AIRCRAFT POWER RECEPTACLE PROTECTION SYSTEM

• US 20120309214A1
• Filed: 06/03/2011
• Published: 12/06/2012
• Est. Priority Date: 06/03/2011
• Status: Abandoned Application

• Current Assignee: Patlon Aircraft & Industries Limited
• Original Assignee: Patlon Aircraft & Industries Limited
• Inventors: Beluse, James
• Application Number:
  US13/152,695
• Publication Number:
  US 20120309214A1
• Time in Patent Office: Days
• US Class Current: 439/180
• CPC Class Codes: B64C 1/14 Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipersfairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06
• CPC Class Codes: H01R 13/633 for disengagement only in combination with safety switch H01R13/7132
• CPC Class Codes: H01R 13/641 by indicating incorrect coupling; by indicating correct or full engagement

Abstract

An aircraft power receptacle protection system is disclosed to protect aircraft from damage from a connected ground power unit. One aspect of the system includes a cable for conducting electricity between a ground power unit and an aircraft that has one or more releasable breakaways that are configured to separate with a determined amount of force. The releasable breakaways are installed inline with the cable and are positioned near the aircraft. The releasable breakaway is light weight and small but is still capable of carrying the required current to the aircraft. Another aspect of the system includes an alarm system for the ground power unit that uses an alarm indicator to alert an operator that the ground power unit is connected to the aircraft. The alarm system can have a aircraft plug with a split connector having to electrically isolated contacts that are connected when the plug is connected to the aircraft receptacle.

Claims

1. A ground power unit cable for conducting electricity between a ground power unit and an aircraft, the cable comprising:

an aircraft plug for inserting into an aircraft power receptacle;

a releasable breakaway having a first mated connector and a second complimentary mated connector, the connectors configured to separate with a determined tension on the cable;

a first insulated wire connecting the aircraft plug to the first mated connector of the releasable breakaway, the first insulated wire having a length to position the breakaway near the aircraft to allow the releasable breakaway to align with tension in the cable; and

a second insulated wire connecting to the second mated connector.

2. The cable of claim 1 further comprising a plurality of releasable breakaways, a plurality of first insulated wires and a plurality of second insulated wires, each of the plurality of breakaways having one of the plurality of first insulated wires connected to one of the two mated connectors and one of the plurality of second insulated wires connected to the other of the two mated connectors, and each of the plurality of first insulated wires connected to the aircraft plug.

3. The cable of claim 1 wherein the first insulated wire has a length in a range of 12 inch to 36 inches.

4. The cable of claim 1 wherein one of the first and second mated connectors is a cylindrical male connector having a depression in outer surface and an other of the first and second mated connectors is a hollow cylindrical socket female connector having a latching mechanism that extends inwards radially to engage the depression in the male connector.

5. The cable of claim 4 wherein the latching mechanism is a circular latching spring.

6. The cable of claim 5 wherein the latching spring is configured to define the determined tension that causes the releasable breakaway to separate.

7. The cable of claim 1 wherein the first mated connector has a flag affixed thereto and a portion of the flag is coupled to the second mated connector to release the flag when the releasable breakaway separates.

8. The cable of claim 7 wherein the flag is coupled to the second mated connector with heat shrink tubing.

9. The cable of claim 1 wherein the aircraft plug has a split connector having two electrically isolated contacts wherein inserting the aircraft plug connects the two electrically isolated contacts.

10. The cable of claim 1 further comprising a handle located near the releasable breakaway, the handle comprising a flexible strap having two end portions, each end portion attached to the cable.

11. An alarm system for preventing damage from to an aircraft from a ground power unit, the alarm system comprising:

an alarm indicator;

an aircraft sensing connector for receiving a signal indicating that the ground power unit is coupled to the aircraft; and

a control module connected to the alarm indicator and the aircraft sensing connector, the control module configured to activate the alarm indicator based on the aircraft sensing connector.

12. The alarm system of claim 11 wherein the aircraft sensing connector has two electrically isolated contacts, the two electrically isolated contacts being electrically connected when the ground power unit is coupled to the aircraft.

13. The alarm system of claim 12 wherein the aircraft sensing connector is an aircraft plug having a split connector comprised of the two electrically isolated contacts.

14. The alarm system of claim 13 further comprises:

a cable having;

a first insulated wire connected to a first contact of the two electrically isolated contacts; and

a second insulated wire connected to a second contact of the two electrically isolated contacts.

15. The alarm system of claim 11 further comprising a tow bar sensor connected to the control module, the control module configured to activate the alarm indicator based on the tow bar sensor and aircraft sensing connector.

16. The alarm system of claim 15 wherein the control module is configured to activate the alarm indicator when the tow bar sensor indicates that a tow bar is moved from a non-towing position and aircraft sensing signal connector indicates the ground power unit is connected to the aircraft.

17. The alarm system of claim 11 wherein the control module further comprises a circuit having the aircraft sensing connector, the alarm indicator, and a power supply connected in series such that the circuit is completed when the ground power unit is coupled to the aircraft.

18. The alarm system of claim 17 further comprising a tow bar switch that is closed when a tow bar is in a towing position, wherein the tow bar switch is connected in series with the aircraft sensing connector.

19. The alarm system of claim 11 wherein the alarm indicator is any one of an audio alarm and a visual alarm.

20. The alarm system of claim 19 wherein the audio alarm is a pulsing alarm.

21. The alarm system of claim 19 wherein the visual alarm is a strobe beacon.