Emergency locator transmitter activation device for enhanced emergency location performance

• US 10,450,084 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: Murphy, Timothy A., Adler, Charles O., Khalil, Fadl I.
• Primary Examiner(s): Nguyen, Chuong P
• Application Number:
  US15/053,982
• Publication Number:
  US 20170248676A1
• Time in Patent Office: 1,335 Days
• Field of Search: 342385, 34235755, 340981
• 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: G01S 1/08 Systems for determining direction or position line
• CPC Class Codes: G01S 1/68 Marker, boundary, call-sign, or like beacons transmitting signals not carrying directional information
• CPC Class Codes: G01S 19/17 Emergency applications
• CPC Class Codes: G01S 5/0231 Emergency, distress or locator beacons

Abstract

An aircraft avionics unit that enhances the emergency location capability of existing Emergency Locator Transmitters (ELTs). This aircraft avionics unit can be integrated with a wide range of existing ELTs and their existing aircraft interfaces by changes to a small number of the signal wires between the ELT and the aircraft systems and the addition of limited inputs from aircraft systems. This system requires no changes to either the current ELTs or the associated aircraft systems. The integrated system maintains the current ELT concept of operations while providing significantly enhanced ELT activation triggering with a low-impact, low-cost approach.

Claims

1. A system onboard an aircraft comprising:

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

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

an emergency locator transmitter connected to the antenna; and

an activation/trigger device connected to the switch of the ELT remote panel and to the emergency locator transmitter,

wherein the emergency locator transmitter is also connected to the switch of the ELT remote panel;

wherein the activation/trigger device comprises a common ELT crew activation input interface, ELT activation logic configured to process inputs received from the common ELT crew activation input interface, and a common ELT crew activation output interface comprising first, second and third terminals and a switch;

wherein the first terminal of the common ELT crew activation output interface is connected to the emergency locator transmitter and the third terminal of the common ELT crew activation output interface is connected to ground;

wherein the switch has an input terminal connected to the second and third terminals, an ARM terminal and an ON terminal connected to the first terminal, the switch being switchable between a first switch state wherein the input terminal is electrically connected to the ARM terminal and a second state wherein the ON terminal is electrically connected to the input terminal; and

wherein the state of the switch is controlled by the ELT activation logic.

2. The system as recited in claim 1, further comprising an aircraft avionics system connected to the activation/trigger device.

3. The system as recited in claim 2, wherein the ELT activation logic is further configured to determine, based on inputs from aircraft avionics systems and ELT crew activation inputs from the switch of the ELT remote panel, whether an ELT activation signal should be sent to the emergency locator transmitter or not.

4. The system as recited in claim 3, wherein the inputs from the output data port of the aircraft avionics system comprise aircraft discrete inputs.

5. The system as recited in claim 3, wherein the inputs from the output data port of the aircraft avionics system comprise aircraft navigation inputs.

6. The system as recited in claim 1, wherein the first terminal is connected to an ELT External On line and the second terminal is connected to an ELT Common line.

7. The system as recited in claim 1, wherein the common ELT crew activation input interface comprises fourth, fifth and sixth terminals and a processor configured to output an ELT ON state signal to the ELT activation logic if an impedance between the fourth and sixth terminals is effectively zero or if an impedance between the fourth and fifth terminals is effectively zero.

8. A system onboard an aircraft comprising:

a manually operable switch incorporated in an ELT remote panel;

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

an emergency locator transmitter having a radio frequency signal port connected to the antenna; and

an activation/trigger device connected to the switch of the ELT remote panel by wiring and connected to the emergency locator transmitter by wiring,

wherein the emergency locator transmitter is also connected to the switch of the ELT remote panel by wiring;

wherein the activation/trigger device comprises a common ELT crew activation input interface, ELT activation logic configured to process inputs received from the common ELT crew activation input interface, and a common ELT crew activation output interface comprising first, second and third terminals and a switch;

wherein the first terminal of the common ELT crew activation output interface is connected to the emergency locator transmitter and the third terminal of the common ELT crew activation output interface is connected to ground;

wherein the switch has an input terminal connected to the second and third terminals, an ARM terminal and an ON terminal connected to the first terminal, the switch being switchable between a first switch state wherein the input terminal is electrically connected to the ARM terminal and a second state wherein the ON terminal is electrically connected to the input terminal; and

wherein the state of the switch is controlled by the ELT activation logic.

9. The system as recited in claim 8, further comprising an aircraft avionics system connected to the activation/trigger device.

10. The system as recited in claim 9, wherein the ELT activation logic is further configured to determine, based on inputs from aircraft avionics systems and ELT crew activation inputs from the switch of the ELT remote panel, whether an ELT activation signal should be sent to the emergency locator transmitter or not.

11. The system as recited in claim 8, wherein the first terminal is connected to an ELT External On line and the second terminal is connected to an ELT Common line.

12. The system as recited in claim 8, wherein the common ELT crew activation input interface comprises fourth, fifth and sixth terminals and a processor configured to output an ELT ON state signal to the ELT activation logic if an impedance between the fourth and sixth terminals is effectively zero or if an impedance between the fourth and fifth terminals is effectively zero.

13. An emergency locator transmitter (ELT) activation/trigger device 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.

14. The ELT activation/trigger device as recited in claim 13, wherein the input interface 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.

15. The ELT activation/trigger device 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, 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.

16. The ELT activation/trigger device as recited in claim 13, further comprising an output interface comprising fourth, fifth and sixth terminals and a switch, wherein the switch has an input terminal connected to the fifth and sixth terminals, an ARM terminal, and an ON terminal connected to the fourth terminal, the switch being switchable between a first switch state wherein the input terminal is electrically connected to the ARM terminal and a second state wherein the ON terminal is electrically connected to the input terminal, the state of the switch being controlled by the ELT activation logic.