Loading of aircraft landing gear

Patent metadata

Field	Value
Publication number	US-9643738-B2
Application number	US-201514714192-A
Country	US
Kind code	B2
Filing date	May 15, 2015
Priority date	May 15, 2015
Publication date	May 9, 2017
Grant date	May 9, 2017

Abstract

A method of loading a landing gear in an aircraft comprises accessing an ideal path specifying movement of the landing gear from a starting location to an expected mounting location on the aircraft; determining a difference between the expected mounting location and an actual mounting location on the aircraft; modifying the ideal path to move the expected mounting location to the actual mounting location; and moving the landing gear along the modified path.

First claim

The invention claimed is:

1. A method of loading a landing gear in an aircraft, the method comprising:
accessing an ideal path specifying movement of the landing gear from a starting location at which the landing gear is not installed on the aircraft to an expected mounting location on the aircraft where the landing gear will be affixed to the aircraft;
determining a difference between the expected mounting location and an actual mounting location on the aircraft;
modifying the ideal path to move the expected mounting location to the actual mounting location;
moving the landing gear along the modified path; and
loading the landing gear onto the aircraft at the actual mounting location.

2. The method of claim 1 , wherein the landing gear is loaded above grade at current aircraft working height.

3. The method of claim 1 , wherein the landing gear is moved continuously along the modified path.

4. The method of claim 1 , wherein the landing gear is loaded outside of a factory.

5. The method of claim 1 , wherein the aircraft includes primary structural members and the landing gear includes load bearing interfaces; and wherein moving the landing gear includes translating the landing gear along a primarily forward axis while translating and tilting the landing gear about other axes to walk the landing gear underneath the primary structural members until the load bearing interfaces are positioned at mounting locations of the primary structural members.

6. The method of claim 5 , wherein the landing gear is a main landing gear; and wherein a wing of the aircraft includes the primary structural members.

7. The method of claim 1 , wherein a metrology system is used to determine the difference between the expected mounting location and the actual mounting location.

8. The method of claim 1 , wherein a multi-axis loader is used to move the landing gear along the modified path during loading, the ideal path determined with respect to a local coordinate system of the multi-axis loader.

9. The method of claim 8 , wherein the multi-axis loader includes first and second linear rails that extend along x-axes of the local coordinate system; a first pair of towers moved along the first linear rail; and a second pair of towers movable along the second linear rail; wherein each tower is mounted to the landing gear at a mounting point; and wherein each mounting point is independently moved along y-axes of the local coordinate system.

10. The method of claim 9 , wherein the multi-axis loader is moved across a factory floor and parked at indexed positions on the factory floor, and wherein the aircraft is moved to a designated position on the factory floor.

11. A system for loading aircraft landing gear in an aircraft, the system comprising:
a multi-axis loader for rotating and translating the landing gear; and
a controller programmed to access an ideal path for commanding the loader to move the landing gear from a starting location and orientation at which the landing gear is not installed on the aircraft to an ending orientation at an expected mounting location where the landing gear will be affixed to the aircraft; receive information about an actual mounting location in the aircraft; modify the ideal path so the loader moves the landing gear from the starting orientation and location to the ending orientation at the actual mounting location instead of the expected mounting location, and loading the landing gear onto the aircraft at the actual mounting location.

12. The system of claim 11 , wherein the controller is programmed to command the multi-axis loader to move the landing gear continuously along the modified path.

13. The system of claim 11 , further comprising a metrology system for determining a difference between the actual and expected mounting locations of the landing gear; wherein the controller is programmed to use the difference to modify the ideal path.

14. The system of claim 11 , wherein the multi-axis loader includes first and second linear rails; a first pair of loading towers movable along the first linear rail; and a second pair of loading towers movable along the second linear rail; wherein each loading tower is mounted to the landing gear.

15. The system of claim 14 , further comprising a first beam mounted to the first pair of loading towers; a second beam mounted to the second pair of loading towers; and aircraft landing gear clamped to the first and second beams.

16. The system of claim 14 , wherein the loading towers are independently movable along the linear rails and independently controllable in a vertical direction.

17. The system of claim 16 , wherein the linear rails define x-axes of a coordinate system of the multi-axis loader and the loading towers define y-axes of the coordinate system; and wherein the ideal path is determined with respect to the coordinate system.

Assignees

• Boeing Co

Inventors

• Desjardien Matthew R
• Nelson Blair P
• Kremenich Allan M
• Al Aqrabawi Zeyad A
• Van Horne Brian

Classifications

• B64F5/50

  Handling or transporting aircraft components · CPC title

• G05B2219/23007

  CAD to develop sequential control system, use data also to test · CPC title

• G05D1/00

  Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots (drive control systems specially adapted for autonomous road vehicles B60W60/00) · CPC title

• B64F5/10 Primary

  Manufacturing or assembling aircraft, e.g. jigs therefor · CPC title