US4171785A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Apparatus and method for manufacturing laminar flow control aircraft structure
Assignee: Boeing Co
•
Filing: 1977-06-30
•
Granted: 1979-10-23
•
Expires: 1997-06-30
Abstract
Abstract A method for manufacturing a laminar flow control aircraft structure, typically a wing or other aerodynamic surface, having an outer skin in which a plurality of spanwise oriented and chordwise spaced recesses have been machined. The method includes the installation of a strip of slot assembly tape in each of said recesses, preferably with an adhesive, and the removal of an element of the tape called a cover plate to expose a spanwise slot through which boundary layer air can be drawn. Also disclosed is a slot assembly tape having a protective cover plate and a pair of sidewalls, and a laminar flow control aircraft structure, typically a wing, in which the slot assembly tape has been employed.
Inventors
- 👤 Jack M. Isenberg
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 18:34
CPC Classifications
B; B64; B64C; B64C3/00; B64C3/26
Claims Analysis
Total Claims: 10
Claim 1
Independent Claim
81 words
A method for manufacturing a laminar flow control structure for an aircraft, said method comprising the steps of: providing an outer skin including an outer surface exposed to airflow and defining a spanwise recess therein; providing a slot assembly tape including a pair of sidewalls removably attached to a cover plate; positioning said slot assembly tape over said recess; bonding said pair of sidewalls within said recess with a first adhesive; and stripping away said cover plate to expose said sidewalls.
Claim 2
Independent Claim
81 words
A method for manufacturing a laminar flow control structure for an aircraft, said method comprising the steps of: providing an outer skin including an outer surface exposed to airflow and defining a spanwise recess therein; providing a slot assembly tape including a pair of sidewalls removably attached to a cover plate; positioning said slot assembly tape over said recess; bonding said pair of sidewalls within said recess with a first adhesive; and stripping away said cover plate to expose said sidewalls.
Claim 3
Dependent Claim
13 words
The method of claim 1 wherein said first adhesive is a pressure-sensitive adhesive.
Claim 4
Dependent Claim
74 words
A method for manufacturing a laminar flow control structure as in claim 1 including the additional steps of: forming said slot assembly tape by providing a strip of stiff material and bonding said strip of stiff material to a first portion of a lower surface of said cover plate with a second adhesive; and cutting a slot completely through said strip of material to form said pair of sidewalls, each having a lower surface.
Claim 5
Dependent Claim
12 words
The method of claim 3 wherein said slot is of uniform width.
Claim 6
Dependent Claim
24 words
The method of claim 3 further including the step of applying a layer of a third adhesive to the lower surface of each sidewall.
Claim 7
Dependent Claim
26 words
The method of claim 3 further including the step of applying a parting agent to a second portion of said lower surface of said cover plate.
Claim 8
Independent Claim
97 words
A method for manufacturing a laminar flow control structure for an aircraft, said structure including an outer surface having a plurality of spanwise recesses therein, comprising the steps of: bonding a metal strip of stiff material to a first portion of a lower surface of a cover plate with a first adhesive; cutting a slot completely through said metal strip to form a pair of spaced sidewalls; positioning said pair of sidewalls within an associated spanwise recess using said cover plate as a guide; and bonding said pair of sidewalls within said recess with a second adhesive.
Claim 9
Independent Claim
97 words
A method for manufacturing a laminar flow control structure for an aircraft, said structure including an outer surface having a plurality of spanwise recesses therein, comprising the steps of: bonding a metal strip of stiff material to a first portion of a lower surface of a cover plate with a first adhesive; cutting a slot completely through said metal strip to form a pair of spaced sidewalls; positioning said pair of sidewalls within an associated spanwise recess using said cover plate as a guide; and bonding said pair of sidewalls within said recess with a second adhesive.
Claim 10
Dependent Claim
19 words
The method of claim 7 further including the step of stripping away said cover plate to expose said sidewalls.
References Cited (Backward Citations)
US2746893A
Cited
US3117751A
Cited
US3298850A
Cited
US3276933A
Cited
US3279969A
Cited
US3475259A
Cited
US3521837A
Cited
US3473218A
Cited
US3810812A
Cited
US3598689A
Cited
US3592722A
Cited
US3985602A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1982-10-22 | 1983-04-23 | 1983-10-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1986-10-22 | 1987-04-23 | 1987-10-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1990-10-22 | 1991-04-23 | 1991-10-23 | $7700.00 | Window Closed / Lapsed |