SYSTEM AND METHOD FOR AIRCRAFT NAVIGATION ASSISTANCE

• US 20140229100A1
• Filed: 02/06/2014
• Published: 08/14/2014
• Est. Priority Date: 02/08/2013
• Status: Active Grant

• Current Assignee: Dassault Aviation (Groupe Industriel Marcel Dassault)
• Original Assignee: Dassault Aviation (Groupe Industriel Marcel Dassault)
• Inventors: MARCON, Pierre
• Granted Patent: US 9,031,785 B2
• Time in Patent Office: Days
• US Class Current: 701/469
• CPC Class Codes: G01C 21/12 executed aboard the object being navigated; Dead reckoning
• CPC Class Codes: G01C 21/165 combined with non-inertial navigation instruments
• CPC Class Codes: G01S 19/49 whereby the further system is an inertial position system, e.g. loosely-coupled

Abstract

This aircraft navigation assistance system comprises an inertial navigation module adapted for providing first positional information from accelerometric and gyrometric measurements, and a module adapted for determining second positional information from satellite positioning data. The system is characterized in that it comprises means for estimating a first localization of the aircraft at a time of estimation on the basis of first positional information determined from accelerometric and gyrometric measurements at said time of estimation and second positional information determined from positioning data received prior to said time of estimation, said first localization being determined independently from any positioning data received in a time interval preceding said time of estimation, advantageously equal to a time to alert.

Claims

1. A navigation assistance system to be used on board an aircraft, comprising:

an inertial navigation module, adapted for providing first aircraft positional information resulting at least partially from accelerometric and gyrometric measurements,

a satellite positioning module, comprising at least one satellite navigation data receiver, said positioning module being adapted for determining second aircraft positional information from satellite positioning data received by said satellite navigation data receiver,

said system comprising estimation means adapted for estimating a first localization of the aircraft at a given time of estimation on the basis of;

first aircraft positional information, resulting at least partially from accelerometric and gyrometric measurements at said time of estimation, and

second aircraft positional information, determined from satellite positioning data received by said satellite navigation data receiver prior to said time of estimation,

said first localization being determined independently from any satellite positioning data received in a predetermined time interval preceding said time of estimation and including said time of estimation, said predetermined time interval being advantageously equal to a time to alert.

2. The navigation assistance system according to claim 1, wherein said satellite positioning module comprises means for validating or invalidating said satellite positioning data, depending on the precision of said satellite positioning data and/or depending on the operating mode of said satellite positioning module.

3. The navigation assistance system according to claim 2, wherein the second aircraft positional information includes an estimate of a position of the aircraft at least at a given time of determination and an estimate of a precision of said position, determined from satellite positioning data, and in that said satellite positioning module is adapted for comparing the estimate of the precision of said position to a required minimum precision at said time of determination, and validating said satellite positioning data, at a validation time after said time of determination), if the estimate of the precision of said position is in accordance with said required minimum precision, the time interval between said time of determination and said validation time being less or equal to said time to alert.

4. The navigation assistance system according to claim 2, wherein said first localization is determined independently from any satellite positioning data which has not been validated by said satellite positioning module.

5. The navigation assistance system according to claim 2, comprising a unit for storing a deviation recorded at an earlier time between first aircraft positional information and second aircraft positional information, adapted for storing said deviation (e) at least between said earlier time and said time of estimation:

said estimation means being adapted for determining said first localization of the aircraft at said time of estimation;

depending on the deviation recorded at said earlier time if said satellite positioning data at said earlier time is validated, or

depending on a deviation recorded at the last time for which satellite positioning data has been validated, if said satellite positioning data at said earlier time is not validated.

6. The navigation assistance system according to claim 2, comprising a unit for storing a deviation recorded at an earlier between second aircraft positional information and a first localization determined at said earlier time (by said estimation means, said storage unit being adapted for storing said deviation at least between said earlier time and said time of estimation,

said estimation means being adapted for determining said first localization of the aircraft at said time of estimation:

depending on the deviation recorded at said earlier time if said satellite positioning data at said earlier time is validated, or

depending on a deviation recorded at the last time for which satellite positioning data has been validated, if said satellite positioning data at said earlier time not validated.

7. The navigation assistance system according to claim 1, wherein said estimation means is adapted for determining a second localization of the aircraft at a time of estimation, on the basis of hybridization between:

first positional information of the aircraft resulting at least partially from accelerometric and gyrometric measurements at said time of estimation; and

second positional information of the aircraft determined from satellite positioning signals received by said satellite navigation data receiver at said time of estimation.

8. The navigation assistance system according to claim 7, comprising a selection module adapted for determining an enhanced-reliability localization of the aircraft, at a time of estimation associated with a predetermined requirement of responsiveness, said localization with enhanced reliability being:

equal to said first localization if said time to alert is not in accordance with said requirement of responsiveness; and

equal to said second localization if said time to alert is in accordance with said requirement of responsiveness.

9. The navigation assistance system according to claim 1, wherein said satellite positioning module comprises means of receiving differential positioning signals and signals from an SBAS-type system enhancing the precision of the positioning.

10. The navigation assistance system according to claim 1, wherein said first localization of the aircraft is estimated on the basis of hybridization between said first positional information of the aircraft and said second positional information of the aircraft.

11. A method of aircraft navigation assistance, comprising, in at least a first phase of flight of the aircraft, a step of estimating a first localization of the aircraft at a given time of estimation comprising:

a phase of determining first positional information of the aircraft, resulting at least partially from accelerometric and gyrometric measurements of an inertial navigation center at said time of estimation;

a phase of determining second positional information of the aircraft, from satellite positioning data received by a satellite navigation data receiver prior to said time of estimation; and

a phase of estimating said first localization of the aircraft on the basis of said first and second positional information, said first localization being estimated independently from any satellite positioning data received at a predetermined time interval preceding said time of estimation and including said time of estimation, said predetermined time interval being advantageously equal to a time to alert.

12. The method according to claim 11, comprising a step of validating said satellite positioning data, depending on the precision of said satellite positioning data and/or depending on the operating mode of said satellite positioning module.

13. The method according to claim 12, wherein the phase of determining second positional information comprises an estimate of a position of the aircraft at least at a given time of determination and an estimate of a precision of said position from said satellite positioning data, said validation step comprising a phase of comparing the estimate of the precision of said position to a required minimum precision at said time of determination, said satellite positioning data being validated, at a validation time after said time of determination, if and only if the estimate of the precision of said position is in accordance with said required minimum precision, the time interval between said time of determination and said validation time being less or equal to said time to alert.

14. The method according to claim 12, wherein said first localization is determined independently from any satellite positioning data not validated.

15. The method according claim 11, comprising, in at least a second phase of flight of the aircraft, a step of estimating a second localization of the aircraft at a time of estimation, on the basis of hybridization between:

first positional information of the aircraft resulting at least partially from accelerometric and gyrometric measurements at said time of estimation; and

second positional information of the aircraft determined from satellite positioning signals received by said satellite navigation data receiver at said time of estimation.