US3756542A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Aircraft having an auxiliary lift device
Assignee: Bertin Technologies SAS
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Filing: 1971-05-03
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Granted: 1973-09-04
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Expires: 1991-05-03
Abstract
Abstract An aircraft has at the trailing edge of its wing a liftaugmenter flap towards which there can be directed, in the maximum lift configuration, a fluid stream elongated in the wing span direction and produced by a flat fish-tail jet nozzle disposed below the wing undersurface forwards of and near the lift-augmenter flap, so as to increase the lift by deflection of the elongated fluid stream with a correct flow adhesion of the fluid over the upper surface of the flap. The fish-tail nozzle is subdivided into elementary nozzles producing as many elementary streams of motive gases which contribute to jet propulsion; these elementary nozzles are in the form of slots extending parallel to one another, in the wing span direction and/or right-angles thereto.
Inventors
- 👤 J Bertin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-30 05:49
CPC Classifications
F; F16; F16D; F16D65/00; F16D65/02; F16D65/04; B; B64; B64C; B64C23/00; B64C23/005; F16D69/00; F16D69/04; F16D2069/0425; F16D2069/0441
Claims Analysis
Total Claims: 18
Claim 1
Independent Claim
216 words
An STOL aircraft having at the trailing edge of its wing a lift-augmenter flap system deflectable to lift augmenting position, and a lift-augmenter device designed for producing a fluid stream elongated in the wing span direction and directed to engage said flap system when in said lift augmenting position thereof in order to enhance lift augmentation through aerodynamic action of said fluid stream, said device comprising: a flat fiSh-tail jet nozzle assembly presenting a succession of elementary nozzles spaced substantially parallel to said wing span direction and each in the form of a generally rectangular slot substantially perpendicular to said direction, and an open-ended flat ejector shroud having a forwardly facing air intake end and a rearwardly facing stream discharge end which extends below the wing undersurface at a location forward of said flap system, both said ends being of generally recrangular shape with a major side extending substantially parallel to said wing span direction, said flat ejector shroud surrounding said jet nozzle assembly and forming therewith a flat injector wherein ambient air taken in by said rectangular intake end is induced due to the entraining action of the motive gas issuing from said elementary rectangular slot-like nozzles and mixes with said gas to form said elongated fluid stream which issues from said rectangular discharge end.
Claim 2
Dependent Claim
216 words
An STOL aircraft having at the trailing edge of its wing a lift-augmenter flap system deflectable to lift augmenting position, and a lift-augmenter device designed for producing a fluid stream elongated in the wing span direction and directed to engage said flap system when in said lift augmenting position thereof in order to enhance lift augmentation through aerodynamic action of said fluid stream, said device comprising: a flat fiSh-tail jet nozzle assembly presenting a succession of elementary nozzles spaced substantially parallel to said wing span direction and each in the form of a generally rectangular slot substantially perpendicular to said direction, and an open-ended flat ejector shroud having a forwardly facing air intake end and a rearwardly facing stream discharge end which extends below the wing undersurface at a location forward of said flap system, both said ends being of generally recrangular shape with a major side extending substantially parallel to said wing span direction, said flat ejector shroud surrounding said jet nozzle assembly and forming therewith a flat injector wherein ambient air taken in by said rectangular intake end is induced due to the entraining action of the motive gas issuing from said elementary rectangular slot-like nozzles and mixes with said gas to form said elongated fluid stream which issues from said rectangular discharge end.
Claim 3
Dependent Claim
48 words
An aircraft as claimed in claim 1, wherein said flat fish-tail jet nozzle assembly further comprises a slot-like outlet extending substantially parallel to said wing span direction and intersecting said elementary recrangular slot-like nozzles which extend substantially perpendicular thereto, whereby said jet nozzle assembly is of cruciform pattern.
Claim 4
Dependent Claim
46 words
An aircraft as claimed in claim 2, wherein said flat fish-tail jet nozzle assembly is at least in part pivotable about an axis substantially parallel to said wing span direction, whereby said assembly is effectively orientable in a plane substantially perpendicular to said wing span direction.
Claim 5
Dependent Claim
20 words
An aircraft as claimed in claim 3, wherein said flat fish-tail jet nozzle assembly is bodily pivotable about said axis.
Claim 6
Dependent Claim
59 words
An aircraft as claimed in claim 1, wherein said flat ejector shroud is substantially throughout its longitudinal extension of generally rectangular cross-section and comprises an upper wall and a lower wall opposite each other, which first converge towards each other starting from said rectangular air intake end and then diverge from each other towards said rectangular stream discharge end.
Claim 7
Dependent Claim
31 words
An aircraft as claimed in claim 5, wherein said flat fish-tail jet nozzle assembly and said flat rectangular ejector shroud are separately borne by said wing at chordwise spaced locations thereof.
Claim 8
Dependent Claim
30 words
An aircraft as claimed in claim 6, wherein each of said flat fish-tail nozzle assembly and said flat rectangular ejector shroud is pod-mounted in vertically spaced relation below said wing.
Claim 9
Dependent Claim
22 words
An aircraft as claimed in claim 6, wherein said flat rectangular ejector shroud is fast with and adjacent to said wing undersurface.
Claim 10
Dependent Claim
41 words
An aircraft as claimed in claim 8, further comprising a passage formed through said wing from the oversurface to the undersurface thereof and leading into said flat rectangular ejector shroud, whereby said flat injector sucks ambient air from said wing oversurface.
Claim 11
Dependent Claim
45 words
An aircraft as claimed in claim 5, wherein said flat rectangular ejector shroud further comprises a stream deflector vane pivotable about an axis substantially parallel to said wing span direction and fitted adjacent said rectangular stream discharge end, generally parallel to said major side thereof.
Claim 12
Dependent Claim
26 words
An aircraft as claimed in claim 10, wherein said pivotable stream deflector vane is adjustable to a feathering position causing substantially no deflection of said stream.
Claim 13
Dependent Claim
30 words
An aircraft as claimed in claim 11, wherein said pivotable stream deflector vane, when in said feathering position, forms a streamlined rear extension of at least one of said walls.
Claim 14
Dependent Claim
27 words
An aircraft as claimed in claim 12, wherein said pivotable stream deflector vane, when in said feathering position, forms a streamlined rear extension of said lower wall.
Claim 15
Dependent Claim
30 words
An aircraft as claimed in 12, wherein said pivotable stream deflector vane, when in said feathering position, forms a streamlined rear extension of each of said upper and lower walls.
Claim 16
Dependent Claim
44 words
An aircraft as claimed in claim 14, Wherein each pivotable stream deflector vane is adjustable to a stream deflecting position in which said stream is fractionated into two parts respectively deflected upwards to engage said lift-augmenter flap system and downwards to produce lifting thrust.
Claim 17
Dependent Claim
35 words
An aircraft as claimed in claim 12, wherein said pivotable stream deflector vane is adjustable to a stream deflecting position in which it is dipped right into said stream issuing from said rectangular discharge end.
Claim 18
Dependent Claim
48 words
An aircraft as claimed in claim 12, further comprising a retractable guide blade system fitted under said wing and projectable downwards to an operative position within said stream intermediate said rectangular stream discharge end and said lift-augmenter flap system, said guide blade system being retractable into said wing.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-09-03 | 1977-03-05 | 1977-09-04 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-09-03 | 1981-03-05 | 1981-09-04 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-09-03 | 1985-03-05 | 1985-09-04 | $7700.00 | Window Closed / Lapsed |