US4169749A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Method of making a hollow airfoil
Assignee: United States Department of the Navy
•
Filing: 1977-09-21
•
Granted: 1979-10-02
•
Expires: 1997-09-21
Abstract
Abstract A method of making hollow aircraft rotor blades from laminated material. Anxpandable mandrel is first made from curable materials and then a composite build-up of epoxy material is made by layering a plurality of prepreg plies of curable material over the expandable mandrel. The mandrel and build-up of epoxy materials are then placed in a mold and pressure is applied to expand the mandrel which, in turn, expands the build-up of material against the mold. The mandrel and composite build-up of material are then cured and the mandrel becomes an integral part of the rotor blade.
Inventors
- 👤 Frank B. Clark
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 13:51
CPC Classifications
B; B29; B29D; B29D99/00; B29D99/0025; B29D99/0028; B29C; B29C33/00; B29C33/0011; B29C33/0016; B29C33/44; B29C33/48; B29C33/485; B29C70/00; B29C70/04; B29C70/28; B29C70/40; B29C70/42; B29C70/44; B29C70/446; B64; B64C; B64C27/00; B64C27/32; B64C27/46; B64C27/473; B29C43/00; B29C43/02; B29C43/10; B29C43/12; B64C2027/4733; B64C2027/4736
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
139 words
A method of making a section of a hollow aircraft rotor blade comprising the steps of: forming a hollow expandable mandrel by connecting an upper skin panel, a lower skin panel, a leading edge channel and an aft channel, said panels and channels being of resin reinforced curable materials which are cemented together, then laying a plurality of prepreg plies of curable material onto said hollow expandable mandrel to form a composite build-up, then placing said hollow expandable mandrel with said plurality of prepreg plies thereon in a female mold, then placing a pressure diaphragm inside said hollow mandrel which applies pressure to the inside of said hollow mandrel which, in turn, expands and transmits uniform pressure to said composite build-up, then curing said mandrel and build-up whereby said mandrel becomes an integral part of said aircraft rotor blade.
Claim 2
Independent Claim
139 words
A method of making a section of a hollow aircraft rotor blade comprising the steps of: forming a hollow expandable mandrel by connecting an upper skin panel, a lower skin panel, a leading edge channel and an aft channel, said panels and channels being of resin reinforced curable materials which are cemented together, then laying a plurality of prepreg plies of curable material onto said hollow expandable mandrel to form a composite build-up, then placing said hollow expandable mandrel with said plurality of prepreg plies thereon in a female mold, then placing a pressure diaphragm inside said hollow mandrel which applies pressure to the inside of said hollow mandrel which, in turn, expands and transmits uniform pressure to said composite build-up, then curing said mandrel and build-up whereby said mandrel becomes an integral part of said aircraft rotor blade.
Claim 3
Dependent Claim
39 words
A method of making a section of a hollow aircraft rotor blade as set forth in claim 1 wherein said upper skin panel, lower skin panel, leading edge channel and aft channel are cemented with heat curing epoxy adhesive.
Claim 4
Dependent Claim
54 words
A method of making a section of a hollow aircraft rotor blade as set forth in claim 1 wherein said upper skin panel, lower skin panel, leading edge channel and aft channel are comprised of epoxy laminate, "S" glass reinforced materials which are partially cured to an advanced "B" stage with heat and pressure.
Claim 5
Dependent Claim
34 words
A method of making a section of a hollow aircraft rotor blade as set forth in claim 1 wherein said plurality of prepreg plies of curable material are of epoxy laminate, "S" glass reinforced.
Claim 6
Dependent Claim
46 words
A method of making a section of a hollow aircraft rotor blade as set forth in claim 1 wherein said female mold with said composite build-up, said expandable mandrel and said pressure diaphragm therein are vacuum bagged so that autoclave pressure is exerted on said diaphragm.
Claim 7
Dependent Claim
39 words
A method of making a section of a hollow aircraft rotor blade as set forth in claim 5 wherein said composite build-up and said expandable mandrel are cured at a temperature of about 350 degrees F. at autoclave pressure.
References Cited (Backward Citations)
US1504547A
Cited
US2202042A
Cited
US2202014A
Cited
DE732923C
Cited
US3138506A
Cited
US3330550A
Cited
US3967996A
Cited
US3988103A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-10-01 | 1983-04-02 | 1983-10-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-10-01 | 1987-04-02 | 1987-10-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-10-01 | 1991-04-02 | 1991-10-02 | $7700.00 | Window Closed / Lapsed |