"'s section of one of the plurality of aircrafts.

15. A method for an aircraft tractor to safely tow aircrafts, the method comprising steps of:

measuring, by a force sensor disposed between one of a front end and a rear end of an aircraft tractor and an aircraft tractor hitch coupled to an aircraft tow bar, push-and-pull forces transmitted on the aircraft tow bar;

providing a force sensor output, by the force sensor, to at least one processor;

receiving, by the at least one processor, a user'"'"'s first selection of one of a plurality of aircrafts stored in a memory communicatively coupled to the at least one processor;

determining, by the at least one processor, at least one shear pin breaking force threshold associated with the user'"'"'s first selection of one of the plurality of aircrafts; and

providing, by an indicator communicatively coupled to the at least one processor, an alert as a result of the force sensor measuring a force that meets or exceeds the at least one shear pin breaking force threshold.

16. The method in accordance with claim 15, further comprising a step of:

integrating the at least one processor and the indicator into an aircraft tractor.

17. The method in accordance with claim 15, further comprising steps of:

coupling a tow bar head of the aircraft tow bar to a nose gear of an aircraft; and

coupling a shear pin to the tow bar head.

18. The method in accordance with claim 15, further comprising:

revising, by the at least one processor, the at least one shear pin breaking force threshold based on a user'"'"'s second selection of a second one of the plurality of aircrafts, different from the user'"'"'s first selection of one of the plurality of aircrafts.

19. The method in accordance with claim 15, further comprising a step of:

automatically preventing, by the at least one processor, acceleration of an aircraft tractor on which the force sensor is disposed as a result of the force sensor measuring a force that meets or exceeds the at least one shear pin breaking force threshold.

20. The method in accordance with claim 15, further comprising a step of:

receiving, by the at least one processor, a shear pin breaking force threshold input by the user.