Systems and methods for modular battery replacement in aircraft

• US 20080211309A1
• Filed: 03/01/2007
• Published: 09/04/2008
• Est. Priority Date: 03/01/2007
• Status: Abandoned Application

• Current Assignee: Bright Holdings, LLC
• Original Assignee: Bright Holdings, LLC
• Inventors: Nolte, William J.
• Application Number:
  US11/713,463
• Publication Number:
  US 20080211309A1
• Time in Patent Office: Days
• US Class Current: 307/66
• CPC Class Codes: H02J 7/0045 concerning the insertion or the connection of the batteries

Abstract

A modular aircraft emergency backup battery system and methods for operating the system as well as removing and replacing the modules within the system are described. The system includes a module cabinet enclosure that positions and interconnects the modules. A wiring harness provides the necessary electrical connections to and from the aircraft avionics to recharge the batteries within the system to allow the system to provide a source of power when battery backup is required. The cabinet enclosure provides positioned connections for one or more battery cell modules and one or more power control circuitry modules. A hinged front panel allows access to the battery cell modules and provides a switch and an indicator for operation of a test circuit. The modular enclosure is positioned in place of existing aircraft emergency battery backup systems and connects to the aircraft within the same space.

Claims

1. A modular battery system for use within an aircraft, the system comprising:

(a) a battery cell assembly module comprising at least one battery cell;

(b) a power supply control module comprising circuitry for charging the at least one battery cell and circuitry for allowing the discharge of the at least one battery cell to power the avionics of the aircraft; and

(c) a connector assembly comprising a plurality of electrical conductors and connectors between the battery cell assembly module, the power supply control module, and the aircraft avionics.

2. The system of claim 1 wherein the battery cell assembly module further comprises at least one battery heater.

3. The system of claim 1 wherein the battery cell assembly module further comprises a battery voltage monitor.

4. The system of claim 1 wherein the battery cell assembly module further comprises battery cell assembly test circuitry for verifying operational functionality of the battery cell assembly.

5. The system of claim 4 wherein the battery cell assembly test circuitry is user switch activated.

6. The system of claim 4 wherein the battery cell assembly test circuitry further comprises a visual indicator of the operational functionality of the battery cell assembly.

7. The system of claim 6 wherein the visual indicator comprises an indicator LED.

8. The system of claim 1 wherein the battery cell assembly further comprises a low voltage cutoff switch.

9. The system of claim 1 wherein the power supply control module further comprises power supply control test circuitry for verifying operational functionality of the power supply control module.

10. The system of claim 9 wherein the power supply control test circuitry is user switch activated.

11. The system of claim 9 wherein the power supply control test circuitry further comprises a visual indicator of the operational functionality of the power supply control module.

12. The system of claim 11 wherein the visual indicator comprises an indicator LED.

13. The system of claim 1 wherein the power supply control module further comprises AC inverter circuitry.

14. The system of claim 1 wherein the power supply control module further comprises DC converter circuitry.

15. The system of claim 1 wherein the connector assembly comprises a connector plug-in panel arranged to receive mateable connectors on the battery cell assembly module and the power supply control module.

16. The system of claim 15 wherein the connector plug-in panel further comprises a wiring harness and an end connector for connecting the system to the aircraft avionics and power buss.

17. The system of claim 1 further comprising a cabinet enclosure, the cabinet enclosure retaining the connector assembly and structured to receive and retain the battery cell assembly module and the power supply control module.

18. The system of claim 17 wherein the cabinet enclosure further comprises a plurality of rails for guiding the sliding insertion of the battery cell assembly module and the power supply control module into the cabinet enclosure.

19. The system of claim 17 wherein the cabinet enclosure further comprises a front panel, the front panel movable to allow the removal and insertion of the battery cell assembly module.

20. The system of claim 19 wherein the front panel is hingedly connected to a balance of the cabinet enclosure.

21. The system of claim 19 wherein the battery cell assembly module further comprises battery cell assembly test circuitry for verifying operational functionality of the battery cell assembly, the front panel comprises a circuit board configured with at least one connector mateable to at least one connection on the battery cell assembly module, and the battery cell assembly test circuitry is activated with a switch positioned on the front panel and an operational condition is indicated on a visual indicator positioned on the front panel.

22. A method for monitoring the condition of a modular avionics battery system in an aircraft and for removing and replacing individual modules within the system, the method comprising the steps of:

(a) providing a battery cell assembly module comprising at least one battery cell, a battery voltage monitoring circuit and a battery cell assembly test circuit;

(b) providing a power supply control module comprising battery cell charging circuitry, battery discharge circuitry, and a power supply control test circuit;

(c) connecting the battery cell assembly module through the power supply control module to the avionics system of the aircraft and the power buss of the aircraft;

(d) monitoring the charge condition of the at least one battery cell in the battery cell assembly module;

(e) periodically activating the battery cell assembly test circuit to determine the operational functionality of the battery cell assembly module;

(f) periodically activating the power supply control test circuit to determine the operational functionality of the power supply control module;

(g) on failure of the battery cell assembly module, removing and replacing the battery cell assembly module; and

(h) on failure of the power supply control module, removing and replacing the power supply control module;

wherein the removal and replacement of either the battery cell assembly module or the power supply control module may occur without the necessity of removing any other component of the avionics battery system.

23. The method of claim 22 wherein the step of periodically activating the battery cell assembly test circuit comprises the pre-flight steps of activating a user activated switch positioned on the battery cell assembly module and illuminating a visual indicator with either a good condition indication or a faulty condition indication.

24. The method of claim 22 wherein the step of periodically activating the power supply control test circuit comprises the pre-flight steps of activating a user activated switch positioned on the power supply control module and illuminating a visual indicator with either a good condition indication or a faulty condition indication.

25. The method of claim 22 wherein the battery cell assembly module is slidably positioned within a cabinet enclosure, the cabinet enclosure comprising the connectors for carrying out the step of connecting the battery cell assembly module and the power supply control module to each other and to the aircraft avionics, the step of removing the battery cell assembly module comprising pulling out and unplugging the module and slidably removing it from the cabinet enclosure.

26. The method of claim 22 wherein the power supply control module is slidably positioned within a cabinet enclosure, the cabinet enclosure comprising the connectors for carrying out the step of connecting the battery cell assembly module and the power supply control module to each other and to the aircraft avionics, the step of removing the power supply control module comprising pulling and unplugging the module and slidably removing it from the cabinet enclosure.