Method for the joining of wings or control surfaces to an airplane fuselage

Patent metadata

Field	Value
Publication number	US-9856011-B2
Application number	US-201514819792-A
Country	US
Kind code	B2
Filing date	Aug 6, 2015
Priority date	Aug 6, 2015
Publication date	Jan 2, 2018
Grant date	Jan 2, 2018

Abstract

Methods of joining a first aerostructure part with a second aerostructure part are disclosed, for example, methods of joining an airplane wing or control surface to an airplane fuselage or joining fins to a rocket body. The method comprises aligning a plurality of connection elements in a linear array within the second aerostructure part, wherein the connection elements comprise a plurality of flexible connection elements and at least one rigid connection element, and attaching the first aerostructure part to the second aerostructure part at a plurality of connection points with the plurality of connection elements. The second aerostructure part expands linearly at a greater rate when exposed to heat than the first aerostructure part resulting in a difference in linear distance between the first aerostructure part and the second aerostructure part and the flexible connection elements are configured to flex to accommodate for this linear distance difference.

First claim

What is claimed is:

1. A method of joining a first aerostructure part with a second aerostructure part comprising
aligning a plurality of connection elements in a linear array within the second aerostructure part, wherein the connection elements comprise a plurality of flexible connection elements and at least one rigid connection element, wherein the flexible connection elements are flexible plates, and
attaching the first aerostructure part to the second aerostructure part at a plurality of connection points with the plurality of connection elements,
wherein the second aerostructure part expands linearly at a greater rate when exposed to heat than the first aerostructure part resulting in a difference in linear distance between the first aerostructure part and the second aerostructure part, and wherein the flexible connection elements are configured to flex to accommodate for this linear distance difference,
wherein the flexible plates comprise at least two stacks of flexible plates and wherein the flexible plates comprise a flexible spacer between the stacks of plates configured to prevent buckling of the flexible plates.

2. The method of claim 1 , wherein the flexible plates have an “A” shape profile.

3. The method of claim 1 , wherein the first aerostructure part is an airplane fuselage.

4. The method of claim 1 , wherein the second aerostructure part is an airplane wing.

5. The method of claim 1 , wherein the second aerostructure part is a control surface.

6. The method of claim 1 , further comprising positioning the rigid connection element such that the amount of flex in the plurality of flexible connection elements is equalized on both sides of the rigid connection element.

7. The method of claim 4 , further comprising aligning the plurality of flexible connection elements such that the thinnest dimension of the flexible connection element is in a chordwise direction of the airplane wing.

8. The method of claim 1 , wherein the flexible connection elements are flexible in a chordwise direction and rigid in other load directions.

9. The method of claim 1 , wherein the flexible connection elements comprise metallic material.

10. The method of claim 1 , wherein the flexible connection elements comprise ceramic material.

11. A method of joining an airplane wing with an airplane fuselage comprising
aligning a plurality of flexible plates and one rigid connection element in the airplane wing, such that the thinnest part of each flexible plate is aligned with a chordwise direction of the airplane wing and the length of each flexible plate is aligned with a spanwise direction of the airplane wing, and
attaching the wing to the fuselage with the flexible plates and the rigid connection element at a plurality of connection points, wherein the rigid connection element connects the wing to fuselage at a fixed location,
wherein the flexible plates flex to accommodate chordwise expansion of the airplane wing, and wherein the flexible plates resist vertical shear and bending moment, and
wherein the flexible plates comprise at least two stacks of plates and wherein the flexible plates comprise a flexible spacer between the stacks of plates configured to prevent buckling of the flexible plates.

12. The method of claim 11 , further comprising positioning the rigid connection element such that the amount of flex in the plurality of flexible plates is equalized on both sides of the rigid connection element.

13. The method of claim 11 , wherein the airplane wing comprises ceramic matrix composite material and wherein the airplane fuselage comprises metallic materials.

14. The method of claim 11 , wherein the plurality of flexible plates are A-shaped.

Assignees

• Boeing Co

Inventors

• Topf Richard P
• Embler Jonathan D
• Pinney Thomas R

Classifications

• B64C9/02

  Mounting or supporting thereof · CPC title

• B64C1/26

  Attaching the wing or tail units or stabilising surfaces · CPC title

• B64C1/38 Primary

  Constructions adapted to reduce effects of aerodynamic or other external heating · CPC title

• B64C30/00

  Supersonic type aircraft · CPC title

• Y02T50/40

  Weight reduction · CPC title