Method and device for monitoring a position indication of an aircraft

• US 7,908,046 B2
• Filed: 05/19/2008
• Issued: 03/15/2011
• Est. Priority Date: 05/23/2007
• Status: Active Grant

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Airbus France
• Inventors: Ortet, Gregory, Guillet, Alain, Dattler, Stephane, Huynh, Jean-Philippe
• Primary Examiner(s): Hellner; Mark
• Assistant Examiner(s): Algahaim; Helal A
• Application Number:
  US12/123,327
• Publication Number:
  US 20080294306A1
• Time in Patent Office: 1,030 Days
• Field of Search: 701/3, 701/14, 340/945, 340/963, 342/357.32
• US Class Current: 701/14
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled
• CPC Class Codes: G08G 5/006 in accordance with predefined flight zones, e.g. to avoid prohibited zones

Abstract

A device and method calculate a global error relating to a position indication of an aircraft and compare the global error with a threshold value, which depends on flight constraints.

Claims

1. A method for monitoring a position indication of an aircraft, said position indication representing a current position of the aircraft, which is determined with the aid of information arising from an onboard positioning section, which cooperates with a satellite positioning system, and of inertial information generated by an onboard inertial system, the method comprising the following series of successive operations that are carried out in an automatic and repetitive manner:

a) determining at least one first position error which represents an estimated maximum error of said position indication of the aircraft;

b) determining at least one second position error which represents an estimated maximum error of the position of the aircraft for a particular future duration, and which depends on a problem in determining said position indication;

c) summing said first and second position errors so as to obtain a global error;

d) comparing the global error with at least one threshold value which depends on flight constraints of the aircraft, which must fly inside a predetermined flight corridor; and

e) emitting an alarm signal if said global error is greater than said threshold value.

2. The method as claimed in claim 1, wherein:

said inertial system comprises several inertial platforms, each of said inertial platforms making it possible to determine a current position of the aircraft,

in step a) a plurality of first position errors is determined, each of these first position errors relating to one of these current positions and being associated with the inertial platform which has determined the corresponding current position,

in step b) a plurality of second position errors associated respectively with said inertial platforms is determined, and

in step c) the sum of first and second position errors which are associated with the same inertial platform is formed so as to obtain a plurality of sums, and said global error is determined on the basis of this plurality of sums.

3. The method as claimed in claim 1, wherein, in step b), said second position error is determined by assuming a total loss of the information arising from said onboard positioning section.

4. The method as claimed in claim 1, wherein that, in step b), said second position error is determined by taking account of the flight dynamics relating to the future flight of the aircraft over said future duration.

5. The method as claimed in claim 1, wherein:

in step d), the global error is compared with each of a plurality of threshold values, and

in step e), in the event that the alarm signal is emitted, the threshold values which are exceeded by said global error are indicated.

6. The method as claimed in claim 1, wherein, upon the emission of the alarm signal in step e), an additional step 1) is carried out, in which the inertial system calculates, in an automatic and repetitive manner, a current position with the aid of a pure-inertia mode, for which the information arising from at least one receiver of said onboard positioning section is discarded from the position calculation after the emission of the alarm signal.

7. The method as claimed in claim 6, wherein:

the inertial system calculates the current position with the aid of the pure-inertia mode and the latest valid information provided by the onboard positioning section,

said inertial system comprises a plurality of inertial platforms, each of which calculates a current position, and

in step f), a consolidated current position of the aircraft is determined on the basis of these various current positions.

8. The method as claimed in claim 6, wherein, upon the emission of the alarm signal in step e), steps a) to e) continue to be carried out in an automatic and repetitive manner, and as soon as the global error again becomes less than the threshold value, the inertial system ceases the calculation of the current position with the aid of the pure-inertia mode, such as provided for in step f).

9. The method as claimed in claim 1, wherein said flight constraints relate to required navigation and guidance performance.

12. The method as claimed in claim 4, wherein to determine the second position error the method further comprises:

identifying, for a trajectory of the future flight, trajectory portions along which the roil of the aircraft varies,

deducing an upper bound on the total time the aircraft will fly along the trajectory portions,

deducing the number of dynamic variations of turning rate for the aircraft while flying along the trajectory portions, and

calculating a predicted performance of the aircraft based on a roll rate over the upper bound of the total time and the number of dynamic variations.

10. A device for monitoring a position indication of an aircraft, said position indication representing a current position of the aircraft and being determined with the aid of information arising from an onboard positioning section, which cooperates with a satellite positioning system, and of inertial information generated by an onboard inertial system, the device comprising:

a first position-error determining section that determines at least one first position error which represents an estimated maximum error of said position indication of the aircraft;

a second position-error determining section that determines at least one second position error which represents an estimated maximum error of the position of the aircraft for a particular future duration, and which depends on a problem in determining said position indication;

a summer that sums said first and second position errors so as to obtain a global error;

a comparator that compares the global error with at least one threshold value which depends on flight constraints of the aircraft, which must fly inside a predetermined flight corridor; and

an alarm section that emits an alarm signal if said global error is greater than said threshold value.

11. A method for monitoring a position indication of an aircraft, said position indication representing a current position of the aircraft, which is determined with the aid of information arising from an onboard positioning section, which cooperates with a satellite positioning system, and of inertial information generated by an onboard inertial system, the method comprising the following series of successive operations that are carried out in an automatic and repetitive manner:

a) determining at least one first position error which represents an estimated maximum error of said position indication of the aircraft;

b) determining at least one second position error which represents an estimated maximum error of the position of the aircraft for a particular future duration, and which depends on a problem in determining said position indication;

c) summing said first and second position errors so as to obtain a global error;

d) comparing the global error with at least one threshold value which depends on flight constraints of the aircraft, which must fly inside a predetermined flight corridor; and

e) emitting an alarm signal if said global error is greater than said threshold value, wherein;

f) comparing the global error to a plurality of threshold values, and

g) indicating, in the event that the alarm signal is emitted, the threshold values which are exceeded by said global error and those which are not.