System and method for TCAS based navigation

• US 8,952,841 B1
• Filed: 01/13/2012
• Issued: 02/10/2015
• Est. Priority Date: 01/13/2012
• Status: Active Grant

• Current Assignee: Rockwell Collins, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Rockwell Collins, Inc. (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Billsberry, Mark A., Ellery, Phillip L.
• Primary Examiner(s): GREGORY, BERNARR E
• Application Number:
  US13/349,975
• Time in Patent Office: 1,124 Days
• Field of Search: 342 29- 40, 342/59, 342/118, 342120-122, 342 25 R- 25 F, 342 73- 76, 342/104, 342/107, 342/117, 342/165, 342173-175, 342/195, 342/350, 342/385, 342/417, 342/442, 342/450, 342/454, 342/455, 342/105, 342/106, 342108-116, 342146-157
• US Class Current: 342/107
• CPC Class Codes: G01S 13/60 wherein the transmitter and receiver are mounted on the moving object, e.g. for determining ground speed, drift angle, ground track G01S13/64 takes precedence
• CPC Class Codes: G01S 13/872 Combinations of primary radar and secondary radar
• CPC Class Codes: G01S 13/933 of aircraft or spacecraft

Abstract

A traffic collision avoidance system (TCAS) based navigation system including a TCAS equipped with a directional antenna, the TCAS configured to generate a RF transmission pattern at a selected frequency, the transmission pattern including a plurality of directional beams, receive a plurality of RF signals reflected from the ground across a selected frequency band, the selected frequency band including the selected frequency, and measure frequency differences between one or more beams of the plurality of RF beams and one or more beams of the plurality of RF signals reflected from the ground, and a computing systems in communication with the TCAS, the computing system configured to calculate a ground speed of the aircraft utilizing the measured frequency differences, calculate a drift angle of the aircraft utilizing the measured plurality of frequency differences, receive a heading reference of the aircraft, and determine an aircraft navigation parameter of the aircraft.

Claims

1. A traffic collision avoidance system based navigation system, comprising:

a traffic collision avoidance system (TCAS) associated with an aircraft, the TCAS including one or more directional antennas, the TCAS configured to;

generate a radio frequency (RF) transmission pattern at a selected frequency, the transmission pattern including a plurality of RF beams, each RF beam being directed to a different region of the ground;

receive a plurality of RF signals reflected from the ground across a selected frequency band, the selected frequency band including the selected frequency; and

measure a plurality of frequency differences, the plurality of frequency differences including at least a frequency difference between each of the plurality of RF beams and the plurality of reflected RF signals; and

one or more computing systems in communication with the TCAS, the one or more computing systems configured to;

calculate a ground speed of the aircraft utilizing one or more of the measured plurality of frequency differences;

calculate a drift angle of the aircraft utilizing one or more of the measured plurality of frequency differences;

receive a heading reference of the aircraft; and

determine one or more aircraft navigation parameters of the aircraft utilizing at least one of the calculated ground speed of the aircraft, the calculated drift angle of the aircraft, or the received heading reference of the aircraft.

2. The system of claim 1, wherein the plurality of RF beams of the generated transmission pattern includes at least a first RF beam having a first angle of transmission, a second RF beam having a second angle of transmission, a third RF beam having a third angle of transmission, and a fourth RF beam having a fourth angle of transmission, the first angle of transmission, the second angle of transmission, the third angle of transmission, and the fourth angle of transmission being measured relative to a center line of the aircraft.

3. The system of claim 2, wherein each of the first angle of transmission, the second angle of transmission, the third angle of transmission, and the fourth angle of transmission are oriented at substantially 45°

relative to the center line of the aircraft.

4. The system of claim 1, wherein the one or more directional antennas of the TCAS are configured to transmit a plurality of RF beams at a frequency within the L-band.

5. The system of claim 4, wherein the one or more directional antennas of the TCAS are configured to transmit a plurality of RF beams at substantially 1030 MHz.

6. The system of claim 1, wherein the one or more directional antennas of the TCAS are configured to receive a plurality of RF signals reflected from the ground across a selected frequency band within the L-band, the selected frequency band including the selected frequency.

7. The system of claim 6, wherein the one or more directional antennas of the TCAS are configured to receive a plurality of RF signals reflected from the ground across a selected frequency band, the selected frequency band including a frequency of 1030 MHz.

8. A traffic collision avoidance system based navigation system, comprising:

a traffic collision avoidance system (TCAS) associated with an aircraft, the TCAS including one or more directional antennas, the TCAS configured to;

generate a radio frequency (RF) transmission pattern at a selected frequency, the transmission pattern including at least a first RF beam transmitted along a first direction toward a first region of the ground, a second RF beam transmitted along a second direction toward a second region of the ground, a third RF beam transmitted along a third direction toward a third region of the ground, and a fourth RF beam transmitted along a fourth direction toward a fourth region of the ground;

receive a plurality of RF signals reflected from the ground across a selected frequency band, the selected frequency band including the selected frequency, the plurality of reflected RF signals including a first RF signal reflected from the first region of the ground toward the TCAS along the first direction, a second RF signal reflected from the second region of the ground toward the TCAS along the second direction, a third RF signal reflected from the third region of the ground toward the TCAS along the third direction, and a fourth RF signal reflected from the fourth region of the ground toward the TCAS along the fourth direction; and

measure a plurality of frequency differences, the plurality of frequency differences including at least a frequency difference between the first transmitted RF beam and the first reflected RF signal, a frequency difference between the second transmitted RF beam and the first reflected RF signal, a frequency difference between the third transmitted RF beam and the third reflected RF signal, and a frequency difference between the fourth transmitted RF beam and the fourth reflected RF signal; and

one or more computing systems in communication with the TCAS, the one or more computing systems configured to;

calculate a ground speed of the aircraft utilizing one or more of the measured plurality of frequency differences;

calculate a drift angle of the aircraft utilizing one or more of the measured plurality of frequency differences;

receive a heading reference of the aircraft; and

determine one or more aircraft navigation parameters of the aircraft utilizing at least one of the calculated ground speed of the aircraft, the calculated drift angle of the aircraft, or the received heading reference of the aircraft.

9. The system of claim 8, wherein the generated transmission pattern includes at least a first RF beam having a first angle of transmission, a second RF beam having a second angle of transmission, a third RF beam having a third angle of transmission, and a fourth RF beam having a fourth angle of transmission, the first angle of transmission, the second angle of transmission, the third angle of transmission, and the fourth angle of transmission being measured relative to a center line of the aircraft.

10. The system of claim 9, wherein each of the first angle of transmission, the second angle of transmission, the third angle of transmission, and the fourth angle of transmission are oriented at substantially 45°

relative to the center line of the aircraft.

11. The system of claim 8, wherein at least one of the plurality of frequency differences measured by the TCAS comprises:

at least one of a front-left frequency difference defined by the frequency difference between a forward-left beam transmitted along a forward-left direction of the aircraft and an RF signal reflected by the ground toward the TCAS along the forward-left direction of the aircraft, a front-right frequency difference defined by the difference between forward-right beam transmitted along a forward-right direction of the aircraft and an RF signal reflected by the ground toward the TCAS along the forward-right direction of the aircraft, an aft-left frequency difference defined by the difference between an aft-left beam transmitted along an aft-left direction of the aircraft and an RF signal reflected by the ground toward the TCAS along the aft-left direction of the aircraft, or an aft-right frequency difference defined by a frequency difference between an aft-right beam transmitted along an aft-right direction of the aircraft and an RF signal reflected by the ground toward the TCAS along the aft-right direction of the aircraft.

12. The system of claim 11, wherein the one or more computing systems are configured to calculate the ground speed of the aircraft utilizing at least one of the front-left frequency difference, the front-right frequency difference, the aft-left frequency difference or the aft-right frequency difference.

13. The system of claim 11, wherein the one or more computing systems are configured to calculate the drift angle of the aircraft utilizing at least one of the front-left frequency difference, the front-right frequency difference, the aft-left frequency difference or the aft-right frequency difference.

14. The system of claim 8, wherein the one or more aircraft navigation parameters of the aircraft comprise:

at least one of a present position of the aircraft, a course of the aircraft, and a distance to destination of the aircraft.

15. The system of claim 8, wherein the TCAS is configured to provide Barker encoded differential phase shift keying (DPSK) within at least one of the first transmitted RF beam, the second transmitted RF beam, the third transmitted RF beam, or the fourth transmitted RF beam.

16. The system of claim 15, wherein the TCAS is configured to encode a signal of at least one of the first transmitted RF beam, the second transmitted RF beam, the third transmitted RF beam, or the fourth transmitted RF beam with a miscalculated cyclic redundancy code (CRC).

17. The system of claim 8, wherein the TCAS is configured to filter the plurality of reflected signals utilizing a bearing of return for each of the reflect signals.

18. A method of traffic collision avoidance system (TCAS) based navigation of an aircraft, comprising:

generating a TCAS radio frequency (RF) transmission pattern including a plurality of transmitted TCAS RF beams, each of the RF beams transmitted at a selected frequency, each of the transmitted TCAS RF beams directed toward a different region of the ground;

receiving a plurality of TCAS RF signals reflected from the ground across a selected frequency band, the selected frequency band including the selected frequency;

measuring a plurality of frequency differences, the plurality of frequency differences including at least a frequency difference between a first transmitted TCAS RF beam and a first reflected TCAS RF signal, a frequency difference between a second transmitted TCAS RF beam and a second reflected TCAS RF signal, a frequency difference between a third transmitted TCAS RF beam and a third reflected TCAS RF signal, and a frequency difference between a fourth transmitted TCAS RF beam and a fourth reflected TCAS RF signal;

calculating a ground speed of the aircraft utilizing one or more of the measured plurality of frequency differences;

calculating a drift angle of the aircraft utilizing one or more of the measured plurality of frequency differences;

receiving a heading reference of the aircraft; and

determining one or more aircraft navigation parameters of the aircraft utilizing at least one of the calculated ground speed of the aircraft, the calculated drift angle of the aircraft, or the received heading reference of the aircraft.

19. The method of claim 18, wherein the generating a TCAS radio frequency (RF) transmission pattern including a plurality of transmitted TCAS RF beams comprises:

generating a TCAS RF transmission pattern including at least a first TCAS RF beam transmitted along a first direction toward a first region of the ground, a second TCAS RF beam transmitted along a second direction toward a second region of the ground, a third TCAS RF beam transmitted along a third direction toward a third region of the ground, and a fourth TCAS RF beam transmitted along a fourth direction toward a fourth region of the ground.

20. The method of claim 18, wherein the receiving a plurality of TCAS RF signals reflected from the ground comprises:

receiving at least a first TCAS RF signal reflected from a first region of the ground along a first direction, a second TCAS RF signal reflected from a second region of the ground along a second direction, a third RF signal reflected from a third region of the ground toward along a third direction, and a fourth RF signal reflected from a fourth region of the ground along a fourth direction.

21. The method of claim 18, wherein the measuring a plurality of frequency differences comprises:

measuring at least one of a front-left frequency difference defined by a frequency difference between a forward-left beam transmitted along a forward-left direction of the aircraft and an RF signal reflected by the ground toward along the forward-left direction of the aircraft, a front-right frequency difference defined by a difference between a forward-right beam transmitted along a forward-right direction of the aircraft and an RF signal reflected by the ground along the forward-right direction of the aircraft, an aft-left frequency difference defined by a difference between an aft-left beam transmitted along an aft-left direction of the aircraft and an RF signal reflected by the ground along the aft-left direction of the aircraft, or an aft-right frequency difference defined by a frequency difference between an aft-right beam transmitted along an aft-right direction of the aircraft and an RF signal reflected by the ground along the aft-right direction of the aircraft.