Device and method for determining the weight and/or a characteristic value of the position of the centre of gravity of an aircraft

• US 7,484,424 B2
• Filed: 04/04/2006
• Issued: 02/03/2009
• Est. Priority Date: 04/04/2005
• Status: Active Grant

• Current Assignee: Safran Landing Systems
• Original Assignee: Messier-Bugatti (Safran SA)
• Inventors: Pradier, Jean-Clair
• Primary Examiner(s): NOORI, MAX H
• Application Number:
  US11/396,550
• Publication Number:
  US 20060243855A1
• Time in Patent Office: 1,036 Days
• Field of Search: 738/08, 738/02, 701/124, 703/802
• US Class Current: 73/802
• CPC Class Codes: G01G 19/07 for weighing aircraft
• CPC Class Codes: G01M 1/125 of aircraft

Abstract

Method and device for determining the weight and/or a characteristic value of the position of the center of gravity of an aircraft standing on the ground by means of a plurality of undercarriages, each undercarriage including at least one structural element exhibiting a variable level of stresses depending on the fraction of the weight of the aircraft transmitted to the ground through the undercarriage. The method includes the steps of

a) measuring on each undercarriage at least one parameter representing the stress level of the element; and b) evaluating the characteristic value and/or the weight according to the parameters measured in step a). At least one parameter measured in step a) is a magnetic or electrical characteristic of the structural element of the undercarriage.

Claims

1. A method of determining the weight and/or a characteristic value of the position of the centre of gravity of an aircraft having a plurality of undercarriages (1) standing on the ground, each undercarriage (1) comprising at least one structural element (6, 8) exhibiting a variable level of stresses depending on the fraction (Pi) of the weight (P) of the aircraft transmitted to the ground through said undercarriage (1), this method comprising the following steps:

a/ measurement on each undercarriage (1) of at least one parameter representing the stress level of said element;

b/ evaluation of the characteristic value and/or of the weight according to the parameters measured in step a/;

wherein at least one parameter measured in step a/ is a magnetic or electrical characteristic of the structural element (6, 8, 2) of the undercarriage.

2. The method as claimed in claim 1, wherein the magnetic or electrical characteristic measured is a characteristic chosen from the group consisting of the magnetic permeability (μ

), the electrical conductivity (σ

) and the electrical permittivity of the material constituting the structural element (6, 8, 2)

3. The method as claimed in claim 1, wherein the magnetic or electrical characteristic is measured by mans of a Foucault current sensor (15).

4. The method as claimed in claim 1, wherein step b/ comprises a sub-step b1/ of evaluation of the fraction (Pi) of the weight of the aircraft transmitted to the ground by each undercarriage (1) as a function of the parameters measured in step a/, and a substep b2/ of determining the position of the center of gravity of the aircraft as a function of the fractions (Pi) evaluated in sub-step b1/.

5. The method as claimed in claim 4, wherein the fraction (Pi) of the weight of the aircraft transmitted through each undercarriage (1) is evaluated as a function of the magnetic or electrical characteristic measured in step a/ by means of a transfer function.

6. The method as claimed in claim 1, wherein the magnetic or electrical characteristic is measured in a single direction along which the level of stresses in the structural element (6, 8, 2) varies as a function of the fraction (Pi) of the weight of the aircraft transmitted to the ground through said undercarriage.

7. The method as claimed in claim 6, wherein there is measured on the structural element (6, 8, 2) in step a/ the magnetic or electrical characteristic in at least one other predetermined direction and/or the variation of the magnetic or electrical characteristic resulting from the torsion or shear force imposed on the structural element (6, 8, 2), these measurements being used to refine the evaluation of the representative value carried our in step b/.

14. The method as claimed in claim 2, wherein the magnetic or electrical characteristic is measured by means of a Foucault current sensor (15).

8. A device for determining the weight and/or a characterisnac value of the position of the centre of gravity of an aircraft standing on the ground by means of a plurality of undercarriages (1), each undercarriage (1) comprising at least one structural element (6, 8, 2) exhibiting a level of stresses that varies as a function of the fraction (Pi) of the weight of the aircraft transmitted to the ground through said undercarriage (1), this device comprising on each undercarriage (1) at least one sensor (15) for measuring a parameter representing the stress level of said element and means for determining the characteristic value as a function of the measured parameters, wherein the sensor is able to measure, as a representative parameter, a magnetic or electrical characteristic of the structural element (6, 8, 2) of the undercarriage (1).

9. The device as claimed in claim 8, wherein the sensor is able to measure a magnetic or electrical characteristic chosen from the group consisting of the magnetic permeability (μ

), the electrical conductivity (σ

) and the electrical permittivity of the material constituting the structural element (6, 8, 2).

10. The device as claimed in claim 8, wherein the sensor (15) for measuring the magnetic or electrical characteristic is a Foucault current sensor.

11. The device as claimed in claim 8, wherein it comprises means for evaluating the fraction (Pi) of the weight of the aircraft transmitted to the ground though each undercarriage (1) as a function of the measured parameters, and means for evaluating the position of the center of gravity of the aircraft as a function of the evaluated fractions.

12. The device as claimed in claim 11, wherein the means for determining the fraction (Pi) of the weight of the aircraft transmitted through each undercarriage comprise at least one transfer function.

13. An aircraft comprising a plurality of undercarriages (1) able to stand on the ground whilst supporting the weight of the aircraft and a device for determining the weight and/or a characteristic value of the position of the centre of gravity of the aircraft as claimed in claim 8, each undercarriage (1) comprising at least one structural element (6, 8, 2) exhibiting a level of stresses that varies as a function of the fraction (Pi) of the weight of the aircraft transmitted to the ground through said undercarriage.

15. The device as claimed in claim 9, wherein the sensor (15) for measuring the magnetic or electrical characteristic is a Foucault current sensor.

16. The device as claimed in claim 9, vherein it comprises means for evaluating the fraction (Pi) of the night of the aircraft transmitted to the ground though each undercarriage (1) as a function of the measured parameters, and means for evaluating the position of the center of gravity of the aircraft as a function of the evaluated fractions.

17. The device as claimed in claim 10, wherein it comprises means for evaluating the fraction (Pi) of the night of the aircraft transmitted to the ground though each undercarriage (1) as a function of the measured parameters, and means for evaluating the position of the center of gravity of the aircraft as a function of the evaluated fractions.

18. A method of determining at least one of a weight and characteristic value of a position of a centre of gravity of an aircraft, comprising:

measuring on each undercarriage of the aircraft a stress level of at least one structural element of each undercarriage with a sensor attached to the at least one structural element, the sensor measuring at learnt one of a magnetic and electrical characteristic of the at least structural element; and

evaluating the at least one of the weight and characteristic value according to the measuring,

wherein, the at least one structural element exhibits a variable level of stress depending on the fraction of the weight borne by each undercarriage of the aircraft.