Reconfigurable aircraft radio communications system

• US 8,081,933 B2
• Filed: 07/13/2007
• Issued: 12/20/2011
• Est. Priority Date: 07/13/2007
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Malaga, Alfonso, Meiyappan, Palaniappan, Wilson, Chad E., Hunter, Jeffrey K., Triplett, Gregory
• Primary Examiner(s): Pan, Yuwen
• Assistant Examiner(s): AYOTUNDE, AYODEJI O
• Application Number:
  US11/777,468
• Publication Number:
  US 20090017777A1
• Time in Patent Office: 1,621 Days
• Field of Search: None
• US Class Current: 455/90.2
• CPC Class Codes: H04B 1/0466 Fault detection or indication H04B1/0483 takes precedence
• CPC Class Codes: H04B 1/406 with more than one transmission mode, e.g. analog and digital modes
• CPC Class Codes: H04B 7/18506 Communications with or from aircraft, i.e. aeronautical mobile service

Abstract

A reconfigurable radio communications system is disclosed. The system comprises a digital data bus, a control bus, and first and second reconfigurable radio communication units responsive to the digital data bus and the control bus. Each of the first and second reconfigurable radio communication units further include a first and a second multifunction radio transceiver, with the first reconfigurable radio communication unit responsive to at least a first antenna, and the second reconfigurable radio communication unit responsive to at least a second antenna. Each of the first and the second multifunction radio transceivers of the first and the second reconfigurable radio communication units are operable to simultaneously transmit and receive data on at least two separate channels from different frequency bands. Within the system, one of the multifunction radio transceivers is automatically reconfigurable to maintain radio communication functions previously performed by a faulted multifunction radio transceiver.

Claims

1. A reconfigurable radio communications system, comprising:

a digital data bus;

a control bus;

a first reconfigurable radio communication unit responsive to the digital data bus and the control bus, the first reconfigurable radio communication unit including a first and a second multifunction radio transceiver responsive to at least a first antenna, the first reconfigurable radio communication unit further comprising;

a first power supply voltage converter configured to derive voltages from a first normal power supply and a first emergency power supply; and

a second power supply voltage converter configured to derive voltages from the first normal power supply and the first emergency power supply, the first emergency power supply remaining operable when the first normal power supply fails;

a second reconfigurable radio communication unit responsive to the digital data bus and the control bus, the second reconfigurable radio communication unit including a first and a second multifunction radio transceiver responsive to at least a second antenna, the second reconfigurable radio communication unit further comprising;

a third power supply voltage converter configured to derive voltages from a second normal power supply and a second emergency power supply; and

a fourth power supply voltage converter configured to derive voltages from the second normal power supply and the second emergency power supply,

the second emergency power supply remaining operable when the second normal power supply fails;

wherein each of the first and the second multifunction radio transceivers of the first and the second reconfigurable radio communication units are operable to simultaneously transmit and receive data on at least two separate channels from different frequency bands; and

wherein one of the multifunction radio transceivers is automatically reconfigurable to maintain radio communication functions previously performed by a faulted multifunction radio transceiver.

2. The system of claim 1, further comprising:

at least one high frequency coupler unit communicatively coupled to the first or the second multifunction radio transceivers in each of the reconfigurable radio communication units; and

a high frequency antenna, communicatively coupled to the coupler unit, operable to transmit and receive data on at least one high frequency band channel of the first or the second multifunction radio transceivers in each of the reconfigurable radio communication units.

3. The system of claim 1, wherein the digital bus is a digital crosstalk bus operable to transfer transmit and receive data between each of the multifunction radio transceivers within the system.

4. The system of claim 1, wherein each of the multifunction radio transceivers comprises a high frequency radio transceiver and a very high frequency radio transceiver.

5. The system of claim 1, wherein each of the multifunction radio transceivers comprises at least one of a high frequency radio transceiver, a very high frequency radio transceiver, and a satellite communications radio transceiver.

6. The system of claim 1, wherein each of the reconfigurable radio communication units further comprise at least one antenna switch to route the radio frequency signals for the multifunction radio transceiver, configured as the first multifunction radio transceiver, to the at least one first antenna or the at least one second antenna.

7. The system of claim 1, wherein each of the reconfigurable radio communication units further comprise:

at least one digital processing module communicatively coupled to the first multifunction radio transceiver; and

an input/output module communicatively coupled to the at least one digital processing module through the digital bus to transfer transmit and receive data between each of the multifunction radio transceivers.

8. The system of claim 7, wherein at least one of the input/output modules coordinates and controls future reconfigurations of each of the operable multifunction radio transceivers.

9. A reconfigurable aircraft radio communications system, comprising:

at least two reconfigurable radio communications units coupled to a digital crosstalk bus, each of the reconfigurable radio communications units comprising;

at least two multifunction radio transceivers operable to simultaneously transmit and receive radio dispatches between an aircraft and a plurality of ground stations on at least two separate frequency band channels with at least a first antenna and a second antenna;

at least two digital processing modules, each of the digital processing modules communicatively coupled to a respective one of the multifunction radio transceivers;

at least two power amplifiers, each of the power amplifiers communicatively coupled to a respective one of the multifunction radio transceivers;

an input/output module, communicatively coupled to at least one of the digital processing modules, configured to manage communication data between each of the reconfigurable radio communication units;

a first power supply voltage converter coupled to one of the digital processing modules, one of the multifunction radio transceivers, one of the power amplifiers, and the input/output module, wherein the first power supply voltage converter is configured to derive voltages from a normal power supply and an emergency power supply; and

a second power supply voltage converter coupled to at least one other of the digital processing modules, at least one other of the multifunction radio transceivers, at least one other of the power amplifiers, and the input/output module, wherein the second power supply voltage converter is configured to derive voltages from the normal power supply and the emergency power supply;

wherein the system automatically reconfigures at least one of the multifunction radio transceivers designated as a standby multifunction radio transceiver once a fault in at least one of the reconfigurable radio communications units is detected; and

wherein the system automatically reconfigures at least one of the reconfigurable radio communications units to operate under emergency supply conditions when a system emergency power mode indication occurs.

10. The system of claim 9, further comprising at least one high frequency coupler unit communicatively coupled to at least one of the multifunction radio transceivers in each of the reconfigurable radio communication units.

11. The system of claim 9, wherein each of the multifunction radio transceivers operate simultaneously on at least one high frequency channel and at least two very high frequency channels.

12. The system of claim 9, wherein the normal power supply in each of the reconfigurable radio communications units supplies power to each of the multifunction radio transceivers, each of the digital processing modules, each of the power amplifiers, and the input/output module.

13. The system of claim 9, wherein each of the reconfigurable radio communication units further comprise at least one antenna switch to route the radio dispatch for a multifunction radio transceiver, configured as the standby multifunction radio transceiver, to the at least one first antenna or the at least one second antenna.

14. The system of claim 9, wherein each of the multifunction radio transceivers is at least one of a high frequency radio transceiver or a very high frequency radio transceiver.

15. A method for maintaining radio communications in a reconfigurable aircraft radio communications system, the method comprising:

detecting a communications fault in a reconfigurable radio communications unit with at least one multifunction radio transceiver, the reconfigurable radio communications unit configured to include at least two communications functions capable of simultaneous operation on at least two channel frequencies, the reconfigurable radio communication unit comprising;

a first power supply voltage converter configured to derive voltages from a normal power supply and an emergency power supply; and

a second power supply voltage converter configured to derive voltages from the normal power supply and the emergency power supply;

once the communications fault is detected, automatically reconfiguring a hot-standby multifunction radio transceiver in the reconfigurable radio communications unit to continue operating the at least two communications functions on the at least two channel frequencies without manual intervention; and

if a system emergency power mode indication occurs, reconfiguring the communications system to operate under emergency supply conditions.

16. The method of claim 15, wherein detecting the fault in the reconfigurable radio communications unit further comprises periodically monitoring each of the communications functions during operation.

17. The method of claim 15, wherein automatically reconfiguring the hot-standby multifunction radio transceiver further comprises:

controlling future reconfigurations of any remaining multifunction radio transceivers from an input/output module; and

reporting the fault when more than two failures of any of the multifunction radio transceivers in the communications system occur.

18. The method of claim 15, wherein reconfiguring the communications system to operate under emergency supply conditions further comprises managing the assignment of power supply voltage converters and the at least two communications functions to the at least one multifunction radio transceiver that remains operational when the system experiences a loss of normal electrical power input.

19. A non-transitory computer readable medium having computer-executable instructions for performing a method for maintaining radio communications in a reconfigurable radio communications system according to claim 15.