Aircraft Tracking Method and Device and Method of Installation

• US 20170052258A1
• Filed: 08/21/2015
• Published: 02/23/2017
• Est. Priority Date: 08/21/2015
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Murphy, Timothy Allen
• Granted Patent: US 9,964,646 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: G01S 19/14 specially adapted for specific applications
• CPC Class Codes: G01S 19/17 Emergency applications
• CPC Class Codes: G01S 19/24 Acquisition or tracking or demodulation of signals transmitted by the system synchronisation aspects of direct sequence spread spectrum modulation H04B1/7073
• CPC Class Codes: G01S 19/34 Power consumption
• CPC Class Codes: G01S 19/35 Constructional details or hardware or software details of the signal processing chain
• CPC Class Codes: G01S 19/42 Determining position
• CPC Class Codes: G01S 5/0027 of actual mobile position, i.e. position determined on mobile
• CPC Class Codes: G08G 5/0013 with a ground station
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/0056 in an emergency situation, e.g. hijacking
• CPC Class Codes: G08G 5/0082 for monitoring traffic from a ground station radar or analogous systems specially adapted for traffic control G01S13/91

Abstract

A method and apparatus for tracking the position of an aircraft. A tracking device comprises a satellite navigation system receiver, a satellite communications transceiver, and a processor hermetically sealed within a housing attached on an outside of the aircraft. The satellite navigation system receiver is used to identify the position of the aircraft using navigation signals received from a satellite navigation system. The processor generates position information identifying the position of the aircraft as identified using the navigation system receiver. The processor sends the position information to a receiving station via a communications satellite in a low Earth orbit using the satellite communications transceiver. The position information is automatically generated by the processor and sent to the receiving station at a desired rate.

Claims

1. An apparatus comprising:

a satellite navigation system receiver configured to identify a position of an aircraft using navigation signals received from a satellite navigation system;

a satellite communications transceiver;

a number of antennas for the satellite navigation system receiver and the satellite communications transceiver;

a processor configured to generate position information identifying the position of the aircraft as identified by the satellite navigation system receiver and send the position information to a receiving station via a communications satellite in a low Earth orbit using the satellite communications transceiver, wherein the processor is configured to generate and send the position information automatically at a rate; and

a housing attached to the aircraft on an outside of the aircraft, wherein the satellite navigation system receiver, the satellite communications transceiver, the number of antennas, and the processor are hermetically sealed within the housing.

2. The apparatus of claim 1, wherein a footprint of the apparatus on the outside of the aircraft matches a footprint on the outside of the aircraft of an antenna for an emergency locator transmitter that was removed from the aircraft.

3. The apparatus of claim 1, wherein:

an only electrical connection between an interior of the housing attached to the aircraft on the outside of the aircraft and an inside of the aircraft consists of a power line connecting the interior of the housing to a power source on the inside of the aircraft; and

further comprising a battery contained within the housing and configured to provide backup power for the apparatus when power for the apparatus from the power source on the inside of the aircraft is lost.

4. The apparatus of claim 1, wherein the number of antennas comprise:

a satellite navigation system receiver antenna for the satellite navigation system receiver and a satellite communications antenna for the satellite communications transceiver.

5. The apparatus of claim 1, wherein:

the satellite navigation system receiver is configured to receive the navigation signals from satellites in the satellite navigation system selected from the group of satellite navigation systems consisting of a Global Positioning System and a Global Navigation Satellite System; and

the satellite communications transceiver is configured to send the position information to the receiving station via an Iridium communications satellite.

6. The apparatus of claim 1, wherein the processor is further configured to:

receive instructions via the satellite communications transceiver; and

change the rate at which the position information is generated and sent to the receiving station in response to receiving the instructions.

7. The apparatus of claim 1 further comprising:

a distress identifier configured to identify when the aircraft is in distress; and

wherein the processor is configured to increase the rate at which the position information is generated and sent to the receiving station in response to the distress identifier identifying that the aircraft is in distress.

8. The apparatus of claim 1 further comprising:

a distress identifier configured to identify when the aircraft is in distress; and

wherein the processor is configured to generate and send an alert indicating that the aircraft is in distress to the receiving station via the communications satellite using the satellite communications transceiver in response to the distress identifier identifying that the aircraft is in distress.

9. A method of tracking a position of an aircraft, comprising:

identifying, using a satellite navigation system receiver, the position of the aircraft using navigation signals received from a satellite navigation system;

generating, by a processor, position information identifying the position of the aircraft as identified using the satellite navigation system receiver;

sending, by the processor, the position information to a receiving station via a communications satellite in a low Earth orbit using a satellite communications transceiver;

wherein the processor generates and sends the position information automatically at a rate; and

wherein the satellite navigation system receiver, the processor, and the satellite communications transceiver are hermetically sealed within a housing attached to the aircraft on an outside of the aircraft.

10. The method of claim 9, wherein:

an only electrical connection between an interior of the housing attached to the aircraft on the outside of the aircraft and an inside of the aircraft consists of a power line connected to a power source on the inside of the aircraft; and

further comprising providing backup power from a battery contained within the housing when power from the power source on the inside of the aircraft is lost.

11. The method of claim 9 further comprising:

a satellite navigation system receiver antenna for the satellite navigation system receiver and a satellite communications antenna for the satellite communications transceiver contained within the housing.

12. The method of claim 9, wherein:

the navigation signals are received from the satellite navigation system selected from the group of satellite navigation systems consisting of a Global Positioning System and a Global Navigation Satellite System; and

the position information is sent to the receiving station via an Iridium communications satellite.

13. The method of claim 9 further comprising:

receiving instructions, by the processor, via the satellite communications transceiver; and

changing the rate at which the position information is generated and sent to the receiving station in response to receiving the instructions by the processor.

14. The method of claim 9 further comprising:

identifying when the aircraft is in distress; and

increasing the rate at which the position information is generated and sent to the receiving station in response to identifying that the aircraft is in distress.

15. The method of claim 9 further comprising:

identifying when the aircraft is in distress; and

generating an alert indicating that the aircraft is in distress and sending the alert to the receiving station via the communications satellite using the satellite communications transceiver in response to identifying that the aircraft is in distress.

16. A method of attaching a tamper-proof tracking device to an aircraft, comprising:

removing an antenna for an emergency locator transmitter from a location on a skin of the aircraft where the antenna for the emergency locator transmitter is attached to the skin of the aircraft; and

attaching the tamper-proof tracking device to the skin of the aircraft at the location on the skin of the aircraft where the antenna for the emergency locator transmitter was attached to the skin of the aircraft, wherein the tamper-proof tracking device comprises;

a satellite navigation system receiver configured to identify a position of the aircraft using navigation signals received from a satellite navigation system;

a satellite communications transceiver;

a number of antennas for the satellite navigation system receiver and the satellite communications transceiver;

a processor configured to generate position information identifying the position of the aircraft as identified by the satellite navigation system receiver and send the position information to a receiving station via a communications satellite in a low Earth orbit using the satellite communications transceiver; and

a housing containing the satellite navigation system receiver, the satellite communications transceiver, the number of antennas, and the processor, wherein the satellite navigation system receiver, the satellite communications transceiver, the number of antennas, and the processor are hermetically sealed within the housing.

17. The method of claim 16, wherein attaching the tamper-proof tracking device to the skin of the aircraft comprises:

attaching the tamper-proof tracking device to the skin of the aircraft such that a footprint of the tamper-proof tracking device on the skin of the aircraft matches a footprint of the antenna for the emergency locator transmitter on the skin of the aircraft.

18. The method of claim 16, wherein attaching the tamper-proof tracking device to the skin of the aircraft comprises:

attaching a base plate to the skin of the aircraft in a footprint on the skin of the aircraft where the antenna for the emergency locator transmitter was attached to the skin of the aircraft; and

attaching the housing to the base plate.

19. The method of claim 16, wherein attaching the tamper-proof tracking device to the skin of the aircraft comprises:

attaching an electromagnetic interference shielding gasket between the tamper-proof tracking device and the skin of the aircraft.

20. The method of claim 16 further comprising:

extending a power line from the tamper-proof tracking device to a power source on an inside of the aircraft via a through hole in the skin of the aircraft, wherein the power line comprises an only electrical connection between the tamper-proof tracking device attached to the skin of the aircraft and the inside of the aircraft.