US4687691A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Honeycomb spliced multilayer foam core aircraft composite parts and method for making same
Assignee: RTX Corp
•
Filing: 1986-04-28
•
Granted: 1987-08-18
•
Expires: 2006-04-28
Abstract
Abstract Aircraft composite components having foam cores comprising at least two foam sheets joined with a sheet of honeycomb to form a foam-honeycomb-foam sandwich. The layers of sheet foam are in contact with each other and the honeycomb cells extend a substantially equal depth into and generally perpendicular to the sheet foam layers. The composite component has increased shear strength. The aircraft composite component can be made by aligning a layer of honeycomb between and generally perpendicular to two layers of sheet foam. A compressive force is applied generally perpendicular to at least one layer of sheet foam so that the honeycomb cells penetrate each of the two layers of sheet foam to a substantially equal depth so that the layers of foam contact each other to form a foam-honeycomb-foam sandwich. The foam core is surrounded by resin impregnated fibers and cured.
Inventors
- 👤 Bruce F. Kay
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 19:55
CPC Classifications
B; B32; B32B; B32B3/00; B32B3/10; B32B3/12; B29; B29C; B29C44/00; B29C44/02; B29C44/12; B29C44/1266; B29C44/18; B29C44/186; B32B5/00; B32B5/18; B32B7/00; B32B7/02; B32B7/022; B64; B64C; B64C27/00; B64C27/32; B64C27/46; B64C27/473; B64C3/00; B64C3/20; E; E04; E04C; E04C2/00; E04C2/02; E04C2/10; E04C2/20; E04C2/205; B32B2266/00; B32B2266/08; B32B2305/00; B32B2305/02; B32B2305/024; B32B2307/00; B32B2307/70; B32B2307/718; B32B2605/00; B32B2605/18; B64C2027/4733; B64C2027/4736; Y; Y10; Y10T; Y10T156/00; Y10T156/10; Y10T156/1052; Y10T156/1056; Y10T428/00; Y10T428/23; Y10T428/234; Y10T428/236; Y10T428/239; Y10T428/24; Y10T428/24149; Y10T428/24157; Y10T428/24273; Y10T428/24322; Y10T428/24331; Y10T428/24942; Y10T428/24992; Y10T428/249921; Y10T428/249953; Y10T428/249978; Y10T428/24998; Y10T428/249981
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
131 words
Aircraft composite components, comprising a composite skin surrounding a foam core wherein the improvement comprises: a. said foam core comprising alternating layers of at least two layers of sheet foam and at least one layer of honeycomb having cells; b. said honeycomb layer having a greater compressive strength than said layers of sheet foam; c. said layers of sheet foam having substantially equal compressive strength; d. said layers of sheet foam in contact with each other at least through each of the honeycomb openings; and e. said layer of honeycomb cells extending a substantially equal depth into and generally perpendicular to each of said two layers of sheet foam but not penetrating entirely through said sheet foam layers to form a foam-honeycomb-foam sandwich; wherein the composite component has increased shear strength.
Claim 2
Dependent Claim
131 words
Aircraft composite components, comprising a composite skin surrounding a foam core wherein the improvement comprises: a. said foam core comprising alternating layers of at least two layers of sheet foam and at least one layer of honeycomb having cells; b. said honeycomb layer having a greater compressive strength than said layers of sheet foam; c. said layers of sheet foam having substantially equal compressive strength; d. said layers of sheet foam in contact with each other at least through each of the honeycomb openings; and e. said layer of honeycomb cells extending a substantially equal depth into and generally perpendicular to each of said two layers of sheet foam but not penetrating entirely through said sheet foam layers to form a foam-honeycomb-foam sandwich; wherein the composite component has increased shear strength.
Claim 3
Dependent Claim
62 words
The aircraft composite components as recited in claim 1 wherein said sheet foam is about 0.4 inch to about 4 inches in thickness and said cells are about 0.0625 inch to about 1 inch in thickness and said layer of honeycomb cells extend a depth of about 0.2 inch to about 1 inch into each of said two layers of sheet foam.
Claim 4
Independent Claim
163 words
A method of making an aircraft composite component comprising joining at least two foam sheets to make a foam core, surrounding the foam core with resin impregnated fibers, and curing said resin impregnated fibers wherein the improvement comprises joining said foam sheets by a. aligning a layer of honeycomb having cells so that said cells are between and generally perpendicular to two layers of sheet foam, and said honeycomb cells having a compressive strength greater than that of the sheet foam; and b. applying a compressive force generally perpendicular to at least one layer of sheet foam so that the honeycomb cells pentrate each of the two layers of sheet foam to a substantially equal depth where said layers of foam contact each other at least through each of the honeycomb openings to form a foam-honeycomb-foam sandwich said honeycomb not penetrating entirely through said foam sheets; resulting in a composite component that has increased shear strength in comparison to adhesively bonded foam sheets.
Claim 5
Independent Claim
163 words
A method of making an aircraft composite component comprising joining at least two foam sheets to make a foam core, surrounding the foam core with resin impregnated fibers, and curing said resin impregnated fibers wherein the improvement comprises joining said foam sheets by a. aligning a layer of honeycomb having cells so that said cells are between and generally perpendicular to two layers of sheet foam, and said honeycomb cells having a compressive strength greater than that of the sheet foam; and b. applying a compressive force generally perpendicular to at least one layer of sheet foam so that the honeycomb cells pentrate each of the two layers of sheet foam to a substantially equal depth where said layers of foam contact each other at least through each of the honeycomb openings to form a foam-honeycomb-foam sandwich said honeycomb not penetrating entirely through said foam sheets; resulting in a composite component that has increased shear strength in comparison to adhesively bonded foam sheets.
Claim 6
Dependent Claim
69 words
The method of making an aircraft composite component as recited in claim 3 wherein said layer of honeycomb is about 0.0625 inch to about 1 inch in thickness and said layer of sheet foam is about 0.4 inch to about 4 inches in thickness and said honeycomb cells penetrate each of said layers of sheet foam to a substantially equal depth of about 0.2 inch to about 1 inch.
Claim 7
Independent Claim
191 words
A method of making an aircraft composite component comprising joining at least two foam sheets to make a foam core, surrounding the foam core with resin impregnated fibers, and curing said resin impregnated fibers wherein the improvement comprises joining said foam sheets by a. aligning a layer of honeycomb having cells so that the cells are generally perpendicular to a first layer of sheet foam; b. applying a compressive force generally perpendicular to said layer of sheet foam so that the honeycomb cells penetrate said layer of sheet foam; c. aligning a second layer of sheet foam, having a compressive strength substantially less than said first layer, generally perpendicular so said layer of honeycomb against said honeycomb layer's exposed side; and d. applying a compressive strength generally perpendicular to at least one layer of sheet foam so that the honeycomb cells penetrate said layers of sheet foam to a depth where said layers of foam contact each other at least through each of the honeycomb openings to form a foam-honeycomb-foam sandwich said honeycomb not in contact with said resin impregnated fibers; resulting in a composite component that has increased shear strength.
Claim 8
Independent Claim
191 words
A method of making an aircraft composite component comprising joining at least two foam sheets to make a foam core, surrounding the foam core with resin impregnated fibers, and curing said resin impregnated fibers wherein the improvement comprises joining said foam sheets by a. aligning a layer of honeycomb having cells so that the cells are generally perpendicular to a first layer of sheet foam; b. applying a compressive force generally perpendicular to said layer of sheet foam so that the honeycomb cells penetrate said layer of sheet foam; c. aligning a second layer of sheet foam, having a compressive strength substantially less than said first layer, generally perpendicular so said layer of honeycomb against said honeycomb layer's exposed side; and d. applying a compressive strength generally perpendicular to at least one layer of sheet foam so that the honeycomb cells penetrate said layers of sheet foam to a depth where said layers of foam contact each other at least through each of the honeycomb openings to form a foam-honeycomb-foam sandwich said honeycomb not in contact with said resin impregnated fibers; resulting in a composite component that has increased shear strength.
Claim 9
Dependent Claim
17 words
The aircraft composite component of claim 1 wherein said layers of sheet foam are adhesively bonded together.
Claim 10
Dependent Claim
22 words
The method of making an aircraft composite component of claim 3 wherein said two layers of sheet foam are adhesively bonded together.
Claim 11
Dependent Claim
22 words
The method of making an aircraft composite component of claim 5 wherein said two layers of sheet foam are adhesively bonded together.
Claim 12
Dependent Claim
115 words
Aircraft composite comopnents, comprising a composite skin surrounding foam core wherein the improvement comprises: a. said foam core comprising alternating layers of at least two layers of sheet foam and at least one layer of honeycomb having cells; b. said honeycomb layer having a greater compressive strength than said layers of sheet foam; c. said layers of sheet foam in contact with each other at least through each of the honeycomb openings; and d. said layer of honeycomb cells extending into and generally perpendicular to each of said two layers of sheet foam but not penetrating entirely through said sheet foam layer to form a foam-honeycomb-foam sandwich; wherein the composite component has increased shear strength.
Claim 13
Dependent Claim
115 words
Aircraft composite comopnents, comprising a composite skin surrounding foam core wherein the improvement comprises: a. said foam core comprising alternating layers of at least two layers of sheet foam and at least one layer of honeycomb having cells; b. said honeycomb layer having a greater compressive strength than said layers of sheet foam; c. said layers of sheet foam in contact with each other at least through each of the honeycomb openings; and d. said layer of honeycomb cells extending into and generally perpendicular to each of said two layers of sheet foam but not penetrating entirely through said sheet foam layer to form a foam-honeycomb-foam sandwich; wherein the composite component has increased shear strength.
Claim 14
Dependent Claim
19 words
The aircraft composite component as recited in claim 9 wherein said layers of sheet foam are adhesively bonded together.
References Cited (Backward Citations)
US3249659A
Cited
US3578526A
Cited
US3650863A
Cited
US4042746A
Cited
US3998219A
Cited
US4132042A
Cited
US4351870A
Cited
US4409054A
Cited
US4594120A
Cited
US4598008A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1990-08-17 | 1991-02-16 | 1991-08-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1994-08-17 | 1995-02-16 | 1995-08-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1998-08-17 | 1999-02-16 | 1999-08-18 | $7700.00 | Window Closed / Lapsed |