SYSTEM AND METHOD FOR COMPUTING FLIGHT TIME FROM AN EQUI-DISTANCE POINT TO A REFERENCE POINT

• US 20120109428A1
• Filed: 07/19/2010
• Published: 05/03/2012
• Est. Priority Date: 07/20/2009
• Status: Active Grant

• Current Assignee: Airbus Group India Private Limited
• Original Assignee: Airbus Engineering Centre India Co.
• Inventors: Narasimhulu, Veeresh Kumar Masaru, Kushwaha, Dinesh Kumar
• Granted Patent: US 8,463,468 B2
• Time in Patent Office: Days
• US Class Current: 701/16
• CPC Class Codes: G01S 5/0284 Relative positioning
• CPC Class Codes: G08G 5/0052 for cruising combined instruments indicating more than one navigational value G01C23/00

Abstract

A system and method for computing flight time from an equi-distance point (EDP) to a reference point is disclosed. In one embodiment, a method of a flight management system (FMS) of an aircraft for computing flight time from an EDP to a reference point for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency and determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by the FMS. Further, the method includes generating the EDP for the aircraft by locating a point in the remaining flight path, and calculating an expected flight time of the aircraft from the EDP to each of the at least two reference points based on a plurality of factors affecting the flight time of the aircraft.

Claims

1. A method of a flight management system (FMS) of an aircraft for computing flight time from an equi-distance point (EDP) to a reference point for an emergency landing of the aircraft, comprising:

receiving at least two reference points for landing the aircraft upon an occurrence of an emergency;

determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by the flight management system;

generating the equi-distance point for the aircraft by locating a point in the remaining flight path which is equidistant from the at least two reference points; and

calculating an expected flight time of the aircraft from the equi-distance point to each of the at least two reference points based on a plurality of factors affecting the flight time of the aircraft.

2. The method of claim 1, wherein the at least two reference points are received from a pilot of the aircraft.

3. The method of claim 1, wherein the at least two reference points comprise a departure airport and an arrival airport for the aircraft by default.

4. The method of claim 1, wherein the plurality of factors affecting the flight time comprises at least one of a wind velocity, characteristics of the aircraft, and a distance from the equi-distance point to the each one of the at least two reference points.

5. The method of claim 1, wherein the calculating the expected flight time of the aircraft from the equi-distance point to the each one of the at least two reference points is performed based on a default flight profile encompassing a great circle distance.

6. The method of claim 5, wherein the great circle distance comprises a cruise distance and a descent distance of the aircraft from the equi-distance point to the each one of the at least two reference points.

7. The method of claim 6, further comprising calculating a descent time for the descent distance based on allowances stored in a performance database of the aircraft.

8. The method of claim 7, wherein the descent time is further based on a wind velocity at the each of the at least two reference points.

9. The method of claim 6, further comprising calculating a cruise time for the cruise distance based on:

the cruise time=cruise distance/ground speed, wherein the ground speed is a sum of a true air speed (TAS) and a wind velocity at a cruise altitude.

10. The method of claim 9, wherein the calculating the cruise time is based on an assumption that an expected cruise flight of the aircraft for the cruise distance is carried out at an optimum mach based on a predicted gross weight of the aircraft and an effect of wind at the equi-distance point.

11. An article, comprising:

a storage medium having instructions, that when executed by a computing platform of a flight management system (FMS) of an aircraft, result in execution of a method for computing flight time from an equi-distance point (EDP) to a reference point for an emergency landing of the aircraft, comprising;

receiving at least two reference points for landing the aircraft upon an occurrence of an emergency;

determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by the flight management system;

generating the equi-distance point for the aircraft by locating a point in the remaining flight path which is equidistant from the at least two reference points; and

calculating an expected flight time of the aircraft from the equi-distance point to each of the at least two reference points based on a plurality of factors affecting the flight time of the aircraft.

12. The article of claim 11, wherein the plurality of factors affecting the flight time comprises at least one of a wind velocity, characteristics of the aircraft, and a distance from the equi-distance point to the each one of the at least two reference points.

13. The article of claim 11, wherein the calculating the expected flight time of the aircraft from the equi-distance point to the each one of the at least two reference points is performed based on a default flight profile flying a great circle distance.

14. The article of claim 13, wherein the great circle distance comprises a cruise distance and a descent distance of the aircraft from the equi-distance point to the each one of the at least two reference points.

15. The article of claim 14, further comprising calculating a descent time for the descent distance based on allowances stored in a performance database of the aircraft.

16. The article of claim 15, wherein the descent time is further based on a wind velocity at the each of the at least two reference points.

17. The article of claim 14, further comprising calculating a cruise time for the cruise distance based on:

the cruise time=cruise distance/ground speed, wherein the ground speed is a sum of a true air speed (TAS) and a wind velocity at a cruise altitude.

18. The article of claim 17, wherein the calculating the cruise time is based on an assumption that an expected cruise flight of the aircraft for the cruise distance is carried out at an optimum mach based on a predicted gross weight of the aircraft and an effect of wind at the equi-distance point.

19. A system of a flight management system (FMS) of an aircraft for computing flight time from an equi-distance point (EDP) to a reference point for an emergency landing of the aircraft, comprising:

a processor; and

a memory coupled to the processor and configured for storing a set of instructions, when executed by the processor, causes the processor to perform a method comprising;

receiving at least two reference points for landing the aircraft upon an occurrence of an emergency;

determining a remaining flight path for the aircraft based on a current location of the aircraft and a flight plan serviced by the flight management system;

generating the equi-distance point for the aircraft by locating a point in the remaining flight path which is equidistant from the at least two reference points; and

calculating an expected flight time of the aircraft from the equi-distance point to each of the at least two reference points based on a plurality of factors affecting the flight time of the aircraft.

20. The system of claim 19, further comprising a performance database coupled to the processor for storing allowances used to calculate a descent time of the aircraft for the emergency landing.