Trajectory specification for high capacity air traffic control

• US 7,650,232 B1
• Filed: 09/22/2005
• Issued: 01/19/2010
• Est. Priority Date: 09/22/2005
• Status: Expired due to Fees

• Current Assignee: USA As Represented By The Administrator Of The NASA
• Original Assignee: United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration
• Inventors: Paielli, Russell A.
• Primary Examiner(s): Bolda; Eric
• Assistant Examiner(s): Diacou; Ari M
• Application Number:
  US11/239,456
• Time in Patent Office: 1,580 Days
• Field of Search: 701/205
• US Class Current: 701/205
• CPC Class Codes: G01C 23/005 Flight directors indicating arrangements specially adapted for rotary gyroscopes G01C19/32
• CPC Class Codes: G08G 5/0043 Traffic management of multiple aircrafts from the ground G08G5/003 takes precedence; data processing specially designed for resource management, e.g. scheduling or allocating time, human or machine resources G06Q10/06

Abstract

Method and system for analyzing and processing information on one or more aircraft flight paths, using a four-dimensional coordinate system including three Cartesian or equivalent coordinates (x, y, z) and a fourth coordinate δ that corresponds to a distance estimated along a reference flight path to a nearest reference path location corresponding to a present location of the aircraft. Use of the coordinate δ, rather than elapsed time t, avoids coupling of along-track error into aircraft altitude and reduces effects of errors on an aircraft landing site. Along-track, cross-track and/or altitude errors are estimated and compared with a permitted error bounding space surrounding the reference flight path.

Claims

1. A system for analyzing and presenting information on an aircraft flight path, the system comprising a computer that is programmed:

to provide a description of aircraft location along an actual flight path in terms of Cartesian coordinates (x, y, z), referenced to a selected coordinate system, and in terms of an estimated distance δ

moved by the aircraft along a reference flight path during an elapsed time interval corresponding to the present time;

to estimate coordinates (x_p, y_p, z_p) for present location for the aircraft;

to estimate location of a perpendicular foot, having location coordinates (x_foot, y_foot, z_foot) of the aircraft on a curve C representing the reference flight path;

to interpret the perpendicular foot location as a nearest reference flight path location corresponding to the present location of the aircraft;

to estimate an arc length along the curve C from an initial reference location to the nearest flight path location;

to interpret the arc length as the estimated distance δ

;

to estimate, at each of a sequence of values of the estimated distance δ

, an error value, including at least one of an along-track (“

AT”

) error, a cross-track (“

CT”

) error and an altitude (“

ALT”

) error for the aircraft relative to the reference flight path;

to provide, for at least one of the sequence of values of δ

, a permitted error range for at least one of the AT error, the CT error and the ALT error, wherein the AT error, the CT error and the ALT error define a bounding space that maintains a minimum required separation distance; and

to present at least one of a visually perceptible display, an audibly perceptible display and an alphanumeric display of at least one of the AT error, the CT error and the ALT error as an error value for at least two of the sequence of values of δ

.

2. The system of claim 1, wherein said computer is further programmed:

to advise an operator of said aircraft of a magnitude of said error value; and

to recommend an action to be taken by said aircraft to correct or reduce the magnitude of said error value, when said error value lies outside a corresponding permitted error range.

3. The system of claim 1, wherein each of M locations (M≧

2), numbered m=1, . . . , M, on said curve C qualifies as said perpendicular foot for said aircraft location on said curve C with a corresponding estimated distance δ

(foot;

m), and said computer is further programmed to estimate a designated perpendicular foot, for purposes of estimating said arc length along said curve C, by a process comprising;

(1) estimating said distance δ

(foot;

m) (m=1, . . . , M) for the perpendicular foot on said curve C for the location number m; and

(2) the designated perpendicular foot is determined for a location number m=m1 (1≦

m1≦

M) for which δ

(foot;

m1) is no greater than any of the distances δ

(foot;

m) (m=1, . . . , M).

4. The system of claim 1, wherein said computer is further programmed:

to estimate a second distance δ

(PLAET) that said aircraft would have flown along said reference flight path in said elapsed time interval; and

to estimate said AT error as a distance δ

(AT)=|δ

−

δ

-(PLAET)|.

5. The system of claim 1, wherein said computer is further programmed:

to estimate a second distance δ

(PLAET), having location coordinates (x_PLAET, y_PLAET, z_PLAET), that said aircraft would have flown along said reference flight path in said elapsed time interval; and

to estimate said CT error as a distance δ

(CT)=d1∥

(x_p,y_p)−

(x_PLAET,y_PLAET)∥

, where d1∥

∥

is a selected distance metric for two locations in a plane having location coordinates (x_p,y_p) and (x_PLAET,y_PLAET).

6. The system of claim 1, wherein said computer is further programmed:

to estimate a second distance δ

(PLAET), calculated from location coordinates (x_PLAET, y_PLAET, z_PLAET), that said aircraft would have flown along said reference flight path in said elapsed time interval; and

to estimate said ALT error as a distance δ

(ALT)=|(z_p), (z_PLAET)|.

7. The system of claim 1, wherein said computer is further programmed:

to estimate a second distance δ

(PLAET), having location coordinates (x_PLAET, y_PLAET, z_PLAET), that said aircraft would have flown along said reference flight path in said elapsed time interval;

to estimate said AT error as a distance δ

(AT)=|δ

−

δ

(PLAET);

to estimate said CT error as a distance δ

(CT) d1∥

(x_p,y_p)−

(x_PLAET,y_PLAET)∥

, where d1∥

∥

is a selected distance metric for two locations in a plane having location coordinates (x_p,y_p) and (x_PLAET,y_PLAET); and

to estimate a horizontal error as a distance

δ

(horiz)={δ

(AT)²+δ

(CT)²}^1/2.

8. The system of claim 7, wherein said computer is further programmed:

to estimate said ALT error as a distance δ

(ALT)=|(z_p), (z_PLAET)|; and

δ

(total)={δ

(AT)²+δ

(CT)²+δ

(ALT)²}^1/2.