Method and apparatus for an avionics system utilizing both ARINC 429 and ARINC 629 compliant systems

• US 5,805,828 A
• Filed: 09/17/1996
• Issued: 09/08/1998
• Est. Priority Date: 05/14/1996
• Status: Expired due to Fees

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Lee, Stephen Y., Deloe, Derek E., Sherwin, Greg J., Drake, Jeffrey K.
• Primary Examiner(s): Rinehart, Mark H.
• Application Number:
  US08/710,448
• Time in Patent Office: 721 Days
• Field of Search: 395/200.8, 395/200.79, 395/200.76, 395/281, 395/306, 395/308, 395/309, 395/311, 370/402, 370/462, 370/463
• US Class Current: 709/249
• CPC Class Codes: G06F 13/4027 using bus bridges G06F13/4022 takes precedence

Abstract

An aircraft avionics system utilizes ARINC 429 compliant equipment, connected to one or more ARINC 429 data buses, and ARINC 629 equipment, coupled to one or more ARINC 629 data buses. Communication between the ARINC 429 and ARINC 629 equipment is facilitated by a data conversion gateway function (DCGF) system. The DCGF transforms ARINC 429 signals on one ARINC 429 bus for transmission over a second ARINC 429 bus, or over one or more ARINC 629 buses. The DCGF also transforms ARINC 629 signals on one ARINC 629 bus for transmission over a second ARINC 629 bus, or over one or more ARINC 429 buses.

Claims

1. An aircraft avionics system utilizing Aeronautical Radio, Inc. (ARINC) standard equipment comprising:

an ARINC 429 compliant data bus;

at least one ARINC 429 compliant avionics system coupled to said ARINC 429 bus;

an ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said ARINC 629 data bus; and

a data conversion gateway function (DCGF) system including logic means for converting a signal produced by said ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said ARINC 629 data bus to said ARINC 629 compliant avionics system.

2. The aircraft avionics system of claim 1, wherein said DCGF logic means further comprises means for converting a signal produced by said ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said ARINC 429 data bus to said ARINC 429 compliant avionics system.

3. The aircraft avionics system of claim 1 further comprising:

a second ARINC 429 compliant data bus;

at least one ARINC 429 compliant avionics system coupled to said second ARINC 429 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said second ARINC 429 data bus to said at least one ARINC 429 system coupled thereto.

4. The aircraft avionics system of claim 2 further comprising:

a second ARINC 429 compliant data bus;

at least one ARINC 429 compliant avionics system coupled to said second ARINC 429 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said second ARINC 429 data bus to said at least one ARINC 429 system coupled thereto.

5. The aircraft avionics system of claim 1 further comprising:

a second ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

6. The aircraft avionics system of claim 2 further comprising:

a second ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

7. The aircraft avionics system of claim 3 further comprising:

a second ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

8. The aircraft avionics system of claim 4 further comprising:

a second ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

9. An aircraft avionics system utilizing Aeronautical Radio, Inc. (ARINC) standard equipment comprising:

an ARINC 429 compliant data bus;

at least one ARINC 429 compliant avionics system coupled to said ARINC 429 bus;

an ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said ARINC 629 data bus; and

a data conversion gateway function (DCGF) system including logic means for converting a signal produced by said ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said ARINC 429 data bus to said ARINC 429 compliant avionics system.

10. The aircraft avionics system of claim 9, wherein said DCGF logic means further comprises means for converting a signal produced by said ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said ARINC 629 data bus to said ARINC 629 compliant avionics system.

11. The aircraft avionics system of claim 9 further comprising:

a second ARINC 429 compliant data bus;

at least one ARINC 429 compliant avionics system coupled to said second ARINC 429 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said second ARINC 429 data bus to said at least one ARINC 429 system coupled thereto.

12. The aircraft avionics system of claim 10 further comprising:

a second ARINC 429 compliant data bus;

at least one ARINC 429 compliant avionics system coupled to said second ARINC 429 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said second ARINC 429 data bus to said at least one ARINC 429 system coupled thereto.

13. The aircraft avionics system of claim 9 further comprising:

a second ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

14. The aircraft avionics system of claim 10 further comprising:

a second ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

15. The aircraft avionics system of claim 11 further comprising:

a second ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

16. The aircraft avionics system of claim 12 further comprising:

a second ARINC 629 compliant data bus;

at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

said DCGF system logic means further comprising means for converting a signal produced by said at least one ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

17. In an aircraft avionics system utilizing Aeronautical Radio, Inc. (ARINC) standard 429 and 629 compliant equipment, a method for providing communication among such equipment comprising the steps of:

providing an ARINC 429 compliant data bus;

providing at least one ARINC 429 compliant avionics system coupled to said ARINC 429 data bus;

providing an ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said ARINC 629 data bus; and

providing a data conversion gateway function (DCGF) system including logic means for performing the step of converting a signal produced by said ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said ARINC 629 data bus to said ARINC 629 compliant avionics system.

18. The aircraft avionics system of claim 17 wherein said DCGF logic means further performs the step of converting a signal produced by said ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said ARINC 429 data bus to said ARINC 429 compliant avionics system.

19. The method of claim 17 including the further steps of:

providing a second ARINC 429 compliant data bus;

providing at least one ARINC 429 compliant avionics system coupled to said second ARINC 429 data bus; and

said DCGF system logic means further performing the step of converting a signal produced by said at least one ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said second ARINC 429 data bus to said at least one ARINC 429 system coupled thereto.

20. The method of claim 18 including the further steps of:

providing a second ARINC 429 compliant data bus;

providing at least one ARINC 429 compliant avionics system coupled to said second ARINC 429 data bus; and

said DCGF system logic means further performing the step of converting a signal produced by said at least one ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said second ARINC 429 data bus to said at least one ARINC 429 system coupled thereto.

21. The method of claim 17 comprising the furthers steps of:

providing a second ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

wherein said DCGF system logic performs the further step of converting a signal produced by said at least one ARINC compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

22. The method of claim 18 comprising the furthers steps of:

providing a second ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

wherein said DCGF system logic performs the further step of converting a signal produced by said at least one ARINC compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

23. The method of claim 19 comprising the furthers steps of:

providing a second ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

wherein said DCGF system logic performs the further step of converting a signal produced by said at least one ARINC compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

24. The method of claim 20 comprising the furthers steps of:

providing a second ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

wherein said DCGF system logic performs the further step of converting a signal produced by said at least one ARINC compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

25. In an aircraft avionics system utilizing Aeronautical Radio, Inc. (ARINC) standard 429 and 629 compliant equipment, a method for providing communication among such equipment comprising the steps of:

providing an ARINC 429 compliant data bus;

providing at least one ARINC 429 compliant avionics system coupled to said ARINC 429 data bus;

providing an ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said ARINC 629 data bus; and

providing a data conversion gateway function (DCGF) system including logic means for performing the step of;

converting a signal produced by said ARINC 629 compliant avionics system on said ARINC 629 data bus for transmission over said ARINC 429 data bus to said ARINC 429 compliant avionics system.

26. The method of claim 25 wherein said DCGF logic means performs the further step of converting a signal produced by said ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said ARINC 629 data bus to said ARINC 629 compliant avionics system.

27. The method of claim 25 comprising the further steps of:

providing a second ARINC 429 compliant data bus;

providing at least one ARINC 429 compliant avionics system coupled to said second ARINC 429 data bus; and

said DCGF system logic means further performing the step of converting a signal produced by said at least one ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said second ARINC 429 data bus to said at least one ARINC 429 system coupled thereto.

28. The method of claim 26 comprising the further steps of:

providing a second ARINC 429 compliant data bus;

providing at least one ARINC 429 compliant avionics system coupled to said second ARINC 429 data bus; and

said DCGF system logic means further performing the step of converting a signal produced by said at least one ARINC 429 compliant avionics system on said ARINC 429 data bus for transmission over said second ARINC 429 data bus to said at least one ARINC 429 system coupled thereto.

29. The method of claim 25 including the further steps of:

providing a second ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

wherein said DCGF system logic means performs the further step of converting a signal produced by said at least one ARINC compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

30. The method of claim 26 including the further steps of:

providing a second ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

wherein said DCGF system logic means performs the further step of converting a signal produced by said at least one ARINC compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

31. The method of claim 27 including the further steps of:

providing a second ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

wherein said DCGF system logic means performs the further step of converting a signal produced by said at least one ARINC compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.

32. The method of claim 28 including the further steps of:

providing a second ARINC 629 compliant data bus;

providing at least one ARINC 629 compliant avionics system coupled to said second ARINC 629 data bus; and

wherein said DCGF system logic means performs the further step of converting a signal produced by said at least one ARINC compliant avionics system on said ARINC 629 data bus for transmission over said second ARINC 629 data bus to said at least one ARINC 629 system coupled thereto.