US4063981A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method of making a composite sandwich lattice structure
Assignee: National Aeronautics and Space Administration
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Filing: 1977-05-20
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Granted: 1977-12-20
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Expires: 1997-05-20
Abstract
Abstract This invention relates to a lattice type structural panel utilizing the unidirectional character of filamentary epoxy impregnated composites to produce stiff lightweight structural panels for use in constructing large area panels for space satellites and the like.
Inventors
- 👤 Marvin D. Rhodes
- 👤 Martin M. Mikulas, Jr.
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 15:24
CPC Classifications
B; B32; B32B; B32B3/00; B32B3/10; B32B3/12; B32B7/00; B32B7/04; B32B7/12; E; E04; E04C; E04C2/00; E04C2/02; E04C2/10; E04C2/20; E04C2/22; E04C2/30; E04C2/34; E04C2/36; B32B2250/00; B32B2250/40; B32B2260/00; B32B2260/02; B32B2260/021; B32B2260/04; B32B2260/046; B32B2262/00; B32B2262/10; B32B2262/106; B32B2305/00; B32B2305/02; B32B2305/024; B32B2305/07; B32B2305/076; B32B2307/00; B32B2307/70; B32B2307/718; B32B2607/00; B32B2607/02; Y; Y10; Y10S; Y10S428/00; Y10S428/902; Y10T; Y10T428/00; Y10T428/23; Y10T428/234; Y10T428/236; Y10T428/24; Y10T428/24149; Y10T428/24273; Y10T428/24322; Y10T428/24331
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
281 words
A method of making a lightweight composite sandwich lattice structrual panel comprising: providing a mold formed of top and bottom halves each of which has an identical matching angular grid groove pattern formed in the surfaces thereof facing each other when the mold halves are assembled, coating the individual grooves in the matching grid patterns with a chemical release agent, providing silicon rubber blankets precut to match the grid pattern in each of the mold halves and positioning these blankets, one each, in the grid grooves of the mold halves, coating each silicon rubber blanket with a chemical release agent, positioning individual strips of prepreg tape over the silicon rubber blankets to form a tape surface in each groove of the grip patterns, providing a honeycomb core sheet having a plurality of honeycomb cells extending transversely therethrough with angular portions of the sheet being removed to provide a lattice network that will mesh with the grid grooves of the top and bottom mold halves, coating the honeycomb core sheet with a bonding adhesive and positioning the top and bottom mold halves to enclose the core sheet therebetween and in contact with the prepreg tape strips, applying pressure to and heating the closed mold at a temperature of approximately 200° F for approximately 15 minutes to bond the honeycomb core and prepreg tapes into a unitary structural panel, removing the unitary structural panel to a vacuum oven and heating the panel under vacuum at a temperature of 355° ± 10° F for a period of 120 ± 5 minutes to effect thermosetting cure of the resin in the prepreg tapes, and recovering a lightweight composite sandwich lattice structural panel from the oven.
Claim 2
Independent Claim
281 words
A method of making a lightweight composite sandwich lattice structrual panel comprising: providing a mold formed of top and bottom halves each of which has an identical matching angular grid groove pattern formed in the surfaces thereof facing each other when the mold halves are assembled, coating the individual grooves in the matching grid patterns with a chemical release agent, providing silicon rubber blankets precut to match the grid pattern in each of the mold halves and positioning these blankets, one each, in the grid grooves of the mold halves, coating each silicon rubber blanket with a chemical release agent, positioning individual strips of prepreg tape over the silicon rubber blankets to form a tape surface in each groove of the grip patterns, providing a honeycomb core sheet having a plurality of honeycomb cells extending transversely therethrough with angular portions of the sheet being removed to provide a lattice network that will mesh with the grid grooves of the top and bottom mold halves, coating the honeycomb core sheet with a bonding adhesive and positioning the top and bottom mold halves to enclose the core sheet therebetween and in contact with the prepreg tape strips, applying pressure to and heating the closed mold at a temperature of approximately 200° F for approximately 15 minutes to bond the honeycomb core and prepreg tapes into a unitary structural panel, removing the unitary structural panel to a vacuum oven and heating the panel under vacuum at a temperature of 355° ± 10° F for a period of 120 ± 5 minutes to effect thermosetting cure of the resin in the prepreg tapes, and recovering a lightweight composite sandwich lattice structural panel from the oven.
Claim 3
Dependent Claim
20 words
The method of claim 1 wherein the prepreg tapes are continuous length graphite fibers embedded in an epoxy resin matrix.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1980-12-19 | 1981-06-20 | 1981-12-20 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1984-12-19 | 1985-06-20 | 1985-12-20 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1988-12-19 | 1989-06-20 | 1989-12-20 | $7700.00 | Window Closed / Lapsed |