Adhesively Joining Airframe Members at Solid Insert

• US 20170259904A1
• Filed: 05/22/2017
• Published: 09/14/2017
• Est. Priority Date: 02/08/2016
• Status: Active Grant

• Current Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Original Assignee: Bell Helicopter Textron Incorporated (Textron Inc)
• Inventors: Kooiman, James Everett, Decker, George Ryan, Stanney, Keith Alan, Chris, Robert Mark
• Granted Patent: US 10,450,054 B2
• Time in Patent Office: Days
• CPC Class Codes: B29C 70/00 Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
• CPC Class Codes: B29D 24/005 the structure having joined ribs, e.g. honeycomb
• CPC Class Codes: B29D 99/0021 provided with plain or filled structures, e.g. cores, placed between two or more plates or sheets, e.g. in a matrix
• CPC Class Codes: B32B 2305/024 Honeycomb
• CPC Class Codes: B32B 2305/34 Inserts
• CPC Class Codes: B32B 2605/18 Aircraft
• CPC Class Codes: B64C 29/0033 the propellers being tiltable relative to the fuselage
• CPC Class Codes: B64C 3/18 Spars; Ribs; Stringers
• CPC Class Codes: B64C 3/187 Ribs
• CPC Class Codes: B64C 3/26 Construction, shape, or attachment of separate skins, e.g. panels

Abstract

An airframe assembly for an aircraft. The airframe assembly includes a first airframe member having a first skin, a second skin, a large cell core joined between the first and second skins and a solid insert having a side surface. The solid insert is joined between the first and second skins such that at least a portion of the side surface is adjacent to the large cell core. The first skin has a first surface disposed opposite the solid insert. The airframe assembly also includes a second airframe member having a second surface. An adhesive joint is disposed between the first and second surfaces structurally bonding the first airframe member to the second airframe member such that the second airframe member is positioned opposite the solid insert.

Claims

1. An airframe assembly for an aircraft comprising:

a first airframe member having a first skin, a second skin, a large cell core joined between the first and second skins and a solid insert having a side surface, the solid insert joined between the first and second skins such that at least a portion of the side surface is adjacent to the large cell core, the first skin having a first surface disposed opposite the solid insert;

a second airframe member having a second surface; and

an adhesive joint disposed between the first and second surfaces structurally bonding the first airframe member to the second airframe member such that the second airframe member is positioned opposite the solid insert.

2. The airframe assembly as recited in claim 1 wherein the large cell core is joined to the adjacent portion of the side surface of the solid insert.

3. The airframe assembly as recited in claim 1 wherein the large cell core is selected from the group consisting of large cell composite cores and large cell carbon cores.

4. The airframe assembly as recited in claim 1 wherein the first skin, the second skin and the solid insert further comprise a material selected from the group consisting of composite materials and carbon composite materials.

5. The airframe assembly as recited in claim 1 wherein the first skin, the second skin and the solid insert have generally matching coefficients of thermal expansion.

6. The airframe assembly as recited in claim 1 wherein the large cell core and the solid insert are structurally bonded between the first and second skins.

7. The airframe assembly as recited in claim 1 wherein the large cell core is structurally bonded to the adjacent portion of the side surface of the solid insert.

8. A wing assembly for an aircraft comprising:

a wing skin having an inner skin member, an outer skin member, a large cell core joined between the inner and outer skin members and a solid insert having a side surface, the solid insert joined between the inner and outer skin members such that at least a portion of the side surface is adjacent to the large cell core, the inner skin member having a first surface disposed opposite the solid insert;

a rib having a second surface; and

an adhesive joint disposed between the first and second surfaces structurally bonding the rib to the inner skin member of the wing skin such that the rib is positioned opposite the solid insert.

9. The wing assembly as recited in claim 8 wherein the large cell core is joined to the adjacent portion of the side surface of the solid insert.

10. The wing assembly as recited in claim 8 wherein the large cell core is selected from the group consisting of large cell composite cores and large cell carbon cores.

11. The wing assembly as recited in claim 8 wherein the inner skin member, the outer skin member and the solid insert further comprise a material selected from the group consisting of composite materials and carbon composite materials.

12. The wing assembly as recited in claim 8 wherein the inner skin member, the outer skin member and the solid insert have generally matching coefficients of thermal expansion.

13. The wing assembly as recited in claim 8 wherein the large cell core and the solid insert are structurally bonded between the inner and outer skin members.

14. The wing assembly as recited in claim 8 wherein the large cell core is structurally bonded to the adjacent portion of the side surface of the solid insert.

15. An aircraft comprising:

a first airframe member having a first skin, a second skin, a large cell core joined between the first and second skins and a solid insert having a side surface, the solid insert joined between the first and second skins such that at least a portion of the side surface is adjacent to the large cell core, the first skin having a first surface disposed opposite the solid insert;

a second airframe member having a second surface; and

an adhesive joint disposed between the first and second surfaces structurally bonding the first airframe member to the second airframe member such that the second airframe member is positioned opposite the solid insert.

16. The aircraft as recited in claim 15 wherein the large cell core is joined to the adjacent portion of the side surface of the solid insert.

17. The aircraft as recited in claim 15 wherein the large cell core is selected from the group consisting of large cell composite cores and large cell carbon cores.

18. The aircraft as recited in claim 15 wherein the first skin, the second skin and the solid insert further comprise a material selected from the group consisting of composite materials and carbon composite materials.

19. The aircraft as recited in claim 15 wherein the first skin, the second skin and the solid insert have generally matching coefficients of thermal expansion.

20. The aircraft as recited in claim 15 wherein the large cell core and the solid insert are structurally bonded between the first and second skins.

21. The aircraft as recited in claim 15 wherein the large cell core is structurally bonded to the adjacent portion of the side surface of the solid insert.