Method for assembling an aircraft structure assembly without use of any of shimming, locating fixtures and final-hole-size drill jigs

Patent metadata

Field	Value
Publication number	US-10160070-B2
Application number	US-201715846508-A
Country	US
Kind code	B2
Filing date	Dec 19, 2017
Priority date	May 4, 2015
Publication date	Dec 25, 2018
Grant date	Dec 25, 2018

Abstract

A method is provided for assembling an aircraft structure assembly composed of a plurality of sections without use of any shimming, locating fixtures or final-hole-size drill jigs. The method includes supporting a first and second frame sections on respective adjustable supports, and positioning an interconnecting frame section therebetween. The method includes aligning first pre-drilled mating holes in the interconnecting frame section, and installing fasteners through the aligned, first pre-drilled mating holes. The method includes aligning second pre-drilled mating holes in structural mating sections, and installing fasteners through the aligned, second pre-drilled mating holes. The method includes positioning the structural mating sections relative to the first and second frame sections and the interconnecting frame section. The structural mating sections are assembled inwardly from the first and second frame sections that form an outer perimeter structure of the aircraft structure assembly.

First claim

What is claimed is:

1. A method of assembling an aircraft structure assembly composed of a plurality of sections including first and second frame sections, an interconnecting frame section and a plurality of structural mating sections, the method comprising without use of any of shimming, locating fixtures and final-hole-size drill jigs:
supporting the first and second frame sections on respective adjustable supports positioned to align the first and second frame sections in a spaced-apart relationship at a predetermined distance from each other corresponding to a length of the interconnecting frame section;
positioning the interconnecting frame section between the first and second frame sections;
aligning first pre-drilled mating holes in the interconnecting frame section with first pre-drilled mating holes in the first and second frame sections, the first pre-drilled mating holes being pre-drilled to a final hole size corresponding to first fasteners, and installing the first fasteners through the aligned, first pre-drilled mating holes without the use of locating fixtures for positioning and securing the interconnecting frame section and the first and second frame sections; and
for each structural mating section of the plurality of structural mating sections:
positioning the structural mating section relative to the first and second frame sections and the interconnecting frame section; and
aligning second pre-drilled mating holes in the structural mating section with second pre-drilled mating holes in at least one of the interconnecting frame section, first frame section or second frame section, and installing second fasteners through the aligned, second pre-drilled mating holes to secure the structural mating section,

wherein the plurality of structural mating sections that are positioned relative to the first and second frame sections and the interconnection frame section are assembled inwardly from the first and second frame sections that form an outer perimeter structure of the aircraft structure assembly.

2. The method of claim 1 further comprising positioning the adjustable supports at baseline positions for positioning and aligning the first and second frame sections in the spaced-apart relationship, the adjustable supports being positioned using a laser metrology system.

3. The method of claim 1 further comprising numerically-controlled machining at least two of the plurality of sections based on respective three-dimensional geometry models thereof, the at least two of the plurality of sections in the respective three-dimensional models having an identical mating surface feature profile such that the at least two of the plurality of sections are machined to have an identical mating surface feature profile.

4. The method of claim 1 , wherein the structural mating section is positioned, the second pre-drilled mating holes are aligned and the second fasteners are installed through the aligned, second pre-drilled mating holes, for the plurality of structural mating sections to assemble the aircraft structure assembly inwardly from the first and second frame sections that form the outer perimeter structure thereof.

5. The method of claim 1 , wherein the first and second frame sections are respectively leading edge and aft frame sections, and the interconnecting frame section includes inner and outer span-wise sections, and
wherein positioning the interconnecting frame section includes positioning the inner and outer span-wise sections between the leading edge and aft frame sections without use of any shimming, locating fixtures and final-hole-size drill jigs.

6. The method of claim 1 , wherein the first pre-drilled mating holes are pre-drilled prior to alignment of the first pre-drilled mating holes, the first pre-drilled mating holes being pre-drilled to a nominal hole diameter that is a final hole size for a class hole diameter corresponding to the first fasteners, such that installing the first fasteners includes inserting the first fasteners through the aligned, first pre-drilled mating holes without use of locating fixtures for positioning and securing the interconnecting frame section and first and second frame sections relative to each other.

7. The method of claim 1 , wherein the second pre-drilled mating holes are pre-drilled prior to alignment of the second pre-drilled mating holes, the second pre-drilled mating holes being pre-drilled to a nominal hole diameter that is a final hole size for a class hole diameter corresponding to the second fasteners, such that installing the second fasteners includes inserting the second fasteners through the aligned, second pre-drilled mating holes without use of locating fixtures for positioning and securing the structural mating section and the at least one of the interconnecting frame section, first frame section or second frame section relative to each other.

8. A method of assembling an aircraft wing assembly composed of a plurality of sections including leading edge and aft frame sections, inner and outer span-wise sections and a plurality of internal structural members, the method comprising without use of any of locating fixtures for alignment of the plurality of sections and final-hole-size drill jigs for drilling holes:
supporting the leading edge and aft frame sections on respective adjustable supports positioned to align the leading edge and aft frame sections in a spaced-apart relationship at a predetermined distance from each other corresponding to lengths of the inner and outer span-wise sections;
positioning the inner and outer span-wise sections between the leading edge and aft frame sections;
aligning first pre-drilled mating holes in the inner and outer span-wise sections with first pre-drilled mating holes in the leading edge and aft frame sections, the first pre-drilled mating holes being pre-drilled to a final hole size corresponding to first fastners, and installing the first fasteners through the aligned, first pre-drilled mating holes without the use of locating fixtures for positioning and securing the inner and outer span-wise sections and the leading edge and aft frame sections, to thereby form an outer perimeter structure of the aircraft wing assembly; and
for each internal structural member of the plurality of internal structural members:
positioning the internal structural member within the outer perimeter structure;
aligning second pre-drilled mating holes in the internal structural member with second pre-drilled mating holes in at least one of another internal structural member of the plurality of internal structural members, the inner span-wise section or the outer span-wise section, and installing second fasteners through the aligned, second pre-drilled aligned holes to secure the internal structural member,

wherein the plurality of internal structural members that are positioned relative to the leading edge and aft frame sections and the inner and outer span-wise sections are assembled inwardly from the leading edge and aft frame sections that form the outer perimeter structure of the aircraft wing assembly.

9. The method of claim 8 , wherein each of the plurality of internal structural members includes a main spar, and for each of the plurality of internal structural members including the main spar, positioning the internal structural member and aligning second pre-drilled mating holes comprises:
positioning the main spar within the outer perimeter structure; and
aligning second pre-drilled mating holes in the main spar with second pre-drilled mating holes in at least one of another internal structural member of the plurality of internal structural members, the inner span-wise section or the outer span-wise section, and installing the second fa

Assignees

• Boeing Co

Inventors

• Turner David Ray
• Erion Donald L
• Finchamp Teresa M
• Goodman Gregory Jon

Classifications

• G05B19/4097

  characterised by using design data to control NC machines, e.g. CAD/CAM (G05B19/4093 takes precedence) · CPC title

• B64F5/10 Primary

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

• B23P2700/01

  Aircraft parts · CPC title

• Y10T29/49948

  Multipart cooperating fastener [e.g., bolt and nut] · CPC title

• Y10T29/49956

  Riveting · CPC title