Integrated interface architecture and control logic for enhanced emergency location functionality

• US 10,451,743 B2
• Filed: 02/25/2016
• Issued: 10/22/2019
• Est. Priority Date: 02/25/2016
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Adler, Charles O., Murphy, Timothy A., Mitchell, Timothy M.
• Primary Examiner(s): Edwards, Jerrah
• Application Number:
  US15/054,000
• Publication Number:
  US 20170248701A1
• Time in Patent Office: 1,335 Days
• CPC Class Codes: B64D 2045/0065 Black boxes, devices automatically broadcasting distress signals
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64D 45/0059 by communicating emergency situations to ground control or between crew members
• CPC Class Codes: G01S 19/17 Emergency applications
• CPC Class Codes: G01S 5/0231 Emergency, distress or locator beacons

Abstract

Aircraft tracking and emergency location avionics architectures that integrate existing fixed Emergency Locator Transmitter (ELT) installations, their associated aircraft avionics systems and existing flight deck interfaces with an Autonomous Distress Tracker (ADT) transceiver unit in a coupled configuration. Some of the architectures allow the ADT unit and its advanced distress detecting and reporting capabilities to monitor the activation control path for the ELT and the associated ELT activation outputs. Other architectures place the ADT unit and its advanced distress detection capabilities and ground-controlled capabilities in the activation control path for the ELT. Additional architectures entail the connection of an ADT unit to an ELT remote panel on the flight deck of an aircraft.

Claims

1. An ADT unit comprising:

first processing means comprising ELT activation logic; and

an input interface comprising first, second and third terminals and second processing means configured to output an ELT ON state signal to the ELT activation logic if an impedance between the first and third terminals is effectively zero or if an impedance between the first and second terminals is effectively zero.

2. The ADT unit as recited in claim 1, wherein the first and second processing means comprise a common processor.

3. The ADT unit as recited in claim 1, wherein the first processing means comprise a first processor and the second processing means comprises a second processor.

4. The ADT unit as recited in claim 1, wherein the input interface further comprises a high-impedance buffer circuit connected to the first, second and third terminals.

5. The ADT unit as recited in claim 4, wherein the input interface further comprises an analog-to-digital converter between the high-impedance buffer circuit and the second processing means.

6. The ADT unit as recited in claim 1, wherein the first processing means further comprises an aircraft behavior state estimator and ADT trigger logic that receives an estimated aircraft behavior state signal from the aircraft behavior state estimator and the ELT ON state signal from the second processing means, and is configured to send an ELT activation request signal to the ELT activation logic if the estimated aircraft behavior state signal indicates an abnormal or distress state or an ELT ON state signal has been received.

7. A system onboard an aircraft comprising:

an ELT remote panel on the flight deck of the aircraft, the ELT remote panel comprising a switch;

a first antenna that is attached to an exterior of a fuselage skin of the aircraft; and

an ADT unit connected to the first antenna and comprising;

first processing means comprising ELT activation logic; and

a first input interface comprising first, second and third terminals, and second processing means configured to output an ELT ON state signal to the ELT activation logic if an impedance between the first and third terminals is effectively zero or if an impedance between the first and second terminals is effectively zero,

wherein the switch of the ELT remote panel is connected to the first terminal of the first input interface by wiring.

8. The system as recited in claim 7, wherein the first and second processing means comprise a common processor.

9. The system as recited in claim 7, wherein the first processing means comprise a first processor and the second processing means comprises a second processor.

10. The system as recited in claim 7, wherein the switch of the ELT remote panel is not connected to either of the second and third terminals of the first input interface and the third terminal of the first input interface is connected to ground.

11. The system as recited in claim 7, wherein the switch of the ELT remote panel is also connected to the second terminal of the first input interface by wiring.

12. The system as recited in claim 7, wherein the first input interface of the ADT unit further comprises:

a high-impedance buffer circuit connected to the first, second and third terminals; and

an analog-to-digital converter between the high-impedance buffer circuit and the second processing means.

13. The system as recited in claim 7, further comprising:

a second antenna that is attached to an exterior of a fuselage skin of the aircraft; and

an ELT unit connected to the second antenna and to the ADT unit.

14. The system as recited in claim 13, wherein the ELT unit is also connected to the switch of the ELT remote panel.

15. The system as recited in claim 13, wherein the ADT unit further comprises a first output interface that comprises a terminal connected to the ELT unit and third processing means configured to output an ELT ON state signal to the terminal of the first output interface in response to receipt of an ELT ON state signal from the ELT activation logic.

16. The system as recited in claim 15, wherein the ELT activation logic comprises trigger activation filtering logic and trigger activation input pass-through logic configured to apply the ELT ON state signal to the terminal of the first output interface subject to the trigger activation filtering logic.

17. The system as recited in claim 13, wherein the first processing means further comprises an aircraft behavior state estimator and trigger logic that receives an estimated aircraft behavior state signal from the aircraft behavior state estimator and the ELT ON state signal from the second processing means, the trigger logic being configured to send an ELT activation request signal to the ELT activation logic if the estimated aircraft behavior state signal indicates an abnormal or distress state or an ELT ON state signal has been received.

18. The system as recited in claim 17, wherein the ELT activation logic comprises crew activation filtering logic and crew activation input pass-through logic configured to apply the ELT ON state signal from the second processing means to the terminal of the first output interface subject to the crew activation filtering logic.

19. The system as recited in claim 13, further comprising an aircraft avionics system, wherein the ADT unit further comprises a second input interface and a second output interface connected to the aircraft avionics system by wiring.