Systems and methods for aircraft mass determination

Patent metadata

Field	Value
Publication number	US-10156469-B2
Application number	US-201715441436-A
Country	US
Kind code	B2
Filing date	Feb 24, 2017
Priority date	Feb 24, 2017
Publication date	Dec 18, 2018
Grant date	Dec 18, 2018

Abstract

An example methods for aircraft mass determination at pushback includes determining an acceleration of a pushback vehicle while moving an aircraft, determining a pushback force applied by the pushback vehicle while moving the aircraft, and determining a total mass of the aircraft based on the pushback force, the acceleration of the pushback vehicle during pushback, and a coefficient of static friction between tires of the aircraft and a surface on which the aircraft moves. An example system includes a pushback vehicle coupled to an acceleration sensor and a force sensor, and a computing device having one or more processors to determine a total mass of the aircraft based on the pushback force, the acceleration of the pushback vehicle during pushback, and a coefficient of static friction between tires of the aircraft and a surface on which the aircraft moves.

First claim

What is claimed is:

1. A method comprising:
moving an aircraft by a pushback vehicle coupled to the aircraft;
determining an acceleration of the pushback vehicle while moving the aircraft;
measuring, by a force sensor, a pushback force applied by the pushback vehicle while moving the aircraft; and
determining a total mass of the aircraft based on the pushback force, the acceleration of the pushback vehicle, and a coefficient of static friction between tires of the aircraft and a surface on which the aircraft moves.

2. The method of claim 1 , wherein determining the total mass of the aircraft comprises calculating the total mass of the aircraft fully loaded and ready for take-off.

3. The method of claim 1 , further comprising:
determining the coefficient of static friction between tires of the aircraft and the surface on which the aircraft moves based on a weather condition.

4. The method of claim 1 , further comprising:
causing an alarm based on the determined total mass of the aircraft being over, by a threshold amount, an estimated mass used for a fuel burn calculation.

5. The method of claim 1 , further comprising:
receiving pushback force data;
receiving acceleration data of the pushback vehicle while moving the aircraft;
determining a first timepoint where acceleration was greater than zero;
determining a second timepoint having a same acceleration to establish a constant acceleration;
retrieving a force data point from the pushback force data at a timepoint between the first timepoint and the second timepoint; and
using the constant acceleration and the force data point to determine the total mass of the aircraft.

6. The method of claim 1 , wherein determining the acceleration of the pushback vehicle while moving the aircraft comprises determining a first acceleration, and wherein determining the pushback force applied by the pushback vehicle while moving the aircraft comprises determining a first pushback force, and the method further comprises:
applying a known mass to the aircraft;
determining a second acceleration of the pushback vehicle while moving the aircraft with the known mass;
determining a second pushback force applied by the pushback vehicle while moving the aircraft with the known mass; and
determining the coefficient of static friction between tires of the aircraft and a surface on which the aircraft moves based on the known mass, the first acceleration, the first pushback force, the second acceleration, and the second pushback force.

7. The method of claim 1 , wherein determining the total mass of the aircraft comprises determining the total mass of the aircraft using the following:

m
=

F
Pushback

a
+

g
×

μ
0

,

where m is the total mass of the aircraft, F Pushback is the pushback force, a is the acceleration of the pushback vehicle, g is acceleration due to gravity, and μ 0 is the coefficient of static friction between the tires of the aircraft and the surface on which the aircraft moves.

8. A method comprising:
moving an aircraft by a pushback vehicle coupled to the aircraft;
determining a first acceleration of the pushback vehicle while moving the aircraft;
measuring, by a force sensor, a first pushback force applied by the pushback vehicle while moving the aircraft;
applying a known mass to the aircraft;
determining a second acceleration of the pushback vehicle while moving the aircraft with the known mass;
measuring, by the force sensor, a second pushback force applied by the pushback vehicle while moving the aircraft with the known mass; and
determining a coefficient of static friction between tires of the aircraft and a surface on which the aircraft moves based on the known mass, the first acceleration, the first pushback force, the second acceleration, and the second pushback force.

9. The method of claim 8 , wherein determining the coefficient of static friction comprises using the following:

Δ
⁢

⁢
m

=

F

Pushback

⁢
2

a
2

+

g
×

μ
0

-

F

Pushback

⁢
1

a
1

+

g
×

μ
0

where Δm is the known mass, F Pushback 1 is the first pushback force, F Pushback 2 is the second pushback force, a 1 is the first acceleration, a 2 is the second acceleration, g is acceleration due to gravity, and μ 0 is the coefficient of static friction.

10. The method of claim 9 , further comprising iteratively solving for values for μ 0 until convergence.

11. A system comprising:
a pushback vehicle coupled to an aircraft and moving the aircraft, and coupled to an acceleration sensor to determine an acceleration of the pushback vehicle while moving the aircraft, and coupled to a force sensor to determine a pushback force applied by the pushback vehicle while moving the aircraft; and
a computing device having one or more processors to determine a total mass of the aircraft based on the pushback force, the acceleration of the pushback vehicle, and a coefficient of static friction between tires of the aircraft and a surface on which the aircraft moves.

12. The system of claim 11 , wherein the pushback vehicle includes an airplane tug.

13. The system of claim 11 , wherein the acceleration sensor is positioned on the pushback vehicle to capture an acceleration in a pushback direction.

14. The system of claim 11 , wherein the force sensor includes a strain gauge.

15. The system of claim 11 , further comprising:
a rod between the pushback veh

Assignees

• Boeing Co

Inventors

• Kneuper Nils
• Cabos Ralf Rene

Classifications

• G01G19/086

  wherein the vehicle mass is dynamically estimated · CPC title

• G01G19/024 Primary

  using electrical weight-sensitive devices · CPC title

• B64F1/225

  Vehicles specially adapted therefor, e.g. aircraft tow tractors · CPC title

• G01G19/07 Primary

  for weighing aircraft · CPC title

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title