Inference and interpolation of continuous 4D trajectories

1. A method of updating a flight plan of an aircraft ( 702 ), the method comprising:

detecting ( 502 ) a plurality of aircraft states ( 102 ) of the aircraft ( 702 ), each aircraft state ( 102 ) comprising a latitude value, a longitude value, an altitude value, and a time value, whereby the plurality of states ( 102 ) of the aircraft are stored in electronic memory ( 712 ) in temporal order;

determining ( 504 ), for each of a plurality of pairs of adjacent aircraft states ( 102 ), a respective aircraft transition ( 104 ), each transition comprising a planar turn radius ( 208 ) value, a vertical turn radius ( 218 ) value, and an acceleration ( 230 ) value, whereby a plurality of aircraft transitions ( 104 ) are stored in electronic memory ( 712 ) in temporal order;

detecting ( 506 ) a plurality of pairs of repeat adjacent aircraft transitions ( 104 ) comprising: respective planar turn radii ( 208 ) values whose difference is no more than a first threshold, respective vertical turn radii ( 218 ) values whose difference is no more than a second threshold, and respective acceleration ( 230 ) values whose difference is no more than a third threshold;

discarding ( 506 ), for each pair of repeat adjacent aircraft transitions, a respective aircraft state ( 104 ) from the plurality of aircraft states ( 104 ), whereby an amount of data for the plurality of states of the aircraft stored in electronic memory ( 712 ) is reduced;

electronically transmitting ( 508 ) from a first aircraft ( 792 ) system to a Flight Management System (FMS) the plurality of aircraft states ( 104 ) after the discarding; and

updating, by the FMS, a flight plan for the aircraft ( 702 ) to represent at least a portion of a trajectory interpolated from the plurality of aircraft states ( 104 ), whereby an updated flight plan is produced.

2. The method of claim 1 , wherein the detecting ( 506 ) is performed by the aircraft.

3. The method of claim 1 , wherein the detecting ( 506 ) is performed by a terrestrial system.

4. The method of claim 1 , wherein the determining ( 504 ), for each of the plurality of pairs of adjacent aircraft states ( 102 ), the respective aircraft transition ( 104 ) comprises computing respective headings ( 202 ) at each aircraft state ( 102 ) of a respective pair of adjacent aircraft states ( 102 ).

5. The method of claim 1 , wherein the determining ( 504 ), for each of the plurality of pairs of adjacent aircraft states ( 102 ), the respective aircraft transition ( 104 ) comprises computing respective pitches ( 212 ) at each aircraft state ( 102 ) of a respective pair of adjacent aircraft states ( 102 ).

6. The method of claim 1 , wherein the determining ( 504 ), for each of the plurality of pairs of adjacent aircraft states ( 102 ), the respective aircraft transition ( 104 ) comprises computing respective speeds ( 222 ) at each aircraft state ( 102 ) of a respective pair of adjacent aircraft states ( 102 ).

7. The method of claim 1 , wherein the electronically transmitting ( 508 ) comprises electronically transmitting ( 508 ) from the aircraft ( 702 ) to a ground station ( 706 ).

8. The method of claim 1 , wherein the electronically transmitting ( 508 ) comprises electronically transmitting ( 508 ) from a ground station ( 706 ) to the aircraft ( 702 ).

9. The method of claim 1 , wherein the first threshold, the second threshold, and the third threshold are all zero.

10. The method of claim 1 , further comprising:

directing, by the FMS, the aircraft to follow the updated flight plan.

11. A system for updating a flight plan of an aircraft ( 702 ), the system comprising:

a communications interface ( 708 ) configured to detect ( 502 ) a plurality of aircraft states ( 102 ) of the aircraft, each aircraft state ( 102 ) comprising a latitude value, a longitude value, an altitude value, and a time value, whereby the plurality of states ( 102 ) of the aircraft are stored in electronic memory ( 712 ) in temporal order;

at least one electronic processor ( 710 ) configured to:

determine ( 504 ), for each of a plurality of pairs of adjacent aircraft states ( 102 ), a respective aircraft transition ( 104 ), each transition ( 104 ) comprising a planar turn radius ( 208 ) value, a vertical turn radius ( 218 ) value, and an acceleration ( 230 ) value;

store a plurality of aircraft transitions ( 104 ) in electronic memory ( 712 ) in temporal order;

detect ( 506 ) a plurality of pairs of repeat adjacent aircraft transitions ( 104 ) comprising: respective planar turn radii ( 208 ) values whose difference is no more than a first threshold, respective vertical turn radii ( 218 ) values whose difference is no more than a second threshold, and respective acceleration ( 230 ) values whose difference is no more than a third threshold;

discard ( 506 ) from the electronic memory ( 712 ), for each pair of repeat adjacent aircraft transitions ( 104 ), a respective aircraft state ( 102 ) from the plurality of aircraft states ( 102 ), whereby a filtered plurality of aircraft states is produced, and whereby an amount of data stored in electronic memory ( 712 ) is reduced; and

a transmitter ( 708 ) configured to electronically transmit the filtered plurality of aircraft states ( 102 ) from a first aircraft ( 702 ) system to a Flight Management System (FMS) configured to update a flight plan for the aircraft ( 702 ) to represent at least a portion of a trajectory interpolated from the plurality of aircraft states ( 104 ), whereby an updated flight plan is produced.

12. The system of claim 11 , further comprising instrumentation aboard the aircraft ( 702 ) configured to detect ( 502 ) the plurality of aircraft states ( 102 ) of the aircraft ( 702 ).

13. The system of claim 11 , further comprising instrumentation present in a ground station ( 706 ) configured to detect the plurality of aircraft states ( 102 ) of the aircraft ( 702 ).

14. The system of claim 11 , wherein the at least one electronic processor ( 710 ) configured to determine, for each of the plurality of pairs of adjacent aircraft states ( 102 ), the respective aircraft transition ( 104 ) is further configured to compute respective headings ( 202 ) at each aircraft state ( 102 ) of a respective pair of adjacent aircraft states ( 102 ).

15. The system of claim 11 , wherein the at least one electronic processor ( 710 ) configured to determine, for each of the plurality of pairs of adjacent aircraft states ( 102 ), the respective aircraft transition ( 104 ) is further configured to compute respective pitches ( 212 ) at each aircraft state ( 102 ) of a respective pair of adjacent aircraft states ( 102 ).

16. The system of claim 11 , wherein the at least one electronic processor ( 710 ) configured to determine, for each of the plurality of pairs of adjacent aircraft states ( 102 ), the respective aircraft transition ( 104 ) is further configured to compute respective speeds ( 222 ) at each aircraft state ( 102 ) of a respective pair of adjacent aircraft states ( 102 ).

17. The system of claim 11 , wherein the transmitter ( 708 ) comprises a wireless transmitter ( 708 ) present aboard the aircraft ( 702 ).

18. The system of claim 11 , wherein the transmitter ( 708 ) comprises a wireless transmitter ( 708 ) present at a ground station ( 706 ).

19. The system of claim 11 , wherein the first threshold, the second threshold, and the third threshold are all zero.

20. The system of claim 11 , wherein the FMS is further configured to direct the aircraft to follow the updated flight plan.