Method and apparatus for the application of frame to fuselage pull-up force via fuselage skin waterline tensioning

Patent metadata

Field	Value
Publication number	US-11866201-B2
Application number	US-202217735426-A
Country	US
Kind code	B2
Filing date	May 3, 2022
Priority date	May 3, 2022
Publication date	Jan 9, 2024
Grant date	Jan 9, 2024

Abstract

A device to assemble a skin and a frame of an aircraft fuselage. The device includes first and second brace members that extend along opposing sides of a gap. Arches are spaced apart and fixedly connected to the first and second brace members and that extend across the gap. A strongback is attached to and movable along the first and second brace members with the strongback having a curved shape that matches the plurality of arches. The strongback includes clamps configured to engage with the frame. First and second tension devices apply tension to the skin at the strongback.

First claim

What is claimed is:

1. A method of assembling a skin and a frame of an aircraft fuselage, the method comprising:
aligning the skin on a support platform and contacting the support platform against the skin at a first number of points;
attaching the frame to the skin at limited points along the frame comprising attaching an apex of the frame to the skin at a first point and lateral sides of the frame to the skin at second and third points and with a remainder of the frame being unattached to the skin;
moving a strongback along the support platform and engaging the strongback to the frame;
reducing the contact between the skin and the support platform; and
while the contact is reduced, applying tension to the skin at the frame.

2. The method of claim 1 , wherein aligning the skin on the support platform comprises connecting a leading edge of the skin to a first indexing member at a first end of the support platform and a connecting a trailing edge of the skin to a second indexing member at a second end of the support platform.

3. The method of claim 1 , further comprising detaching the lateral sides of the frame from the skin at the second and third points after engaging the strongback to the frame and prior to applying the tension to the skin.

4. The method of claim 1 , further comprising engaging the strongback to the frame while the frame is attached to the skin at the limited points.

5. The method of claim 1 , further comprising:
extending fingers of the support platform into contact with the skin;
engaging the strongback to the frame while the fingers are in contact with the skin; and
retracting the fingers away from the skin and then applying the tension to the skin.

6. The method of claim 1 , further comprising applying the tension to the skin while the skin is attached to the frame at just a single connector at the apex of the frame.

7. The method of claim 1 , wherein applying the tension to the skin at the frame comprises applying the tension at sides of the skin.

8. A method of assembling a skin and a frame of an aircraft fuselage, the method comprising:
aligning the skin relative to a support platform with the skin comprising an arched shaped with a midpoint and opposing lateral sides that terminate at an outer edge;
supporting the skin at arches that are spaced apart along a length of the support platform;
securing the skin to the frame with connectors at the midpoint and at each of the lateral sides;
translating a strongback that is secured to the support platform along the support platform and into contact with the frame;
engaging the strongback with the frame;
after engaging the frame, removing the connectors at the lateral sides; and
applying tension to the skin at the lateral sides of the skin with the tension being applied at the frame.

9. The method of claim 8 , further comprising applying the tension to the skin at just the frame.

10. The method of claim 8 , wherein aligning the skin relative to the support platform comprises connecting a first tab on a forward end of the skin to a first one of the arches on the support platform and connecting a second tab on a rear end of the skin to a second one of the arches on the support platform.

11. The method of claim 8 , wherein engaging the strongback with the frame comprises engaging clamps on the strongback to the frame.

12. The method of claim 8 , further comprising securing the skin to the frame at just an apex of the frame while applying the tension to the skin.

13. The method of claim 8 , further comprising securing the strongback to the support platform after engaging the strongback with the frame and prior to applying the tension.

14. A method of assembling a skin and a frame of an aircraft fuselage, the method comprising:
aligning the skin relative to a support platform;
supporting the skin at arches that are spaced apart along the support platform;
connecting the skin to the frame at limited points along the skin with the limited points comprising a first connection within a central section that includes an apex, a second connection within first lateral section that extends between the central section and a first end of the skin, and a third connection within a second lateral section that extends between the central section and a second end of the skin;
connecting a strongback that is movably connected to the support platform to the frame;
after connecting the strongback to the frame, removing the second and third connections and applying tension to the skin at the frame.

15. The method of claim 14 , further comprising spacing the strongback away from the frame while connecting the skin to the frame.

16. The method of claim 14 , further comprising connecting the skin to the frame with a first connector at the first connection, with a second connector at the second connection, and with a third connector at the third connection.

17. The method of claim 14 , further comprising positioning the first connection at the apex of the frame.

18. The method of claim 14 , further comprising applying the tension to the skin while the skin is attached to the frame at just the apex of the frame.

19. The method of claim 14 , further comprising applying the tension to the skin at just the frame.

20. The method of claim 14 , further comprising moving the strongback along the support platform and into contact with the frame prior to applying the tension.

Assignees

• Boeing Co

Inventors

• Mejia Santiago
• Macko Patrick James
• Autry Byron James
• Werntges Paul Gabriel
• Smotherman Larry Scott
• Raines David
• Murphy Sara

Classifications

• B64F5/10 Primary

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

• B23P2700/01

  Aircraft parts · CPC title

• B64C1/061

  Frames · CPC title

• B64C1/068

  Fuselage sections · CPC title

• B64C1/12

  Construction or attachment of skin panels · CPC title