Integrated avionics system

• US 20080174472A1
• Filed: 04/10/2007
• Published: 07/24/2008
• Est. Priority Date: 04/10/2006
• Status: Active Grant

• Current Assignee: Aviation Communication and Surveillance Systems LLC (L3Harris Technologies, Inc.)
• Original Assignee: L-3 Communications Corporation (L3Harris Technologies, Inc.)
• Inventors: Stayton, Gregory T., Stone, Cyro A., Troxel, James R.
• Granted Patent: US 8,768,540 B2
• Time in Patent Office: Days
• US Class Current: 342/30
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/0086 for monitoring terrain radar or analogous systems specially adapted for terrain avoidance G01S13/935
• CPC Class Codes: G08G 5/04 Anti-collision systems

Abstract

There is provided an avionics system that provides several avionics functions within a single LRU. In one embodiment, the system comprises a software-configurable RF assembly, one or more processor assemblies that are configured to provide multiple TAWS/TCAS/Mode S/ADS-B/ATC functions, interfaces to allow connections to aircraft electronics and data loaders, and multipurpose antennas. In one embodiment, a common processor architecture allows generic avionics processors to be configured to operate a number of TAWS/TCAS/Mode S/ADS-B/ATC functions without the need for multiple LRUs, and software-defined RF functions allow RF circuitry that interfaces to the processors to handle current and future communication needs.

Claims

1. An avionics system comprising:

a software-configurable RF assembly;

a processor assembly including;

input-output logic circuitry;

RF logic and control circuitry;

a plurality of surveillance communication processors (SCPs), each SCP including an integrated processor coupled to;

a nonvolatile memory including executable code;

a volatile memory; and

control logic; and

a bus coupling the SCPs, the input-output logic circuitry, and RF logic and control circuitry; and

means for electronically interconnecting the software-configurable RF assembly and the processor assembly.

2. The avionics system as defined in claim 1 further comprising a housing defining a volume, wherein the software-configurable RF assembly, processor assembly, and electronic interconnection means are configured to operate within the defined volume.

3. The avionics system as defined in claim 1 wherein the executable code, when executed by the integrated processor, enables the avionics system to perform an avionics function selected from the group consisting of:

Ground Proximity Warning (GPWS);

Ground Collision Avoidance (GCAS);

Terrain Awareness and Warning (TAWS);

Traffic Collision Avoidance (TCAS);

Air Traffic Control (ATC);

Automatic Dependent Surveillance Broadcast (ADS-B);

Standard Mode S Transponder support;

Universal Access Transceivers (UAT) datalink support; and

combinations thereof.

4. The avionics system as defined in claim 1 wherein:

a first SCP of the plurality of SCPs is configured to perform a traffic collision and avoidance function; and

a second SCP of the plurality of SCPs is configured to perform a terrain awareness and warning function.

5. The avionics system as defined in claim 1 further comprising an external interface coupled to the electronic interconnection means, whereby the processor assembly may be reconfigured by:

downloading, through the external interface, modified executable code; and

storing the modified executable code in at least one of the nonvolatile memories.

6. The avionics system as defined in claim 1 further comprising an external interface coupled to the electronic interconnection means, whereby the software-configurable RF assembly may be reconfigured by downloading, through the external interface, modified software instructions to reconfigure a software programmable demodulator.

7. The avionics system as defined in claim 1 further comprising:

an external interface coupled to the electronic interconnection means; and

a directional antenna coupled to the external interface, whereby the directional antenna is configured, via the software-configurable RF assembly, to;

operate in a directional traffic collision avoidance mode; and

operate in an omnidirectional transponder mode.

8. The avionics system as defined in claim 1 further comprising an external connector coupled to the electronic interconnection means, whereby the connector is configured to connect to an ARINC 615A portable data loader-compliant computer.

9. The avionics system as defined in claim 1 wherein the bus coupling the SCPs, the input-output logic circuitry, and RF logic and control circuitry includes a PCI bus.

10. The avionics system as defined in claim 1 wherein the integrated processor includes a Power PC processor.

11. An avionics system comprising:

a software-configurable RF assembly;

a common power supply;

a processor assembly including;

input-output logic circuitry;

RF logic and control circuitry;

a TCAS surveillance communication processor configured to;

alert a pilot to avoid a mid-air collision; and

perform transponder functions;

a TAWS surveillance communication processor configured to alert a pilot to avoid controlled flight into terrain;

a bus coupling the TCAS surveillance communication processor, the TAWS surveillance communication processor, the input-output logic circuitry, and RF logic and control circuitry; and

,

means for electronically interconnecting the software-configurable RF assembly, the common power supply and the processor assembly.

12. The avionics system as defined in claim 11 further comprising a housing defining a volume, wherein the software-configurable RF assembly, common power supply, processor assembly, and electronic interconnection means are configured to operate within the defined volume.

13. The avionics system as defined in claim 11 further comprising an external interface coupled to the electronic interconnection means, whereby the processor assembly may be reconfigured by:

downloading, through the external interface, modified executable code; and

storing the modified executable code in at least one of the nonvolatile memories.

14. The avionics system as defined in claim 11 further comprising an external interface coupled to the electronic interconnection means, whereby the software-configurable RF assembly may be reconfigured by downloading, through the external interface, modified software instructions to reconfigure a software programmable demodulator.

15. The avionics system as defined in claim 11 further comprising:

an external interface coupled to the electronic interconnection means; and

a directional antenna coupled to the external interface, whereby the directional antenna is configured, via the software-configurable RF assembly, to;

operate in a directional traffic collision avoidance mode; and

operate in an omnidirectional transponder mode.

16. The avionics system as defined in claim 11 further comprising an external connector coupled to the processor assembly, whereby the connector is configured to connect to an ARINC 615A portable data loader-compliant computer.

17. The avionics system as defined in claim 11 wherein the bus coupling the TCAS surveillance communication processor, the TAWS surveillance communication processor, the input-output logic circuitry, and RF logic and control circuitry is a PCI bus.

18. An avionics system comprising:

an interconnection backplane;

two processor assemblies coupled to the backplane, each processor comprising;

input-output logic circuitry;

RF logic and control circuitry;

a TCAS surveillance communication processor configured to;

alert a pilot to avoid a mid-air collision; and

perform transponder functions;

a TAWS surveillance communication processor configured to alert a pilot to avoid controlled flight into terrain;

a high speed data interface;

a bus coupling the SCPs, the input-output logic circuitry, and RF logic and control circuitry; and

,

a software-configurable RF assembly coupled to the backplane;

power supply coupled to the backplane; and

a spare expansion slot, allowing coupling of an additional assembly to the backplane.

19. The avionics system as defined in claim 18 further comprising an external interface coupled to the backplane, whereby the software-configurable RF assembly may be reconfigured by downloading, through the external interface, modified software instructions to reconfigure a software programmable demodulator.

20. The avionics system as defined in claim 18 further comprising:

an external interface coupled to the backplane; and

a directional antenna coupled to the external interface, whereby the directional antenna is configured, via the software-configurable RF assembly, to;

operate in a directional traffic collision avoidance mode; and

operate in an omnidirectional transponder mode.

21. The avionics system as defined in claim 18 further comprising an external connector coupled to the processor assembly, whereby the connector is configured to connect to an ARINC 615A portable data loader-compliant computer.

22. The avionics system as defined in claim 18 further comprising an external interface coupled to the backplane, whereby the processor assembly may be reconfigured by:

downloading, through the external interface, modified executable code; and

storing the modified executable code in at least one of the nonvolatile memories.

23. An avionics system comprising:

a software-configurable RF assembly;

a processor assembly coupled to the RF assembly, the processor assembly comprising;

an air traffic avionics processor; and

a terrain avionics processor;

executable air traffic code stored within air traffic avionics processor that when executed by the air traffic avionics processor, implements a function selected from the group of;

determining that an alert should be provided to avoid a mid-air collision; and

performing a transponder function; and

executable terrain warning code stored within the terrain avionics processor that when executed by the terrain avionics processor, determines whether a terrain hazard exists.

24. The avionics system as defined in claim 23 wherein the transponder function is selected from the group consisting of

forming an identity message including a 24-bit address code;

configuring the air traffic avionics processor to enter a listen mode;

determining that an interrogation signal has been received;

formatting a message for ADS-B broadcast;

receiving data regarding a speed parameter, direction parameter, and relative altitude parameter of an aircraft;

obtaining location data regarding an aircraft;

augmenting an identity message with location data; and

combinations thereof.

25. The avionics system as defined in claim 23 wherein the terrain warning code configures the terrain avionics processor to format a warning indicia selected from the group consisting of

excessive rate of descent warning;

excessive closure rate to terrain warning;

altitude loss after takeoff warning;

negative climb rate warning;

flight into terrain when not in landing configuration warning;

excessive downward deviation from glideslope warning;

forward looking terrain avoidance warning;

premature decent alerts; and

combinations thereof.