Power converter having airplane power source detector

• US 7,554,218 B2
• Filed: 08/12/2005
• Issued: 06/30/2009
• Est. Priority Date: 08/12/2005
• Status: Expired due to Fees

• Current Assignee: iGo, Inc.
• Original Assignee: iGo, Inc.
• Inventors: McCoy, Bryan W., DuBose, Richard G.
• Primary Examiner(s): Jackson, Stephen W
• Assistant Examiner(s): RUTLAND WALLIS, MICHAEL
• Application Number:
  US11/202,815
• Publication Number:
  US 20070035287A1
• Time in Patent Office: 1,418 Days
• Field of Search: 307/73, 307/75, 307/129, 307/87, 307/130, 307/9.1, 307/10.1, 307/139, 713/300
• US Class Current: 307/10.1
• CPC Class Codes: H02M 1/10 Arrangements incorporating converting means for enabling loads to be operated at will from different kinds of power supplies, e.g. from ac or dc
• CPC Class Codes: H02M 3/003 Constructional details, e.g. physical layout, assembly, wiring or busbar connections

Abstract

A power converter having an aircraft power source detector adapted to limit the amount of power that can be drawn by the power converter when utilized in an aircraft. The power converter may detect an artifact of the aircraft power source, such as the 400 Hz ripple noise on an aircraft power line, or existing in the aircraft cabin, such EMI or aircraft lighting.

Claims

1. A power converter, comprising:

a first circuit having an input adapted to receive a power source having a first voltage, and adapted to convert the first voltage to a second voltage provided to an output, the first circuit adapted to power a portable electronic device; and

a second circuit coupled to the first circuit and adapted to identify if the power source is an aircraft power source by detecting a mechanical member displacement;

wherein the power converter further includes a plug adapted to couple to the aircraft power source and having a displaceable member; and

wherein the displaceable member is adapted to be depressed upon coupling of the plug to the aircraft power source.

2. The power converter as specified in claim 1 wherein the first circuit is adapted to respond to the second circuit when the aircraft power source is detected.

3. The power converter as specified in claim 2 wherein the first circuit limits an output power provided to output when the aircraft power source is detected.

4. The power converter as specified in claim 3 wherein the first circuit limits a current of the output power when the aircraft power source is detected.

5. The power converter as specified in claim 1 wherein the second circuit detects a frequency component of the power source.

6. The power converter as specified in claim 1 wherein the second circuit detects the absence of a frequency component of the power source.

7. The power converter as specified in claim 5 wherein the second circuit detects a presence of generally a 400 Hz signal provided by the power source.

8. The power converter as specified in claim 6 wherein the second circuit detects the absence of generally a 50-60 Hz signal provided by the power source.

9. The power converter as specified in claim 1 wherein the displaceable member is adapted to be depressed by a second member forming a portion of the aircraft power source.

10. The power converter as specified in claim 9 wherein the portion of the aircraft power source comprises a protruding said displaceable member.

11. The power converter as specified in claim 10 wherein the protruding displaceable member comprises an annular member.

12. The power converter as specified in claim 5 wherein second circuit is adapted to be electrically coupled to the aircraft power source.

13. The power converter as specified in claim 1 wherein the plug has an electrode adapted to couple to the aircraft power source.

14. The power converter as specified in claim 13 wherein the plug is adapted to couple to a receptacle of the aircraft power source.

15. The power converter as specified in claim 5 wherein the second circuit comprises a receiver adapted to wirelessly sense the frequency component of the power source.

16. The power converter as specified in claim 5 wherein the second circuit comprises a filter circuit adapted to filter the frequency component from the power source.

17. The power converter as specified in claim 16 wherein the filter is selected from the group consisting of a gyrator, a tuned digital filter, a phase locked loop, and a resonant tank.

18. The power converter as specified in claim 5 wherein the second circuit is adapted to detect the frequency component of an aircraft auxiliary power unit (APU).

19. The power converter as specified in claim 1 wherein the second circuit comprises a switch adapted to switch states upon the second circuit coupling to the aircraft power source.

20. The power converter as specified in claim 1 wherein the second circuit provides a signal at the output indicative of the presence of the aircraft power source.

21. The power converter as specified in claim 1 wherein the second circuit detects an artifact of the aircraft power source.

22. The power converter as specified in claim 5 further comprising a loading circuit configured to be selectively coupled to the second circuit and enhance signal detection of the frequency component.