SYSTEM AND METHOD FOR LOCATION OF AIRCRAFT

• US 20160047880A1
• Filed: 08/03/2015
• Published: 02/18/2016
• Est. Priority Date: 08/14/2014
• Status: Abandoned Application

• Current Assignee: Embry-Riddle Aeronautical University Incorporated
• Original Assignee: Embry-Riddle Aeronautical University Incorporated
• Inventors: Helfrick, Albert D.
• Application Number:
  US14/816,160
• Publication Number:
  US 20160047880A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64D 2045/0065 Black boxes, devices automatically broadcasting distress signals
• CPC Class Codes: G01S 2205/03 Airborne
• CPC Class Codes: G01S 5/0231 Emergency, distress or locator beacons

Abstract

A system and method are provided that includes an aircraft secondary radar transponder activity detector that monitors an aircraft'"'"'s transponder transmissions and activates an emergency locator transmitter to begin transmitting should the aircraft transponder transmissions cease to help locate an aircraft that may have become undetectable by conventional aircraft surveillance and tracking systems.

Claims

1. A system of locating an aircraft in an emergency condition, comprising:

an emergency locator transmitter (ELT) located on board the aircraft; and

an ELT detection/locating system including an interface unit in communication with the ELT, the interface unit includes a transponder activity detector configured to monitor an aircraft transponder transmission signal;

wherein the ELT is directed to transmit a signal configured to be detected by satellite-or terrestrial-based receivers when the transponder activity detector fails to detect an expected transmission signal from the aircraft transponder while the aircraft is in operation.

2. The system of claim 1, wherein the interface unit is powered by a power bus connection to the aircraft.

3. The system of claim 2, wherein the transponder activity detector triggers the ELT to transmit upon detection of cessation of current passing through the power bus, and the transponder activity detector begins receiving power from a short term power source.

4. The system of claim 1, further comprising a rectifier to harvest energy from at least the transmission signal.

5. The system of claim 1, wherein the interface unit of the detection/locating system determines an air/ground status of the aircraft from an on-the-ground switch of the aircraft to determine when a transmission from the transponder is expected.

6. The system of claim 1, wherein the ELT and the ELT detection/locating system are located within a pod.

7. The system of claim 6, further comprising an ejection mechanism configured to automatically separate the pod from the aircraft,

wherein the ELT transmits the signal when separated from the aircraft.

8. The system of claim 7, wherein the ejection mechanism comprises an impact detector to separate the ELT from the aircraft after an impact.

9. The system of claim 7, wherein the ejection mechanism comprises a submersion detector to separate the ELT from the aircraft when the ELT becomes submerged under water.

10. The system of claim 1, wherein the ELT has an antenna configured to transmit an emergency signal;

and

the transponder activity detector has a receiver configured to receive the aircraft transponder transmission signal.

11. A method of initiating an emergency transmission from an aircraft for use in locating or detecting a position of the aircraft, comprising:

monitoring expected transmissions from a Mode-S transponder aboard the aircraft using a transponder activity detector located on the aircraft while the aircraft is in flight;

initiating an active alarm state when the transponder activity detector fails to receive the expected transmission; and

triggering an emergency locator transmitter (ELT) to transmit a signal indicative of an emergency condition from the ELT.

12. The method of claim 11, further comprising powering the transponder activity detector from a power bus of the aircraft.

13. The method of claim 12, further comprising triggering the ELT when current from the power bus ceases.

14. The method of claim 11, further comprising harvesting energy from the transmissions provided by the transponder of the aircraft using a rectifier;

and

storing the harvested energy to extend the operating time of the transponder activity detector and/or the ELT when aircraft power is lost.

15. The method of claim 11, further comprising communicating with an on-the-ground switch of the aircraft and determining if a transmission from the transponder is expected by receipt of an active signal from the on-the-ground switch before triggering the ELT.

16. The method of claim 11, further comprising ejecting the ELT from the aircraft.

17. The method of claim 16, further comprising detecting an impact of the aircraft and ejecting the ELT in response to the impact.

18. The method of claim 16, further comprising detecting a submersion of the aircraft under water, and ejecting the ELT in response to the submersion.

19. The method of claim 11, wherein the signal includes position indication and is transmitted for receipt by the SARSAT network, and

wherein the expected transmission is a data signal sent from an S-mode transponder.

20. The method of claim 11, further comprising:

prohibiting resetting the ELT while the aircraft remains in flight.