System and method for computing an equi-time point for aircrafts

• US 8,467,916 B2
• Filed: 07/19/2010
• Issued: 06/18/2013
• Est. Priority Date: 07/24/2009
• 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
• Primary Examiner(s): Trammell, James
• Assistant Examiner(s): Marc, McDieunel
• Application Number:
  US13/382,289
• Publication Number:
  US 20120123616A1
• Time in Patent Office: 1,065 Days
• Field of Search: 701/3, 701/4, 701/8, 701/10, 701/11, 701/13, 701/15, 701/16, 701/120, 701/122, 701/123, 701/301, 701/411, 701/467, 701/528, 701/532, 701/533, 244/76.R, 244/175, 244/186, 340/945, 455/66.1, 455/98
• US Class Current: 701/3
• CPC Class Codes: A61P 1/00 Drugs for disorders of the alimentary tract or the digestive system
• CPC Class Codes: A61P 1/04 for ulcers, gastritis or reflux esophagitis, e.g. antacids, inhibitors of acid secretion, mucosal protectants
• CPC Class Codes: A61P 11/06 Antiasthmatics
• CPC Class Codes: A61P 17/06 Antipsoriatics
• CPC Class Codes: A61P 19/02 for joint disorders, e.g. arthritis, arthrosis
• CPC Class Codes: A61P 29/00 Non-central analgesic, antipyretic or antiinflammatory agents, e.g. antirheumatic agents; Non-steroidal antiinflammatory drugs [NSAID]
• CPC Class Codes: A61P 9/10 for treating ischaemic or atherosclerotic diseases, e.g. antianginal drugs, coronary vasodilators, drugs for myocardial infarction, retinopathy, cerebrovascula insufficiency, renal arteriosclerosis
• CPC Class Codes: G01C 23/00 Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration
• CPC Class Codes: G08G 5/0056 in an emergency situation, e.g. hijacking

Abstract

A method of a flight management system (FMS) of an aircraft for generating an equi-time point (ETP) for an emergency landing of the aircraft includes receiving at least two reference points for landing the aircraft upon an occurrence of an emergency. The method also includes determining an equi-distance point (EDP) for the aircraft by locating a first point on the remaining flight path of the aircraft which is equidistant from the at least two reference points. The method further includes generating an ETP for the aircraft by locating a second point on the remaining flight path such that time difference between any two of expected flight times of the aircraft from the second point to the at least two reference points is less than a threshold value.

Claims

1. A method of a flight management system (FMS) of an aircraft for generating an equi-time point (ETP) for an emergency landing of the aircraft, comprising:

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

determining, by the processor, an equi-distance point (EDP) for the aircraft by locating a first point on a remaining flight path of the aircraft which is equidistant from the at least two reference points; and

generating, by the processor, an equi-time point (ETP) for the aircraft by locating a second point on the remaining flight path of the aircraft, wherein a time difference between any two of expected flight times of the aircraft from the second point to the at least two reference points is less than a threshold value, and wherein an approximation of the second point is initially based on the equi-distance point.

2. The method of claim 1, wherein the remaining flight path for the aircraft is determined based on a current location of the aircraft and a flight plan serviced by the flight management system.

3. The method of claim 1, wherein the at least two reference points comprises a first reference point and a second reference point.

4. The method of claim 3, wherein the generating the equi-time point of the aircraft comprises:

computing a first expected flight time from the approximation of the second point to the first reference point;

computing a second expected flight time taken from the approximation of the second point to the second reference point; and

determining the second point as the equi-time point when a difference between the first expected flight time and the second expected flight time is less than the threshold value.

5. The method of claim 3, wherein the generating the equi-time point of the aircraft comprises:

(a) computing a first expected flight time from the approximation of the second point to the first reference point;

(b) computing a second expected flight time taken from the approximation of the second point to the second reference point; and

(c) shifting the approximation of the second point when a difference between the first expected flight time and the second expected flight time is greater than the threshold value.

6. The method of claim 5, wherein the generating the equi-time point of the aircraft further comprises:

repeating steps (a), (b), and (c) until the difference between the first expected flight time and the second expected flight time is less than the threshold value; and

determining the second point as the equi-time point.

7. The method of claim 5, wherein the shifting the approximation of the second point comprises moving the approximation of the second point along the remaining flight path toward the first reference point by a step when the first expected flight time to the first reference point is greater than the second expected flight time to the second reference point for more than the threshold value.

8. The method of claim 5, wherein the shifting the approximation of the second point comprises moving the approximation of the second point along the remaining flight path toward the second reference point by a step when the second expected flight time to the second reference point is greater than the first expected flight time to the first reference point for more than the threshold value.

9. The method of claim 7 or 8, wherein the step is based on a vector difference between a first wind velocity at the first reference point in nautical miles per hour and a second wind velocity in nautical miles per hour at the second reference point multiplied by 0.1 hour.

10. The method of claim 1, wherein the threshold value comprises one minute.

11. An article, comprising:

a non-transitory computer readable 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 generating an equi-time point (ETP) 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 an equi-distance point (EDP) for the aircraft by locating a first point on a remaining flight path of the aircraft which is equidistant from the at least two reference points; and

generating an equi-time point (ETP) for the aircraft by locating a second point on the remaining flight path of the aircraft, wherein a time difference between any two of expected flight times of the aircraft from the second point to the at least two reference points is less than a threshold value, and wherein an approximation of the second point is initially based on the equi-distance point.

12. The article of claim 11, wherein the at least two reference points comprises a first reference point and a second reference point.

13. The article of claim 12, wherein the generating the equi-time point of the aircraft comprises:

computing a first expected flight time from the approximation of the second point to the first reference point;

computing a second expected flight time taken from the approximation of the second point to the second reference point; and

determining the second point as the equi-time point when a difference between the first expected flight time and the second expected flight time is less than the threshold value.

14. The article of claim 12, wherein the generating the equi-time point of the aircraft comprises:

(a) computing a first expected flight time from the approximation of the second point to the first reference point;

(b) computing a second expected flight time taken from the approximation of the second point to the second reference point; and

(c) shifting the approximation of the second point when a difference between the first expected flight time and the second expected flight time is greater than the threshold value.

15. The article of claim 14, wherein the generating the equi-time point of the aircraft further comprises:

repeating steps (a), (b), and (c) until the difference between the first expected flight time and the second expected flight time is less than the threshold value; and

determining the second point as the equi-time point.

16. The article of claim 14, wherein the shifting the approximation of the second point comprises moving the approximation of the second point along the remaining flight path toward the first reference point by a step when the first expected flight time to the first reference point is greater than the second expected flight time to the second reference point for more than the threshold value.

17. The article of claim 14, wherein the shifting the approximation of the second point comprises moving the approximation of the second point along the remaining flight path toward the second reference point by a step when the second expected flight time to the second reference point is greater than the first expected flight time to the first reference point for more than the threshold value.

18. The article of claim 16 or 17, wherein the step is based on a vector difference between a first wind velocity at the first reference point in nautical miles per hour and a second wind velocity in nautical miles per hour at the second reference point multiplied by 0.1 hour.

19. A system of a flight management system (FMS) of an aircraft for generating an equi-time point (ETP) 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 an equi-distance point (EDP) for the aircraft by locating a first point on a remaining flight path of the aircraft which is equidistant from the at least two reference points; and

generating an equi-time point (ETP) for the aircraft by locating a second point on the remaining flight path of the aircraft, wherein a time difference between any two of expected flight times of the aircraft from the second point to the at least two reference points is less than a threshold value, and wherein an approximation of the second point is initially based on the equi-distance point.

20. The system of claim 19, further comprising a performance database coupled to the processor for storing performance data used to calculate the expected flight times of the aircraft.