Patent US3941335A successfully refreshed from Google Patents.
US3941335A
Expired / Lapsed
US
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Automatic boundary layer control in an ejector wing aircraft
Assignee: United States Department of the Air Force
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Filing: 1975-06-19
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Granted: 1976-03-02
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Expires: 1995-06-19
Abstract
Abstract An ejector wing, for an aircraft, having inlet and diffuser doors which move from an open take-off configuration to a closed forward flight configuration and having hypermixing nozzles and root nozzles for supplying primary air into a plurality of channels in the wing structure. Apparatus is provided for controlling the air flow from the root nozzles in the boundary layer in the channels. A plurality of sensing ports are provided in the channels upstream of the root nozzles. The differential pressures at the sensing ports are used to divide the flow to the root nozzles on opposite sides of the channels.
Inventors
- 👤 Hermann Viets
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 19:35
CPC Classifications
B; B64; B64C; B64C21/00; B64C21/02; B64C21/025; B64C2230/00; B64C2230/06; B64C2230/20; Y; Y02; Y02T; Y02T50/00; Y02T50/10; Y10; Y10T; Y10T137/00; Y10T137/0536; Y10T137/0645
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
135 words
In an aircraft ejector wing having a plurality of spar members with air flow thrust channel being formed between pairs of spar members; means for providing closable inlets to said flow thrust channels; means for providing closable outlet diffuser doors for said thrust channels; means for providing a primary air flow through said thrust channels to thereby entrain a secondary flow through the thrust channels; said means for providing a primary air flow including a plurality of nozzles adapted to provide a flow of air into the boundary layer adjacent the opposite sides of said thrust channels; a plurality of pressure sensing ports in said thrust channels upstream of said nozzles; means responsive to the pressure at said sensing ports for controlling the flow from said nozzles into the boundary layer in said thrust channels.
Claim 2
Dependent Claim
135 words
In an aircraft ejector wing having a plurality of spar members with air flow thrust channel being formed between pairs of spar members; means for providing closable inlets to said flow thrust channels; means for providing closable outlet diffuser doors for said thrust channels; means for providing a primary air flow through said thrust channels to thereby entrain a secondary flow through the thrust channels; said means for providing a primary air flow including a plurality of nozzles adapted to provide a flow of air into the boundary layer adjacent the opposite sides of said thrust channels; a plurality of pressure sensing ports in said thrust channels upstream of said nozzles; means responsive to the pressure at said sensing ports for controlling the flow from said nozzles into the boundary layer in said thrust channels.
Claim 3
Dependent Claim
148 words
The device as recited in claim 1 wherein said means for providing a primary air flow through said thrust channels includes a plurality of hypermixing nozzles and a plurality of root nozzles, located between the hypermixing nozzles; said root nozzles being the nozzles adapted to provide a flow of air into the boundary layer adjacent the opposite side of said thrust channels; means for supplying an air flow through said spar members to said hypermixing nozzles; tubular air supply means within said spar members for supplying air to said root nozzles; said means for controlling the flow from said nozzles including means for directing a flow of air into the tubular air supply means for the root nozzles on opposite sides of each thrust channel as a function of the pressure difference at the sensing ports upstream of the root nozzles on opposite sides of each thrust channel.
Claim 4
Dependent Claim
167 words
The device as recited in claim 2 wherein said means for directing a flow of air into the tubular air supply means includes a fluidic control device for each thrust channel; means for supplying an air flow to the fluidic control devices; each of said fluidic control devices having first output channels connected to the tubular air supply means on one side of said thrust channels and second output channel connected to the tubular air supply means on the opposite sides of said thrust channels; each of said fluidic control devices having a flow splitter between said first output channel and the second output channel; each of said fluidic control devices having a pair of control ports connected to the sensing ports on opposite sides of said thrust channels, for controlling the flow between the first output channels and the second output channels of the fluidic control devices as a function of the pressure difference at the sensing ports on the opposite sides of each thrust channel.
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) | 1979-03-02 | 1979-09-01 | 1980-03-02 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1983-03-02 | 1983-09-01 | 1984-03-02 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1987-03-02 | 1987-09-01 | 1988-03-02 | $7700.00 | Window Closed / Lapsed |