System and method for aircraft performance predictions for descent and approach phases

• US 9,442,490 B2
• Filed: 04/23/2012
• Issued: 09/13/2016
• Est. Priority Date: 04/29/2011
• Status: Active Grant

• Current Assignee: Airbus Group India Private Limited
• Original Assignee: Airbus Engineering Centre India Co.
• Inventors: Mn, Veeresh Kumar, Kushwaha, Dinesh Kumar, Kumar, Chaitanya Pavan
• Primary Examiner(s): CASS, JEAN PAUL
• Application Number:
  US13/452,967
• Publication Number:
  US 20120277936A1
• Time in Patent Office: 1,604 Days
• Field of Search: 340/963, 340/945, 340/946, 340/969, 340/970, 701/16
• US Class Current: 1/1
• CPC Class Codes: G05D 1/0676 specially adapted for landing

Abstract

A system and method for aircraft performance predictions for descent and approach phases are disclosed. In one embodiment, cruise computation is stopped substantially around a default distance from a destination. Further, current predicted aircraft state is determined using a total energy of the aircraft starting from the default distance. Furthermore, descent and approach phase profiles are computed using the determined current predicted aircraft state. In addition, the aircraft performance predictions are obtained using the computed descent and approach phase profiles.

Claims

1. A method of aircraft performance predictions for descent and approach phases in a flight management system (FMS), comprising:

stopping cruise computation substantially around a default distance from a destination by an aircraft performance prediction module residing in a memory of the FMS;

determining current predicted aircraft state using a total energy of the aircraft starting from the default distance by the aircraft performance predictions module;

computing descent and approach phase profiles including a flight path using the determined current predicted aircraft state by the aircraft performance prediction module, comprising;

selecting a starting top of descent distance from the destination while the aircraft is in cruise altitude by the aircraft performance predictions module;

performing an iterative backward computation from the destination to the cruise altitude by the aircraft performance predictions module to compute the descent and approach phase profiles including the flight path using the determined current predicted aircraft state; and

obtaining the aircraft performance predictions along the flight path based on the computed descent and approach phase profiles by the aircraft performance predictions module that comprises;

obtaining a first top of descent distance from the obtained descent and approach profiles;

determining whether a difference between the starting top of descent distance and the first top of descent distance is within a design value; and

if so, determining the aircraft performance predictions along the flight path using the descent and the approach phase profiles in a forward computation from the cruise altitude to the destination; and

if not, considering the first top of descent distance to be the starting top of descent distance; and

using the considered starting top of descent,

repeating the steps of performing the iterative backward computation,

obtaining the first top of descent, and

determining whether the difference between the starting top of descent distance and the first top of descent distance is within the design value, until the difference is within the design value; and

guiding the aircraft through the descent and approach phase profiles based on the aircraft performance predictions.

2. The method of claim 1, wherein the current predicted aircraft state includes flight parameters selected from the group consisting of aircraft gross weight, flying altitude, distance covered by the aircraft and aircraft speed.

3. The method of claim 1, wherein the starting top-of-descent distance comprises a point at which the descent phase intercepts the cruise altitude.

4. The method of claim 1, wherein determining the aircraft performance predictions using the descent and approach phase profiles in the forward computation comprises:

determining the aircraft performance predictions for each way point using the descent and approach phase profiles in the forward computation.

5. An aircraft comprising:

a flight management system (FMS), wherein the FMS further comprises;

a processor; and

memory coupled to the processor, wherein the memory includes an aircraft performance predictions module having instructions to;

stop cruise computation substantially around a default distance from a destination;

determine a current predicted aircraft state using a total energy of the aircraft starting from the default distance;

compute descent and approach phase profiles including a flight path using the determined current predicted aircraft state, wherein the aircraft performance prediction module further having instructions to;

select a starting top of descent distance from the destination while the aircraft is in cruise altitude; and

perform an iterative backward computation from the destination to the cruise altitude to compute the descent and the approach phase profiles including the flight path using the determined current predicted aircraft state; and

obtain the aircraft performance predictions along the flight path based on the computed descent and approach phase profiles, wherein the aircraft performance predictions module further having instructions to;

obtain a first top of descent distance from the obtained descent and approach profiles;

determine whether a difference between the starting top of descent distance and the first top of descent distance is within a design value; and

if so, determine the aircraft performance predictions along the flight path using the descent and the approach phase profiles in a forward computation from the cruise altitude to the destination;

if not, consider the first top of descent distance to be the starting top of descent distance; and

using the considered starting top of descent, repeat the steps of performing the iterative backward computation,

obtain the first top of descent, and

determining whether the difference between the starting top of descent distance and the first top of descent distance is within the design value, until the difference is within the design value; and

guide the aircraft through the descent and approach phases based on the aircraft performance predictions.

6. A flight management system (FMS), comprising:

a processor; and

a memory coupled to the processor, wherein the memory includes an aircraft performance predictions module having instructions to;

stop cruise computation substantially around a default distance from a destination;

determine current predicted aircraft state using a total energy of the aircraft starting from the default distance;

compute descent and approach phase profiles including a flight path using the determined current predicted aircraft state, wherein the aircraft performance prediction module, further having instructions to;

select a starting top of descent distance from the destination while the aircraft is in cruise altitude; and

perform an iterative backward computation from the destination to the cruise altitude to compute the descent and the approach phase profiles including the flight path using the determined current predicted aircraft state; and

obtain the aircraft performance predictions along the flight path based on the computed descent and approach phase profiles, wherein the aircraft performance predictions module further having instructions to;

obtain a first top of descent distance from the obtained descent and approach profiles;

determine whether a difference between the starting top of descent distance and the first top of descent distance is within a design value; and

if so, determine the aircraft performance predictions along the flight path using the descent and the approach phase profiles in a forward computation from the cruise altitude to the destination;

if not, consider the first top of descent distance to be the starting top of descent distance; and

using the considered starting top of descent, repeat the steps of performing the iterative backward computation, obtain the first top of descent, and

determining whether the difference between the starting top of descent distance and the first top of descent distance is within the design value, until the difference is within the design value; and

guide the aircraft through the descent and approach phase profiles based on the aircraft performance predictions.

7. The FMS of claim 6, wherein the current predicted aircraft state includes flight parameters selected from the group consisting of aircraft gross weight, flying altitude and aircraft speed.

8. The FMS of claim 6, wherein the aircraft performance predictions module farther having instructions to:

determine the aircraft performance predictions for each way point using the descent and approach phase profiles in the forward computation.

9. A non transitory computer readable storage medium for aircraft performance predictions for descent and approach phases in a flight management system (FMS), having instructions that, when executed by the FMS, cause the FMS to perform a method comprising:

stopping cruise computation substantially around a default distance from a destination by an aircraft performance prediction module residing in a memory of the FMS;

determining current predicted aircraft state using a total energy of the aircraft starting from the default distance by the aircraft performance predictions module;

computing descent and approach phase profiles including a flight path using the determined current predicted aircraft state by the aircraft performance prediction module, comprising;

selecting a starting top of descent distance from the destination while the aircraft is in cruise altitude; and

performing an iterative backward computation from the destination to the cruise altitude to compute the descent and approach phase profiles including the flight path using the determined current predicted aircraft state; and

obtaining the aircraft performance predictions along the flight path based on the computed descent and approach phase profiles that comprises;

obtaining a first top of descent distance from the obtained descent and approach profiles;

determining whether a difference between the starting top of descent distance and the first top of descent distance is within a design value and

if so, determining the aircraft performance predictions along the flight path using the descent and the approach phase profiles in a forward computation from the cruise altitude to the destination;

if not, considering the first top of descent distance to be the starting top of descent distance; and

using the considered starting top of descent distance,

repeating the steps of performing the iterative backward computation,

obtaining the first top of descent distance, and determining whether the difference between starting top of descent distance and the first top of descent distance is within the design value, until the difference is within the design value; and

guiding the aircraft through the descent and approach phase profiles based on the aircraft performance predictions.

10. The non-transitoty computer-readable storage medium of claim 9, wherein the current predicted aircraft state includes flight parameters selected from the group consisting of aircraft gross weight, flying altitude and aircraft speed.

11. The non-transitory computer-readable storage medium of claim 9, wherein determining the aircraft performance predictions using the descent and approach phase profiles in the forward computation comprises:

determining the aircraft performance predictions for each way point using the descent and approach phase profiles in the forward computation.