Methods using predictive shimming to optimize part-to-part alignment

Patent metadata

Field	Value
Publication number	US-10450053-B2
Application number	US-201615151577-A
Country	US
Kind code	B2
Filing date	May 11, 2016
Priority date	May 11, 2016
Publication date	Oct 22, 2019
Grant date	Oct 22, 2019

Abstract

Methods for using predictive shimming to optimize part-to-part alignment. In accordance with one embodiment, the process uses measurement data acquired from mating surfaces and key features to virtually align two parts in a manner that optimizes the final orientation of the parts and determines the geometry of the shim needed to achieve this orientation during assembly.

First claim

The invention claimed is:

1. A method for fabricating a shim fittable between first and second parts, comprising:
(a) measuring a first mating surface, a top surface of a web and mating features of a first part to obtain first measurement data in a frame of reference of a measurement system;
(b) measuring a second mating surface and mating features of the second part to obtain second measurement data in the frame of reference of the measurement system;
(c) using a weighted fit algorithm to align the first measurement data to first engineering location data that includes data representing a specified plane locating the web in a frame of reference of an engineering model, the weighted fit algorithm comprising weighting that minimizes an angular deviation of the web from the specified plane;
(d) aligning the second measurement data to second engineering location data that represents a specified location of the second part in the frame of reference of the engineering model;
(e) fitting a first virtual surface to a measurement data set of the first aligned measurement data corresponding to the first mating surface;
(f) fitting a second virtual surface to a measurement data set of the second aligned measurement data corresponding to the second mating surface;
(g) estimating gaps between the first and second virtual surfaces to obtain estimated gaps; and
(h) fabricating the shim having a thickness which varies as a function of the estimated gaps.

2. The method as recited in claim 1 , further comprising using the estimated gaps to develop a shim model, wherein step (h) comprises fabricating the shim in accordance with the shim model.

3. The method as recited in claim 1 , wherein the first part is a structural component of an aircraft and the second part is a skin of the aircraft.

4. The method as recited in claim 1 , wherein step (c) comprises aligning mating feature data included in the first measurement data with corresponding mating feature data included in the first engineering location data, and step (d) comprises aligning mating feature data included in the second measurement data with corresponding mating feature data included in the second engineering location data.

5. The method as recited in claim 1 , wherein the mating features of the first and second parts are holes in the first part and holes in the second part, and step (a) comprises:
placing optical targets in the holes in the first part;
scanning the first mating surface of the first part using a three-dimensional scanner to acquire first point cloud scan data and first measured hole vector data; and
scanning the top surface of the web of the first part using a three-dimensional scanner to acquire second point cloud scan data.

6. The method as recited in claim 5 , wherein step (b) comprises:
placing optical targets in the holes in the second part; and
scanning the second mating surface of the second part using a three-dimensional scanner to acquire third point cloud scan data and second measured hole vector data.

7. The method as recited in claim 6 , wherein step (c) comprises aligning the first measured hole vector data with corresponding hole vector data included in the first engineering location data, and step (d) comprises aligning the second measured hole vector data with corresponding hole vector data included in the second engineering location data.

8. The method as recited in claim 1 , wherein the shim has a flat surface and a non-flat surface, the distances between the flat and non-flat surfaces of the shim being equal to the thickness which varies as a function of the estimated gaps.

9. A method for attaching a structural component to a skin of an aircraft, comprising:
(a) using a measurement system to measure a first mating surface, a top surface of a web and mating features of a structural component of an aircraft to obtain first measurement data in a frame of reference of the measurement system;
(b) using the same or a different measurement system to measure a second mating surface and mating features of a skin of the aircraft to obtain second measurement data in a frame of reference of the same or different measurement system;
(c) using a weighted fit algorithm to align the first measurement data to first engineering location data that includes data representing a specified plane locating the web in a frame of reference of an engineering model, the weighted fit algorithm comprising weighting that minimizes an angular deviation of the web from the specified plane;
(d) aligning the second measurement data to second engineering location data that represents a specified location of the skin in the frame of reference of the engineering model;
(e) fitting a first virtual surface to a measurement data set of the first aligned measurement data corresponding to the first mating surface;
(f) fitting a second virtual surface to a measurement data set of the second aligned measurement data corresponding to the second mating surface;
(g) estimating gaps between the first and second virtual surfaces to obtain estimated gaps;
(h) fabricating a shim having a thickness which varies as a function of the estimated gaps; and
(i) assembling the structural component and the skin of the aircraft with the shim therebetween.

10. The method as recited in claim 9 , further comprising using the estimated gaps to develop a shim model, wherein step (h) comprises fabricating the shim in accordance with the shim model.

11. The method as recited in claim 9 , wherein the structural component is a longeron comprising a flange and the web, the first mating surface comprises a surface of the flange, and the skin is a fuselage skin.

12. The method as recited in claim 9 , wherein the shim has a flat surface and a non-flat surface, the distances between the flat and non-flat surfaces of the shim being equal to the thickness which varies as a function of the estimated gaps.

Assignees

• Boeing Co

Inventors

• Doyle Joseph D
• Greer Christopher A
• Smith Brian D
• Wcislak Richard M

Classifications

• G06F30/17

  Mechanical parametric or variational design · CPC title

• G06F30/15

  Vehicle, aircraft or watercraft design · CPC title

• B64C1/06

  Frames; Stringers; Longerons {; Fuselage sections} · CPC title

• B23P19/105

  using sensing means · CPC title

• B64C3/26 Primary

  Construction, shape, or attachment of separate skins, e.g. panels · CPC title